A test device simulating the blow of a rocket ejection seat out of the cabin
Through the high-speed cylinder-driven windshield plate and the electric cylinder-driven rotation mechanism, the problems of reverse overload and angle adjustment in the rocket ejection seat exit test are solved, and efficient simulation in the open wind tunnel and Flexible angle adjustment, adapting to 1400km/h high-speed airflow environment.
Patent Information
- Application Number
- CN201911125662.0
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- Filing Date
- 2019-11-15
- Publication Date
- 2024-12-17
- Estimated Expiration
- 2039-11-15
AI Technical Summary
In the existing rocket launch seat blow-attack simulation test, the seat needs to decelerate for a short distance when rising at high speed, resulting in reverse impact overload affecting structural strength and functional performance, and inconvenient adjustment of the exit angle, affecting the test results and flexibility of the test. sex.
A test device is designed including a high-speed cylinder-driven windshield plate and an electric cylinder-driven rotary mechanism. The windshield plate moves through the guide rail to simulate the seat exposure process, eliminates the reverse braking overload, and adjusts the outlet angle through the rotary mechanism. .
It realizes the entire process of simulating the rocket ejection seat exit in an open wind tunnel, eliminating the impact of reverse braking overload, and facilitating the angle of the exit, adapting to a high-speed airflow environment of 1400km/h, with a simple and safe structure.
Smart Images
Figure CN110749411B_ABST
Abstract
Description
Technical Field
[0001] The invention belongs to test equipment technology and relates to a test device for simulating the blowout of a rocket ejection seat. Background Art
[0002] At present, the general open wind tunnel rocket ejection seat outboard blow simulation test method is: first install the seat below the open wind tunnel test area, then open the wind tunnel at the set wind speed, wait for the airflow in the test area to stabilize, use wire rope traction or hydraulic cylinder lifting method to make the seat rise rapidly along the guide rail angle and stay completely in the test area, until the blow time meets the requirements, and then close the wind tunnel, so as to achieve the whole process simulation of the rocket ejection seat from ejection start to full exposure outboard. However, due to the size of the wind tunnel test area, after the seat rises to the test area at high speed, it needs to decelerate to a standstill within a very short distance to ensure that it stays completely in the test area, resulting in the seat being subjected to a negative impact overload of more than 15g during deceleration, which seriously affects the structural strength and functional performance of the seat, especially when the aerodynamic load is superimposed. This effect is more obvious, which makes it difficult to judge the test results; at the same time, whether it is wire rope traction or hydraulic cylinder lifting method, the seat guide angle is not easy to adjust, which makes it difficult to test the seat blow at different outboard angles. Summary of the invention
[0003] The technical purpose of the present invention is as follows: The present invention provides a test device for simulating the rocket ejection seat ejection, which overcomes the problems in the existing test methods that the negative overload of deceleration affects the test result judgment and the difficulty in adjusting the seat ejection angle. The device can withstand the high-speed airflow of 1400km / h and can simulate the seat ejection process in an open wind tunnel. It can not only eliminate the influence of the reverse braking overload of the seat, but also facilitate the adjustment of the seat ejection angle.
[0004] The technical solution adopted by the present invention to solve its technical problems is: a test device for simulating the rocket ejection seat out of the cabin, including a seat mounting platform, a seat mounting plate, an open wind tunnel, and a rocket ejection seat. The rocket ejection seat is mounted on the seat mounting plate and is located in front of the wind direction port of the open wind tunnel. A wind shield is provided between the open wind tunnel and the rocket ejection seat. The lower end of the wind shield is connected to the piston rod of the high-speed cylinder, and the two sides are connected to the guide rail through pulleys. The wind shield moves up and down along the guide rail under the drive of the high-speed cylinder.
[0005] In the above scheme, the wind shielding mechanism includes a mounting base, a high-speed oil cylinder, an accumulator and a servo valve. The high-speed oil cylinder is mounted on the base, and the accumulator and the servo valve are mounted on the high-speed oil cylinder.
[0006] In the above scheme, the wind shield can completely cover the rocket ejection seat and can also quickly leave the blowing area.
[0007] In the above solution, the servo valve can control the high-speed oil cylinder piston rod to be in two postures: a fully extended state and a fully retracted state.
[0008] In the above solution, the wind shield is connected to the guide rail via a pulley.
[0009] In the above solution, the accumulator and the servo valve are directly fixed on the high-speed cylinder.
[0010] In the above scheme, the seat mounting platform also includes an electric cylinder, one end of the electric cylinder is installed on the seat mounting platform, and the other end is installed on the upper end of the seat mounting plate through a screw, the lower end of the seat mounting plate is installed on the seat mounting platform through a rotating shaft, and the rocket ejection seat is installed on the seat mounting plate. The length of the electric cylinder screw is adjusted to drive the seat mounting plate and the rocket ejection seat on the seat mounting platform to rotate along the rotating shaft to the required angle.
[0011] In the above scheme, the rocket ejection seat is located below the air outlet, and the lifting mechanism moves the rocket ejection seat to a test area that can accept wind attacks.
[0012] The beneficial effects of the present invention are:
[0013] 1. A windshield driven downward by a high-speed cylinder is set between the wind tunnel exit and the rocket ejection seat. Guide rails are set on both sides of the windshield to simulate the exposure process of the rocket ejection seat from top to bottom relative to the airflow. The entire process of the rocket ejection seat from ejection start to full exposure to the airflow is simulated in the limited test area of the open wind tunnel, eliminating the impact of the reverse braking overload of the seat.
[0014] 2. The rocket ejection seat needs to withstand high-speed airflows of up to 1,400 km / h, eliminating the technical prejudice that it is impossible to use a movable windshield in a high-speed airflow environment.
[0015] 3. The angle of exit of the rocket ejection seat can be adjusted by setting a rotating mechanism driven by an electric cylinder on the seat mounting platform.
[0016] 4. The device has a simple structure and high safety. After completing the rocket ejection seat extravehicular blowing test, it can be recovered to the bottom of the wind tunnel exit without any impact on the progress of other tests. BRIEF DESCRIPTION OF THE DRAWINGS
[0017] The present invention is further described below in conjunction with the accompanying drawings and embodiments.
[0018] Figure 1 It is a schematic diagram of the structure of the present invention;
[0019] Figure 2 It is a schematic diagram of the working state of the present invention.
[0020] Figure 3 It is a schematic structural diagram of the windshield device of the present invention.
[0021] Figure 4 It is a schematic diagram of the structure of the test piece installation platform of the present invention.
[0022] In the figure, 1-mounting base; 2-high-speed cylinder; 3-accumulator; 4-servo valve; 5-wind deflector; 6-guide rail; 7-electric cylinder; 8-seat mounting platform; 9-seat mounting plate assembly; 10-open wind tunnel; 11-rocket ejection seat; 12-piston rod; 13-pulley; 14-screw; 15-rotating shaft. DETAILED DESCRIPTION
[0023] The present invention will be further described below in conjunction with the accompanying drawings.
[0024] As shown in the figure, a test device for simulating a rocket ejection seat being blown out of a cabin, comprises a seat mounting platform 8, a seat mounting plate 9, an open wind tunnel 10, and a rocket ejection seat 11. The rocket ejection seat 11 is mounted on the seat mounting plate 9 and is located in front of the wind direction port of the open wind tunnel 10. A wind shield 5 is provided between the open wind tunnel 10 and the rocket ejection seat 11. The lower end of the wind shield 5 is connected to the piston rod 12 of the high-speed cylinder 2, and both sides are connected to the guide rail 6 through a pulley 13. Driven by the high-speed cylinder 2, the wind shield 5 moves up and down along the guide rail 6.
[0025] The wind shielding mechanism 5 comprises a mounting base 1, a high-speed oil cylinder 2, an accumulator 3 and a servo valve 4. The high-speed oil cylinder 2 is mounted on the base 1, and the accumulator 3 and the servo valve 4 are mounted on the high-speed oil cylinder 1, and are located below the test area of the open wind tunnel (10).
[0026] The windshield 5 can completely cover the rocket ejection seat 11 and can also quickly leave the blowing area.
[0027] The servo valve 4 can control the piston rod of the high-speed oil cylinder 2 to be in two postures: a fully extended state and a fully retracted state.
[0028] The wind deflector 5 is connected to the guide rail 6 via a pulley 13 .
[0029] The accumulator 3 and the servo valve 4 are directly fixed on the high-speed cylinder 1 .
[0030] The seat mounting platform 8 also includes an electric cylinder 7, one end of which is mounted on the seat mounting platform 8, and the other end is mounted on the upper end of the seat mounting plate 9 through a screw 14. The lower end of the seat mounting plate 9 is mounted on the seat mounting platform 8 through a rotating shaft 15. The rocket ejection seat 11 is mounted on the seat mounting plate 9. The length of the screw (14) of the electric cylinder 7 is adjusted to drive the seat mounting plate 9 and the rocket ejection seat 11 on the seat mounting platform 8 to rotate to the required angle.
[0031] The rocket ejection seat 11 is located below the air outlet, and the lifting mechanism moves the rocket ejection seat 11 to a test area that can accept wind attacks.
[0032] like Figure 2 As shown, the process of simulating the rocket ejection seat exiting the cabin of the present invention is: the servo valve 4 first controls the piston rod of the high-speed cylinder 2 to be in a fully extended state, the wind shield 5 completely blocks the rocket ejection seat 11, and the open wind tunnel 10 is started until the airflow in the test area is stable. Then, the servo valve 4 is reversed, and the accumulator 3 supplies energy to the high-speed cylinder 2 to quickly retract the piston rod, driving the wind shield 5 to move downward, so that the rocket ejection seat 11 is gradually exposed to the airflow of the open wind tunnel 10 from top to bottom, until the piston rod of the high-speed cylinder 2 is in a fully retracted state, the wind shield 3 is in the lowest position, and the rocket ejection seat 11 is completely exposed to the open wind tunnel 10.
[0033] The process of adjusting the seat exit angle of the present invention is as follows: adjusting the length of the lead screw 14 of the electric cylinder 7 to drive the seat mounting plate 9 on the seat mounting platform 8 and the rocket ejection seat 11 to rotate to the required angle.
[0034] The embodiments of the present invention are described above in conjunction with the accompanying drawings, but the present invention is not limited to the above-mentioned specific implementation modes, which are merely illustrative rather than restrictive. Under the guidance of the present invention, ordinary technicians in this field can also make many forms without departing from the scope of protection of the present invention and the claims, all of which are within the protection of the present invention.
Claims
1. A test device for simulating a rocket ejection seat ejection attack, comprising a mounting base (1), a high-speed oil cylinder (2), an accumulator (3), a servo valve (4), a wind deflector (5), a guide rail (6), a seat mounting platform (8), a seat mounting plate (9), an open wind tunnel (10), a rocket ejection seat (11), a piston rod (12) and a pulley (13), wherein the high-speed oil cylinder (2) is mounted on the base (1), the accumulator (3) and the servo valve (4) are mounted on the high-speed oil cylinder (2), and the rocket ejection seat (11) is mounted on the seat mounting plate (9) and is located in front of the wind direction port of the open wind tunnel (10), characterized in that: A windshield (5) is provided between the open wind tunnel (10) and the rocket ejection seat (11). The lower end of the windshield (5) is connected to the piston rod (12) of the high-speed oil cylinder (2), and both sides are connected to the guide rail (6) through pulleys (13). When driven by the high-speed oil cylinder (2), the windshield (5) moves up and down along the guide rail.
2. A test device for simulating rocket ejection seat out of cabin blow according to claim 1, characterized in that: The windshield (5) can completely cover the rocket ejection seat (11) and can also quickly leave the wind-affected area.
3. A test device for simulating rocket ejection seat out of cabin blow according to claim 1, characterized in that: The servo valve (4) can control the piston rod of the high-speed oil cylinder (2) to be in two postures: a fully extended state and a fully retracted state.
4. The test device for simulating rocket ejection seat ejection attack according to claim 1, characterized in that: The accumulator (3) and the servo valve (4) are directly fixed on the high-speed oil cylinder (2).
5. The test device for simulating rocket ejection seat out of cabin blow according to claim 1, characterized in that: The seat mounting platform (8) further comprises an electric cylinder (7), a lead screw (14) and a rotating shaft (15); one end of the electric cylinder (7) is mounted on the seat mounting platform (8), and the other end is mounted on the upper end of the seat mounting plate (9) via the lead screw (14); the lower end of the seat mounting plate (9) is mounted on the seat mounting platform (8) via the rotating shaft (15); the rocket ejection seat (11) is mounted on the seat mounting plate (9); the length of the lead screw (14) is adjusted under the drive of the electric cylinder (7), so as to drive the seat mounting plate (9) and the rocket ejection seat (11) on the seat mounting platform (8) to rotate along the rotating shaft (15) to a required angle.
6. A test device for simulating rocket ejection seat out of cabin blow according to claim 1, characterized in that: The seat mounting platform (8) is placed on the lifting mechanism and is located below the air outlet.