Performance verification system of liquid carrier rocket self-destruction device

Abstract

The performance verification system of the liquid carrier rocket self-destruction device comprises a solid rocket, a simulation storage box, a solid rocket fixing tool, a simulation storage box fixing tool and a power supply device, and the solid rocket fixing tool and the simulation storage box fixing tool are both fixed to the ground; the simulation storage tank is vertically fixed on the simulation storage tank fixing tool; the solid rocket is arranged on the outer side of the simulation storage tank, and the solid rocket is fixed on the solid rocket fixing tool and placed in the direction perpendicular to the simulation storage tank. The verification system meets rocket safety control requirements, and is low in cost, safe and effective.

Description

Technical Field

[0001] The utility model relates to the technical field of liquid rockets, in particular to a performance verification system for a self-destruction device, in particular to a performance verification system for a liquid carrier rocket self-destruction device. Background Art

[0002] At present, based on a previously proposed new type of liquid-propellant rocket self-destruction device - a small solid rocket, when safety control is required, the small solid rocket ignites, generating a jet that burns through the upper and lower bottoms of the tank, completing the rocket self-destruction. In order to verify the reliability, safety and functionality of the self-destruction device, a verification test is required on the ground. The test state should be consistent with the actual flight state or cover the flight state to ensure the validity of the test conclusions. Since it is impossible to use the actual flight conditions for test verification, and the actual conditions require huge costs, we use simulation parts to simulate the conditions during flight, and compare the data after the test to obtain data and conclusions close to the actual conditions.

[0003] In summary, the prior art has the following problem: how to verify whether a small solid rocket has reliability, functionality and safety when used as a self-destruct device in a liquid launch vehicle. Utility Model Content

[0004] The utility model provides a performance verification system for a liquid carrier rocket self-destruction device, so as to verify the reliability, functionality and safety of a small solid rocket when used as a self-destruction device in a liquid carrier rocket.

[0005] To this end, the utility model proposes a performance verification system for a liquid launch vehicle self-destruction device, which adopts the following technical solutions:

[0006] A performance verification system for a liquid launch vehicle self-destruction device, comprising: a solid rocket, a simulated tank, a solid rocket fixing tool, a simulated tank fixing tool and a power supply device;

[0007] The solid rocket fixing tool and the simulated tank fixing tool are both fixed on the ground;

[0008] The simulated tank is vertically fixed on the simulated tank fixing tool;

[0009] The solid rocket is arranged outside the simulated tank, the solid rocket is fixed on the solid rocket fixing tool and is placed in a direction perpendicular to the simulated tank; a nozzle is arranged at one end of the solid rocket, and the nozzle is close to one side of the simulated tank;

[0010] The power supply device is arranged outside the solid rocket and is electrically connected to the solid rocket.

[0011] Furthermore, the distance between the solid rocket and the simulated tank is 15mm-30mm.

[0012] Furthermore, the simulated storage tank is a cylindrical canned structure.

[0013] Furthermore, the simulated tank comprises a compressed air section and a liquid section, the compressed air section is arranged at the upper section of the simulated tank, and the liquid section is arranged at the lower section of the simulated tank.

[0014] Furthermore, the simulated tank is made of aluminum alloy, and the wall thickness of the simulated tank is less than or equal to 8 mm.

[0015] Furthermore, the placement height of the solid rocket is lower than the liquid level of the liquid section.

[0016] Furthermore, the simulated tank fixing tool is sleeved outside the simulated tank, and the shape of the simulated tank fixing tool matches the simulated tank.

[0017] Furthermore, it also includes a fixing plate, which is installed on the ground, and the solid rocket fixing tool and the simulated tank fixing tool are both fixed on the fixing plate.

[0018] Furthermore, it also includes an air compressor, the top of the simulated tank is provided with an air inlet, and the air compressor is connected to the air inlet.

[0019] The performance verification system of the liquid carrier rocket self-destruction device provided by the utility model adopts simulation parts to simulate the working conditions during flight, the simulation tank is vertically fixed on the simulation tank fixing tooling, the solid rocket is arranged on the outside of the simulation tank, and the nozzle on the solid rocket is close to one side of the simulation tank. The verification system covers the flight state on the arrow, and the heat flow generated by the solid small rocket can burn through the tank, and the time required for this action is short, and no other abnormal phenomena occur, which meets the rocket safety control requirements and effectively verifies the functionality, reliability and safety of the solid small rocket as a rocket self-destruction device. The test verification system is low in cost, safe and effective, and can effectively reduce the development cost of the rocket program stage. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 It is a structural schematic diagram of the utility model.

[0021] Description of Figure Numbers:

[0022] 1. Solid rocket; 11. Nozzle; 2. Simulated tank; 3. Solid rocket fixing tool; 4. Simulated tank fixing tool; 5. Power supply device; 6. Fixed plate; 21. Compressed air section; 22. Liquid section; 23. Air inlet; 9. Air compressor. DETAILED DESCRIPTION

[0023] In order to have a clearer understanding of the technical features, purposes and effects of the utility model, the utility model is now described.

[0024] 1. Technical solution

[0025] The utility model provides a performance verification system for a liquid launch vehicle self-destruction device, such as Figure 1 As shown, the solid rocket fixing tool 3 and the simulated tank fixing tool 4 are installed on the ground, and can also be installed through a fixing plate 6. The fixing plate 6 is, for example, a steel plate, and the steel plate is fixed on the ground; the simulated tank 2 is vertically fixed on the simulated tank fixing tool 4, and the simulated tank fixing tool 4 is sleeved outside the simulated tank 2. The shape of the simulated tank fixing tool 4 matches the simulated tank 2. The simulated tank 2 is a cylindrical canned structure. The simulated tank 2 is, for example, a gas cylinder. The gas cylinder is welded to the steel plate. The simulated tank 2 includes a compressed air section 21 and a liquid section 22. The liquid section is, for example, water, liquid oxygen or kerosene. The compressed air section 21 is arranged at the upper section of the simulated tank 2, and the liquid section 22 is arranged at the lower section of the simulated tank 2. For example, water is added to the gas cylinder to a certain capacity, and the gas cylinder is pressurized (compressed air) to a certain pressure; the simulated tank 2 is made of aluminum alloy, and the wall thickness of the simulated tank 2 is less than or equal to 8 mm. The material of the simulated tank 2 is aluminum alloy.

[0026] The solid rocket 1 is arranged outside the simulated tank 2. The solid rocket 1 is fixed on the solid rocket fixing fixture 3 and placed in a direction perpendicular to the simulated tank 2. The solid rocket vertical cylinder is installed at the lower end of the cylinder. The solid rocket fixing fixture 3 is fixed on the fixing plate 6. A nozzle 11 is arranged at one end of the solid rocket 1. The nozzle 11 is close to one side of the simulated tank 2. The distance between the tail end of the solid rocket nozzle and the cylinder should be consistent with the installation distance on the arrow. The distance between the solid rocket 1 and the simulated tank 2 is 15mm-30mm. The placement height of the solid rocket 1 is lower than the liquid level of the liquid section 22 to verify the effectiveness of the device.

[0027] Furthermore, the power supply device 5 is arranged outside the solid rocket 1 and is electrically connected to the solid rocket 1. The ignition current (the current for detonating the explosive) is 5-10A, and the duration is not less than 50ms to ensure that the explosive in the solid rocket can be detonated.

[0028] Furthermore, the performance verification system of the liquid launch vehicle self-destruction device also includes an air compressor 9. An air inlet 23 is provided on the top of the simulated tank 2. The air compressor 9 and the air inlet 23 are connected to input compressed air. 2. Specific embodiments

[0030] In order to verify the ablation penetration capability of a small solid rocket on an aluminum alloy tank with a propellant heat sink, an ablation test of a small solid rocket and a gas cylinder was carried out. The test process is as follows:

[0031] 1. Test equipment is shown in Table 1.

[0032] Table 1 Verification system matching table

[0033]

[0034]

[0035] 2. Experimental plan

[0036] (1) Add water to the gas cylinder to a certain capacity and pressurize the gas cylinder (compressed air) to a certain pressure;

[0037] (2) Prepare a steel plate, weld the gas cylinder fixture to the steel plate, and fix the gas cylinder vertically on the gas cylinder fixture;

[0038] (3) Install the solid rocket vertical cylinder at the lower end of the cylinder (the solid engine is arranged outside the liquid);

[0039] (4) Welding the solid rocket fixing fixture to the steel plate;

[0040] (5) The distance between the tail end of the solid rocket nozzle and the gas cylinder should be consistent with the installation distance on the rocket;

[0041] (6) The ignition current is 5-10A and the duration is not less than 50ms.

[0042] 3. Test and measurement facilities

[0043] (1) Measurement of water volume added to the gas cylinder: Use a 3L water bottle to add water and ensure the volume and height of the water in the gas cylinder;

[0044] (2) Use air compressor 9 to pressurize the gas cylinder and use a pressure gauge to test the pressure, which should be consistent with the test requirement;

[0045] (3) Measure the installation distance between the gas cylinder and the nozzle, which should be consistent with the test requirement;

[0046] (4) During the test, use a camera, mobile phone, etc. to record the test process;

[0047] (5) After the test, take photos to record the status of each product on site.

[0048] 4. Test results

[0049] The small solid rocket burned through the gas cylinder, and no other abnormal phenomena occurred.

[0050] 5. Analysis of test results

[0051] (1) The test results show that the small solid rocket meets the requirements of on-rocket self-destruction and can be used as a self-destruct device in liquid launch vehicles;

[0052] (2) The test conditions cover the flight conditions on the rocket, and the safety and control capabilities have margin (statistical term);

[0053] (3) Analysis of the high-temperature mechanical properties of aluminum alloy materials showed that as the temperature increased, the strength of the aluminum alloy materials decreased and the tank was burned through;

[0054] (4) Safety analysis: The production technology of solid small rockets is mature, meeting the requirements of rocket force and thermal environment, and is safe and reliable;

[0055] (5) Functional analysis: The heat flux generated by the small solid rocket can burn through the tank, and this action takes a short time, meeting the rocket safety control requirements;

[0056] There are currently pyrotechnic products such as explosives and cutting ropes that can also achieve the purpose of self-destruction.

[0057] The performance verification system of the liquid carrier rocket self-destruction device provided by the utility model effectively verifies the functionality, reliability and safety of the solid small rocket as a rocket self-destruction device. This test verification method is low-cost, safe and effective, and effectively reduces the development cost of the rocket program stage.

[0058] The above description is only an illustrative embodiment of the utility model and is not intended to limit the scope of the utility model. The components of the utility model can be combined with each other without conflict, and any equivalent changes and modifications made by any technician in the field without departing from the concept and principle of the utility model should fall within the scope of protection of the utility model.

Claims

1. A performance verification system for a liquid launch vehicle self-destruction device, characterized in that: include: A solid rocket (1), a simulated tank (2), a solid rocket fixing tool (3), a simulated tank fixing tool (4) and a power supply device (5); The solid rocket fixing fixture (3) and the simulated tank fixing fixture (4) are both fixed on the ground; The simulated tank (2) is vertically fixed on the simulated tank fixing tool (4); The solid rocket (1) is arranged outside the simulated tank (2), and the solid rocket (1) is fixed on the solid rocket fixing tool (3) and placed in a direction perpendicular to the simulated tank (2); a nozzle (11) is arranged at one end of the solid rocket (1), and the nozzle (11) is close to one side of the simulated tank (2); The power supply device (5) is arranged outside the solid rocket (1) and is electrically connected to the solid rocket (1).

2. A liquid launch vehicle self-destruction device performance verification system according to claim 1, characterized in that: The distance between the solid rocket (1) and the simulated tank (2) is 15 mm-30 mm.

3. A performance verification system for a liquid launch vehicle self-destruction device according to claim 1, characterized in that: The simulated storage tank (2) is a cylindrical canned structure.

4. A liquid launch vehicle self-destruction device performance verification system according to claim 1, characterized in that: The simulated tank (2) comprises a compressed air section (21) and a liquid section (22), wherein the compressed air section (21) is arranged at the upper section of the simulated tank (2), and the liquid section (22) is arranged at the lower section of the simulated tank (2).

5. The performance verification system of a liquid launch vehicle self-destruction device according to claim 1, characterized in that: The simulated tank (2) is made of an aluminum alloy material, and the wall thickness of the simulated tank (2) is less than or equal to 8 mm.

6. A liquid launch vehicle self-destruction device performance verification system according to claim 4, characterized in that: The placement height of the solid rocket (1) is lower than the liquid surface of the liquid section (22).

7. A liquid launch vehicle self-destruction device performance verification system according to claim 1, characterized in that: The simulated tank fixing tool (4) is sleeved outside the simulated tank (2), and the shape of the simulated tank fixing tool (4) matches that of the simulated tank (2).

8. The performance verification system of a liquid launch vehicle self-destruction device according to claim 1, characterized in that: It also includes a fixing plate (6), which is installed on the ground, and the solid rocket fixing tool (3) and the simulated tank fixing tool (4) are both fixed on the fixing plate (6).

9. A liquid launch vehicle self-destruction device performance verification system according to claim 1, characterized in that: It also includes an air compressor (9). The top of the simulated tank (2) is provided with an air inlet (23), and the air compressor (9) is connected to the air inlet (23).

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