Outboard protection device for aircraft interstage separation and aircraft

Abstract

The invention provides an outboard protection device for aircraft interstage separation and an aircraft. The outboard protection device comprises an outboard protection device unit and a limiting bulge, an out-cabin protection device is installed at the position close to the stage separation position of the cabin body, the out-cabin protection device is composed of a plurality of sections of out-cabin protection device units which define a circular ring, limiting protrusions are arranged on the out-cabin protection device units, positioning grooves are formed in the surface of the cabin body, and the limiting protrusions and the positioning grooves are installed in a matched mode. The aircraft structure is enhanced and protected through the outboard protection device when the aircraft is subjected to interstage separation, the adverse effect of detonation waves generated by the interstage separation device on the aircraft structure is reduced to the maximum extent, and meanwhile the heat-proof coating of the interstage separation area is protected.

Description

Technical Field

[0001] The present invention relates to the field of aircraft parts, in particular to an extravehicular protection device for aircraft inter-stage separation and an aircraft. Background Art

[0002] The aircraft is equipped with an interstage separation device to achieve two-stage separation, ensuring that the normal flight of the aircraft after interstage separation is not affected. When the two stages of the aircraft are separated, the detonation wave generated by the interstage separation device may cause structural damage to the cabin, and may also peel off the thermal protection coating, which will have an adverse effect on the structural strength and thermal protection performance of the aircraft. Therefore, it is necessary to design an extravehicular protection device for interstage separation of aircraft to enhance the structure of the aircraft, ensure the structural safety of the aircraft, and protect the external thermal protection coating, so as to achieve safe and reliable interstage separation of the aircraft. Summary of the invention

[0003] In view of the defects in the prior art, an object of the present invention is to provide an extravehicular protection device for aircraft stage separation and an aircraft.

[0004] According to the present invention, an extravehicular protection device for aircraft interstage separation includes: an extravehicular protection device unit and a limiting protrusion;

[0005] An extravehicular protection device is installed near the interstage separation of the cabin body. The extravehicular protection device is composed of a plurality of extravehicular protection device units that are surrounded in a circular ring. A limiting protrusion is provided on the extravehicular protection device unit, and a positioning groove is provided on the surface of the cabin body. The limiting protrusion is installed in cooperation with the positioning groove.

[0006] Preferably, the cabin body is coated with a heat-resistant coating, and the outer cabin protection device is installed between the heat-resistant coating and the interstage separation and is close to the end of the heat-resistant coating.

[0007] Preferably, the extravehicular protection device comprises: a left-flap extravehicular protection device and a right-flap extravehicular protection device;

[0008] The left-valve cabin protection device and the right-valve cabin protection device are configured as mirror-symmetrical semicircular segments, and the left-valve cabin protection device and the right-valve cabin protection device are installed together on the peripheral side of the cabin body.

[0009] Preferably, the plurality of sections of the extravehicular protection device units are fixed to the cabin body by radial screws, and the plurality of sections of the extravehicular protection device units are fixed to each other by circumferential screws.

[0010] Preferably, the radial screws are provided in plurality and arranged in two rows in the axial direction of the cabin.

[0011] Preferably, the outboard protection device is made of stainless steel.

[0012] Preferably, the left valve outboard protection device and the right valve outboard protection device both include: a straight area, a concave area and a curved area;

[0013] Both ends of the straight area are connected to the concave area, and one end of the concave area away from the straight area is connected to the curved area.

[0014] Compared with the prior art, the present invention has the following beneficial effects:

[0015] The present application uses an extravehicular protection device to enhance and protect the aircraft structure when the aircraft stages separate, minimize the adverse effects of the detonation wave generated by the interstage separation device on the aircraft structure, and protect the thermal protection coating in the interstage separation area. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Other features, objects and advantages of the present invention will become more apparent from the detailed description of non-limiting embodiments made with reference to the following drawings:

[0017] Figure 1 Schematic diagram of installing the extravehicular protection device on the cabin;

[0018] Figure 2 This is a side view of the extravehicular protection device;

[0019] Figure 3 This is the main view of the extravehicular protection device;

[0020] Figure 4 This is a cross-sectional view of the extravehicular protection device;

[0021] As shown in the figure:

[0022] DETAILED DESCRIPTION

[0023] The present invention is described in detail below in conjunction with specific embodiments. The following embodiments will help those skilled in the art to further understand the present invention, but are not intended to limit the present invention in any form. It should be noted that, for those of ordinary skill in the art, several changes and improvements can also be made without departing from the concept of the present invention. These all belong to the protection scope of the present invention.

[0024] like Figure 1-2 As shown, this embodiment adopts a solution of setting an extravehicular protection device 1 at the interstage separation 202 near the cabin 2 to protect against the damage caused by the detonation wave. The extravehicular protection device 1 can effectively enhance the structure of the aircraft, ensure the structural safety of the aircraft, and protect the external thermal protection coating 201. The extravehicular protection device 1 includes: a plurality of extravehicular protection device units enclosed in a ring and a limiting protrusion 105 set on the extravehicular protection device unit.

[0025] like Figure 4 As shown, the surface of the cabin 2 is provided with a positioning groove 203 for matching the installation of the limiting protrusion 105. The cabin 2 is coated with a heat-resistant coating 201 on one side of the positioning groove 203, and the outer cabin protection device 1 is installed between the heat-resistant coating 201 and the positioning groove 203. The outer cabin protection device 1 is close to the end of the heat-resistant coating 201, and there is no heat-resistant coating 201 below the outer cabin protection device 1. During installation, the limiting protrusion 105 of the outer cabin protection device 1 is aligned with the positioning groove 203 on the outside of the cabin 2, which plays a role of positioning and limiting in the axial direction.

[0026] like Figure 3 As shown, the multi-stage outboard protection device units are fixed to the cabin body 2 by radial screws 103, and the multi-stage outboard protection device units are fixed by circumferential screws 104. There are multiple radial screws 103 and they are arranged in two rows in the axial direction of the cabin body 2.

[0027] In one embodiment, the outboard protection device 1 includes: a left-flap outboard protection device 101 and a right-flap outboard protection device 102; the left-flap outboard protection device 101 and the right-flap outboard protection device 102 are configured as two semicircular segments arranged in a left-right mirror-symmetrical manner. When the stages are separated, the impact on the cabin 2 is not completely uniform in the circumferential direction, so an equal strength design is adopted to minimize the structural weight of the device while ensuring the structural strength. Figure 3 , a straight line area is set to surround the middle area of ​​the extravehicular protection device 1, wrapping the cabin to the maximum extent to increase rigidity and strength. Then there is a concave area, and finally transitions to a curved area, which can effectively reduce stress concentration. At the same time, the shape is simple and clear, and has good processing technology. The left-flap extravehicular protection device 101 and the right-flap extravehicular protection device 102 are installed on the surrounding side of the cabin 2. The left-flap extravehicular protection device 101 and the right-flap extravehicular protection device 102 are both made of stainless steel arc-shaped thin plates and have sufficient structural strength. The left-flap extravehicular protection device 101 and the right-flap extravehicular protection device 102 are fastened together by upper and lower circumferential screws 104 to further enhance the structural support for the cabin 2.

[0028] In one embodiment, the outboard protection device 1 is made of stainless steel.

[0029] In one embodiment, the left flap extravehicular protection device 101 and the right flap extravehicular protection device 102 are radially connected to the cabin body 2 through 8 radial screws 103. The 8 radial screws 103 are divided into two rows in the axial direction, which can effectively increase the structural strength and positioning function in the axial direction, and 4 screws are evenly distributed on the radial end surface in each row. It ensures that the extravehicular protection device 1 is firmly connected to the cabin body 2, and plays a role in structural support and strengthening the cabin body 2.

[0030] In the description of the present application, it should be understood that the terms "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the present application.

[0031] The above describes the specific embodiments of the present invention. It should be understood that the present invention is not limited to the above specific embodiments, and those skilled in the art can make various changes or modifications within the scope of the claims, which does not affect the essence of the present invention. In the absence of conflict, the embodiments of the present application and the features in the embodiments can be combined with each other arbitrarily.

Claims

1. An extravehicular protection device for aircraft stage separation, characterized in that: include: An outer protective device unit and a limiting protrusion (105); An extravehicular protection device (1) is installed near the interstage separation (202) of the cabin (2), and the extravehicular protection device (1) is composed of a plurality of extravehicular protection device units that are surrounded in a circular ring, and a limiting protrusion (105) is provided on the extravehicular protection device unit. A positioning groove (203) is provided on the surface of the cabin (2), and the limiting protrusion (105) is installed in cooperation with the positioning groove (203).

2. The extravehicular protection device for aircraft stage separation according to claim 1, characterized in that: The cabin body (2) is coated with a heat-resistant coating (201), and the outer cabin protection device (1) is installed between the heat-resistant coating (201) and the interstage separation (202) and is closely attached to the end of the heat-resistant coating (201).

3. The extravehicular protection device for aircraft stage separation according to claim 1, characterized in that: The extravehicular protection device (1) comprises: a left-flap extravehicular protection device (101) and a right-flap extravehicular protection device (102); The left-flap cabin exterior protection device (101) and the right-flap cabin exterior protection device (102) are configured as two semicircular segments arranged left and right, and the left-flap cabin exterior protection device (101) and the right-flap cabin exterior protection device (102) are installed together on the circumference of the cabin body (2).

4. The extravehicular protection device for aircraft stage separation according to claim 1, characterized in that: The multiple sections of the outboard protection device units are fixed to the cabin body (2) via radial screws (103), and the multiple sections of the outboard protection device units are fixed to each other via circumferential screws (104).

5. The extravehicular protection device for aircraft stage separation according to claim 4, characterized in that: The radial screws (103) are provided in plurality and arranged in two rows in the axial direction of the cabin body (2).

6. The extravehicular protection device for aircraft stage separation according to claim 1, characterized in that: The outboard protection device (1) is made of stainless steel.

7. The extravehicular protection device for aircraft stage separation according to claim 3, characterized in that: The left-flap extravehicular protection device (101) and the right-flap extravehicular protection device (102) are mirror-symmetrical structures.

8. The extravehicular protection device for aircraft stage separation according to claim 3, characterized in that: The left flap extravehicular protection device (101) and the right flap extravehicular protection device (102) both comprise: a straight area, a concave area and a curved area; Both ends of the straight area are connected to the concave area, and one end of the concave area away from the straight area is connected to the curved area.

9. An aircraft, characterized in that: An extravehicular protection device for aircraft interstage separation as described in claims 1 to 8 is adopted.

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