Device for pneumatic test of hypersonic aircraft

Abstract

The utility model discloses a device for a pneumatic test of a hypersonic aircraft, which is applied to the field of aircrafts and is characterized in that a pressing head is moved, the pressing head moves to drive a pressing rod to move, the pressing rod moves to drive a clamping head to move, the clamping head moves to enable the clamping head to be separated from a clamping hole, and then the aircraft is taken down. The mounting rod on the aircraft is inserted into the mounting seat, and the pressing rod drives the clamping head to be clamped with the clamping hole under the action of the spring so as to fix the clamping head and the clamping hole, so that the purpose of conveniently assembling and disassembling the aircraft is achieved, the workload is reduced, and the working efficiency is improved. The worm gear rotates to enable the supporting rod to drive the sensor to rotate, the sensor rotates to drive the mounting base to rotate, the mounting base rotates to drive the aircraft to rotate, the angle of the aircraft is changed, and therefore the purpose of conveniently adjusting the angle is achieved, the workload is reduced, the adjusting efficiency is improved, and use is convenient.

Description

Technical Field

[0001] The utility model relates to the field of aircraft, in particular to a device for aerodynamic testing of hypersonic aircraft. Background Art

[0002] At present, a Chinese utility model with a publication number of CN216746690U discloses an aerodynamic performance test device for fixing a fan, including a test device housing and a test fan, a movable plate is arranged on one side of the inner side of the test device housing, the movable plate is slidably connected to the inner wall of the test device housing, a structural device is arranged on the movable plate, the structural device includes a sliding plate, a sliding groove, a side block, a connecting rod, an intermediate block and a first telescopic spring, and the sliding groove is arranged on the surface of the movable plate. The aerodynamic performance test device for fixing a fan described in the utility model belongs to the technical field of aerodynamic performance testing, and the sliding plate can clamp a toy or a simulation model under the action of the first telescopic spring, or it can be directly placed on the movable plate, so that a before-and-after comparison can be made, and the experimental data is accurate, and the fixing plate is obliquely inserted between the fastening bolts, so that the fixing plate can be quickly fixed on the test device housing.

[0003] Existing aerodynamic test devices are not convenient for disassembling and assembling aircraft. Generally, when testing an aircraft, the aircraft needs to be installed on a test bench, and the aircraft and the test bench are fixed and installed by multiple bolts. Therefore, when disassembling and assembling the aircraft, tools are needed to disassemble and assemble it. The disassembly and assembly process is relatively cumbersome, which increases the workload and reduces the work efficiency. It is also not convenient to adjust the angle of the aircraft. Generally, when testing an aircraft, it is necessary to test at multiple angles. When adjusting the angle of the aircraft, the aircraft needs to be disassembled and assembled, and then installed after adjusting the angle, which is very troublesome, increases the workload, reduces the adjustment efficiency, and is inconvenient to use. In order to solve the above-mentioned problems, we propose a device for aerodynamic testing of hypersonic aircraft. Utility Model Content

[0004] The utility model aims to provide a device for aerodynamic testing of hypersonic aircraft, which has the advantages of being convenient for disassembling and assembling the aircraft and for adjusting the angle of the aircraft.

[0005] The above technical objectives of the utility model are achieved through the following technical solutions: a device for aerodynamic testing of hypersonic aircraft, comprising a test cabin, an airflow generating mechanism is arranged on the surface of the test cabin, a fixing seat is bolted to the inner wall of the test cabin, a mounting seat is arranged on the top of the fixing seat, a mounting rod is slidably sleeved on the inner wall of the mounting seat, an aircraft is bolted to the top of the mounting rod, a pressing rod is slidably sleeved on the inner wall of the mounting seat, a spring is arranged between one end of the pressing rod and the inner wall of the mounting seat, and a clamp is bolted to the surface of the pressing rod. A joint, a snap-in hole is provided on the surface of the mounting rod, and the snap-in joint is snap-connected with the snap-in hole, a motor is bolted to the surface of the fixing seat, an output end of the motor extends to the interior of the fixing seat and is connected to a worm through a coupling, and the other end of the worm is rotatably connected to the inner wall of the fixing seat, a worm wheel is meshed on the surface of the worm wheel, a rotating shaft is fixedly sleeved at the axis of the worm wheel, and both ends of the rotating shaft are rotatably connected to the inner wall of the fixing seat, a support rod is bolted to the surface of the worm wheel, a sensor is bolted to the top of the support rod, and the top of the sensor is bolted to the bottom of the mounting seat.

[0006] By adopting the above technical scheme, the pressing head is moved, and the movement of the pressing head drives the pressing rod to move, and the movement of the pressing rod drives the card joint to move, and the movement of the card joint causes the card joint to disengage from the card hole, and then the aircraft is removed. During installation, the mounting rod on the aircraft is inserted into the mounting seat, and the pressing rod drives the card joint to engage with the card hole under the action of the spring to fix it, thereby achieving the purpose of facilitating the assembly and disassembly of the aircraft, reducing the workload, and improving the work efficiency. The rotation of the motor drives the worm to rotate, the rotation of the worm drives the worm wheel to rotate, the rotation of the worm wheel drives the support rod to rotate, the rotation of the support rod drives the sensor to rotate, the rotation of the sensor drives the mounting seat to rotate, and the rotation of the mounting seat drives the aircraft to rotate, so that the angle of the aircraft changes, thereby achieving the purpose of facilitating the adjustment of the angle, reducing the workload, improving the adjustment efficiency, and facilitating use.

[0007] The utility model is further configured as follows: the airflow generating mechanism includes a first diffuser, one end of the first diffuser is connected to the surface of the test chamber, the other end of the diffuser is fixedly sleeved with a power chamber, a high-speed fan is installed inside the power chamber, and the input end of the high-speed fan is connected to one end of the first diffuser, the output end of the high-speed fan is connected to a second diffuser, and the other end of the second diffuser is fixedly sleeved with the inner wall of the test chamber.

[0008] By adopting the above technical solution and setting up an airflow generating mechanism, the test is facilitated.

[0009] The utility model is further configured as follows: a protective shell is bolted to the surface of the fixing seat, and the motor is located inside the protective shell.

[0010] By adopting the above technical solution, the motor is protected by providing a protective shell.

[0011] The utility model is further configured as follows: a pressing head is bolted to one end of the pressing rod.

[0012] By adopting the above technical solution and providing a pressing head, it is convenient to move the pressing rod.

[0013] The utility model is further configured as follows: one end of the clamping joint is wedge-shaped.

[0014] By adopting the above technical solution, one end of the clamping joint is arranged to be wedge-shaped, so as to facilitate fixing of the mounting rod.

[0015] The utility model is further configured as follows: guide plates are bolted to the inner walls of the first diffuser tube and the second diffuser tube.

[0016] By adopting the above technical solution, the airflow is guided by setting the guide plate to improve the stability of the airflow.

[0017] The utility model is further configured as follows: a heat exchanger is installed inside the second diffusion tube.

[0018] By adopting the above technical solution, a heat exchanger is provided to dissipate heat from the device to ensure stability.

[0019] In summary, the utility model has the following beneficial effects:

[0020] 1. The utility model moves the pressing head, the pressing head drives the pressing rod to move, the pressing rod drives the clamping joint to move, the clamping joint moves to make the clamping joint and the clamping hole disengage, and then the aircraft is removed. When installing, the mounting rod on the aircraft is inserted into the mounting seat, and the pressing rod drives the clamping joint and the clamping hole to be clamped and fixed under the action of the spring, so as to achieve the purpose of facilitating the assembly and disassembly of the aircraft, reduce the workload, and improve the work efficiency;

[0021] 2. The utility model drives the worm to rotate through the rotation of the motor, the worm drives the worm wheel to rotate, the worm wheel drives the support rod to rotate, the support rod drives the sensor to rotate, the sensor drives the mounting base to rotate, the mounting base drives the aircraft to rotate, so that the angle of the aircraft is changed, thereby achieving the purpose of facilitating the adjustment of the angle, reducing the workload, improving the efficiency of adjustment, and facilitating use. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 It is a three-dimensional diagram of the structure of the utility model;

[0023] Figure 2 It is a top view cross-sectional view of the structure of the utility model;

[0024] Figure 3 It is a partial structural cross-sectional view of the utility model;

[0025] Figure 4 This utility model Figure 3 A magnified view of the structure in the middle.

[0026] Figure numerals: 1. test cabin; 2. air flow generating mechanism; 3. fixing seat; 4. mounting seat; 5. mounting rod; 6. aircraft; 7. pressing rod; 8. spring; 9. snap joint; 10. snap hole; 11. motor; 12. worm; 13. worm gear; 14. rotating shaft; 15. supporting rod; 16. sensor; 17. first diffuser; 18. power cabin; 19. high-speed fan; 20. second diffuser; 21. protective shell; 22. pressing head; 23. guide plate; 24. heat exchanger. DETAILED DESCRIPTION

[0027] The utility model is further described in detail below in conjunction with the accompanying drawings.

[0028] Embodiment 1:

[0029] refer to Figure 1 , Figure 2 , Figure 3 and Figure 4 A device for aerodynamic testing of a hypersonic aircraft comprises a test cabin 1, an airflow generating mechanism 2 is arranged on the surface of the test cabin 1, a fixing seat 3 is bolted to the inner wall of the test cabin 1, a mounting seat 4 is arranged on the top of the fixing seat 3, a mounting rod 5 is slidably sleeved on the inner wall of the mounting seat 4, an aircraft 6 is bolted to the top of the mounting rod 5, a pressing rod 7 is slidably sleeved on the inner wall of the mounting seat 4, a spring 8 is arranged between one end of the pressing rod 7 and the inner wall of the mounting seat 4, a clamping joint 9 is bolted to the surface of the pressing rod 7, and a clamping hole is opened on the surface of the mounting rod 5 10, and the card joint 9 is carded with the card hole 10, by moving the pressing head 22, the pressing head 22 moves to drive the pressing rod 7 to move, the pressing rod 7 moves to drive the card joint 9 to move, the card joint 9 moves to make the card joint 9 disengage from the card hole 10, and then the aircraft 6 is removed. When installing, the mounting rod 5 on the aircraft 6 is inserted into the mounting seat 4, and the pressing rod 7 drives the card joint 9 to card the card hole 10 under the action of the spring 8 to fix it, thereby achieving the purpose of facilitating the assembly and disassembly of the aircraft 6, reducing the workload and improving the work efficiency.

[0030] refer to Figure 1 and Figure 2 The airflow generating mechanism 2 includes a first diffuser 17, one end of which is connected to the surface of the test chamber 1, and the other end of the diffuser is fixedly connected with a power chamber 18. A high-speed fan 19 is installed inside the power chamber 18, and the input end of the high-speed fan 19 is connected to one end of the first diffuser 17, and the output end of the high-speed fan 19 is connected to a second diffuser 20, and the other end of the second diffuser 20 is fixedly connected with the inner wall of the test chamber 1. The airflow generating mechanism 2 is arranged to facilitate testing.

[0031] refer to Figure 3 One end of the pressing rod 7 is bolted with a pressing head 22 , and the pressing head 22 is provided to facilitate the movement of the pressing rod 7 .

[0032] refer to Figure 4 One end of the card joint 9 is wedge-shaped, and by setting one end of the card joint 9 to be wedge-shaped, it is convenient to fix the installation rod 5.

[0033] refer to Figure 2 The inner walls of the first diffuser 17 and the second diffuser 20 are both bolted with guide plates 23. By providing the guide plates 23, the airflow is guided to improve the stability of the airflow.

[0034] Embodiment 2:

[0035] refer to Figure 3 A motor 11 is bolted to the surface of the fixed seat 3, and the output end of the motor 11 extends to the inside of the fixed seat 3 and is connected to a worm 12 through a coupling, and the other end of the worm 12 is rotatably connected to the inner wall of the fixed seat 3, and a worm wheel 13 is meshed on the surface of the worm 12, and a rotating shaft 14 is fixedly sleeved at the axis of the worm wheel 13, and both ends of the rotating shaft 14 are rotatably connected to the inner wall of the fixed seat 3, and a support rod 15 is bolted to the surface of the worm wheel 13, and a sensor 16 is bolted to the top of the support rod 15, and the top of the sensor 16 is bolted to the bottom of the mounting seat 4. The rotation of the motor 11 drives the worm 12 to rotate, the rotation of the worm 12 drives the worm wheel 13 to rotate, the rotation of the worm wheel 13 drives the support rod 15 to rotate, the rotation of the support rod 15 drives the sensor 16 to rotate, the rotation of the sensor 16 drives the mounting seat 4 to rotate, and the rotation of the mounting seat 4 drives the aircraft 6 to rotate, so that the angle of the aircraft 6 changes, thereby achieving the purpose of facilitating the adjustment of the angle, reducing the workload, improving the efficiency of the adjustment, and facilitating use.

[0036] refer to Figure 3 A protective shell 21 is bolted to the surface of the fixing seat 3, and the motor 11 is located inside the protective shell 21. By providing the protective shell 21, the motor 11 is protected.

[0037] refer to Figure 2 A heat exchanger 24 is installed inside the second diffusion tube 20. By setting the heat exchanger 24, the device is cooled to ensure stability.

[0038] A brief description of the use process: move the pressing head 22, the pressing head 22 moves to drive the pressing rod 7 to move, the pressing rod 7 moves to drive the clamping joint 9 to move, the clamping joint 9 moves to disengage the clamping joint 9 from the clamping hole 10, and then the aircraft 6 is removed. During installation, the mounting rod 5 on the aircraft 6 is inserted into the mounting seat 4, and the pressing rod 7 drives the clamping joint 9 to clamp with the clamping hole 10 under the action of the spring 8 to fix it, thereby achieving the purpose of facilitating the assembly and disassembly of the aircraft 6; the rotation of the motor 11 drives the worm 12 to rotate, the rotation of the worm 12 drives the worm wheel 13 to rotate, the rotation of the worm wheel 13 drives the support rod 15 to rotate, the rotation of the support rod 15 drives the sensor 16 to rotate, the rotation of the sensor 16 drives the mounting seat 4 to rotate, and the rotation of the mounting seat 4 drives the aircraft 6 to rotate, so that the angle of the aircraft 6 changes, thereby achieving the purpose of facilitating the adjustment of the angle.

[0039] This specific embodiment is merely an explanation of the present invention and is not a limitation of the present invention. After reading this specification, those skilled in the art may make non-creative modifications to the present embodiment as needed, but such modifications are protected by patent law as long as they are within the scope of the claims of the present invention.

Claims

1. A device for aerodynamic testing of a hypersonic vehicle, comprising a test chamber (1), characterized in that: The surface of the test cabin (1) is provided with an airflow generating mechanism (2); the inner wall of the test cabin (1) is bolted with a fixing seat (3); the top of the fixing seat (3) is provided with a mounting seat (4); the inner wall of the mounting seat (4) is slidably sleeved with a mounting rod (5); the top of the mounting rod (5) is bolted with an aircraft (6); the inner wall of the mounting seat (4) is slidably sleeved with a pressing rod (7); a spring (8) is provided between one end of the pressing rod (7) and the inner wall of the mounting seat (4); a clamping joint (9) is bolted with the surface of the pressing rod (7); a clamping hole (10) is provided on the surface of the mounting rod (5), and the clamping joint (9) is clamped with the clamping hole (10).

2. The device for aerodynamic testing of hypersonic aircraft according to claim 1, characterized in that: A motor (11) is bolted to the surface of the fixing seat (3); an output end of the motor (11) extends to the interior of the fixing seat (3) and is connected to a worm (12) via a coupling, and the other end of the worm (12) is rotatably connected to the inner wall of the fixing seat (3); a worm wheel (13) is meshed on the surface of the worm wheel (12); a rotating shaft (14) is fixedly sleeved at the axis of the worm wheel (13), and both ends of the rotating shaft (14) are rotatably connected to the inner wall of the fixing seat (3); a support rod (15) is bolted to the surface of the worm wheel (13); a sensor (16) is bolted to the top of the support rod (15), and the top of the sensor (16) is bolted to the bottom of the mounting seat (4).

3. The device for aerodynamic testing of hypersonic vehicles according to claim 1, characterized in that: The airflow generating mechanism (2) comprises a first diffuser (17), one end of the first diffuser (17) is connected to the surface of the test chamber (1), the other end of the diffuser is fixedly sleeved with a power chamber (18), a high-speed fan (19) is installed inside the power chamber (18), and the input end of the high-speed fan (19) is connected to one end of the first diffuser (17), the output end of the high-speed fan (19) is connected to a second diffuser (20), and the other end of the second diffuser (20) is fixedly sleeved with the inner wall of the test chamber (1).

4. The device for aerodynamic testing of hypersonic aircraft according to claim 2, characterized in that: A protective shell (21) is bolted to the surface of the fixing seat (3), and the motor (11) is located inside the protective shell (21).

5. The device for aerodynamic testing of hypersonic aircraft according to claim 1, characterized in that: One end of the pressing rod (7) is bolted with a pressing head (22).

6. The device for aerodynamic testing of hypersonic vehicles according to claim 1, characterized in that: One end of the card connector (9) is wedge-shaped.

7. The device for aerodynamic testing of hypersonic aircraft according to claim 3, characterized in that: The inner walls of the first diffuser tube (17) and the second diffuser tube (20) are both bolted with guide plates (23).

8. The device for aerodynamic testing of hypersonic aircraft according to claim 3, characterized in that: A heat exchanger (24) is installed inside the second diffusion pipe (20).

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