A solar array may include a first rigid composite solar panel including solar cells secured to a first substrate. The solar array may further include a second rigid composite solar panel including solar cells secured to a second substrate. The solar array may also include solar panel modules including solar cells secured to a flexible sheet of material. The solar panel modules may be coupled between the first composite solar panel and the second composite solar panel. The solar array may be configured to be retained in a stowed arrangement with the solar panel modules between the first rigid composite solar panel and the second rigid composite solar panel. The solar array further configured to be extended with an extendable arm until each of the first rigid composite solar panel, the second rigid composite solar panel and the solar panel modules are arranged in a substantially straight line.
An insulation precursor composition comprises ethylene propylene diene monomer, an aramid, and a bromine-containing flame retardant. Rocket motors comprising a case, an energetic material within the case, and an insulation material comprising a reaction produce of ethylene propylene diene monomer, an aramid, and a flame retardant comprising bromine are also disclosed. Related precursor compositions are also disclosed.
C08L 23/16 - Copolymères de l’éthylène et du propylène ou de l’éthylène, du propylène et de diène
F02K 9/34 - CartersChambres de combustionLeurs chemises
C08L 77/10 - Polyamides dérivés de groupes amino et carboxyle liés aromatiquement soit d'acides aminocarboxyliques, soit de polyamines et d'acides polycarboxyliques
An apparatus (100) for additively manufacturing an article (102) comprises a heat block (132), a nozzle (112) configured to receive a feed material (106) in operable communication with the heat block (132), and a radiator (130) configured to transfer heat from the heat block to an external environment by thermal radiation. Related tools for additively manufacturing a material in a vacuum, and related methods are also disclosed.
B29C 64/118 - Procédés de fabrication additive n’utilisant que des matériaux liquides ou visqueux, p. ex. dépôt d’un cordon continu de matériau visqueux utilisant un matériau filamentaire mis en fusion, p. ex. modélisation par dépôt de fil en fusion [FDM]
B29C 48/86 - Traitement thermique de la matière à mouler par extrusion ou des pièces ou des couches préformées, p. ex. par chauffage ou refroidissement dans la zone de la filière
4.
PRECURSOR COMPOSITIONS FOR A PROTECTIVE ARTICLE, PROTECTIVE ARTICLES COMPRISING A REACTION PRODUCT OF THE PRECURSOR COMPOSITION, RELATED AEROSPACE STRUCTURES, AND RELATED METHODS
A precursor composition comprising, before cure, an acrylic ethylene monomer (AEM), a foaming agent, and one or more of a strengthening additive, a thermal ablation additive, or a reflectivity additive. The precursor composition is cured to form a protective article comprising a foamed protective material. A method of forming a protective article is also disclosed, as is an aerospace structure comprising the foamed protective material.
C08J 9/00 - Mise en œuvre de substances macromoléculaires pour produire des matériaux ou objets poreux ou alvéolairesLeur post-traitement
C08J 9/32 - Mise en œuvre de substances macromoléculaires pour produire des matériaux ou objets poreux ou alvéolairesLeur post-traitement à partir de compositions contenant des microbilles, p. ex. mousses syntactiques
A solar panel module has a flexible circuit board, a matrix of solar cells surface mounted thereto, a coverglass extending over the matrix of solar cells and the flexible circuit board bonded to a rigid support panel. The circuitry including electrical connection pads in an arrangement on the first side surface for electrical connection of the circuitry to each of the matrix of solar cells, flat bypass diodes may be disposed on the first side surface under the cells and connecting to the circuitry. Conductive adhesives adhering each of the solar cells to the flex circuit at the electrical connection pads that correlate to electrical connection points on underside of each solar cells. The first side having a plurality of standoffs for receiving each of the matrix of solar cells providing raised levels for the solar cells, the landing portions projecting outwardly from a base level surface.
B64G 1/44 - Aménagements ou adaptations des systèmes fournissant l'énergie utilisant des radiations, p. ex. panneaux solaires déployables
H01L 31/04 - Dispositifs à semi-conducteurs sensibles aux rayons infrarouges, à la lumière, au rayonnement électromagnétique d'ondes plus courtes, ou au rayonnement corpusculaire, et spécialement adaptés, soit comme convertisseurs de l'énergie dudit rayonnement e; Procédés ou appareils spécialement adaptés à la fabrication ou au traitement de ces dispositifs ou de leurs parties constitutives; Leurs détails adaptés comme dispositifs de conversion photovoltaïque [PV]
6.
SPACECRAFT SERVICING DEVICES AND RELATED ASSEMBLIES, SYSTEMS, AND METHODS
Spacecraft servicing devices or pods and related methods may be configured to be deployed from a carrier spacecraft and include at least one spacecraft servicing component configured to perform at least one servicing operation on the target spacecraft. The spacecraft servicing devices may be configured to be transported from an initial orbit to another orbit after the spacecraft servicing device is deployed from the carrier spacecraft.
B64G 1/64 - Systèmes pour réunir ou séparer des véhicules spatiaux ou des parties de ceux-ci, p. ex. aménagement pour l'accostage ou l'amarrage
7.
BARRIER COATING RESIN FORMULATIONS, BARRIER COATINGS FORMED FROM THE BARRIER COATING RESIN FORMULATIONS, ARTICLES COMPRISING THE BARRIER COATINGS, ROCKET MOTORS COMPRISING THE BARRIER COATINGS, AND RELATED METHODS
A barrier coating resin formulation comprising at least one polycarbosilane preceramic polymer, at least one organically modified silicon dioxide preceramic polymer, at least one filler, and at least one solvent. A barrier coating comprising a reaction product of the at least one polycarbosilane preceramic polymer and the at least one organically modified silicon dioxide preceramic polymer and the at least one filler is also disclosed, as are articles comprising the barrier coating, rocket motors comprising the barrier coating, and methods of forming the articles.
Methods of forming a composite structure (106) include conforming at least one ply of material (8112) to a forming surface of a tool (102) having differing features. Apparatuses (100) for forming a composite structure include a forming tool (102) and a material feed assembly (104) configured to hold a supply of material, where the material feed assembly may be configured to pivot the supply of material relative to the forming tool (102). Composite structures (106) having an at least partially annular shape are formed by an at least partially automated process.
B29C 70/32 - Façonnage par empilage, c.-à-d. application de fibres, de bandes ou de feuilles larges sur un moule, un gabarit ou un noyauFaçonnage par pistolage, c.-à-d. pulvérisation de fibres sur un moule, un gabarit ou un noyau sur un moule, un gabarit ou un noyau rotatifs
B29C 70/38 - Empilage automatisé, p. ex. utilisant des robots, par application de filaments selon des modèles prédéterminés
B29C 70/56 - Tensionnage des renforcements avant ou pendant le façonnage
An explosive separation joint system having an expandable tube containing a mild detonating fuse (MDF) in separable portions of the joint. The MDF extends into a detonation manifold at a first port, an end of the MDF having booster bonded thereto and axially movable within the manifold. An external initiating ordnance transfer line enters the manifold at an initiating ordnance (IO) port has an IO end tip. A transfer booster is positioned between the IO end tip and the MDF booster. The IO end tip provides a detonation impulse train where each detonating component is axially aligned within a passageway with the next detonating component. In embodiments, particular detonating components of the detonation train are fixed in place where other detonating components are movable.
Spacecraft servicing devices and related methods may include a propellant tank configured to store a propellant and to be placed into fluid communication with a portion of the target spacecraft.
An area denial system may be operationally placed with communication latency compensation. The area denial system may include a plurality of munitions, one or more sensor devices, and a command and control unit, networked together and having a command and control latency for communication between the command and control unit and the remainder of the area denial system. Latency compensation may include determining a first target position, determining a first predicted position area for the target using the command and control latency and the first target position, receiving an authorization to arm one or more of the munitions, determining a second target position, and determining that the second target position is outside a threshold distance from a first authorized munition of the one or more authorized munitions, and in response, de-authorizing the first authorized munition.
F41H 11/00 - Installations de défenseDispositifs de défense Moyens destinés à déminer ou à détecter les mines terrestres
F41A 17/08 - Mécanismes de sûreté, p. ex. sûretés pour empêcher le tir dans une direction prédéterminée, p. ex. le tir sur une personne amie ou le tir sur une aire protégée
12.
Solid propellant bonding agents and methods for their use
Bonding agents for use in formulating solid propellants are described. The bonding agents have a Schiff base, or Schiff base and hydroxyl or amine functionality. These materials are synthesized by reacting a primary amine with an aldehyde to form a Schiff base. By definition, a Schiff base comprises the reaction product of a primary amine and an aldehyde. In one embodiment of the invention, such a product is produced by the reaction of a polyoxyalkyleneamine (JEFFAMINE®) with p-nitrobenzaldehyde and glycidol. The result is a polyether having both hydroxyl and Schiff base functionality. The bonding agents provide superior performance, while avoiding problems, such as ammonia production during processing, encountered when using existing bonding agents. Propellants formulated using these bonding agents have mechanical properties within acceptable ranges.
C06B 23/00 - Compositions caractérisées par des constituants non explosifs ou non thermiques
C06B 29/22 - Compositions contenant un sel inorganique d'un composé d'halogène et d'oxygène, p. ex. chlorate, perchlorate le sel étant du perchlorate d'ammonium
13.
Precision controlled variable thrust solid propellant rocket motor
A multiple-stage solid rocket motor is operated in a manner designed to control its mass discharge profile. This is accomplished by providing means for igniting one stage and then igniting a subsequent stage while the first continues to burn.
Gas-generating devices with grain-retention structures and related methods and systems are described. In particular, gas-generating devices having at least one retention structure fixed to a frame and positioned between adjacent gas-generant grains arranged in a longitudinal stack. Fire suppression systems comprising such gas-generating devices are also described. Additionally, methods of manufacturing gas-generating devices, as well as methods of generating a gas and methods of suppressing a fire utilizing such gas-generating devices are described.
B60R 21/26 - Moyens gonflables de retenue ou d'immobilisation des occupants prévus pour se gonfler lors d'un choc ou en cas de choc imminent, p. ex. sacs gonflables caractérisés par la source de fluide de gonflage ou par les moyens de commande de l'écoulement du fluide de gonflage
C06B 45/00 - Compositions ou produits définis par une structure ou des dispositions particulières des composants ou du produit
12 - Véhicules; appareils de locomotion par terre, par air ou par eau; parties de véhicules
Produits et services
(1) Transportation equipment, namely, rocket powered launch vehicles for use in propelling payloads along suborbital, orbital or supra orbital trajectories.
