阅读说明：本技术 一种模拟火箭弹射座椅出舱吹袭的试验装置 (Test device for simulating rocket ejection seat out-of-cabin blowing ) 是由 谢武俊 闵立武 李洪文 段宝利 洪涛 于 2019-11-15 设计创作，主要内容包括：本发明提供了一种模拟火箭弹射座椅出舱吹袭的试验装置,包括座椅安装平台(8)、座椅安装板(9)、开口风洞(10)、火箭弹射座椅(11),火箭弹射座椅(11)安装在座椅安装板(9)上,位于开口风洞(10)风向口前方,在开口风洞(10)和火箭弹射座椅(11)之间设有挡风板(5),所述挡风板(5)下端同高速油缸(2)的活塞杆(12)连接,两侧与通过滑轮(13)同导轨(6)相连,在高速油缸(2)驱动下挡风板(5)沿导轨上下移动,实现挡风板抵御1400km/h的高速气流吹袭；通过在座椅安装平台上设置由电动缸驱动的旋转机构,实现座椅出舱角度的调节。该装置结构简单,安全性高,测试数据准确。(The invention provides a test device for simulating rocket ejection seat out-of-cabin blowing attack, which comprises a seat mounting platform (8), a seat mounting plate (9), an open wind tunnel (10) and a rocket ejection seat (11), wherein the rocket ejection seat (11) is mounted on the seat mounting plate (9) and is positioned in front of a wind direction opening of the open wind tunnel (10), a wind shield (5) is arranged between the open wind tunnel (10) and the rocket ejection seat (11), the lower end of the wind shield (5) is connected with a piston rod (12) of a high-speed oil cylinder (2), two sides of the wind shield are connected with a guide rail (6) through pulleys (13), and the wind shield (5) is driven by the high-speed oil cylinder (2) to move up and down along the guide rail so as to resist the high-speed air flow blowing attack of 1400 km; the seat out-of-cabin angle is adjusted by arranging the rotating mechanism driven by the electric cylinder on the seat mounting platform. The device simple structure, the security is high, and the test data is accurate.)

1. The utility model provides a test device that simulation rocket launches seat to go out cabin and blow, includes seat mounting platform (8), seat mounting panel (9), opening wind-tunnel (10), rocket launch seat (11), and rocket launch seat (11) are installed on seat mounting panel (9), are located opening wind-tunnel (10) wind direction mouth the place ahead, and its characterized in that is equipped with deep bead (5) between opening wind-tunnel (10) and rocket launch seat (11), deep bead (5) lower extreme is connected with piston rod (12) of high-speed hydro-cylinder (2), and both sides with link to each other with guide rail (6) through pulley (13), and deep bead (5) reciprocate along the guide rail under high-speed hydro-cylinder (2) drive.

2. The test device for simulating rocket ejection seat outbreak blowing according to claim 1, wherein said wind shielding mechanism (5) comprises a mounting base (1), a high-speed oil cylinder (2), an energy accumulator (3) and a servo valve (4), the high-speed oil cylinder (2) is mounted on the base (1), and the energy accumulator (3) and the servo valve (4) are mounted on the high-speed oil cylinder (1).

3. The test device for simulating rocket ejection seat out-of-cabin blowing according to claim 1, wherein the wind shield (5) can completely cover the rocket ejection seat (11) and can rapidly leave the blowing area.

4. The test device for simulating rocket ejection seat outbreak blowing according to claim 1, wherein said servo valve (4) can control the piston rod of the high-speed oil cylinder (2) to be in two postures of fully extended state and fully retracted state.

5. The test device for simulating rocket ejection seat outbreak blowing according to claim 1, wherein said wind deflector (5) is connected with the guide rail (6) through a pulley (13).

6. The test device for simulating rocket ejection seat outbreak blowing according to claim 1, wherein said accumulator (3) and servo valve (4) are directly fixed on the high-speed oil cylinder (1).

7. The test device for simulating the rocket ejection seat outbreak blowing according to claim 1, wherein the seat mounting platform (8) further comprises an electric cylinder (7), one end of the electric cylinder (7) is mounted on the seat mounting platform (8), the other end of the electric cylinder is mounted at the upper end of the seat mounting plate (9) through a lead 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 lead screw (14) is adjusted under the driving of the electric cylinder (7), and the seat mounting plate (9) and the rocket ejection seat (11) on the seat mounting platform (8) are driven to rotate to a required angle along the rotating shaft (15).

8. The test device for simulating rocket ejection seat outbreak blowing according to claim 7, wherein said seat mounting platform (8) is placed on the lifting mechanism under the air outlet.

Technical Field

The invention belongs to the technology of test equipment, and relates to a test device for simulating rocket ejection seat out-of-cabin blowing.

Background

At present, a general open type wind tunnel rocket ejection seat cabin-out blowing simulation test method comprises the following steps: firstly, a seat is installed below an open type wind tunnel test area, then the wind tunnel is opened according to a set wind speed, after airflow in the test area is stable, the seat is rapidly lifted along a guide rail angle and completely stays in the test area by using a steel wire rope traction or hydraulic cylinder jacking mode, and the wind tunnel is closed until the blowing time meets the requirement, so that the simulation of the whole process from ejection starting to complete exposure of the rocket ejection seat is realized. However, due to the limitation of the size of a wind tunnel test area, the seat needs to be decelerated to be static within a short distance after rising to the test area at a high speed so as to be ensured to be completely stopped in the test area, so that the seat bears negative impact overload exceeding 15g during deceleration, the structural strength and the functional performance of the seat are seriously influenced, particularly, the influence is more obvious under the condition of overlaying pneumatic load, and the judgment of a test result is difficult; meanwhile, no matter in a steel wire rope traction mode or a hydraulic cylinder jacking mode, the angle of the seat guide rail is not convenient to adjust, and difficulty is caused in blowing tests of seats with different cabin outlet angles.

Disclosure of Invention

The technical objects of the present invention are: the invention provides a test device for simulating rocket ejection seat out-of-cabin blowing, which overcomes the problems of judgment of test results and difficult adjustment of seat out-of-cabin angles caused by deceleration negative overload in the existing test method, can resist the blowing of 1400km/h high-speed airflow, can simulate the seat ejection out-of-cabin process in an open type wind tunnel, and not only can eliminate the reverse braking overload influence of seats, but also is convenient for adjusting the seat out-of-cabin angles.

The technical scheme adopted by the invention for solving the technical problems is as follows: a test device for simulating rocket ejection seat out-of-cabin blowing attack comprises a seat mounting platform, a seat mounting plate, an opening wind tunnel and a rocket ejection seat, wherein the rocket ejection seat is mounted on the seat mounting plate and located in front of a wind direction opening of the opening wind tunnel, a wind shield is arranged between the opening wind tunnel and the rocket ejection seat, the lower end of the wind shield is connected with a piston rod of a high-speed oil cylinder, the two sides of the wind shield are connected with a guide rail through pulleys, and the wind shield moves up and down along the guide rail under the driving of the high-speed oil cylinder.

In the above scheme, the wind shielding mechanism comprises an installation base, a high-speed oil cylinder, an energy accumulator and a servo valve, wherein the high-speed oil cylinder is installed on the base, and the energy accumulator and the servo valve are installed on the high-speed oil cylinder.

In the scheme, the wind shield can completely cover the rocket ejection seat and can quickly leave a blowing area.

In the scheme, the servo valve can control the piston rod of the high-speed oil cylinder to be in two postures of a fully extending state and a fully retracting state.

In the scheme, the wind shield is connected with the guide rail through the pulley.

In the scheme, the energy accumulator and the servo valve are directly fixed on the high-speed oil cylinder.

In the above scheme, seat mounting platform still includes electronic jar, electronic jar one end is installed on seat mounting platform, and the other end passes through the lead screw to be installed in seat mounting panel upper end, and seat mounting panel lower extreme is installed on seat mounting platform through the pivot, and the rocket launches the seat and installs on the seat mounting panel, adjusts electronic jar lead screw length, drives seat mounting platform upper seat mounting panel and the rotation of rocket ejection seat along the pivot to the required angle.

In the scheme, the rocket ejection seat is located below the air outlet, and the lifting mechanism moves the rocket ejection seat to a test area capable of accepting blowing.

The invention has the beneficial effects that:

1. the wind shield driven by the high-speed oil cylinder to move downwards is arranged between the wind tunnel outlet and the rocket ejection seat, the guide rails are arranged on two sides of the wind shield, so that the simulation of the exposure process of the rocket ejection seat from top to bottom relative to airflow is realized, the simulation of the whole process from ejection starting to completely exposed out-of-cabin blowing of the rocket ejection seat is completed in the limited test area of the open wind tunnel, and the influence of reverse braking overload of the seat is eliminated.

2. The rocket ejection seat needs to bear high-speed airflow blowing up to 1400km/h, and the technical prejudice that a movable wind shield cannot be used in the high-speed airflow blowing environment is eliminated.

3. The rocket ejection seat is adjusted in the cabin exit angle by arranging the rotating mechanism driven by the electric cylinder on the seat mounting platform.

4. The device simple structure, the security is high, still can retrieve to wind-tunnel export below after accomplishing rocket ejection seat and come out of the cabin and blow the experiment, does not have any influence to other experimental going on.

Drawings

The invention is further illustrated with reference to the following figures and examples.

FIG. 1 is a schematic structural view of the present invention;

fig. 2 is a schematic view of the working state of the present invention.

FIG. 3 is a schematic view of the windshield assembly of the present invention.

FIG. 4 is a schematic structural diagram of a test piece mounting platform according to the present invention.

In the drawings, 1-mounting a base; 2-a high-speed oil cylinder; 3-an accumulator; 4-a servo valve; 5-wind shield; 6-a guide rail; 7-an electric cylinder; 8-a seat mounting platform; 9-a seat mounting plate; 10-open wind tunnel; 11-rocket ejection seat; 12-a piston rod; 13-a pulley; 14-a lead screw; 15-rotating shaft.

Detailed Description

The invention is further described below with reference to the accompanying drawings.

As shown in the figure, the test device for simulating the rocket ejection seat to blow out of the cabin comprises a seat mounting platform 8, a seat mounting plate 9, an opening wind tunnel 10 and a rocket ejection seat 11, wherein the rocket ejection seat 11 is mounted on the seat mounting plate 9 and located in front of a wind direction opening of the opening wind tunnel 10, a wind shield 5 is arranged between the opening wind tunnel 10 and the rocket ejection seat 11, the lower end of the wind shield 5 is connected with a piston rod 12 of a high-speed oil cylinder 2, two sides of the wind shield are connected with a guide rail 6 through pulleys 13, and the wind shield 5 is driven by the high-speed oil cylinder 2 to move up and down along the guide rail 6.

The wind shielding mechanism 5 comprises an installation base 1, a high-speed oil cylinder 2, an energy accumulator 3 and a servo valve 4, wherein the high-speed oil cylinder 2 is installed on the base 1, and the energy accumulator 3 and the servo valve 4 are installed on the high-speed oil cylinder 1 and are located below a test area of an opening wind tunnel (10).

The wind deflector 5 can completely cover the rocket ejection seat 11 and can also quickly leave the blow-on area.

The servo valve 4 can control the piston rod of the high-speed oil cylinder 2 to be in two postures of a fully extending state and a fully retracting state.

The wind shield 5 is connected with the guide rail 6 through a pulley 13.

The energy accumulator 3 and the servo valve 4 are directly fixed on the high-speed oil cylinder 1.

Seat mounting platform 8 still includes electronic jar 7, 7 one end of electronic jar is installed on seat mounting platform 8, and the other end passes through lead screw 14 to be installed in seat mounting panel 9 upper end, and seat mounting panel 9 lower extreme is installed on seat mounting platform 8 through pivot 15, and rocket launches seat 11 and installs on seat mounting panel 9, adjusts electronic jar 7 lead screw (14) length, drives seat mounting panel 9 and rocket to launch seat 11 and rotate to the required angle on the seat mounting platform 8.

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 where blowing can be accepted.

As shown in fig. 2, the simulated rocket ejection seat cabin-out process of the invention is as follows: the servo valve 4 firstly controls a piston rod of the high-speed oil cylinder 2 to be in a completely extending state, the wind shield 5 completely shields the rocket ejection seat 11, the open wind tunnel 10 is started until the airflow in the test area is stable, the servo valve 4 is reversed, the energy accumulator 3 supplies energy to the high-speed oil cylinder 2 to enable the piston rod to be quickly retracted, the wind shield 5 is driven to move downwards, the rocket ejection seat 11 is gradually exposed in the airflow in the open wind tunnel 10 from top to bottom until the piston rod of the high-speed oil cylinder 2 is in the completely retracted state, the wind shield 3 is located at the lowest position, and the rocket ejection seat 11 is completely exposed in the.

The invention realizes that the seat goes out of the cabin angle adjustment process is: the length of a lead screw 14 of the electric cylinder 7 is adjusted to drive a seat mounting plate 9 on the seat mounting platform 8 and the rocket ejection seat 11 to rotate to a required angle.

While the present invention has been described with reference to the embodiments shown in the drawings, the present invention is not limited to the embodiments, which are illustrative and not restrictive, and it will be apparent to those skilled in the art that various changes and modifications can be made therein without departing from the spirit and scope of the invention as defined in the appended claims.