High-speed ejection device for aircraft

Abstract

The utility model discloses an aircraft high-speed ejection device which comprises a supporting base, an installation box is arranged on the supporting base, the installation box is communicated with an air inlet mechanism, the air inlet mechanism is used for injecting high-pressure air into the installation box, and an adjusting piece is further arranged on the supporting base and used for adjusting the angle between the installation box and the supporting base. A standard high-pressure pipeline is matched with a high-pressure gas cylinder, different pressures can be adjusted, the device is suitable for testing aircrafts of different structures, sizes and types, test boundary conditions can be adjusted in a multi-dimensional mode, the moving posture of the aircraft in the ejection process is accurately simulated, and test requirements are met.

Description

TECHNICAL FIELD

[0001] The utility model relates to mechanical design manufacturing technical field especially a kind of aircraft high-speed launching device. BACKGROUND

[0002] With the development of science and technology, the concept of "low-altitude economy" gradually rises, relying on low-altitude economy, various industrial-grade, consumer-grade unmanned aircraft rise, and the types, models and purposes of unmanned aircraft are more and more rich, and higher requirements are put forward for the attitude control, launching and flight safety of unmanned aircraft, especially high-speed unmanned aircraft.

[0003] In the prior art, a patent named vehicle-mounted unmanned aerial vehicle launching rack is disclosed, with publication number CN102372091 A, which is specifically composed of a launching guide rail, an air energy accumulator and a trolley device. The air energy accumulator is fixed outside the launching guide rail, and the air outlet of the air energy accumulator is in communication with the gas transmission pipeline extended inside the launching guide rail. The inside of the launching guide rail is provided with a kinetic energy accelerator, the bottom of the trolley device is connected with the kinetic energy accelerator, the other end of the gas transmission pipeline is in communication with the kinetic energy accelerator, and the trolley device is in a launching state and has a parallelogram structure. The present application adopts a launching type take-off form, which has the greatest advantage of reducing the requirement for take-off site and improving the mobility of the aircraft during take-off, thereby solving the problems of dependence on runway during take-off of the aircraft and difficulty in finding take-off site. In addition, the trolley device is arranged in a parallelogram structure, which is more suitable for aircraft models with long tail rods and can accurately hold the center of gravity of the aircraft, so that the launching aircraft can obtain a good attitude when leaving the orbit.

[0004] However, the technology still has some defects. On the one hand, it is not convenient to adjust the take-off attitude angle of the aircraft, so it is not suitable for flight tests of various attitude adjustments of the aircraft. On the other hand, the structure is difficult to meet the take-off power requirements of different sizes of aircraft. UTILITY MODEL CONTENTS

[0005] To solve the above technical problems, the utility model provides a kind of aircraft high-speed launching device.

[0006] The utility model is realized by the following technical solutions.

[0007] The utility model provides a kind of aircraft high-speed launching device, including support base, support base is provided with installation box, installation box is connected with air inlet mechanism, air inlet mechanism is used to inject high-pressure gas into installation box, support base is also equipped with adjusting part, and adjusting part is used to adjust the angle between installation box and support base.

[0008] Preferably, the installation box comprises a box body, a rear valve cover and a piston, the rear valve cover is sealingly connected to the rear end of the box body, and the piston is movably arranged in the box body, and a sealed space is formed between the piston and the rear valve cover.

[0009] Preferably, the adjusting member is an electric cylinder, the electric cylinder is mounted on the support base, an output shaft of the electric cylinder is hingedly connected to the front end of the box body, and the rear end of the box body is hingedly connected to the support base.

[0010] Preferably, the air inlet mechanism comprises a high-pressure gas cylinder, a high-pressure pipeline and a fixing support, the high-pressure gas cylinder is mounted on the fixing support, and the high-pressure gas cylinder is communicated with the rear end of the box body through the high-pressure pipeline.

[0011] Preferably, the rear end of the box body is provided with a sealing skirt.

[0012] Preferably, the high-pressure pipeline is provided with a control valve.

[0013] Preferably, the high-pressure gas cylinder is vertically fixed on the fixing support through bolts.

[0014] Preferably, the electric cylinder is mounted on the support base through bolts.

[0015] The beneficial effects of the utility model lie in that:

[0016] ①The structure is simple, the mechanical structure has high reliability and good economy;

[0017] ②The standard high-pressure pipeline is matched with the high-pressure gas cylinder, different pressures can be adjusted, and the utility model is suitable for testing aircrafts of different structures, sizes and types;

[0018] ③The utility model has high accuracy, can adjust test boundary conditions in multiple dimensions, accurately simulates the movement posture of the aircraft ejection process, and meets the test requirements. BRIEF DESCRIPTION OF DRAWINGS

[0019] Figure 1 is the structural schematic view of the utility model;

[0020] Figure 2 is the structural schematic view of the utility model mainly used for showing the installation box;

[0021] In the drawing: 1-high pressure gas cylinder; 2-fixing support; 3-high pressure pipeline; 4-support base; 5-electric cylinder; 6-installation box; 7-rear valve cover; 8-sealing skirt; 9-piston; 10-aircraft; 11-box body; 12-control valve. DETAILED DESCRIPTION

[0022] The technical solutions in the embodiments of the utility model will be clearly and completely described below with reference to the drawings in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, rather than all the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by those skilled in the art without creative labor fall within the scope of the utility model.

[0023] It should be noted that all the directionality indications (such as up, down, left, right, front, back, etc.) in the embodiments of the utility model are only used to explain the relative position relationship, movement condition, etc. between the components in a certain specific posture (as shown in the drawings), and if the specific posture changes, the directionality indications will also change accordingly.

[0024] In the embodiment, refer to Figure 1 and Figure 2 , the support base 4 is provided with the mounting box 6, the mounting box 6 comprises a box body 11, a rear valve cover 7 and a piston 9, the rear valve cover 7 is sealingly connected to the rear end of the box body 11, the piston 9 is movably arranged in the box body 11, a sealed space is formed between the piston 9 and the rear valve cover 7, a sealing skirt 8 is fixedly installed inside the rear end of the box body 11, the sealing skirt 8 is used to strengthen the sealing degree of the sealed space, the sealed space is used to inject high-pressure gas, and the high-pressure gas forms a thrust to push the launcher to launch.

[0025] In the embodiment, refer to Figure 1 and Figure 2 , the support base 4 is further provided with an adjusting member, the adjusting member is used to adjust the angle between the mounting box 6 and the support base 4, the adjusting member is an electric cylinder 5, the electric cylinder 5 is fixedly installed on the support base 4, the output shaft of the electric cylinder 5 is hingedly connected to the front end of the box body 11, and the rear end of the box body 11 is hingedly connected to the support base 4; the front end of the box body 11 is driven to ascend by starting the electric cylinder 5, so that the angle of the mounting box 6 as a whole is adjusted, multi-dimensional adjustment of test boundary conditions is realized, the movement posture of the launcher 10 in the ejection process is accurately simulated, and the test requirement is met.

[0026] In the embodiment, refer to Figure 1 , the electric cylinder 5 is fixed on the support base 4 by bolts, and the electric cylinder 5 is fixed.

[0027] In the embodiment, refer to Figure 1The installation box 6 is communicated with an air inlet mechanism for injecting high-pressure gas into the installation box 6, the air inlet mechanism comprises a high-pressure gas cylinder 1, a high-pressure pipeline 3 and a fixing support 2, the high-pressure gas cylinder 1 is fixed vertically on the fixing support 2 through bolts, so that the stable output of gas in the high-pressure gas cylinder 1 is ensured, the high-pressure gas cylinder 1 is communicated with the rear end of the box body 11 through the high-pressure pipeline 3, and a control valve 12 is arranged on the high-pressure pipeline 3, so that the closing or opening of the high-pressure pipeline 3 is realized through the control valve 12.

[0028] The working process of the embodiment is as follows: the required pressure of the ejection gas is determined through interior ballistic calculation, the control valve 12 controls the opening of the high-pressure pipeline 3, the gas in the high-pressure gas cylinder 1 is injected into the installation box 6 from the rear valve cover 7 at the calculated pressure, the different launch installation angles of the installation box 6 are adjusted by the electric cylinder 5, the rear valve cover 7, the sealing skirt 8 and the piston 9 in the box body 11 form a high-pressure sealed cavity, the aircraft 10 is ejected out of the box under the action of the high-pressure gas, the out-of-box posture of the aircraft 10 under different launch angles and speeds is obtained by using a high-speed camera, the boundary conditions of the multi-dimensional adjustment test are adjusted, the motion posture of the ejection process of the aircraft 10 is accurately simulated, and the test demand is met.

[0029] The above is only the preferred embodiment of the utility model, and does not limit the patent range of the utility model, and any equivalent structural transformation made under the concept of the utility model, or direct / indirect application in other related technical fields by using the utility model specification and the attached drawings is included in the patent protection range of the utility model.

Claims

1. A high-speed catapult launch device for aircraft, characterized in that: It includes a support base (4), on which a mounting box (6) is provided. The mounting box (6) is connected to an air intake mechanism, which is used to inject high-pressure gas into the mounting box (6). The support base (4) is also provided with an adjustment component, which is used to adjust the angle between the mounting box (6) and the support base (4).

2. The high-speed catapult device for aircraft as described in claim 1, characterized in that: The mounting box (6) includes a box body (11), a rear valve cover (7) and a piston (9). The rear valve cover (7) is sealed to the rear end of the box body (11), and the piston (9) is movably disposed inside the box body (11). A sealed space is formed between the piston (9) and the rear valve cover (7).

3. The high-speed catapult device for aircraft as described in claim 2, characterized in that: The adjusting component is configured as an electric cylinder (5), which is mounted on the support base (4). The output shaft of the electric cylinder (5) is hinged to the front end of the housing (11), and the rear end of the housing (11) is hinged to the support base (4).

4. The high-speed catapult device for an aircraft as described in claim 2, characterized in that: The air intake mechanism includes a high-pressure gas cylinder (1), a high-pressure pipeline (3), and a fixed bracket (2). The high-pressure gas cylinder (1) is installed on the fixed bracket (2), and the high-pressure gas cylinder (1) is connected to the rear end of the housing (11) through the high-pressure pipeline (3).

5. A high-speed catapult launch device for an aircraft as described in claim 2, characterized in that: The rear end of the housing (11) is provided with a sealing skirt (8).

6. The high-speed catapult device for an aircraft as described in claim 4, characterized in that: A control valve (12) is installed on the high-pressure pipeline (3).

7. A high-speed catapult launch device for an aircraft as described in claim 4, characterized in that: The high-pressure gas cylinder (1) is vertically fixed to the fixed bracket (2) by bolts.

8. A high-speed catapult launch device for an aircraft as described in claim 3, characterized in that: The electric cylinder (5) is mounted on the support base (4) by bolts.

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