The flying vehicle in this invention has landing legs with a grounding part, the grounding part being shaped such that the drag force decreases during traveling rather than during landing. The shape of the grounding part is substantially wing-shaped in the front-rear direction of the airframe, and the angle of attack of the grounding part is reduced when the flying vehicle moves forward than when it lands. The grounding part has an inverted wing shape in the longitudinal direction of the airframe, and the angle of attack of the grounding part is reduced during travel rather than during landing. A plurality of landing legs are provided, and the grounding part of the shape is provided only on the landing leg on the forward side of the airframe. The landing legs are connected to the grounding part and provided with an intermediate member extending at least vertically, and the structure of the grounding part is more fragile than the intermediate member.
[Problem] To provide a landing port which improves landing accuracy of a flying body by providing an auxiliary device in which the landing port keeps a predetermined posture, and facilitates precise landing onto a moving body moving or oscillating. [Solution] Provided is a landing port for a flying body, wherein the landing port is provided with: a landing surface on which the flying body can land; and an auxiliary device for providing, to the flying body, information for assisting landing of the flying body onto the landing surface. The auxiliary device has a posture maintaining mechanism for maintaining a predetermined inclination independently of at least one of the landing surface and the installation surface of the auxiliary device and for providing the information in a direction corresponding to the inclination.
A landing method, etc., for a flight vehicle having directional characteristics, which can improve the landing performance of the flight vehicle having directional characteristics by turning the airframe in a nose direction with a good balance between lift and drag based on wind speed data and wind direction data related to the landing site. In the method for landing a flight vehicle of the present invention, the flight vehicle comprises to generate lift in response to wind from the nose direction of the airframe and based on wind speed data and wind direction data related to the landing site, the nose direction of the airframe is controlled and the descent of the airframe is initiated.
The invention is a flying object equipped with a loading part holding a delivery payload, and the loading part or the delivery payload is attached to an airframe so that the loading part or the delivery payload is tilted backward in the forward and backward direction in a landing state or hovering state. The loading part or delivery payload is attached to the airframe so that the loading part or delivery payload is substantially horizontal during cruising.
B64D 1/22 - Enlèvement d'objets à la surface du sol
B64U 10/14 - Plates-formes volantes comportant quatre axes distincts de rotors, p. ex. quadcoptères
B64U 101/60 - Véhicules aériens sans pilote spécialement adaptés à des utilisations ou à des applications spécifiques au transport de passagersVéhicules aériens sans pilote spécialement adaptés à des utilisations ou à des applications spécifiques au transport de marchandises autres que des armes
The invention is a flying vehicle comprising a suspension member for suspending a load, wherein the suspension member comprising a first portion and a second portion comprising a different configuration from the first portion, which is to be grasped. Furthermore, the first portion and the second portion are different cord-like members and are connected to each other. Furthermore, the second portion is made of a thicker member than the first portion. The second portion is covered by said covering member. Furthermore, the second portion comprises a higher coefficient of friction than the first portion.
B64D 1/22 - Enlèvement d'objets à la surface du sol
B64U 10/14 - Plates-formes volantes comportant quatre axes distincts de rotors, p. ex. quadcoptères
B64U 101/67 - Véhicules aériens sans pilote spécialement adaptés à des utilisations ou à des applications spécifiques au transport de passagersVéhicules aériens sans pilote spécialement adaptés à des utilisations ou à des applications spécifiques au transport de marchandises autres que des armes les véhicules aériens sans pilote comprenant des attaches pour descendre les marchandises
According to the invention, a function part can be provided that is adaptable to flying vehicles with rotor blade parts of either the propulsion or traction type, while minimizing the reduction in efficiency of the flying vehicle. The rotorcraft of this invention has a rotor blade part including a motor and a propeller, a connection part connected to a rotating part of the rotor blade part and rotating together with the rotating part, and a function part that is at least partially held by the connection part and maintained at a reduced rotation speed than the rotation speed of the connection part in the rotation of the connection part.
[Problem] To enable a flight body to land more reliably on a takeoff/landing surface and then enable the flight body to independently take off. [Solution] This landing device for a flight body comprises a first member and a second member, each of which has a takeoff/landing surface. The first member comprises, on the takeoff/landing surface side, a first function unit capable of restraining a landing unit for the flight body, and the second member does not comprise, on the takeoff/landing surface side, the first function unit. At least one of the first member and the second member is provided so as to be displaceable.
According to this invention, an aerial vehicle can be provided that reduces the effect of wind in a given direction striking its frame during flight of the aerial vehicle, thereby improving fuel consumption and stability. The aerial vehicle of this invention is equipped with a flight part including a frame to which a plurality of rotor blades including at least a propeller and a motor are connected, wherein the frame includes a right frame and a left frame extending side by side in the front-rear direction of the aerial vehicle, and at least one of the right frame and the left frame has a substantially wing-shaped portion with a leading edge located outside the aerial vehicle and a trailing edge located inside the aerial vehicle relative to a vertical center line in the frame. The substantially wing-shaped shape is a symmetrical wing shape.
B64U 10/14 - Plates-formes volantes comportant quatre axes distincts de rotors, p. ex. quadcoptères
B64U 20/77 - Caractéristiques de construction du corps du véhicule aérien sans pilote le corps étant formé intégralement avec des ailes ou des supports de rotor
[Problem] To improve the amount of impact reduction when a flight vehicle comes in contact with a structure while minimizing an increase in weight. [Solution] Provided is a flight vehicle comprising multiple propellers 110, a main body 50, and contact support members 130, wherein: the contact support member 130 has a pivot shaft part disposed on a main body-side end part and a long member pivotable about the pivot shaft part; and when a state where no load is applied against the contact support member is defined as a first state, and a state where the contact support member has pivoted outward to the maximum extent from inner side due to the pivot shaft part when viewed from the main body side as a result of a load applied against the contact support member is defined as a second state, then an effective length, that is, the difference between a distance between both ends of the contact support member in a vertical direction when in the first state and a distance between the ends of the contact support member in the vertical direction when in the second state, is a half of the diameter of one of the multiple propellers or greater.
[Problem to be Solvent] To provide an aerial vehicle that can efficiently reduce the horizontal dimensions of the airframe. [Solution] The aerial vehicle according to the present invention includes two first frames arranged in a second direction intersecting a first direction, with the first direction being longitudinal, two second frames arranged in the first direction by overlapping the two first frames, with the second direction being longitudinal, first rotor blades mounted to both ends of the first frame, and second rotor blades mounted to both ends of the second frame, wherein the second frame is provided with a hinge part capable of folding the second frame at a midway thereof.
A flight vehicle capable of improving the accuracy of the arrival position of baggage. The flight vehicle according to the present disclosure includes a mounting unit that holds a mounted object, holds the mounting unit via a string member, and has a moving means including a rotor blade provided between the upper end and the lower end of the mounting unit, when the mounting unit is viewed from the side.
A position restriction device for a suspension member that can improve the position accuracy of a flight body by a simple mechanism. The present disclosure is a position restriction device for a suspension member suspended from a flight body, comprising a restriction part for restricting the movement of the position of the suspension member, and a guide part for guiding the suspension member to a position where the movement of the suspension member can be restricted by the restriction part at least.
B64U 60/40 - Trains d’atterrissage pliables ou rétractables
B64U 10/14 - Plates-formes volantes comportant quatre axes distincts de rotors, p. ex. quadcoptères
B64U 101/64 - Véhicules aériens sans pilote spécialement adaptés à des utilisations ou à des applications spécifiques au transport de passagersVéhicules aériens sans pilote spécialement adaptés à des utilisations ou à des applications spécifiques au transport de marchandises autres que des armes à la livraison ou au retrait de colis
13.
FRAME ASSEMBLY AND METHOD FOR MANUFACTURING FRAME ASSEMBLY
To stabilize a frame of a flight body, a frame assembly for a flying body comprises a first frame member extending in at least two parallel and first directions, a second frame member extending in a second direction perpendicular to said first direction, and a fixing member fixed to each of the first and second frame members, wherein at least one of the fixing members has an opening.
A flight vehicle with a more basic structure and safety measures according to the invention comprises a main body part; a propulsion part provided with one or more propulsion means; a connection part connecting the main body part and the propulsion part in a displaceable manner within a predetermined range; and a wing part provided on at least one of the main body part or the propulsion part. With such a configuration, a flight vehicle with a more basic structure and safety measures can be provided.
B64C 27/24 - Giravions complexes, c.-à-d. aéronefs utilisant en vol à la fois les caractéristiques de l'avion et celles du giravion avec pales du rotor fixes en vol de façon à agir comme surfaces de sustentation
B64C 3/38 - Réglage des ailes complètes ou de certaines parties de ces ailes
B64D 9/00 - Appareillage pour manutention du fretAppareillage pour faciliter l'embarquement des passagers ou autres
A landing method for a flight body capable of achieving both vertical takeoff and landing and improving fuel consumption while improving landing performance. A flight body, comprising: a plurality of rotary wing parts that generate at least lift; a thrust drive device; and a fixed wing, wherein the thrust drive device generates thrust on the opposite side of horizontal flight during landing. Furthermore, the thrust drive device is equipped with a propeller, which, when landing, rotates in the opposite direction to that of horizontal flight. Furthermore, the thrust drive system generates more thrust to the opposite side during an emergency crash than during a landing.
B64C 27/26 - Giravions complexes, c.-à-d. aéronefs utilisant en vol à la fois les caractéristiques de l'avion et celles du giravion caractérisé par le fait qu'il est doté d'ailes fixes
16.
AUTHENTICATION METHOD, VALIDITY DETERMINATION METHOD, AERIAL VEHICLE CONTROL METHOD, AUTHENTICATION SYSTEM, AND AERIAL VEHICLE CONTROL SYSTEM
Provided are an authentication method, a validity determination method, an aerial vehicle control method, an authentication system, and an aerial vehicle control system that make it possible to authenticate a drone with greater ease and increased reliability. The present disclosure provides an authentication method relating to authentication of an aerial vehicle which is performed by means of one or more information processing devices, wherein: type information of the aerial vehicle is acquired; a pass/fail determination of the type authentication is performed on the basis of the type information; type authentication information regarding the type authentication of the aerial vehicle determined to be a pass is encrypted by means of a predetermined public key; and a type authentication-pass certificate combining the encrypted type information and the predetermined public key is transmitted to the aerial vehicle and is stored in the aerial vehicle.
H04L 9/32 - Dispositions pour les communications secrètes ou protégéesProtocoles réseaux de sécurité comprenant des moyens pour vérifier l'identité ou l'autorisation d'un utilisateur du système
B64C 13/18 - Dispositifs amorçant la mise en œuvre actionnés automatiquement, p. ex. répondant aux détecteurs de rafales utilisant un pilote automatique
A compact port with a simple mechanism that can improve reliability during load receiving while keeping costs low. A port of the disclosure is a port having a load-receiving part that rotates around a rotating axis extending at least in a vertical direction, wherein the load-receiving part rotates by switching between a load receiving mode and a standby mode based on an external control signal.
[Problem] To provide a flight vehicle capable of improved fuel efficiency while cruising. [Solution] A flight vehicle 100 according to the present technology comprises: a plurality of rotor blades 11; a main body 50 supporting the plurality of rotor blades 11; and a movable part 40 which is provided on the main body 50 and which can be displaced, in full or in part, away from the main body 50, wherein the attitude of the flight vehicle 100 while cruising is tilted farther forward with respect to the cruising direction than the attitude of the flight vehicle 100 while hovering through control of the rotation rate of the plurality of rotor blades 11, and the movable part 40 is controlled to be displaced from the main body 50 while cruising.
Provided is a method for controlling the directional orientation of a flying object so that the flying object faces in a direction that increases the efficiency of flight over the immediately preceding state based on predetermined information. To provide a method of flight control whereby a flying object having directional characteristics according to such a configuration can fly in an attitude suitable for the relative wind direction and wind speed in flight in order to actively utilize lift, reduce drag, and the like. According to such a configuration, the optimal flight attitude can be obtained by adjusting the wind direction and aircraft direction, thereby increasing safety while improving fuel efficiency.
B64C 13/18 - Dispositifs amorçant la mise en œuvre actionnés automatiquement, p. ex. répondant aux détecteurs de rafales utilisant un pilote automatique
B64C 39/02 - Aéronefs non prévus ailleurs caractérisés par un emploi spécial
[PROBLEM TO BE SOLVED] To provide an aircraft having improved efficiency and flexibility of the airframe configuration when installing a functional part in the airframe, and a power unit having a configuration for the improved efficiency and flexibility. [Solution] To provide an aircraft, comprising: a power unit having a first space open at least one of its upper or lower surface; a propeller having a first through-space and connected to the power unit; and a functional part having a predetermined function and located at least partially in an internal space formed by the first space and the first through-space.
A landing facility that enables flight vehicles to land safely even in strong winds. The landing system of the invention includes a first area for landing a flight vehicle, a windbreak part having a predetermined height and cover part at least a portion of the perimeter of the first area, and a second area located away from the windbreak part, where the flight vehicle descends to a predetermined flight altitude. The flight altitude is lower than the predetermined height of the windbreak part. The second area is an area selected from a plurality of permitted areas where vertical descent is permitted. A portion of the windbreak part comprises a net.
An aircraft that flies autonomously using GNSS, etc., and that can improve the reliability of its flight while minimizing cost increases. An aircraft flying autonomously on a designated route, and when the aircraft is not continuing its autonomous flight on the designated route, with a processor which controls the flight of the aircraft based on information about the landing site acquired externally by an external information acquisition device. The external information acquisition device is a sensor. The sensor is an image sensor. The external information acquisition device is a beacon device. The processor executes a safe landing mode in which flight control is performed based on a flight route to acquire information about the landing site.
G08G 5/02 - Aides pour l'atterrissage automatique, c. à d. systèmes dans lesquels les données des vols d'avions arrivant sont traitées de façon à fournir les données d'atterrissage
[Problem] To improve the delivery efficiency of a delivery person. [Solution] An information processing system comprising: a determination unit that, on the basis of request details included in a delivery request pertaining to the delivery or collection of a package that has been registered by a person requesting delivery, determines whether the handling of the delivery request by a delivery person satisfies a condition pertaining to the delivery efficiency of the delivery person; and a generation unit that, on the basis of a determination by the determination unit that the condition is not satisfied, generates delivery instruction information pertaining to the delivery or collection of the package by another delivery means other than the delivery person.
[Problem] To enable the distribution of packages by means of mobile bodies with higher delivery efficiency. [Solution] An information processing system comprising a determination unit in which a factor impeding distribution by a mobile body used for distribution including delivery or collection of a package is used as a basis to determine whether distribution is possible by mobile bodies corresponding to each of movement means for a plurality of movement routes including at least land routes and air routes for distribution which includes delivery or collection of the package.
[Problem] To further improve convenience with regard to receipt of cargo by a recipient. [Solution] An information processing system comprising a notification unit which notifies a recipient who receives cargo of reference information regarding the cargo of another recipient, in accordance with registered information registered in advance by the recipient.
[Problem] To make it possible for a representative who represents a receiver to smoothly receive a package. [Solution] An information processing system comprising: a control unit that acknowledges a candidate for a representative, who can receive a package by representing a receiver designated as the addressee of the package, as the representative; and an authentication unit that performs an authentication process to assess whether or not a request for authentication of receipt of the delivered package is a request from the representative acknowledged by the control unit.
[Problem] To provide a technology contributing to further efficiency in the delivery or collection of a load. [Solution] Provided is an information processing system comprising: a communication unit that issues a notification relating to recruitment for a service to a service provider terminal, which is utilized by a service provider candidate who would provide the services of collecting and delivering a load and which is utilized by a candidate who is, in accordance with a condition relating to the collection and delivery of the load by another different delivery means, estimated to be able to provide the services of collecting and delivering the load; a control unit that approves the service provider candidate as a service provider; and a screen generation unit that generates a notification of information relating to the services of collecting and delivering the load.
[Problem] To further improve the delivery efficiency of a deliverer. [Solution] This information processing system comprises an acquisition unit that acquires position information related to a deliverer, and a setting unit that, on the basis of the position information acquired from the acquisition unit, sets a receiving position indicating the position for the deliverer to receive an object for transport from a first mobile body that relays and transports the object for transport.
[Problem] To further improve convenience pertaining to reception of a package. [Solution] An information processing system comprising: an acquisition unit that acquires schedule information relating to a movement schedule of a recipient who receives a package; and a designation unit that, on the basis of the schedule information, designates a delivery slot that corresponds to a scheduled time at which the recipient will arrive at a location at which the package is received, from among a plurality of delivery slots included in a delivery plan of a moving vehicle that is used for delivering the package.
[Problem] To enable a proxy substituting for a recipient to receive a package smoothly. [Solution] An information processing system comprising: a control unit for setting, as a proxy, a proxy candidate who is able to receive a package in place of a recipient designated in the package address; and a communication unit for reporting information about the package to the proxy or the proxy candidate.
[Problem] To enable streamlining of the delivery of parcels. [Solution] This information processing system comprises a communication unit for notifying a service provider terminal, used by a candidate service provider, of recruitment of a service provider who will be responsible for at least one of: temporary reception, outside a mobile body used for mixed transportation of passenger and freight, of parcels being delivered by the mobile body; transfer of parcels to a delivery person or to a service provider in the mobile body; loading of parcels into the mobile body; transfer of parcels in the mobile body; temporary reception of parcels in the mobile body; or temporary reception of parcels from the delivery person or the service provider in the mobile body.
[Problem] To provide an information processing system, an information processing device, an information processing method, and a program that are new and improved and that are capable of contributing to further efficiency improvement in package delivery or collection. [Solution] Provided is an information processing system comprising: a control unit that generates one or more delivery plans including delivery routes and delivery means of a package; and a candidate determination unit that determines, as service provider candidates, one or more users estimated to be available to provide a service for collection and delivery of the package. Upon approving, as the service provider, one user from among the users determined as the candidates, the control unit performs approval by selecting, from among the generated delivery plans, a delivery plan to a package collection point of the service provider.
An aircraft, etc., which can reduce the shock to a mounted object during unloading and improve the quality of delivery by lowering the mounted object from the aircraft after landing while maintaining its posture and releasing it so that the shock generated to the mounted object at the time of detachment is within a predetermined shock range. An aircraft equipped with a holding mechanism that holds the mounted object, wherein the holding mechanism moves the mounted object at least vertically downward after landing legs of the aircraft are grounded, while maintaining the mounted object horizontal.
[Problem] To provide a VTOL aircraft capable of improved flight efficiency and preventing a reduction in takeoff and landing performance. [Solution] A VTOL aircraft 100 comprising a main wing 21, a first rotary wing part 11, and a second rotary wing part 12, wherein during flight using lift generated by the first rotary wing part 11, at least a part of the main wing 21 is folded so as to reduce the plan projected area of the aircraft 100 and make it harder to be affected by an updraft or the like.
B64C 3/56 - Repliage ou rabattement pour réduire l'encombrement de l'aéronef
B64C 25/12 - Atterrisseurs non fixes, p. ex. largables escamotables, repliables ou ayant un mouvement apparenté latéralement
B64C 25/58 - Aménagements ou adaptations des amortisseurs ou des ressorts
B64C 27/26 - Giravions complexes, c.-à-d. aéronefs utilisant en vol à la fois les caractéristiques de l'avion et celles du giravion caractérisé par le fait qu'il est doté d'ailes fixes
B64C 29/02 - Aéronefs capables d'atterrir ou de décoller à la verticale, p. ex. aéronefs à décollage et atterrissage verticaux [ADAV, en anglais VTOL] dont l'axe matérialisant la direction du vol est vertical lorsque l'aéronef est au sol
B64D 1/08 - Largage ou éjection d'objets les objets étant des dispositifs porte-charges
A drone loaded with a package takes off from a takeoff device and uses a GPS system to fly to a user house that is a delivery destination of the package as the destination. Further, when the drone approaches the user house that is the destination, the flight of the drones is switched from autonomous navigation using the GPS system to remote control performed by a landing device and an in-house control device installed in the user house. The drone lands on the landing device by remote control from the landing device and the in-house control device, separates the package, and then returns to the warehouse using the GPS system and lands on the takeoff device.
G05D 1/06 - Régime de modification de l'altitude ou de la profondeur
A47G 29/14 - Récipients pour déposer des aliments, p. ex. petit déjeuner, laitRécipients similaires pour colis avec accessoires pour éviter que les articles déposés ne soient indûment retirés
B64C 13/20 - Dispositifs amorçant la mise en œuvre actionnés automatiquement, p. ex. répondant aux détecteurs de rafales utilisant des émissions de signaux
B64C 39/02 - Aéronefs non prévus ailleurs caractérisés par un emploi spécial
B64U 50/30 - Alimentation en énergie électrique ou distribution de celle-ci
G05D 1/00 - Commande de la position, du cap, de l'altitude ou de l'attitude des véhicules terrestres, aquatiques, aériens ou spatiaux, p. ex. utilisant des pilotes automatiques
G05D 1/10 - Commande de la position ou du cap dans les trois dimensions simultanément
G08G 5/02 - Aides pour l'atterrissage automatique, c. à d. systèmes dans lesquels les données des vols d'avions arrivant sont traitées de façon à fournir les données d'atterrissage
A47G 29/122 - Éléments, parties constitutives ou accessoires, p. ex. dispositifs avertisseurs, lampes, dispositifs pour laisser des messages
B64U 101/30 - Véhicules aériens sans pilote spécialement adaptés à des utilisations ou à des applications spécifiques à l’imagerie, à la photographie ou à la vidéographie
B64U 101/64 - Véhicules aériens sans pilote spécialement adaptés à des utilisations ou à des applications spécifiques au transport de passagersVéhicules aériens sans pilote spécialement adaptés à des utilisations ou à des applications spécifiques au transport de marchandises autres que des armes à la livraison ou au retrait de colis
G06Q 10/0832 - Marchandises spéciales ou procédures de manutention spéciales, p. ex. manutention de marchandises dangereuses ou fragiles
G06Q 10/0835 - Relations entre l’expéditeur ou le fournisseur et les transporteurs
A flying vehicle with a flight part connected to a plurality of rotor wing parts and a main wing, wherein the main wing is configured such that the lift produced by the main wing during landing is reduced compared to the lift produced by the main wing during cruising. Furthermore, the main wing is fixed at a forward tilt with respect to the flight part. Furthermore, the rotor wing is connected at an angle that produces propulsion and lift during cruise. Furthermore, the rotor blades are connected at an angle that generates propulsive force during cruise.
B64U 10/20 - Aéronefs à décollage et atterrissage verticaux [ADAV, en anglais VTOL]
B64C 27/26 - Giravions complexes, c.-à-d. aéronefs utilisant en vol à la fois les caractéristiques de l'avion et celles du giravion caractérisé par le fait qu'il est doté d'ailes fixes
B64C 29/00 - Aéronefs capables d'atterrir ou de décoller à la verticale, p. ex. aéronefs à décollage et atterrissage verticaux [ADAV, en anglais VTOL]
B64D 45/04 - Aides à l'atterrissageDispositifs de sécurité pour éviter la prise de sol brutale
B64U 50/13 - Propulsion utilisant des soufflantes ou des hélices externes
B64C 3/42 - Réglage autour des axes dans le sens de la corde
37.
AIRCRAFT, LOAD LANDING METHOD, AND TERRESTRIAL VEHICLE
[Problem] To provide an aircraft or the like capable of reducing impact at the time when a loaded object is detached and preventing cases of defects and incompletion of the detachment. [Solution] Provided is an aircraft 100 comprising a loading unit 20 which holds a loaded object 10, and an assist mechanism 60 which applies a force to the loaded object 10 toward a detachment direction when the loaded object 10 is to be detached from the loading unit 20 to thereby assist in moving the loaded object 10 during detachment.
[Problem] The present disclosure facilitates the identification of the total quantity of distributed items (e.g., loaded items such as luggage) by standardizing and managing the distributed items by using container type identification information and enables efficient storage into various storage spaces. [Solution] The present disclosure comprises a residual space calculating unit that calculates residual space information about a residual space in a storage space on the basis of container type information indicating, for each capacity, the type of a container for storing an item to be distributed to a user and reference storage space capacity information indicating the capacity of a storage space for storing at least one container, and a consolidation target distribution extracting unit that extracts consolidation target distribution information indicating the distribution of another user capable of accepting the consolidation of the distributed item for the user in a residual space.
[Problem] The present disclosure formalizes and manages a delivery object (e.g., a load such as a luggage) using storage container type identification information, thereby making it easier to ascertain the overall quantity of the delivery object and enabling efficient storage in various storage spaces. [Solution] The present disclosure comprises: a remaining space calculation unit for calculating remaining space information that indicates the remaining space in a storage space, on the basis of storage container type information indicating the type by volume of a storage container for storing a first in-stock article needing to be delivered, for which a delivery request was made, and reference storage space volume information indicating the volume of a storage space for storing one or more storage containers; and a consolidation stock extraction unit for extracting a second in-stock article needing to be delivered, which is different from the first in-stock article and which is to be stored in a prescribed quantity in the storage container together with the first in-stock article needing to be delivered, on the basis of information relating to the second in-stock article and the remaining space information.
[Problem] The objective of the present disclosure is to use storage container type identification information to standardize and manage delivery items (for example, loads such as luggage), to facilitate an understanding of the overall quantity of delivery items, and to enable efficient storage in various storage spaces. [Solution] An information processing system according to the present disclosure comprises: a storage container type setting unit for setting storage container type information indicating a type, for each capacity, of a storage container for storing a user's purchased products, on the basis of purchased product information selected by the user; a remaining space calculating unit for calculating remaining space information indicating a remaining space in a storage space for storing one or more of the storage containers, on the basis of the set storage container type information and standard storage space capacity information indicating the capacity of the storage space; and a mixed-loading object extracting unit for extracting mixed-loading object information indicating a mixed-loading object capable of being stored in the remaining space of the target storage space.
[Problem] The present disclosure makes it easy to know a comprehensive quantity of delivery objects and enable efficient storing in various storage containers by standardizing and managing the delivery objects (e.g., loading objects such as freight) by using identification information for each storage container classification. [Solution] The present disclosure comprises: a storage container classification setting unit which sets, on the basis of purchase product information selected by a user, storage container classification information that indicates the type for each volume of the storage container for storing the user purchase product as the delivery object; a remaining space calculation unit which calculates remaining space information that indicates the remaining space in the storage space on the basis of reference storage space volume information that indicates the volume of the storage space that stores one or more storage containers, and the set storage container classification information; and a delivery-to-be-mixed extraction unit which extracts delivery-to-be-mixed information that indicates another user's delivery that can be mixed with the user's delivery object in the remaining space.
[Problem] The present disclosure uses accommodation container type-identifying information to systematize and manage delivery items (e.g., loading items such as packages), thereby making it easy to ascertain the overall amount of delivery items and making it possible to efficiently accommodate the delivery items in various accommodation spaces. [Solution] The present disclosure comprises: a remaining space calculation unit that calculates remaining space information indicative of the remaining space in an accommodation space, which accommodates at least one accommodation container, on the basis of accommodation container type information which indicates the volume-based types of accommodation containers for accommodating delivery items to be delivered to users and of reference accommodation space volume information which indicates the volume of the accommodation space; and a consolidation-target object extraction unit that extracts consolidation-target object information indicative of consolidation-target objects which can be accommodated in the remaining space of a target accommodation space.
[Problem] The present disclosure facilitates comprehension of the overall article amount of delivery articles (for example, loaded articles such as packages) and enables effective storage in various storage spaces, by categorizing the delivery articles and managing the same through use of storage container type identification information. [Solution] The present disclosure comprises: a remaining space calculation unit that, on the basis of storage container type information indicating types respectively for the capacities of storage containers for storing delivery articles to users and reference storage space capacity information indicating the capacities of storage spaces for storing the storage containers, calculates remaining space information indicating remaining space in the storage spaces; and a delivery schedule determination unit that, on the basis of at least the remaining space information and a predetermined condition concerning delivery, determines delivery schedules of the delivery articles.
[Problem] The objective of the present disclosure is to use storage container type identification information to standardize and manage stored items (for example, delivery items), to facilitate an understanding of the overall quantity of stored items, and to enable efficient storage in various storage spaces. [Solution] An information processing system according to the present disclosure comprises: a remaining space calculating unit for calculating remaining space information indicating a remaining space in a storage space linked to a user, on the basis of storage container type information indicating a type, for each capacity, of a storage container for storing stored items in the storage space, and storage space capacity information indicating at least the capacity of the storage space; and an additional stored item extracting unit for extracting an additional stored item capable of being stored in the remaining space information in the storage space.
[Problem] The present disclosure addresses the problem of using accommodation container type-identifying information to systematize and manage items (such as packages) to be accommodated, thereby making it easy to ascertain the overall amount of items to be accommodated and making it possible to efficiently accommodate the items to be accommodated in various accommodation spaces. [Solution] The present disclosure comprises: an accommodation position generation unit that, on the basis of accommodation container type information which indicates the volume-based types of accommodation containers for accommodating items to be accommodated in an accommodation space associated with a user and of accommodation state information which indicates the accommodation state of the accommodation space, generates accommodation position information pertaining to the accommodation position of an item to be accommodated in the accommodation space; and an information transmission unit that transmits to a worker terminal the generated accommodation position information and/or accommodation position instruction information which is generated on the basis of the accommodation position information and which is for instruction of the accommodation position.
[Problem] The objective of the present disclosure is to use storage container type identification information to standardize and manage stored items (for example, delivery items), to facilitate an understanding of the overall quantity of stored items, and to enable efficient storage in various storage spaces. [Solution] An information processing system according to the present disclosure comprises: a storage capacity status information generating unit for generating storage capacity status information indicating a status relating to a capacity of a storage space linked to a user, on the basis of storage container type information indicating a type, for each capacity, of a storage container for storing stored items in the storage space, and storage space capacity status information indicating at least the capacity of the storage space; and a notifying unit for generating a notification relating to the storage space in accordance with a determination as to whether the capacity of the space indicated by the storage capacity status information satisfies a prescribed condition.
[Problem] The objective of the present disclosure is to use storage container type identification information to standardize and manage stored items (for example, delivery items), to facilitate an understanding of the overall quantity of stored items, and to enable efficient storage in various storage spaces. [Solution] An information processing system according to the present disclosure is provided with a delivery request management unit which: transmits, to a delivery worker terminal, a delivery request demand including at least storage container type information indicating a type, for each capacity, of a storage container for storing delivery items; and receives, from the delivery worker terminal, delivery request response information indicating whether a delivery request relating to the delivery request demand can be accepted. Further, the storage container type information can be identified on the basis of a storage container capacity obtained by using a prescribed storage space capacity as a standard storage space capacity, and dividing the standard storage space capacity by a prescribed number.
The operational efficiency of a rotorcraft in cruising. The rotary wing aircraft, according to the present disclosure, has a main body and a plurality of motors provided in the main body for rotating each of the rotors, which are parallel to a reference plane. When the main body is inclined with respect to one direction of travel and flying in the direction of travel, the rotational speed of each of the plurality of motors is approximately the same.
B64U 10/16 - Plates-formes volantes comportant au moins cinq axes distincts de rotors, p. ex. octocoptères
B64C 27/24 - Giravions complexes, c.-à-d. aéronefs utilisant en vol à la fois les caractéristiques de l'avion et celles du giravion avec pales du rotor fixes en vol de façon à agir comme surfaces de sustentation
The present disclosure relates to a rotorcraft. The rotorcraft according to the present disclosure has a parachute mechanism for releasing a parachute in a predetermined direction and an attitude control means for setting the aircraft to a specific attitude when releasing said parachute. According to such a configuration, the parachute can be deployed in an attitude suitable for its deployment, thereby reducing damage, etc., that may occur when the flying vehicle falls.
[Problem] The present invention provides a flying object with which any decrease in flight efficiency while the flying object is cruising can be minimized while safety is improved. [Solution] This flying object is provided with a safety device that reduces falling speed, wherein the safety device is mounted at an angle at which drag is reduced during forward travel to a greater extent than during landing or hovering. The frontal projected area of the safety device is lower during forward travel than in a landing state or a hovering state. In a landing state or a hovering state, the center line of the safety device is tilted rearward of the flying object. The tilt angle of the center line of the safety device is the same or similar in magnitude to the forward tilt angle of the flying object during cruising. The safety device encompasses a parachute.
To provide a rotary wing aircraft capable of self-leveling and ensuring a stable landing state. The rotary wing aircraft according to the present disclosure comprises a plurality of rotary blades, an arm part for supporting the plurality of rotary blades, a mounting part for mounting an object, and a connecting part for connecting the mounting part to the arm part in a state where the mounting part is movable within a predetermined range. The position of the connecting part of the rotary wing aircraft of the present disclosure is above the center of gravity of the arm part. Thereby, self-leveling is made possible and a stable landing state can be ensured.
[Problem] To provide landing gears that reduce the influence of wind blowing the landing gears in a prescribed direction during the flight of a flight vehicle and improve fuel consumption and stability, and that make it possible to reduce an impact during a landing. [Solution] A flight vehicle according to the present invention is provided with landing gears having ground contact parts that are each shaped so as to reduce drag during an advance as compared with during a landing. The ground contact parts are each shaped substantially like an airfoil in the front-back direction of the fuselage. In the ground contact parts, the angle of attack decreases during an advance as compared with during a landing. The ground contact parts are each shaped substantially like a reverse airfoil in the front-back direction of the fuselage. In the ground contact parts, the angle of attack decreases during an advance as compared with during a landing. A plurality of the landing gears are provided, and the ground contact parts having the shapes are provided to only the landing gears on the front side of the fuselage. The landing gears are each provided with an intermediate member that is connected to the ground contact part and that extends at least in the vertical direction. The ground contact part is so structured as to be more prone to breakage than the intermediate member.
A frame assembly for unmanned aerial vehicle comprising: at least two parallel first frame members, a second frame member orthogonal to the first frame member, and a fixing member fixed to each of the first and second frame members.
The present disclosure relates to a flying body. The flying body includes a mounting space for mounting an object, a loading port for loading the object in the mounting space, and a take-out port for taking out the object loaded in the mounting space, wherein the loading port and the take-out port are provided at least partially at different positions. According to such a configuration, even a person without specialized knowledge can operate it easily and safely.
[Problem] To provide a flight vehicle for which fuel consumption can be improved and which is capable of transporting an article. [Solution] This flight vehicle comprises a load part for holding a load, wherein, in a landed state or a hovering state, the center position of the load part is arranged more to the front side than the middle position of the front-rear direction of a vehicle body, and more to the lower side than the generation center point of lift. Further, the center position of the load part is arranged more to the lower side than the middle position of the up-down direction of the vehicle body. Further, the center position of the load part is arranged more to the lower side than the position of the center of gravity of the flight vehicle. Further, the position of the center of gravity of the load part is arranged more to the lower side than the position of the center of gravity of the flight vehicle.
[Problem] The present invention can provide a flying object that has improved fuel consumption and can transport articles. [Solution] This flying object comprises a loading part that holds a delivery, the loading part or the delivery being attached to the body of the flying object such that the loading part or the delivery is tilted rearward in the forward-backward direction when the flying object has landed or is hovering. The loading part or the delivery is attached to the body such that the loading part or the delivery is substantially horizontal when the flying object is en route. When the flying object has landed or is hovering, the center of the loading part is in front of the forward-backward directional center of the body and is lower than the center point of lift generation. Alternatively, when the flying object has landed or is hovering, the center of the loading part is to the rear of the forward-backward directional center of the body and is lower than the center point of lift generation.
An aircraft that can improve cruising speed by making the body shape of the airframe (especially, multicopter) into a shape that has less unnecessary positive lift force by the main body and less drag in the cruising posture of the airframe. An aircraft equipped with a plurality of rotary blades including a propeller and a motor, wherein the aircraft comprises a main body with an inverted airfoil shape. The main body has an attack angle that does not generate a lift force or produces a negative lift force during cruising. The main body has a positive attack angle of 12 degrees or less. Further, it is provided with a mounting unit on which a mounted object can be mounted. The mounting unit is connected to the main body via the connection unit.
A moving body that can be transported in a state to stabilize the posture of the transport object, without affecting the transport object due to the inclination of the moving body when moving forward. A moving body comprising a holding mechanism that has a rotation unit that rotates in the pitch direction, and approximately horizontally holds an object to be transported from the side near the center of gravity of a transport unit capable of storage or above the center of gravity. Further, a moving body wherein the holding mechanism has a uniaxial rotation unit that rotates only in the pitch direction. Further, a moving body wherein the holding mechanism approximately horizontally holds the transport unit by active control. Alternatively, the holding mechanism approximately horizontally holds the transport unit by passive control.
B64U 101/60 - Véhicules aériens sans pilote spécialement adaptés à des utilisations ou à des applications spécifiques au transport de passagersVéhicules aériens sans pilote spécialement adaptés à des utilisations ou à des applications spécifiques au transport de marchandises autres que des armes
[Problem] According to the present invention, it is possible to provide a functional section that can be applied to either a propulsion-type aircraft or a tow-type aircraft having rotor blades while minimizing any decrease in the efficiency of the aircraft. [Solution] This rotorcraft has a rotor blade section including a motor and a propeller, a connecting section that is connected to a rotating part of the rotor blade section and that turns together with the rotating part, and a functional section of which at least a portion is held by the connecting section and which is held in a state such that the speed thereof is less than the speed of the turning of the connecting section.
To provide an aircraft that can efficiently improve speed performance and fuel efficiency, the aircraft is an aircraft capable of forward flight and hovering, and includes a lift generating part, a frame for holding the lift generating part, and a loadable object provided on the frame and to be mounted. The front projection area of the frame and the mounting part during forward flight is smaller than the front projection area of the frame and the mounting part during hovering.
A high-place observation device for stably performing a fixed-point observation of a target object from a high place is provided. The high-place observation device provides [Solution] Provides a long pole which is formed to extend and contract freely and which stands on the installation surface, a rotorcraft for positioning the pole to a desirable height position by extending and contracting the pole by a floating force in a connected state, a winding mechanism which fixes and maintains the height position of the pole to the height position set by the rotorcraft, and a camera attached to the rotorcraft.
The present invention is capable of providing a flying vehicle comprising a suspension member for suspending a payload, the suspension member comprising a first part which makes the overall suspension member lightweight, and a second part that can easily be grasped from the outside. The present invention is a flying vehicle that suspends a payload via a suspension member, the suspension member comprising: a first part; and a second part having a different configuration from the first part and serving as an object to be grasped. Moreover, the first part and the second part are different cord-shaped members, and are connected to each other. Furthermore, the second part makes use of a thicker member than the first part. The second part is covered by means of a covering member. Furthermore, the second part is configured to have a higher friction coefficient than the first part.
[Problem] The present invention makes it possible to provide an aerial vehicle in which, during flight of the aerial vehicle, the influence of wind which hits the frame in a prescribed direction is reduced, and fuel efficiency and stability are improved. [Solution] An aerial vehicle according to the present invention comprises a flight part including a frame which is connected to a plurality of rotors that each include at least a propeller and a motor, wherein the frame has two or more types of cross-sectional shapes corresponding to the position thereof. The frame also includes a right frame and a left frame that extend side by side in the front-rear direction of the vehicle body. At least one of the right and left frames has a substantially airfoil-shaped part, the front edge of which is positioned toward the outside of the vehicle body with respect to the vertical center line of the frame, and the rear edge of which is positioned toward the inside of the vehicle body. The substantial airfoil shape is a target airfoil shape.
[Problem] To provide a device for restricting the position of a suspension member, by which it is possible to improve the positional accuracy of a flight vehicle by use of a simple mechanism. [Solution] This device for restricting the position of a suspension member suspended from a flight vehicle comprises: a restriction member which restricts the positional movement of the suspension member; and a guide part which guides the suspension member to a position where the movement of the suspension member can be restricted at least by the restriction member. Further, a cargo receiving part for receiving a load connected to the suspension member is provided at a location lower than the restriction member. The restriction member includes a member that holds the suspension member. The restriction member also includes a roller part that, by rotational movement thereof, moves the suspension member. The restriction member further includes a configuration for maintaining the suspension member within a prescribed enclosed space.
[Problem] To provide a position restriction device which is for a suspension member, and can improve the positional accuracy of a flight body with a simple mechanism. [Solution] The present disclosure is a position restriction device for a suspension member suspended from a flight body, the position restriction device comprising: a restriction member which restricts the movement of the position of the suspension member; and a guide section which guides the suspension member to at least a position where movement restriction can be implemented by the restriction member.
[Problem] To provide a technology capable of stabilizing a frame of an aircraft. [Solution] The primary invention of this invention for solving the above-mentioned problem is a frame assembly for an aircraft, the frame assembly being characterized by comprising: at least two parallel first frame members which extend in a first direction; a second frame member which extends in a second direction perpendicular to the first direction; and fixing members which are fixed to the first and second frame members, respectively, at least one of the fixing members including an opening portion.
[Problem] To provide a feature with which the frame of an aircraft can be stabilized. [Solution] The main invention of the present invention for solving the above problem is a frame assembly for an aircraft, the frame assembly characterized by comprising at least two parallel first frame members extending in a first direction, a second frame member extending in a second direction perpendicular to the first direction, and fixing members fixed to each of the first and second frame members, at least one of the fixing members having an open part.
[Problem] To provide a flight body landing method capable of achieving an improvement in landing performance while achieving vertical takeoff and landing and improving fuel consumption. [Solution] In a flight body comprising at least a plurality of rotary wing parts which generate a lift force, a thrust driving device, and a fixed wing, the thrust driving device generates a thrust force during landing on the opposite side to that during horizontal flight. Furthermore, the thrust driving device comprises a propeller, wherein the propeller is rotated during landing in the reverse direction to that during the horizontal flight. Furthermore, the thrust driving device generates a greater thrust force on the reverse side during emergency fall than that during landing.
[Problem] To provide a flight vehicle landing method and the like, for a directional flight vehicle, whereby it is possible to improve the landing performance of the directional flight vehicle by turning in a nose direction with a good balance of lift and drag on the basis of wind speed data and wind direction data related to a landing site. [Solution] In this flight vehicle landing method, the flight vehicle is configured to generate lift in response to wind from the nose direction of the fuselage. On the basis of wind speed data and wind direction data related to a landing site, the nose direction of the fuselage is controlled and the descent of the fuselage is initiated.
B64C 13/20 - Dispositifs amorçant la mise en œuvre actionnés automatiquement, p. ex. répondant aux détecteurs de rafales utilisant des émissions de signaux
An aircraft that enables an efficient and safe transition from hovering to level-flight. The aircraft according to the present invention includes a lift generating part, a thrust generating part capable of flying and hovering, a connecting part that displaceably connects the lift generating part and the thrust generating part so that the lift generating part can maintain a positive angle of attack with respect to the flying direction at least at the time of ascending. The lift generating part is a wing part having a main surface, and at least at the time of hovering, a propulsion direction by the thrust generating part is along a direction obliquely intersecting the vertical direction. At least at the time of hovering, the propulsion direction and the main surface form an obtuse angle. At least at the time of hovering, the propulsion direction is along the vertical direction.
B64C 3/48 - Variation de la courbure par parties semi-mobiles des structures d'ailes
B64C 3/38 - Réglage des ailes complètes ou de certaines parties de ces ailes
B64C 9/08 - Surfaces ou éléments de commande réglables, p. ex. gouvernes de direction se déplaçant comme un tout
B64C 27/28 - Giravions complexes, c.-à-d. aéronefs utilisant en vol à la fois les caractéristiques de l'avion et celles du giravion avec hélices propulsives de déplacement pouvant pivoter pour agir comme rotors de sustentation
B64C 29/00 - Aéronefs capables d'atterrir ou de décoller à la verticale, p. ex. aéronefs à décollage et atterrissage verticaux [ADAV, en anglais VTOL]
B64C 39/08 - Aéronefs non prévus ailleurs à ailes multiples
A flying body having more basic structure and safety measures. The flying body according to the present invention a fuselage, a thrust unit for generating thrust connected to the fuselage, a main wing at the fuselage and a tail connected to the fuselage, wherein at least at the time of landing, the main wing is deformably configured with respect to the fuselage so that the main wing and the fuselage comprise landing legs.
[Problem] To provide a flight vehicle having a more fundamental structure and provided with safety measures. [Solution] This flight vehicle comprises a main body part, a thrust part provided with one or more thrust means, a connection part for connecting the main body part and the thrust part in a prescribed range so as to enable displacement, and a wing part provided to the main body part and/or the thrust part. The configuration makes it possible to provide a flight vehicle having a more fundamental structure and provided with safety measures.
[Problem] To provide a compact port with which the reliability of loading can be increased with a simple mechanism while also keeping costs low. [Solution] The port according to the present disclosure has a loading part that turns about a rotary shaft extending in at least the vertical direction, wherein the loading part turns by switching between a loading mode and a standby mode on the basis of an external control signal.
B64C 39/02 - Aéronefs non prévus ailleurs caractérisés par un emploi spécial
A47G 29/12 - Réceptacles pour courrier ou journaux, p. ex. boîtes aux lettresOuvertures dans les portes ou similaires pour la distribution du courrier ou des journaux
B64F 1/14 - Tours ou mâts pour l'amarrage des dirigeables ou des ballons
B64F 1/32 - Installations au sol ou installations pour ponts d'envol des porte-avions pour la manutention du fret
74.
AERIAL VEHICLE AND FLYING METHOD OF AERIAL VEHICLE
An aerial vehicle having more basic structure and safety measures. The aerial vehicle according to the present invention includes a thrust unit having a plurality of rotary vanes for generating thrust, a tail, a fuselage that connects the thrust unit and the tail, a main wing provided in a substantially center of the fuselage, and a control unit for controlling at least the main wing. When the aerial vehicle makes a landing, the control unit controls the main wing so that a part of the main wing becomes a lower end.
B64C 39/02 - Aéronefs non prévus ailleurs caractérisés par un emploi spécial
B64C 29/02 - Aéronefs capables d'atterrir ou de décoller à la verticale, p. ex. aéronefs à décollage et atterrissage verticaux [ADAV, en anglais VTOL] dont l'axe matérialisant la direction du vol est vertical lorsque l'aéronef est au sol
75.
Flight vehicle with mounting unit having moving means, and mouning unit
A flight vehicle capable of improving the accuracy of the arrival position of baggage. The flight vehicle according to the present disclosure includes a mounting unit that holds a mounted object, holds the mounting unit via a string member, and has a moving means including a rotor blade provided between the upper end and the lower end of the mounting unit, when the mounting unit is viewed from the side.
[Problem] To provide a flight body in which arrival position precision of cargo can be improved. [Solution] This flight body comprises a mounting unit that holds a mounted object, and has a movement means that holds the mounted object via a string-like member and includes rotating blades provided between the top and bottom ends of the mounted object when the mounted object is viewed from the side. Some of the rotation shafts of four or more rotating blades extend in mutually different directions. Furthermore, the angle formed between the horizontal-direction axis and at least one of the rotating blades of the four or more rotating blades is smaller than the angle formed between the rotating blade and the vertical-direction axis.
A delivery rotary-wing aircraft has a plurality of rotary wings, a central portion to which a plurality of arms for supporting the rotary wings are connected, a first mounting portion for loading a package, a second mounting portion which is located on the opposite side to the first mounting portion as viewed from the central portion, a first supporting member for coupling the first mounting portion with the central portion, and a connection portion between the central portion and the first supporting member. The center point of lift occurring in the rotary-wing aircraft with the rotation of the plurality of rotary wings and the center point of gravity of the rotary-wing aircraft coincide with the center point of the connection portion. The first supporting member is equipped with an adjustment mechanism for vertically downwardly extending the length of the first supporting member.
B64U 70/00 - Dispositions pour le lancement, le décollage ou l'atterrissage
B64U 101/60 - Véhicules aériens sans pilote spécialement adaptés à des utilisations ou à des applications spécifiques au transport de passagersVéhicules aériens sans pilote spécialement adaptés à des utilisations ou à des applications spécifiques au transport de marchandises autres que des armes
39 - Services de transport, emballage et entreposage; organisation de voyages
Produits et services
Freight brokerage; rental of aircraft; providing information
relating to transport services; travel arrangement; document
delivery; food delivery; delivery of packages;
transportation and delivery of goods; pick up, delivery and
storage of personal property; temporary storage of
deliveries; monitoring and tracking of package shipments
[transport information]; air traffic control services.
[Problem] To provide a flying object control method. [Solution] Provided is a method for controlling, on the basis of prescribed information, the body orientation of a flying object so as to be oriented in a direction in which flying efficiency improves as compared to the most recent state of the object. According to such a configuration, in order for a flying object having directivity to exert the effect of making the most of lifting force or reducing fluid resistance, a flight control method that enables flight in an attitude suitable for the relative wind direction and wind speed during flight is provided. According to such a configuration, it is possible to obtain an optimum flight attitude through adjustment of the body orientation with respect to the wind direction, and also to enhance safety while improving fuel efficiency.
B64C 13/18 - Dispositifs amorçant la mise en œuvre actionnés automatiquement, p. ex. répondant aux détecteurs de rafales utilisant un pilote automatique
B64C 39/02 - Aéronefs non prévus ailleurs caractérisés par un emploi spécial
[Problem] To provide a landing facility or the like that enables safe landing of a flight vehicle even under strong wind conditions. [Solution] This landing device comprises: a first region at which a flight vehicle lands; a windbreak that has a prescribed height, and covers at least a portion of the periphery of the first region; and a second region that is located away from the windbreak section, and over which the flight vehicle descends to a prescribed flight altitude. The flight altitude is an altitude lower than the prescribed height of the windbreak. The second region is a region selected from multiple permitted areas where vertical descent is allowed. A portion of the windbreak is constituted of a net.
[Problem] To provide an aircraft or the like with which impact imparted to a load when unloading can be reduced and quality of delivery can be improved by lowering the load from the landed aircraft while maintaining the orientation of the load and releasing the load such that the impact generated on the load at the time of disconnection is within a specified impact range. [Solution] An aircraft provided with a holding mechanism that holds a load, wherein the holding mechanism moves the load at least vertically downward while keeping the load horizontal after the landing gear of the aircraft comes into contact with the ground.
This aircraft, which flies autonomously on a specified route using a GNSS or the like, is provided with a processor which, if the aircraft does not continue the autonomous flight on the specified route, performs flight control of the aircraft on the basis of information relating to a landing point acquired from the outside by means of an external information acquiring device.
39 - Services de transport, emballage et entreposage; organisation de voyages
Produits et services
Freight brokerage; rental of aircraft; providing information in the field of transportation; travel arrangement; document delivery by non-electronic means; food delivery; providing postal delivery services for packages; transportation and delivery of goods; pick up, delivery and storage of personal property; temporary storage of deliveries; locating and tracking of packages for transportation purposes; air traffic control services
[Problem] To provide an aircraft that allows an improvement in cruising speed by making the body shape of the aircraft (especially a multicopter) into a shape that has less unwanted positive lift and drag caused by the body in a cruising attitude of the fuselage. [Solution] An aircraft equipped with a plurality of rotary wings each including a propeller and a motor, the aircraft being characterized by comprising a body in the shape of an inverted wing. The body has an angle of attack that does not produce lift or produces negative lift when cruising. The body has a positive angle of attack of 12 degrees or less. The present invention is also equipped with a mounting portion on which an object to be mounted can be mounted. The mounting portion is connected to the body with a connection portion therebetween.
[Problem] To provide a flying vehicle by which it is possible to simultaneously realize vertical taking-off and landing and improving fuel economy, and realize stable landing. [Solution] This flying vehicle comprises a flight unit to which a plurality of rotary blade parts and a main wing are connected. The main wing is configured such that a lift generated by the main wing during landing is less than the lift generated by the main wing during cruising. Further, the main wing is tilted forward and fixed with respect to the flight unit. Rotary blades are each connected at an angle for generating a thrust and a lift during cruising. Further, the rotary blades are each connected at an angle for generating a thrust during cruising. Further, the flight unit is configured such that the rotary blades do not interfere with the flight unit or the main wing during landing. Further, the main wing is connected to the flight unit through a rotary shaft. The main wing is configured to tilt the angle with respect to the flight unit more forward about the rotary shaft during the landing than during the cruising.
B64C 3/42 - Réglage autour des axes dans le sens de la corde
B64C 27/26 - Giravions complexes, c.-à-d. aéronefs utilisant en vol à la fois les caractéristiques de l'avion et celles du giravion caractérisé par le fait qu'il est doté d'ailes fixes
B64C 39/02 - Aéronefs non prévus ailleurs caractérisés par un emploi spécial
[Problem] To provide a landing facility that enables safe landing of a flight vehicle even under strong wind conditions. [Solution] A landing facility according to the present invention comprises: a first region that allows a flight vehicle to land thereon; and a windbreak part which has a prescribed height and which covers not the entirety of, but at least a portion of, the perimeter of the first region. The windbreak part is formed of a net. The windbreak part has a portion thereof disabled. The first region includes a laying section. The first region includes a high-position landing section. The first region is disposed on both sides of the windbreak part. The windbreak part has a roof portion that provides overhead coverage above the first region. The entirety of the windbreak part is formed from the same material. The first region is disposed on top of a structural object, and the windbreak part is further disposed on the lateral surfaces of the structural object.
A manned aircraft that enables an efficient and safe transition from hovering to leveled flight. The aircraft according to the present disclosure includes, a flight part provided with a blade part and a thrust generating part provided on the blade part, an airframe part supporting the flight part, and a boarding part that can be displaced independently from the airframe part Through such configuration, it is possible to transition safely from hovering to leveled flight.
B64C 29/02 - Aéronefs capables d'atterrir ou de décoller à la verticale, p. ex. aéronefs à décollage et atterrissage verticaux [ADAV, en anglais VTOL] dont l'axe matérialisant la direction du vol est vertical lorsque l'aéronef est au sol
B64C 27/28 - Giravions complexes, c.-à-d. aéronefs utilisant en vol à la fois les caractéristiques de l'avion et celles du giravion avec hélices propulsives de déplacement pouvant pivoter pour agir comme rotors de sustentation
[Problem] To provide a moving body capable of transporting an object to be transported in a state in which a tilt of the moving body during forward travel does not influence the object to be transported, and the posture of the object to be transported is thus stable. [Solution] Provided is a moving body comprising: a rotating unit which rotates in the pitch direction; and a holding mechanism which holds a transport unit sideways at vicinities of the center of gravity of the transport unit or the upper side of the center of gravity thereof so that the transport unit is held substantially horizontally, the transport unit being capable of accommodating an object to be transported. Moreover, provided is a moving body with a holding mechanism comprising a one-axis rotating unit which rotates only in the pitch direction. Further, provided is a moving body with a holding mechanism which holds the transport unit substantially horizontally through active control. Alternately, the holding mechanism holds the transport unit substantially horizontally through passive control.
An aerial vehicle has a loading section whereon a payload and the like can be loaded. The aerial vehicle is capable of traveling at least forward and backward, is provided with lift generation sections, arm sections for holding the lift generation sections, a loading section disposed on the arm sections and positioned posterior to the center of gravity of the aerial vehicle, and a maintaining means for maintaining the aerial vehicle at least in the horizontal attitude, and the loading section has a first connection part for maintaining a loaded object at least in the horizontal attitude. On the basis of the above mentioned, the payload can be prevented from entering slipstream regions created by propellers, improving flight efficiency.
B64U 50/19 - Propulsion utilisant des moteurs électriques
B64U 101/60 - Véhicules aériens sans pilote spécialement adaptés à des utilisations ou à des applications spécifiques au transport de passagersVéhicules aériens sans pilote spécialement adaptés à des utilisations ou à des applications spécifiques au transport de marchandises autres que des armes
[Problem] To provide a flying body with the improved efficiency and flexibility of an airframe configuration when providing a functional unit to an airframe, and a power device having a configuration for improving the efficiency and flexibility. [Solution] Provided is a flying body, etc., including: a power device having a first space, the upper surface and/or lower surface of which is open; a propeller having a first through space and connected to the power device; and a functional unit which has a predetermined function, and which positions at least one section inside an internal space formed by the first space and the first through space.
[Problem] To provide a flying object with which the falling body can be adjusted to a predetermined orientation and a parachute can be deployed more normally. [Solution] The present disclosure relates to a rotorcraft. The rotorcraft according to the present disclosure comprises a parachute mechanism that ejects a parachute in a predetermined direction and an orientation control means for adjusting the body to a specific orientation when the parachute is ejected. With this configuration, it is possible to reduce the damage, etc., caused when the flying object falls because the parachute can be deployed in a suitable orientation when deployed.
[Problem] To provide a flying body that can be simply loaded with an object and unloaded, and can be operated easily and safely even by a person having no specialized knowledge. [Solution] The present disclosure relates to a flying body. This flying body comprises a holding space into which an object is loaded, a loading port through which the object is loaded into the holding space, and an unloading port for use in unloading the object loaded in the holding space. The loading port and the unloading port of the present invention are provided to at least partially different positions. Such a configuration can be operated easily and safely even by a person having no specialized knowledge.
Estimation of its own position with high accuracy.
Estimation of its own position with high accuracy.
The flight vehicle includes two cameras with different focal lengths, a stabilizer for mounting at least the camera with a short focal length among the two cameras, and a flight controller that calculates the moving speed of the flight vehicle based on the images photographed by the two cameras.
An easy extention of a telescopic rod. The telescopic rod extends in the axial direction by a gas forcibly fed to the inside and is provided with a posture control means.
B64C 39/02 - Aéronefs non prévus ailleurs caractérisés par un emploi spécial
F15B 15/16 - Dispositifs actionnés par fluides pour déplacer un organe d'une position à une autreTransmission associée à ces dispositifs caractérisés par la structure de l'ensemble moteur le moteur étant du type à cylindre droit du type télescopique
[Problem] To increase efficiency of operation during cruise of a rotary wing aircraft. [Solution] A rotary wing aircraft 1 according to the present disclosure comprises: a body 2; and a plurality of motors 3 which are provided for the body 2 and rotate rotors 4, respectively, and the rotation speeds of the plurality of motors 3 are substantially the same when the rotary wing aircraft 1 flies in one travel direction substantially parallel with a reference plane while the body 2 is tilted with respect to the travel direction.
[Problem] To provide a frame assembly for an unmanned aircraft which is light, capable of being reduced in size, and inexpensive to produce, and an unmanned aircraft provided with said frame assembly. [Solution] A frame assembly 60 (61) for an unmanned aircraft according to the present disclosure is configured from a first pipe 60A (61A) and a second pipe 60B (second pipe 61B) having an inner diameter which is larger than the outer diameter of the first pipe 60A (61A), wherein the first pipe 60A (61A) and the second pipe 60B (second pipe 61B) are fixed to each other by insertion of the first pipe 60A (61A) into the second pipe 60B (second pipe 61B).
To provide a flying object in which a working part can be close to an operation target at an appropriate distance the flying object according to the present disclosure includes a flight part including at least a plurality of rotary wings and a motor for driving the rotary wings, a main body elongated in a vertical direction, and a connection part that connects the flight part and the main body in a mutually displaceable manner, wherein a total length of the main body in the vertical direction is at least twice a maximum diameter of the flight part in a horizontal direction. The main body has an upper part that is provided above the connection portion, and a lower portion that is provided below the connection portion, and the length of the upper part is three times or more the length of the lower part.
To provide a flying body in which a working part can be brought close to an appropriate distance from a work target the flying body system according to the present disclosure includes a first rotorcraft and a second rotorcraft. The first rotorcraft and the second rotorcraft are connected by a connecting cable. At least, the second rotorcraft includes a working part. The first rotorcraft and the second rotorcraft maintain the flight of the first rotorcraft and the second rotorcraft in a flight mode, and maintain the flight of the first rotorcraft while work is performed by a working unit even if the flight of the second rotorcraft is stopped in a work mode.
[Problem] To configure the frame of a flight body so as to make it possible to stabilize said frame. [Solution] A frame assembly for an uncrewed aircraft, the frame assembly being characterized by comprising at least two parallel first frame members, a second frame member orthogonal to the first frame members, and a fixing member fixed to each of the first and second frame members.
To provide an electronic component capable of performing attitude control of an aircraft in an ex-post manner. An electronic component according to the present disclosure is attachable to an aircraft. The electronic component includes an arm part, an attachment part for attaching to the main body part of the aircraft, and a connecting part for connecting the arm part and the attachment part so that the arm part and the attachment part can be displaced within a predetermined range. The connecting part is connected to a position that coincides with or substantially coincides with the center of gravity of the arm part. Further, when attached to the aircraft, the connecting part coincides with or substantially coincides with the lift generating center of the aircraft.
H04N 23/90 - Agencement de caméras ou de modules de caméras, p. ex. de plusieurs caméras dans des studios de télévision ou des stades de sport
H04N 23/695 - Commande de la direction de la caméra pour modifier le champ de vision, p. ex. par un panoramique, une inclinaison ou en fonction du suivi des objets
B64U 101/30 - Véhicules aériens sans pilote spécialement adaptés à des utilisations ou à des applications spécifiques à l’imagerie, à la photographie ou à la vidéographie
