An isolation control device suitable for attitude and orbit control power system

Abstract

The present invention provides an isolation control device suitable for an attitude and orbit control power system, comprising a gas production device, a gas storage shell, a capillary tube and a gas explosion valve. During the storage of the attitude and orbit control power system, the gas explosion valve is in a closed state and plays an isolation role; when the attitude and orbit control power system is ready to work and needs to release the isolation, the gas production device ignites to produce fuel gas, and the gas storage shell will evenly pressure the generated fuel gas, and transport it to each gas explosion valve through the capillary tube, cut the gas explosion valve, and release the isolation. The gas storage shell is designed with a certain volume, which not only plays a role in reducing the gas production pressure peak of the gas production device, but also plays a role in ensuring that after individual gas explosion valves are opened first, the pressure will not be too low to affect the opening of other gas explosion valves; the capillary tube adopts a stainless steel seamless tube or a titanium capillary tube with a smaller outer diameter, which has good flexibility and is convenient for arrangement in the attitude and orbit control power system, and has a small weight and a strong pressure-bearing capacity.

Description

Technical Field

[0001] The invention relates to an isolation control device suitable for an attitude and orbit control power system, belongs to the technical field of liquid engines, is suitable for the attitude and orbit control power system of rockets and missile weapons, and is particularly suitable for a new type of gas booster power system without a high-pressure gas cylinder. Background Art

[0002] During the storage period of the attitude and orbit control power system, the medium in the tank needs to be separated from the pipeline by an isolation valve. Before the system works, the isolation valve is opened through the control system, and the medium flows into the pipeline. The isolation valve and the control system together form an isolation control device. The existing isolation control device solutions for attitude and orbit control power systems include "non-electric explosion transmission system + electric explosion valve" and "gas cylinder high-pressure gas + gas explosion valve". Due to the application of the new gas booster system in the attitude and orbit control power system, the high-pressure gas cylinder in the system is eliminated, making the gas explosion valve solution unusable; the price of the "non-electric explosion transmission system + electric explosion valve" solution is relatively high and is not suitable for products with strict cost control. Summary of the invention

[0003] The technical problem solved by the present invention is to overcome the shortcomings of the prior art, that is, the problem that the gas explosion valve cannot be used due to the cancellation of the high-pressure gas cylinder, and to provide a low-cost, light-weight, easy-to-manufacture attitude and orbit control power system isolation control device using the gas explosion valve as an isolation valve.

[0004] The technical solution of the present invention is: an isolation control device suitable for an attitude and orbit control power system, the device includes a gas producing device, a gas storage shell, a capillary duct and a gas explosion valve; the gas explosion valve is in a closed state during the storage of the attitude and orbit control power system, and is used to isolate the propellant in the attitude and orbit control power system tank and the downstream pipeline of the tank, so as to prevent the propellant from flowing into the pipeline and leaking during the storage period; when the attitude and orbit control power system is ready for work and the isolation needs to be released, the gas producing device is detonated to generate combustion gas, and the gas storage shell will evenly pressure the generated combustion gas, and transport it to each gas explosion valve through the capillary duct, cutting the gas explosion valve and releasing the isolation.

[0005] The gas storage shell is made of high-temperature alloy material, such as heat-resistant alloy steel, nickel-based alloy or titanium alloy.

[0006] The capillary tube is made of a stainless steel seamless tube or a titanium capillary tube, and the value range of the outer diameter is not greater than 3 mm.

[0007] The gas explosion valve has an opening and wedging function.

[0008] Metal sealing pads are used between the gas production device and the gas storage shell, and between the gas storage shell and the capillary conduit. Sealing is achieved by pressing the metal sealing pads to form end face sealing thorns on the surface of the metal sealing pads.

[0009] The number of the gas explosion valves can be adjusted according to the actual isolation requirements in the system, without quantity limit. Each additional gas explosion valve requires an additional capillary tube for gas supply.

[0010] The propellant is hydrazine, unsymmetrical dimethylhydrazine, methylhydrazine, nitrogen tetroxide or DT3.

[0011] The beneficial effects of the present invention compared with the prior art are:

[0012] (1) The present invention uses the fuel gas generated by the gas generating device to drive the gas explosion valve, replacing the high-pressure gas in the gas cylinder originally used, so that the gas explosion valve can be used in the attitude and orbit control power system without gas cylinders.

[0013] (2) Compared with the "non-electric explosion transmission system + electric explosion valve", the capillary tube structure used in the present invention is light in weight and low in price, which is more conducive to the weight and cost control of the power system;

[0014] (3) The present invention uses capillary tubes for connection, which have good toughness, are easy to arrange in the attitude and orbit control power system, have a lighter weight, and have a stronger pressure-bearing capacity under the same wall thickness.

[0015] (4) In the present invention, only the gas generating device is filled with gunpowder, so the storage safety is higher.

[0016] (5) The gas storage shell of the present invention is designed with a certain volume, which not only plays a role in reducing the gas production pressure peak of the gas production device, but also plays a role in ensuring that after a certain gas explosion valve is opened first, the pressure will not be too low to affect the opening of other gas explosion valves.

[0017] (6) The gas explosion valve of the present invention has an opening wedge-tightening function to prevent the gas explosion valve from being unable to maintain an open state due to a decrease in gas temperature and pressure. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 It is a schematic diagram of the isolation control device of the present invention.

[0019] Figure 2 Schematic diagram of metal gasket sealing. DETAILED DESCRIPTION

[0020] In order to make the solution of the present invention clearer, the present invention is further described below in conjunction with the accompanying drawings and specific embodiments:

[0021] like Figure 1As shown, the present invention provides an isolation control device suitable for an attitude and orbit control power system, the device comprising a gas production device 1, a gas storage shell 2, a capillary tube 3 and a gas explosion valve 4; the gas production device 1 is installed on the gas storage shell 2, and all the gas generated after ignition enters the gas storage shell; one end of the capillary tube is connected to the gas storage shell, and the other end is connected to the gas explosion valve, providing a transmission path for the gas. The gas explosion valve 4 is in a closed state during the storage of the attitude and orbit control power system, and is used to isolate the propellant in the tank of the attitude and orbit control power system and the downstream pipeline of the tank, to prevent the propellant from flowing into the pipeline and leaking during storage; when the attitude and orbit control power system is ready for work and needs to be released from isolation, the gas production device 1 is detonated to produce gas, and the gas storage shell 2 will equalize the pressure of the generated gas, and transport it to each gas explosion valve 4 through the capillary tube 3, cut the gas explosion valve 4, and release the isolation.

[0022] Preferably, the gas storage shell 2 is made of a high-temperature alloy material and has a certain volume. Its internal volume is calculated based on the gas production capacity of the gas production device 1 and the number of gas explosion valves to ensure that the gas explosion valves are provided with gas that meets their cutting pressure. The high-temperature alloy material can be heat-resistant alloy steel, nickel-based alloy or titanium alloy.

[0023] The pressure of the gas generated by the gas production device in the chamber with a volume of V1 is P1, the chamber of each gas explosion valve is V2, the number of gas explosion valves in the isolation control device is x, the inner diameter of the capillary is generally about 1mm, and its internal chamber can be ignored. When the gas explosion valve opening pressure is P2, the safety opening coefficient is a, and the internal volume of the gas storage shell can be calculated by the following formula.

[0024] V=P1V1 / (aP2)-xV2

[0025] The gas storage shell is designed with a certain volume, which not only plays a role in reducing the gas production pressure peak of the gas production device, but also plays a role in ensuring that after an individual gas explosion valve is opened first, the pressure will not be too low to affect the opening of other gas explosion valves.

[0026] Preferably, the capillary tube 3 is made of a stainless steel seamless tube or a titanium capillary tube, and the outer diameter is within a range of no more than 3 mm, so as to ensure that the capillary tube 3 has better bendability. The capillary tube has good toughness, is easy to arrange in the attitude and orbit control power system, has a light weight, and has a strong pressure bearing capacity under the same wall thickness.

[0027] Preferably, the gas explosion valve 4 has an opening and wedging function. When the gas explosion valve 4 is cut, the cutter will not be reset due to the gas pressure decreasing with the temperature, and the gas explosion valve 4 will not be unable to maintain a stable open state.

[0028] Preferably, if Figure 2As shown, metal sealing gaskets are used between the gas production device 1 and the gas storage shell 2, and between the gas storage shell 2 and the capillary tube 3. Sealing is achieved by pressing the metal sealing gasket to form end face sealing thorns on the surface of the metal sealing gasket. Reliable sealing can still be ensured under high temperature conditions to prevent gas leakage caused by high temperature.

[0029] Preferably, the number of the gas explosion valves 4 can be adjusted according to the actual isolation requirements in the system, without quantity limit, and each additional gas explosion valve 4 requires an additional capillary tube 3 to supply gas thereto.

[0030] The isolation control device can be used to isolate various common propellants in attitude and orbit control power systems, such as hydrazine, unsymmetrical dimethylhydrazine, methylhydrazine, nitrogen tetroxide, and DT3.

[0031] The contents not described in detail in the specification of the present invention are well known to those skilled in the art.

Claims

1. An isolation control device suitable for an attitude and orbit control power system, characterized in that: The invention comprises a gas generating device (1), a gas storage shell (2), a capillary conduit (3) and a gas explosion valve (4); the gas explosion valve (4) is in a closed state during the storage of the attitude and orbit control power system, and is used to isolate the propellant in the tank of the attitude and orbit control power system and the downstream pipeline of the tank, so as to prevent the propellant from flowing into the pipeline and leaking during the storage period; when the attitude and orbit control power system is ready for operation and the isolation needs to be released, the gas generating device (1) is detonated to generate combustion gas, and the gas storage shell (2) evenly pressures the generated combustion gas and transports it to each gas explosion valve (4) through the capillary conduit (3), thereby cutting the gas explosion valve (4) and releasing the isolation; Metal sealing gaskets are used between the gas production device (1) and the gas storage shell (2), and between the gas storage shell (2) and the capillary conduit (3), and sealing is achieved by pressing the metal sealing gasket to form end face sealing thorns on the surface of the metal sealing gasket; the gas storage shell (2) has a certain volume, and the volume is calculated based on the gas production capacity of the gas production device and the number of gas explosion valves, so as to ensure that the gas explosion valves are provided with gas that meets their cutting pressure; The gas explosion valve (4) has an opening and wedging function.

2. The isolation control device for an attitude and orbit control power system according to claim 1, characterized in that: The gas storage housing (2) is made of a high-temperature alloy material, such as heat-resistant alloy steel, nickel-based alloy or titanium alloy.

3. The isolation control device for an attitude and orbit control power system according to claim 1, characterized in that: The capillary tube (3) is made of a stainless steel seamless tube or a titanium capillary tube, and the value range of the outer diameter is not greater than 3 mm.

4. The isolation control device for an attitude and orbit control power system according to claim 1, characterized in that: The number of the gas explosion valves (4) can be adjusted according to the actual isolation requirements in the system, and there is no limit on the number. Each additional gas explosion valve (4) requires an additional capillary tube (3) for gas supply.

5. The isolation control device for an attitude and orbit control power system according to claim 1, characterized in that: The propellant is hydrazine, unsymmetrical dimethylhydrazine, methylhydrazine, nitrogen tetroxide or DT3.

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