A high positive and negative pressure ratio auxiliary support type front fragile cover

Abstract

The present invention provides a high positive and negative pressure ratio auxiliary support type front fragile cover, including an inner cover and an outer cover; the inner cover is connected to the outer cover with a sealing frame, a pressure frame is provided on the top, and a fixing seat is provided at one end of the pressure frame; the outer cover is fixedly connected to the pressure frame by a break screw, and a flip hook is provided at one end of the outer cover, and the flip hook cooperates with the fixing seat. The present invention solves the problem of being fragile and having sufficient strength to provide auxiliary support for the aircraft while meeting the requirements of high positive and negative pressure ratios through a double-layer cover body design, different density design of the inner cover auxiliary support, two-time molding process design of the inner cover, and special locking and flipping mechanism design.

Description

Technical Field

[0001] The invention relates to a high positive-negative pressure ratio auxiliary support type front fragile cover, belonging to the technical field of mechanical design. Background Art

[0002] When the aircraft is stored, it is sealed in the launch box by the front cover. Before or during launch, the front cover needs to be opened. There are three main ways to open the front cover: air pressure bursting, impact opening and mechanical opening. The function of the front cover of the launch box makes the front covers of most current launch devices have air pressure bursting type fragile covers. When the aircraft is launched, the air pressure bursting type front cover can be reliably broken into small pieces under a certain positive pressure and blown away by the gas flow, opening the channel for the aircraft launch. When an adjacent aircraft is launched, the front fragile cover has to withstand a higher negative pressure without breaking, protecting the aircraft in the box from the influence of the gas flow of other aircraft. The positive and negative pressure indicators vary according to different models. The positive and negative pressure ratio of most front covers is not greater than 2.

[0003] Because the front cover needs to break under a given pressure, it has the characteristic of being fragile from the inside to the outside. Therefore, the front cover in the field of aircraft launch devices has almost no requirement for auxiliary support of the aircraft. If the front cover needs to provide auxiliary support for the aircraft, it must withstand the overload force during the transportation and loading and unloading of the aircraft. Therefore, the front cover needs to have higher strength. It is difficult for the same product to maintain a balance between high positive and negative pressure ratio, fragility and high strength characteristics. This requirement places extremely high demands on the front cover.

[0004] As described above, in the field of aircraft launch devices, the front cover has the following problems: it is difficult to achieve a high positive-negative pressure ratio, and it is impossible to provide auxiliary support to the aircraft while maintaining its fragile characteristics. Summary of the invention

[0005] In order to solve the above technical problems, the present invention provides a high positive-negative pressure ratio auxiliary support type front fragile cover.

[0006] The present invention is achieved through the following technical solutions.

[0007] The present invention provides a high positive-negative pressure ratio auxiliary support type front fragile cover, comprising an inner cover and an outer cover; the inner cover is outer-connected with a sealing frame, a pressure frame is provided on the top, and a fixing seat is provided at one end of the pressure frame; the outer cover is fixedly connected to the pressure frame by breaking screws, and a flip hook is provided at one end of the outer cover, and the flip hook works in cooperation with the fixing seat.

[0008] The sealing frame and the pressing frame are connected to the inner cover through screws.

[0009] Four auxiliary support rods are arranged inside the inner cover, cowhide pads are connected to the auxiliary support rods, and gaskets are arranged at the ends of the auxiliary support rods that contact the inner cover.

[0010] The sealing frame is provided with a sealing ring and studs.

[0011] The fixing seat is connected with the flip hook through a pin shaft and a split pin, and the flip hook is connected with the outer cover through a screw.

[0012] A fixing plate connected to the pressing frame is provided on the inner side of the outer cover.

[0013] The fixing plate is connected to the outer cover by screws.

[0014] The auxiliary support rod and the inner cover are formed into a whole by a two-step molding process.

[0015] The beneficial effects of the present invention are as follows: through the double-layer cover body design, the different density design of the inner cover auxiliary support, the two-time molding process design of the inner cover and the special locking and flipping mechanism design, the problem of meeting the requirements of high positive and negative pressure ratio while still being fragile and having sufficient strength to provide auxiliary support for the aircraft is solved. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 It is a schematic diagram of the structure of the present invention in the installation locked state;

[0017] Figure 2 It is a schematic diagram of the structure of the present invention in an open cover state;

[0018] Figure 3 yes Figure 2 A schematic diagram of the structure of the middle inner cover;

[0019] Figure 4 yes Figure 1 Schematic diagram of the structure of the middle and outer covers;

[0020] Figure 5 yes Figure 1 Schematic diagram of the structure of the middle flip hook;

[0021] Figure 6 yes Figure 1 A schematic diagram of the structure of the middle fixed seat;

[0022] In the figure: 1-inner cover, 2-outer cover, 3-cowhide pad, 4-gasket, 5-sealing frame, 6-pressure frame, 7-sealing ring, 8-screw, 9-stud, 10-break screw, 11-flip hook, 12-fixing plate, 13-pin shaft, 14-cotter pin, 15-fixing seat. DETAILED DESCRIPTION

[0023] The technical solution of the present invention is further described below, but the scope of protection claimed is not limited to the description.

[0024] like Figures 1 to 6A high positive-negative pressure ratio auxiliary support type front fragile cover shown in the figure includes an inner cover 1 and an outer cover 2; the inner cover 1 is connected to a sealing frame 5, a pressure frame 6 is provided on the top, and a fixing seat 15 is provided at one end of the pressure frame 6; the outer cover 2 is fixedly connected to the pressure frame 6 by a breaking screw 10, and a flip hook 11 is provided at one end of the outer cover 2, and the flip hook 11 works in cooperation with the fixing seat 15, and the flip hook 11 can rotate and disengage around the fixing seat 15.

[0025] The sealing frame 5 and the pressing frame 6 are connected to the inner cover 1 by screws 8 .

[0026] The inner cover 1 is provided with four auxiliary support rods, to which cowhide pads 3 are connected, and a gasket 4 is provided at one end of the auxiliary support rod in contact with the inner cover 1 .

[0027] The sealing frame 5 is provided with a sealing ring 7 and a stud 9, and the stud 9 is used to connect the front fragile cover and the launch box.

[0028] The fixing seat 15 is connected to the flip hook 11 via a pin shaft 13 and a split pin 14 , and the flip hook 11 is connected to the outer cover 2 via a screw 8 .

[0029] A fixing plate 12 connected to the pressing frame 6 is disposed on the inner side of the outer cover 2 .

[0030] The fixing plate 12 is connected to the outer cover 2 via screws 8 .

[0031] Furthermore, the density of the auxiliary support rod of the inner cover 1 is different from that of the rest of the inner cover 1. The auxiliary support rod and the inner cover 1 are formed into a whole by a two-step molding process. The center of the inner cover 1 can support the aircraft through the auxiliary support rod and the cowhide pad 3, and the force of the aircraft can be transmitted to the sealing frame 5 through the gasket 4. The density of the auxiliary support rod can be adjusted according to the overload force of the aircraft to meet the requirements of various models, and the overload force of the aircraft is transmitted to the sealing frame 5 through the auxiliary support rod. The inner cover 1 will not bear the overload of the aircraft, thereby effectively protecting the inner cover 1.

[0032] Furthermore, the outer cover 2 can withstand the vibration caused by the launch of adjacent aircraft and the erosion of gas flow without falling off. When the aircraft in the present launch box is launched, the screws 10 can be normally disconnected, and the outer cover 2 can be flipped over and dropped off to avoid the adjacent aircraft from affecting the aircraft in the present launch box when the aircraft is launched. Moreover, when the aircraft in the present launch box is launched, the outer cover 2 can be flipped over and dropped off to avoid affecting the launch of the aircraft.

[0033] Furthermore, the inner cover 1 can be broken into four main parts according to the design and fly away from the launch box without affecting the launch of the aircraft.

[0034] Furthermore, the inner cover 1 can be limited by the pressing frame 6, which can prevent the inner cover 1 from creeping and shrinking inwards.

[0035] Furthermore, after the inner cover 1 is broken along the prefabricated groove, the residue will not protrude from the inner surface of the launch box, which can prevent the aircraft from hitting the residue and affecting its flight during launch.

[0036] Furthermore, the pressures that the inner cover 1 and the outer cover 2 withstand can be designed according to different negative pressure working conditions. For example, the positive pressure inside the launch box that the inner cover 1 withstands is 100kPa±20kPa, and the negative pressure outside the launch box that the outer cover 2 withstands is not less than 700kPa.

[0037] If the working conditions require, the sizes of the inner cover 1 and the outer cover 2 and the break screws 10 can be changed, and the density of the inner cover 1 and the outer cover 2 can be changed. According to the cost budget, the material of the front fragile cover can be reasonably adjusted.

[0038] In summary, the present invention is installed on a launch box, can seal the launch box, and can assist in supporting the aircraft in the launch box. When an adjacent aircraft is launched, the aircraft in the launch box can be protected from being burned by the gas flow. When the aircraft in the launch box is launched, the inner cover can be broken under the action of the shock wave, and the outer cover can automatically flip and fall off, leaving the passage for the aircraft to fly without affecting the launch of the aircraft. It has the characteristics of high positive and negative pressure ratio, erosion resistance, simple structure, auxiliary support for the aircraft, light weight, and high reliability.

Claims

1. A high positive-negative pressure ratio auxiliary support type front fragile cover, comprising an inner cover (1) and an outer cover (2), characterized in that: The inner cover (1) is connected to a sealing frame (5) on the outside, and a pressing frame (6) is provided on the top, and a fixing seat (15) is provided at one end of the pressing frame (6); the outer cover (2) is fixedly connected to the pressing frame (6) by means of a break screw (10), and a flip hook (11) is provided at one end of the outer cover (2), and the flip hook (11) cooperates with the fixing seat (15); four auxiliary support rods are provided in the inner cover (1), and cowhide pads (3) are connected to the auxiliary support rods, and a gasket (4) is provided at one end of the auxiliary support rod that contacts the inner cover (1); the auxiliary support rods and the inner cover (1) are formed into a whole by a two-step molding process.

2. The high positive-negative pressure ratio auxiliary support type front fragile cover according to claim 1, characterized in that: The sealing frame (5) and the pressing frame (6) are connected to the inner cover (1) via screws (8).

3. The high positive-negative pressure ratio auxiliary support type front fragile cover according to claim 1, characterized in that: The sealing frame (5) is provided with a sealing ring (7) and a stud bolt (9).

4. The high positive-negative pressure ratio auxiliary support type front fragile cover according to claim 1, characterized in that: The fixing seat (15) is connected to the flip hook (11) via a pin shaft (13) and a split pin (14), and the flip hook (11) is connected to the outer cover (2) via a screw (8).

5. The high positive-negative pressure ratio auxiliary support type front fragile cover according to claim 1, characterized in that: A fixing plate (12) connected to the pressing frame (6) is provided on the inner side of the outer cover (2).

6. The high positive-negative pressure ratio auxiliary support type front fragile cover according to claim 5, characterized in that: The fixing plate (12) is connected to the outer cover (2) via screws (8).

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