Abstract

The present disclosure relates to a propulsion assembly having a nacelle surrounding a turbojet engine, the nacelle having an upstream structure with an air inlet including an air inlet lip, the air inlet lip defining, with the air inlet lip, an air inlet chamber, the upstream structure being capable of translational movement along an axis parallel to a longitudinal axis of the nacelle, between a closed position and an open position that allows access to the turbojet engine. The propulsion assembly further includes at least one locking/unlocking device allowing and preventing movement of the upstream structure that in one form is fixed to the air inlet lip and to an upstream flange of the turbojet engine.

IPC Classes  ?

• B64D 29/06 - Attaching of nacelles, fairings, or cowlings
• B64D 27/16 - Aircraft characterised by the type or position of power plants of jet type
• B64D 33/02 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
• B64F 5/60 - Testing or inspecting aircraft components or systems

Abstract

A turboprop includes a rotary propeller upstream from an engine and an air intake that is not coaxial to the propeller, said air intake defining a conduit for supplying air to the engine and further defining a bypass to said conduit, the bypass having an outlet oriented substantially axially towards the downstream of the engine. The turboprop further includes a nacelle surrounding the engine and the air intake, wherein the air intake is secured to a housing of the engine and is not rigidly connected to the nacelle, so as to allow, during operation, relative movements between the air intake and the nacelle. The outlet is connected by a flexible link to an intake of an air circuit carried by the nacelle.

IPC Classes  ?

• B64D 33/02 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
• F01D 25/24 - CasingsCasing parts, e.g. diaphragms, casing fastenings
• F02C 7/04 - Air intakes for gas-turbine plants or jet-propulsion plants
• F02C 7/045 - Air intakes for gas-turbine plants or jet-propulsion plants having provisions for noise suppression
• F02K 3/06 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type with front fan

Abstract

The invention relates to a propulsion assembly comprising a nacelle surrounding a turbo jet engine, the nacelle comprising an upstream structure (9) comprising: an air inlet (11) comprising an air inlet lip (15), an air inlet lip surround (17) defining, with the air inlet lip, an air inlet chamber (19), the upstream structure being capable of translational movement along an axis parallel to a longitudinal axis of the nacelle, between a closed position and an open position that allows access to the turbo jet engine, said propulstion assembly comprising at least one locking/unlocking device (25) allowing and preventing movement of the upstream structure, comprising means of locking and unlocking the upstream structure. The propulsion assembly according to the invention is notable in that the locking and unlocking means are fixed to the air inlet lip surround (17) and to an upstream flange (29) of the turbo jet engine.

IPC Classes  ?

• B64D 29/06 - Attaching of nacelles, fairings, or cowlings
• B64D 29/08 - Inspection panels for power plants
• F02C 7/04 - Air intakes for gas-turbine plants or jet-propulsion plants

Abstract

The invention relates to a propulsion assembly comprising a nacelle surrounding a turbo jet engine, the nacelle comprising an upstream structure (9) comprising: an air inlet (11) comprising an air inlet lip (15), an air inlet lip surround (17) defining, with the air inlet lip, an air inlet chamber (19), the upstream structure being capable of translational movement along an axis parallel to a longitudinal axis of the nacelle, between a closed position and an open position that allows access to the turbo jet engine, said propulstion assembly comprising at least one locking/unlocking device (25) allowing and preventing movement of the upstream structure, comprising means of locking and unlocking the upstream structure. The propulsion assembly according to the invention is notable in that the locking and unlocking means are fixed to the air inlet lip surround (17) and to an upstream flange (29) of the turbo jet engine.

IPC Classes  ?

• B64D 29/06 - Attaching of nacelles, fairings, or cowlings
• B64D 29/08 - Inspection panels for power plants
• F02C 7/04 - Air intakes for gas-turbine plants or jet-propulsion plants

Abstract

Turboprop air intake A turboprop (110), comprising a rotary propeller (112) upstream from an engine (114) and an air intake (116) that is not coaxial to the propeller, said air intake defining a conduit (119) for supplying air to the engine and further defining a bypass (124) to said conduit, the bypass comprising an outlet (126) oriented substantially axially towards the downstream of the engine, the turboprop further comprising a nacelle (130) surrounding the engine and the air intake, characterised in that the air intake is secured to a housing (123) of the engine and is not rigidly connected to the nacelle, so as to allow, during operation, relative movements between the air intake and the nacelle, said outlet (126) being connected by a flexible link (140) to an intake of an air circuit carried by the nacelle.

IPC Classes  ?

• F02C 7/04 - Air intakes for gas-turbine plants or jet-propulsion plants

Abstract

Turboprop air intake A turboprop (110), comprising a rotary propeller (112) upstream from an engine (114) and an air intake (116) that is not coaxial to the propeller, said air intake defining a conduit (119) for supplying air to the engine and further defining a bypass (124) to said conduit, the bypass comprising an outlet (126) oriented substantially axially towards the downstream of the engine, the turboprop further comprising a nacelle (130) surrounding the engine and the air intake, characterised in that the air intake is secured to a housing (123) of the engine and is not rigidly connected to the nacelle, so as to allow, during operation, relative movements between the air intake and the nacelle, said outlet (126) being connected by a flexible link (140) to an intake of an air circuit carried by the nacelle.

IPC Classes  ?

• F02C 7/04 - Air intakes for gas-turbine plants or jet-propulsion plants

Abstract

The invention relates to a composite structuring panel (1) for the trailing edge of an aircraft element, having: an upper surface (3); a lower surface (5); an edge (7) connecting said upper (3) and lower (5) surfaces; the upper surface (3) and the lower surface (5) being connected by transverse stiffeners (9) and the structuring panel being made of a unitary part forming the upper surface (3), the lower surface (5), the edge (7), and the transverse stiffeners (9). The invention also relates to a method for manufacturing such a panel (1), and to an aircraft element comprising such a panel (1).

IPC Classes  ?

• B64C 3/20 - Integral or sandwich constructions
• B64C 3/26 - Construction, shape, or attachment of separate skins, e.g. panels
• B29C 70/30 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core
• B29D 24/00 - Producing articles with hollow walls
• B29D 99/00 - Subject matter not provided for in other groups of this subclass
• B64C 3/18 - SparsRibsStringers
• B29L 31/30 - Vehicles, e.g. ships or aircraft, or body parts thereof

Abstract

The invention related to a device for making a part of a composite material by resin-transfer molding, that includes a manufacturing mold in which is placed a blank of the part to be impregnated with resin, characterized in that the manufacturing mold is divided into a matrix and one or more mobile structural member to be indexed on the matrix, the whole defining, after assembly, an imprint corresponding to the shape of the part to be manufactured.

IPC Classes  ?

• B29C 70/44 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
• B29C 33/30 - Mounting, exchanging or centering
• B29C 70/48 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs and impregnating the reinforcements in the closed mould, e.g. resin transfer moulding [RTM]
• B29D 99/00 - Subject matter not provided for in other groups of this subclass

Abstract

The present invention relates to a process for manufacturing a part made of a composite having a hollow core (1) comprising the following steps: - applying at least one adhesive layer (6) to an open surface of the hollow core, said process being characterized in that the adhesive layer is a polymerizable blocking adhesive layer having, after polymerization, sealing properties with respect to a resin, and capable of preventing the diffusion of a resin into the hollow core; - and polymerizing the blocking adhesive layer so as to seal the hollow core.

IPC Classes  ?

• B29C 70/08 - Fibrous reinforcements only comprising combinations of different forms of fibrous reinforcements incorporated in matrix material, forming one or more layers, with or without non-reinforced layers
• B29C 70/34 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression
• B29C 70/44 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
• B29C 70/86 - Incorporating in coherent impregnated reinforcing layers
• B29D 24/00 - Producing articles with hollow walls

Abstract

The present invention relates to a device for manufacturing a part made of a composite by resin injection moulding, comprising a manufacturing mould intended to receive at least one preform, the mould being subdivided into a die and one or more indexed movable structural elements on the die, the assembly forming a cavity corresponding to the shape of the part to manufactured, characterized in that the mould is combined with at least one positioning frame, the expansions of which are stable or controlled in at least one direction, the positioning frame being designed so as to allow the indexation and retention of one or more movable structural elements, corresponding to at least one singularity, on the die.

IPC Classes  ?

• B29C 70/48 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs and impregnating the reinforcements in the closed mould, e.g. resin transfer moulding [RTM]
• B29C 33/30 - Mounting, exchanging or centering
• B29C 70/54 - Component parts, details or accessoriesAuxiliary operations

Abstract

The present invention relates to a device for manufacturing a part made of a composite by resin injection moulding, comprising a manufacturing mould intended to receive at least one preform, the mould being subdivided into a die and one or more indexed movable structural elements on the die, the assembly forming a cavity corresponding to the shape of the part to manufactured, characterized in that the mould is combined with at least one positioning frame, the expansions of which are stable or controlled in at least one direction, the positioning frame being designed so as to allow the indexation and retention of one or more movable structural elements, corresponding to at least one singularity, on the die.

IPC Classes  ?

• B29C 70/48 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs and impregnating the reinforcements in the closed mould, e.g. resin transfer moulding [RTM]
• B29C 70/54 - Component parts, details or accessoriesAuxiliary operations
• B29C 33/30 - Mounting, exchanging or centering

Abstract

The invention relates to a method for producing a structural composite trailing edge panel (1) for an aircraft element having: an upper surface (3), a lower surface (5), and a trailing edge (7) connecting said upper (3) and lower (5) surfaces, the upper surface (3) and the lower surface (5) being connected by transverse stiffeners (9), at least one longitudinal spar (10) being positioned in such a way that the directrix (Δ10) of each longitudinal spar (10) and the directrix (Δ9) of the transverse stiffeners (9) are not collinear and the structuring panel (1) being made up of a one-piece component forming the upper surface (3), the lower surface (5), the trailing edge (7), the transverse stiffeners (9) and the spar or spars (10).

IPC Classes  ?

• B64C 3/18 - SparsRibsStringers
• B64C 3/28 - Leading or trailing edges attached to primary structures, e.g. forming fixed slots
• B29D 99/00 - Subject matter not provided for in other groups of this subclass
• B29D 24/00 - Producing articles with hollow walls
• B29C 70/30 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core

Abstract

The invention relates to a molding device (1) for receiving fibers onto which a resin is injected, including a base (3), side plates (5) confining the base (3), and a cover (7) capable of engaging with a free end (9) of the side plates (5) in order to define an inner space (11) for receiving the fibers and the resin, wherein said device (1) comprises, in the inner space (11), a skin (21) that is configured to be complementary to the inner surface of the cover (7) and to at least a portion of the inner surface of the side plates (5). The invention also relates to a method for manufacturing a resin part using such a device (1).

IPC Classes  ?

• B29C 70/48 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs and impregnating the reinforcements in the closed mould, e.g. resin transfer moulding [RTM]
• B29C 33/40 - Plastics, e.g. foam or rubber

Abstract

The invention relates to a composite structuring panel (1) for the trailing edge of an aircraft element, having: an upper surface (3); a lower surface (5); an edge (7) connecting said upper (3) and lower (5) surfaces; the upper surface (3) and the lower surface (5) being connected by transverse stiffeners (9) and the structuring panel being made of a unitary part forming the upper surface (3), the lower surface (5), the edge (7), and the transverse stiffeners (9). The invention also relates to a method for manufacturing such a panel (1), and to an aircraft element comprising such a panel (1).

IPC Classes  ?

• B64C 3/20 - Integral or sandwich constructions
• B29D 99/00 - Subject matter not provided for in other groups of this subclass
• B29C 70/08 - Fibrous reinforcements only comprising combinations of different forms of fibrous reinforcements incorporated in matrix material, forming one or more layers, with or without non-reinforced layers
• B29C 70/30 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core
• B29D 24/00 - Producing articles with hollow walls
• B32B 3/06 - Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by features of form at particular places, e.g. in edge regions for securing layers togetherLayered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by features of form at particular places, e.g. in edge regions for attaching the product to another member, e.g. to a support
• B64C 3/18 - SparsRibsStringers
• B64C 3/26 - Construction, shape, or attachment of separate skins, e.g. panels
• B64C 3/28 - Leading or trailing edges attached to primary structures, e.g. forming fixed slots

Abstract

The invention relates to a composite structuring panel (1) for the trailing edge of an aircraft element, having: an upper surface (3); a lower surface (5); an edge (7) connecting said upper (3) and lower (5) surfaces; the upper surface (3) and the lower surface (5) being connected by transverse stiffeners (9) and the structuring panel being made of a unitary part forming the upper surface (3), the lower surface (5), the edge (7), and the transverse stiffeners (9). The invention also relates to a method for manufacturing such a panel (1), and to an aircraft element comprising such a panel (1).

IPC Classes  ?

• B64C 3/18 - SparsRibsStringers
• B64C 3/28 - Leading or trailing edges attached to primary structures, e.g. forming fixed slots
• B29D 99/00 - Subject matter not provided for in other groups of this subclass
• B29D 24/00 - Producing articles with hollow walls
• B29C 70/30 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core
• B32B 3/06 - Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by features of form at particular places, e.g. in edge regions for securing layers togetherLayered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by features of form at particular places, e.g. in edge regions for attaching the product to another member, e.g. to a support
• B64C 3/20 - Integral or sandwich constructions
• B64C 3/26 - Construction, shape, or attachment of separate skins, e.g. panels

Abstract

The invention relates to a device (10) for making a part of a composite material by resin-transfer moulding, that includes a manufacturing mould (10) in which is placed a blank (1) of the part to be impregnated with resin, characterised in that the manufacturing mould (20) is divided into a matrix (21) and one or more mobile structural members (22) to be indexed on the matrix (21), the whole defining, after assembly, an imprint corresponding to the shape of the part to be manufactured.

IPC Classes  ?

• B29C 33/30 - Mounting, exchanging or centering
• B29C 70/44 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
• B29C 70/48 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs and impregnating the reinforcements in the closed mould, e.g. resin transfer moulding [RTM]

Abstract

The invention relates to a device (10) for making a part of a composite material by resin-transfer moulding, that includes a manufacturing mould (10) in which is placed a blank (1) of the part to be impregnated with resin, characterised in that the manufacturing mould (20) is divided into a matrix (21) and one or more mobile structural members (22) to be indexed on the matrix (21), the whole defining, after assembly, an imprint corresponding to the shape of the part to be manufactured.

IPC Classes  ?

• B29C 33/30 - Mounting, exchanging or centering
• B29C 70/44 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
• B29C 70/48 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs and impregnating the reinforcements in the closed mould, e.g. resin transfer moulding [RTM]

Abstract

The invention relates to a composite sandwich panel (1) comprising at least a web (2) provided between an inner skin (3) and an outer skin (4), each skin being made of a composite material from a plurality of fibrous plies (5, 6, 7, 8), characterised in that a portion of the plies of the inner skin and/or of the outer skin each extends at least partially through the web at an uninterrupted area thereof in order to form together a through-reinforcement (9) extending from the inner skin to the outer skin of the composite sandwich panel. The invention further relates to an aircraft element including such a composite sandwich panel.

IPC Classes  ?

• B32B 5/02 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by structural features of a layer comprising fibres or filaments
• B32B 1/00 - Layered products having a non-planar shape
• B32B 7/00 - Layered products characterised by the relation between layers Layered products characterised by the relative orientation of features between layers, or by the relative values of a measurable parameter between layers, i.e. products comprising layers having different physical, chemical or physicochemical properties Layered products characterised by the interconnection of layers
• B64C 1/00 - FuselagesConstructional features common to fuselages, wings, stabilising surfaces or the like