Integrated gas-fuel hybrid propulsion system

Abstract

This utility model relates to the field of satellite propulsion equipment technology, and specifically provides an integrated gas-fuel hybrid propulsion system, including an integrated tank, gas generator, gas container, and thruster. The tank contains a flexible metal diaphragm, with one side forming a gas chamber and the other a liquid chamber. The gas chamber has a gas inlet, and the liquid chamber has a liquid inlet. The liquid inlet's output pipe is connected to the gas generator, the gas generator's output pipe is connected to the gas container, and the gas container's output pipe is connected to the thruster. This utility model solves the problems of low specific impulse in cold gas propulsion systems, heavy thruster mass and large envelope size in monocomponent chemical propulsion systems, and the difficulty in achieving low thrust output in bicomponent chemical propulsion systems, thus meeting the application requirements of satellites.

Description

Technical Field

[0001] This utility model relates to the field of satellite propulsion equipment technology, and in particular provides an integrated gas-fuel hybrid propulsion system. Background Technology

[0002] Cold gas propulsion systems have low specific impulse. To increase the total impulse, the only option is to increase the volume and weight of the propellant tank, which reduces the satellite's payload. However, according to user requirements, the payload generally cannot be reduced. Monocomponent chemical propulsion systems are more mature and widely used in satellite propulsion systems. However, their thrusters are heavy and have large envelope sizes, making it difficult to arrange multiple thrusters on a satellite. Bicomponent chemical propulsion systems have thrusters that are difficult to achieve low thrust output and cannot provide small pulse impulses. Utility Model Content

[0003] To address the aforementioned technical problems, this invention provides an integrated gas-fuel hybrid propulsion system that can solve the problems of low specific impulse in cold gas propulsion systems, heavy thruster mass and large envelope size in monocomponent chemical propulsion systems, and the difficulty in achieving low thrust output in bicomponent chemical propulsion systems, thereby meeting the application requirements of satellites.

[0004] This utility model is implemented as follows: It provides an integrated gas-fuel hybrid propulsion system, including an integrated storage tank, a gas generator, a gas container, and a thruster. The storage tank is equipped with a metal diaphragm, one end of which is the storage tank gas chamber and the other end is the storage tank liquid chamber. The storage tank gas chamber is equipped with a storage tank gas port, and the storage tank liquid chamber is equipped with a storage tank liquid port. The storage tank liquid port output pipeline is connected to the gas generator, the gas generator output pipeline is connected to the gas container, and the gas container output pipeline is connected to the thruster.

[0005] Preferably, one end of the gas inlet of the storage tank is connected to a gas filling and draining valve, and the other end is connected to a high-pressure sensor; one end of the liquid inlet of the storage tank is connected to a liquid filling and draining valve, and the other end is the liquid outlet pipeline of the storage tank.

[0006] Further preferably, a low-pressure sensor is installed on the gas container.

[0007] In a further preferred embodiment, the device also includes a propulsion control circuit board, which is connected to the high-pressure sensor, the solenoid valve of the gas generator, the low-pressure sensor, and the solenoid valve of the thruster.

[0008] Preferably, the thruster switch response time is no more than 10ms, the number of thrusters is configured according to requirements, the thrust range of the thrusters is 0.01~20N, the thrust output accuracy of the thrusters is no more than 5%, and the operating temperature is no higher than 260℃.

[0009] Preferably, the gas generator has been switched on and off at a rate of not less than 1 million times.

[0010] Preferably, the metal diaphragm is a pure aluminum diaphragm or a pure titanium diaphragm, and the edge of the metal diaphragm is fixedly connected to the inner wall of the storage tank.

[0011] Compared with the prior art, the advantages of this utility model are:

[0012] This invention utilizes high-temperature, high-pressure gas catalyzed by a gas generator, and through pressure stabilization control, enables the thruster to produce precise, high specific impulse thrust output. Therefore, it solves the problems of low specific impulse in cold gas propulsion systems, heavy thruster mass and large envelope size in monocomponent chemical propulsion systems, and the difficulty in achieving low thrust output in bicomponent chemical propulsion systems. It achieves beneficial effects such as high specific impulse, simple structure, high reliability, small size, light weight, and stable thrust. This invention is applicable to satellite propulsion systems with multi-thrust configurations, high attitude and orbit control accuracy, low power consumption, and high total impulse requirements. Attached Figure Description

[0013] The present invention will be further described in detail below with reference to the accompanying drawings and embodiments:

[0014] Figure 1 This is a schematic diagram of the structure of this utility model.

[0015] In the diagram: 1-Storage tank, 2-Metal diaphragm, 3-Gas filling and draining valve, 4-High pressure sensor, 5-Liquid filling and draining valve, 6-Gas generator, 7-Gas container, 8-Low pressure sensor, 9-Thruster, 10-Propulsion control circuit board. Detailed Implementation

[0016] To make the objectives, technical solutions, and advantages of this utility model clearer, the present utility model will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the present utility model and are not intended to limit the scope of the present utility model.

[0017] refer to Figure 1 This utility model provides an integrated gas-fuel hybrid propulsion system, including an integrated tank 1, a gas generator 6, a gas container 7, and a thruster 9. The tank 1 has a flexible metal diaphragm, with one side of the diaphragm being a gas chamber and the other side being a liquid chamber. The gas chamber stores high-pressure gas, and the liquid chamber stores liquid-phase mixed propellant. The gas chamber has a gas port, and the liquid chamber has a liquid port. The liquid port output pipe is connected to the gas generator 6. The gas generator 6 is used to catalytically decompose the mixed propellant into high-temperature and high-pressure gas. The output pipe of the gas generator 6 is connected to the gas container 7 to stabilize the inlet pressure of the thruster 9. The output pipe of the gas container 7 is connected to the thruster 9. The thruster 9 provides the thrust and impulse required by the satellite to meet the satellite's attitude and orbit control requirements.

[0018] To facilitate the filling of high-pressure gas into the gas chamber of the storage tank, a gas filling and exhaust valve 3 is connected to one end of the gas port of the storage tank, and a high-pressure pressure sensor 4 is connected to the other end to detect the pressure inside the storage tank 1; to facilitate the filling of propellant into the liquid chamber of the storage tank, a liquid filling and exhaust valve 5 is connected to one end of the liquid port of the storage tank, and the other end is the liquid port output pipeline of the storage tank.

[0019] In order to detect the pressure at the inlet of the thruster 9, a low-pressure sensor 8 is installed on the gas container 7.

[0020] Specifically, it also includes a propulsion control circuit board 10, which is connected to the high-pressure sensor 4, the solenoid valve of the gas generator 6, the low-pressure sensor 8, and the solenoid valve of the thruster 9. The power supply and pressure acquisition of the high-pressure sensor 4 and the low-pressure sensor 8, the power supply and switching control of the solenoid valve of the gas generator 6 and the solenoid valve of the thruster 9, and the pressure stabilization control of the gas capacitor 7 are realized through the propulsion control circuit board 10.

[0021] Preferably, the freezing point of the propellant in the tank 1 is not greater than 0°C, and the propellant is in a state of being pressed tightly by the metal diaphragm 2, without shaking, so as not to affect the satellite's attitude.

[0022] Preferably, the switching response time of the thruster 9 is no more than 10ms, the number of thrusters 9 is configured according to requirements, the thrust range of the thrusters 9 is 0.01~20N, the thrust output accuracy of the thrusters 9 is no more than 5%, and the operating temperature is no higher than 260℃. The switching count of the gas generator 6 is no less than 1 million times.

[0023] Preferably, the metal diaphragm 2 is a pure aluminum diaphragm or a pure titanium diaphragm to ensure that the high-pressure gas can propel the propellant as a whole, and the edge of the metal diaphragm 2 is fixedly connected to the inner wall of the tank 1.

[0024] The working steps of this utility model are as follows:

[0025] Step 1: When the propulsion system is not powered, add propellant through the liquid filling and emptying valve 5. Before adding, evacuate the liquid chamber of the storage tank to below 500Pa. After adding, close the liquid filling and emptying valve 5 and fill with high-pressure gas through the gas filling and emptying valve 3. After filling, close the gas filling and emptying valve 3. Under the action of high-pressure gas, the propellant in the storage tank 1 is squeezed to the inlet of the gas generator 6.

[0026] Step 2: After the propulsion system enters the working state, it first performs pressure stabilization control of the gas container 7. The pressure of the low pressure sensor 8 is collected through the propulsion control circuit board 10, and the solenoid valve of the gas generator 6 is opened or closed according to the preset gas container pressure threshold using a PID control algorithm to achieve the predetermined requirements.

[0027] Step 3: Activate thruster 9 to propel the system. When the propellant flows through the gas generator 6, it generates high-temperature and high-pressure gas, which is then ejected at a high speed through thruster 9, thereby generating a reaction force. During operation, the gas chamber in the storage tank is under pressure drop. Even the lowest pressure after the propellant is emptied can ensure that the gas generator 6 can work normally. The inlet pressure of thruster 9 is under constant pressure control.

[0028] Step 4: After the work is completed, the thruster 9 is turned off.

[0029] This invention utilizes high-temperature, high-pressure gas generated by the catalytic decomposition of a gas generator as the working fluid for thruster 9, resulting in a high specific impulse for thruster 9. Compared to cold gas propulsion schemes, single-component chemical propulsion systems, and dual-component chemical propulsion systems, this scheme makes the propulsion system simpler, more reliable, and has superior overall performance. Extensive testing has verified that this propulsion technology system is simple, has a high specific impulse, high reliability, small size, light weight, and stable thrust.

[0030] The embodiments of the present invention have been described in detail above with reference to the accompanying drawings. However, the present invention is not limited to the above embodiments. Within the scope of knowledge possessed by those skilled in the art, various changes can be made without departing from the spirit of the present invention.

Claims

1. An integrated gas hybrid propulsion system, characterized in that, The system includes an integrated storage tank (1), a gas generator (6), a gas container (7), and a thruster (9). The storage tank (1) is equipped with a flexible metal diaphragm (2). One side of the metal diaphragm (2) is the storage tank gas chamber, and the other side is the storage tank liquid chamber. The storage tank gas chamber is equipped with a storage tank gas port, and the storage tank liquid chamber is equipped with a storage tank liquid port. The storage tank liquid port output pipeline is connected to the gas generator (6), the output pipeline of the gas generator (6) is connected to the gas container (7), and the output pipeline of the gas container (7) is connected to the thruster (9).

2. The integrated gas-fuel hybrid propulsion system according to claim 1, characterized in that, A gas filling and draining valve (3) is connected to one end of the gas port of the storage tank, and a high-pressure sensor (4) is connected to the other end; a liquid filling and draining valve (5) is connected to one end of the liquid port of the storage tank, and the other end is the liquid port output pipeline of the storage tank.

3. The integrated gas-fuel hybrid propulsion system according to claim 2, characterized in that, A low-pressure sensor (8) is installed on the gas container (7).

4. The integrated gas-fuel hybrid propulsion system according to claim 3, characterized in that, It also includes a propulsion control circuit board (10), which is connected to the high pressure sensor (4), the solenoid valve of the gas generator (6), the low pressure sensor (8), and the solenoid valve of the thruster (9).

5. The integrated gas-fuel hybrid propulsion system according to claim 1, characterized in that, The switching response time of the thruster (9) is no more than 10ms. The number of thrusters (9) is configured according to the requirements. The thrust range of the thruster (9) is 0.01 to 20N. The thrust output accuracy of the thruster (9) is no more than 5%. The working temperature is no higher than 260℃.

6. The integrated gas-fuel hybrid propulsion system according to claim 1, characterized in that, The gas generator (6) is switched on and off at a rate of not less than 1 million times.

7. The integrated gas-fuel hybrid propulsion system according to claim 1, characterized in that, The metal diaphragm (2) is a pure aluminum diaphragm or a pure titanium diaphragm, and the edge of the metal diaphragm (2) is fixedly connected to the inner wall of the storage tank (1).

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