Buffer structure capable of being pneumatically separated

Abstract

The buffering structure capable of being pneumatically separated is installed between an outer cover and protected equipment and is restrained on the periphery of the protected equipment through certain extrusion force between the outer cover and the protected equipment, and impact load energy transmitted to the protected equipment is reduced through deformation energy absorption of the buffering structure capable of being pneumatically separated. Impact protection of protected equipment on an aircraft can be achieved, normal work of the equipment is guaranteed by means of pneumatic load separation, the inverted-cone-shaped structure is arranged to increase the pneumatic load during separation, separation reliability is guaranteed, and separation time is shortened; the weak part of the protected equipment is avoided by optimizing the transmission path of the impact load, the protected equipment is more effectively protected, and meanwhile, the structural weight is effectively reduced.

Description

Technical Field

[0001] The present invention belongs to the protection of equipment carried on an aircraft, and specifically relates to a pneumatically separable buffer structure. Background Art

[0002] During the flight of an aircraft, when taking off or landing or completing a specific mission, the equipment carried on the aircraft may be subjected to a large impact force. Therefore, a set of buffer structures need to be designed to reduce the impact load on the equipment. When the aircraft is performing a specific mission, the carried equipment needs to protrude outside the aircraft, and during this period, it may be accompanied by the impact of pyrotechnic device operation and foreign debris such as foreign fragments. Therefore, it is necessary to consider the problems of equipment impact protection and buffer structure separation. After avoiding the impact objects, the buffer structure needs to be reliably separated and disengaged to prevent the protected equipment from being blocked and unable to work properly.

[0003] Some of the equipment carried on the aircraft belongs to precision instruments, and measures cannot be taken at the equipment end, and the impact source cannot be eliminated. Therefore, only measures can be considered on the vibration and impact transmission path.

[0004] Patent document CN210027868U provides a buffer structure that can be detachably connected to the main body. The buffer structure includes: a first part, when the buffer structure is connected to the main body, the second end of the first part is connected to the first end of the main body; a second part, connected to the second end of the first part, when the buffer structure is connected to the main body, the second part can block the first opening of the main body. However, this patent document CN210027868U is applicable to aircraft such as unmanned aerial vehicles and is not applicable to aircraft with an outer cover and protected equipment. Summary of the Invention

[0005] Aiming at the defects in the prior art, the purpose of the present invention is to provide a pneumatically separable buffer structure.

[0006] According to a pneumatically separable buffer structure provided by the present invention, the head of the pneumatically separable buffer structure 2 is conformal with the inner surface of the outer cover 1, and the tail is conformal with the head surface of the protected equipment 3.

[0007] The pneumatically separable buffer structure 2 includes multiple units; the multiple units are uniformly distributed and spliced in the circumferential direction; each unit has a hollowed-out area 201 at the tail of the unit and an inverted conical structure 202 at the head of the unit; the unit is made of buffer structure material.

[0008] Preferably, the overall shape of the pneumatically separable buffer structure 2 is a conical shape with a smaller front and a larger rear.

[0009] Preferably, along the axial direction, the length of the inverted conical structure 202 is greater than the length of the hollowed-out area 201.

[0010] Preferably, along the axial direction, the length ratio of the inverted conical structure 202 to the hollowed-out area 201 is less than 3.

[0011] Preferably, the multiple pieces of units are four-piece units.

[0012] Preferably, the hollowed-out area 201 extends circumferentially, and the hollowed-out areas 201 of adjacent units are not connected.

[0013] Preferably, the pneumatically separable buffer structure 2 is made of a rubber-like material;

[0014] Alternatively, a metal honeycomb structure is adopted, and the deformation of the honeycomb structure is used to absorb impact energy;

[0015] Alternatively, a metal inner core is sprayed with rubber or a soft coating on the outside.

[0016] Preferably, auxiliary separation force is increased by measures such as adding a transverse spring between adjacent two units of the pneumatically separable buffer structure 2.

[0017] An aircraft according to the present invention includes: an outer cover 1, a pneumatically separable buffer structure 2, and a protected device 3;

[0018] The pneumatically separable buffer structure 2 is installed between the outer cover 1 and the protected device 3, and is constrained around the protected device 3 by a certain extrusion force between the outer cover 1 and the protected device 3, and the impact load energy transmitted to the protected device 3 is reduced by the energy absorption through the deformation of the pneumatically separable buffer structure 2.

[0019] Preferably, there is no rigid connection between the outer cover 1, the pneumatically separable buffer structure 2, and the protected device 3; when the outer cover 1 releases the constraint on the pneumatically separable buffer structure 2, the pneumatically separable buffer structure 2 separates under the action of pneumatic load, and the protected device 3 is exposed.

[0020] Compared with the prior art, the present invention has the following beneficial effects:

[0021] 1. The present invention can achieve the impact protection of the protected device on the aircraft, and at the same time rely on the pneumatic load separation to ensure the normal operation of the device.

[0022] 2. In the present invention, the pneumatically separable buffer structure adopts materials such as rubber-like materials, which further plays a buffering role.

[0023] 3. The head of the pneumatically separable buffer structure in the present invention has an inverted conical structure to increase the pneumatic load during separation, ensure separation reliability and shorten the separation time. The tail is a hollow structure, which optimizes the impact load transmission path to avoid the weak parts of the protected device, forms a more effective protection for the protected device, and effectively reduces the structural weight at the same time. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Other features, objects, and advantages of the present invention will become more apparent by reading the following detailed description of non-limiting embodiments with reference to the accompanying drawings:

[0025] Figure 1 Schematic diagram of a pneumatically separable buffer structure of the present invention;

[0026] Figure 2 Installation schematic diagram of the buffer structure;

[0027] As shown in the figure:

[0028] DETAILED DESCRIPTION OF THE EMBODIMENTS

[0029] The present invention will be described in detail below with reference to specific embodiments. The following embodiments will help those skilled in the art to further understand the present invention, but do not limit the present invention in any form. It should be noted that those of ordinary skill in the art can make several changes and improvements without departing from the concept of the present invention. These all belong to the protection scope of the present invention.

[0030] As Figure 2 shown, a flying vehicle provided according to the present invention includes: an outer cover 1, a pneumatically separable buffer structure 2, and a protected device 3; the pneumatically separable buffer structure 2 is installed between the impact source and the protected device for impact protection of the equipment carried on the flying vehicle, that is, the pneumatically separable buffer structure 2 is installed between the outer cover 1 and the protected device 3, and the impact load energy transmitted to the protected device 3 is reduced by the deformation and energy absorption of the pneumatically separable buffer structure 2. Specifically, the pneumatically separable buffer structure 2 is constrained around the protected device 3 by a certain extrusion force between the outer cover 1 and the protected device 3. There is no rigid connection between the outer cover 1, the pneumatically separable buffer structure 2, and the protected device 3; when the outer cover 1 releases the constraint on the pneumatically separable buffer structure 2, the pneumatically separable buffer structure 2 separates under the action of the pneumatic load, and the protected device 3 is exposed;

[0031] The overall pneumatically separable buffer structure 2 presents a conical shape that is smaller at the front and larger at the rear. It is made of rubber-like materials, or a metal honeycomb structure, and uses the deformation of the honeycomb structure to absorb and reduce the impact energy received by the protected device 3. Or it is a material with a buffering effect such as rubber sprayed on the outside of a metal core or a soft coating sprayed.

[0032] The head of the pneumatically separable buffer structure 2 is conformal with the inner surface of the outer cover 1, and the tail is conformal with the head surface of the protected device 3. The pneumatically separable buffer structure 2 is mainly composed of multiple units that are evenly distributed and spliced in contact in the circumferential direction. In the preferred example, it is only composed of multiple units, such as four units, as Figure 1 shown, which shows a comparison structural schematic diagram of one of the four units observed from two perspectives. Each unit includes a hollow area 201 and an inverted conical structure 202.

[0033] The head of the pneumatically separable buffer structure 2 has an inverted conical structure 202 to increase the pneumatic load during separation and ensure separation reliability. In the preferred example, the length ratio of the inverted conical structure 202 to the hollow area 201 is less than 3, so as to shorten the separation time while having enough time to deform and absorb the impact energy as much as possible. The tail is a hollow structure 201, which optimizes the impact load transfer path to avoid the weak parts of the protected device 3, forms a more effective protection for the protected device 3, and effectively reduces the structural weight at the same time.

[0034] In the preferred example, measures such as adding a transverse spring between adjacent two units of the pneumatically separable buffer structure 2 are taken to increase the auxiliary separation force.

[0035] In the description of the present application, it should be understood that the orientation or positional relationship indicated by the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the present application and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation to the present application.

[0036] The specific embodiments of the present invention have been described above. 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. Without conflict, the embodiments of the present application and the features in the embodiments can be combined with each other arbitrarily.

Claims

1. A pneumatically separable buffer structure, characterized in that, The head of the pneumatically separable buffer structure (2) is conformal to the inner surface of the outer cover (1), while the tail is conformal to the head surface of the protected device (3). The pneumatically separable buffer structure (2) includes multiple units; the multiple units are evenly distributed and in contact and joined together circumferentially; each unit has a hollowed-out area (201) at the tail of the unit and an inverted conical structure (202) at the head of the unit; the unit is made of buffer structure material.

2. The pneumatically separable buffer structure according to claim 1, wherein, The overall shape of the pneumatically separable buffer structure (2) is a conical shape that is smaller at the front and larger at the back.

3. The pneumatically separable buffer structure according to claim 1, characterized in that, In the axial direction, the length of the inverted conical structure (202) is greater than the length of the hollowed-out area (201).

4. The pneumatically separable buffer structure according to claim 3, characterized in that In the axial direction, the length ratio of the inverted conical structure (202) to the hollowed-out area (201) is less than 3.

5. The pneumatically separable buffer structure according to claim 1, characterized in that, The multiple units are four units.

6. The pneumatically separable buffer structure according to claim 1, characterized in that, The hollowed-out area (201) extends circumferentially, and the hollowed-out areas (201) of adjacent units are not connected to each other.

7. The pneumatically separable buffer structure according to claim 1, wherein The pneumatically separable buffer structure (2) is made of rubber-like material; Or, a metal honeycomb structure is used, and the deformation of the honeycomb structure is utilized to absorb impact energy; Or, a metal core is used with rubber or a soft coating sprayed on the outside.

8. The pneumatically separable buffer structure according to claim 1, characterized in that, Measures such as adding a transverse spring between adjacent units of the pneumatically separable buffer structure (2) are taken to increase the auxiliary separation force.

9. An aircraft, characterized in that, It includes: An outer cover (1), a pneumatically separable buffer structure (2), and a protected device (3); The pneumatically separable buffer structure (2) is installed between the outer cover (1) and the protected device (3), and is constrained around the protected device (3) by a certain extrusion force between the outer cover (1) and the protected device (3), and the impact load energy transmitted to the protected device (3) is reduced by the energy absorption through the deformation of the pneumatically separable buffer structure (2).

10. According to claim 1, wherein There is no rigid connection between the outer cover (1), the pneumatically separable buffer structure (2), and the protected device (3) pairwise; when the outer cover (1) releases the constraint on the pneumatically separable buffer structure (2), the pneumatically separable buffer structure (2) separates under the action of pneumatic load, exposing the protected device (3).

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