A novel green single-component propulsion system for on-orbit use

Abstract

This invention discloses a novel method for the on-orbit use of a green monocomponent propulsion system, including a method for temperature control of the propulsion system after it enters orbit with the entire satellite, a method for preheating the catalyst bed of the monocomponent thrust chamber before the first start-up, a method for removing functional materials from the monocomponent thrust chamber during the first start-up of the monocomponent thrust chamber, a method for starting the monocomponent thrust chamber during the attitude and orbit control of the propulsion system, and a method for temperature control of the propulsion system during standby. By formulating the above methods, the influence of functional materials on the performance of the monocomponent thrust chamber is effectively eliminated, and the problem of on-orbit use of the novel green monocomponent propulsion system is solved. It has been successfully applied on micro and nano satellites.

Description

Technical Field

[0001] This invention relates to a novel green monocomponent propulsion system for on-orbit use, belonging to the field of monocomponent propulsion technology. Background Technology

[0002] Green monocomponent propulsion systems possess advantages such as being green and non-toxic, and having high specific impulse, making them promising for applications in manned spaceflight, launch vehicles, and satellites. In recent years, microsatellites and nanosatellites have experienced rapid development. To improve on-orbit lifespan and provide deorbit propulsion, satellites need to be equipped with active propulsion output devices. Monocomponent propulsion systems, due to their simplicity, high reliability, and especially their green, non-toxic, and pre-packaged delivery advantages, have gained favor with microsatellite users and have been widely adopted.

[0003] However, the traditional single-component thrust chamber installation method, which requires the nozzle outlet to be vertically downward (orthogonal installation) during transportation, storage, and launch, limits the overall layout of the propulsion system and cannot meet the technical requirements of microsatellites for safe propulsion systems at any angle. This problem was addressed by developing a single-component thrust chamber with anti-inversion functional materials. However, the addition of functional materials increases the difficulty of system operation. Furthermore, since microsatellites generally have low battery capacity, they cannot maintain the on-orbit temperature of the single-component thrust chamber for extended periods. This is highly detrimental to the single-component thrust chamber, primarily resulting in a significantly reduced operational lifespan, especially the warm-start lifespan.

[0004] To address the aforementioned issues, a major challenge limiting the application of green propulsion systems in the field of micro and nano satellites is how to design reasonable on-orbit usage methods to solve the problem of invertible system usage methods, while also taking into account satellite energy shortages through operational design and ensuring the room temperature start-up life requirements of single-component thrust. Summary of the Invention

[0005] To address the shortcomings of current solutions, a novel on-orbit usage method for green monocomponent propulsion systems is proposed. This method provides an on-orbit usage approach for inverted monocomponent thrust chambers and solves the technical challenge of room temperature start-up lifespan for green monocomponent thrust chambers through reasonable operating condition design. This approach has been successfully applied in the field of micro-nano satellites.

[0006] The technical solution adopted by this invention to solve its technical problem is:

[0007] A novel green monocomponent propulsion system is described for on-orbit use. The system comprises a propellant tank, a front-end solenoid valve, a start-up solenoid valve, a monocomponent thrust chamber, and a pressure sensor. The monocomponent thrust chamber is equipped with an anti-inversion membrane, allowing the propulsion system to be installed at any angle on the satellite. The steps and methods for on-orbit use of the monocomponent propulsion system are as follows:

[0008] (1) Temperature control method of propulsion system after the propulsion system enters orbit with the whole satellite: the catalyst bed and nozzle of the single-component thrust chamber are placed outside the whole satellite compartment and no temperature control is applied; the injector of the single-component thrust chamber and the tank, valve, pressure sensor and other components are placed inside the whole satellite compartment and the temperature is controlled within the range of 5℃~60℃.

[0009] (2) Preheating method for the single-component thrust chamber catalyst bed before the first start-up: 1.5 hours before the start-up of the single-component thrust chamber, start the single-component thrust chamber heater to preheat the catalyst bed so that the temperature of the catalyst bed is not lower than 200℃;

[0010] (3) Method for removing the anti-inversion membrane during the first start-up of the single-component thrust chamber: Start the single-component thrust chamber, with an opening time of 0.05s and a closing time of 1s, and repeat 10 times; then perform the catalytic bed heating program: opening time of 0.1s and closing time of 1s, and repeat 20 times to raise the temperature of the single-component thrust chamber catalytic bed to above 400℃. At this temperature, the functional material will completely decompose.

[0011] (4) Satellite attitude control method of propulsion system: The start-up temperature of the single-component thrust chamber catalyst bed is not lower than 200℃, the working pulse width is not less than 25ms, the shutdown time interval is not less than 100ms, and the duty cycle and number of cycles are controlled and adjusted by the control system according to the attitude of the aircraft.

[0012] (5) Propulsion system satellite orbit control adjustment method: The starting temperature of the catalyst bed in the single-component thrust chamber is not lower than 200℃. First, start the catalyst bed heating program: start time 0.1s, shutdown time interval 1s, cycle 10 times, and then perform the steady-state start program. The steady-state working time is controlled and adjusted by the control system according to the attitude of the spacecraft.

[0013] (6) During the standby phase of the propulsion system, the minimum insulation temperature of the catalyst bed in the single-component thrust chamber shall not be lower than 20°C. The temperature of the single-component thrust chamber shall be increased by the onboard autonomous heater. The heating duration shall be controlled and adjusted by the control system according to the onboard energy situation. The temperature control range of components such as tanks, valves, and pressure sensors outside the single-component thrust chamber shall be 5°C to 60°C.

[0014] The method can enable the single-component thrust to start at room temperature for no less than 60 times, with a start temperature of no less than 200°C, a pulse count of no less than 2000 times, and a maximum steady-state working time of no less than 100 seconds.

[0015] The method is applicable to green single-component HAN and ADN propulsion systems where the thrust chamber thrust level is no greater than 5N.

[0016] This invention discloses a novel method for the on-orbit use of a green monocomponent propulsion system, which effectively eliminates the influence of functional materials on the performance of the monocomponent thrust chamber and solves the problem of on-orbit use of the novel green monocomponent propulsion system. It has been successfully applied on micro-nano satellites. Attached Figure Description

[0017] Figure 1 This is a schematic diagram of the green single-component propulsion system structure involved in this invention.

[0018] Figure 2 This is the on-orbit usage method of the green single-component propulsion system involved in Embodiment 1 of the present invention;

[0019] Figure 3 This is the preheating temperature curve of the catalytic bed 2 hours before startup in Example 1 of the present invention;

[0020] Figure 4 This is the data curve of the functional material removal procedure in Embodiment 1 of the present invention;

[0021] Figure 5 This is the functional material thoroughly clearing program data curve of Embodiment 1 of the present invention;

[0022] Figure 6 This is a typical attitude control program data curve from Embodiment 1 of the present invention;

[0023] Figure 7 This is a typical track control program data curve from Embodiment 1 of the present invention. Detailed Implementation

[0024] The following embodiments are provided to illustrate the present invention in more detail, but the present invention is not limited thereto.

[0025] Example 1:

[0026] like Figure 2 The diagram illustrates a novel green monocomponent propulsion system for on-orbit use. The system structure includes a propellant tank 1, a front-end solenoid valve 2, a start-up solenoid valve 3, a monocomponent thrust chamber 4, and a pressure sensor 5. The monocomponent thrust chamber 4 is equipped with an anti-inversion membrane, allowing the propulsion system to be installed at any angle on the satellite. The on-orbit usage steps and methods are as follows:

[0027] S1: Temperature control method of propulsion system after entering orbit with the whole satellite: The catalyst bed and nozzle of the single-component thrust chamber 4 are placed outside the whole satellite compartment and no temperature control is applied; the injector, tank, valve, pressure sensor and other components of the single-component thrust chamber 4 are placed inside the whole satellite compartment and the temperature is controlled within the range of 5℃~35℃.

[0028] S2: As Figure 3As shown, the preheating method for the catalyst bed in the single-component thrust chamber 4 before the first start-up is as follows: 1.5 hours before the start-up of the single-component thrust chamber 4, the heater of the single-component thrust chamber 4 is started to preheat the catalyst bed so that the temperature of the catalyst bed is not lower than 200℃.

[0029] S3: Initial start-up anti-inversion membrane removal method for single-component thrust chamber 4: Start single-component thrust chamber 4, opening time 0.05s, closing time 1s, cycle 10 times. Figure 4 As shown; then perform the catalytic bed heating program: start-up time 0.1s, stop-down time 1s, cycle 20 times, to raise the temperature of the catalytic bed in the single-component thrust chamber 4 to above 400℃, as shown. Figure 5 As shown, at this temperature, the functional material will completely decompose;

[0030] S4: Propulsion system satellite attitude control method: The single-component thrust chamber 4 catalytic bed start-up temperature is not lower than 200℃, the working pulse width is 50ms, the shutdown time interval is 500ms, and the duty cycle and cycle number are controlled and adjusted by the control system according to the spacecraft attitude; the typical operating condition is: catalytic bed 3 start-up temperature 200℃, working pulse width 100ms, time interval 1000ms, cycle number 50, and the data curve is as follows. Figure 6 As shown;

[0031] S5: Propulsion system satellite orbit control adjustment method: The start-up temperature of the single-component thrust chamber 4 catalytic bed is not lower than 200℃. First, start the catalytic bed heating program: start-up time 0.1s, shutdown time interval 1s, cycle 10 times, then proceed with the steady-state start-up program. The steady-state working duration is controlled and adjusted by the control system according to the spacecraft attitude; the typical steady-state condition is a 10s start-up, and the data curve is as follows. Figure 7 As shown;

[0032] S6: During the standby phase of the propulsion system, the minimum insulation temperature of the catalyst bed in the single-component thrust chamber 4 is not lower than 20℃. The temperature of the single-component thrust chamber 4 is increased by the onboard autonomous heater. The heating duration is controlled and adjusted by the control system according to the onboard energy situation. The temperature control range of components other than the single-component thrust chamber 4, such as tanks, valves, and pressure sensors, is 5℃~35℃.

[0033] Using the above method, the system can achieve 60 warm starts, a warm start temperature of not less than 200℃, 2000 pulses, and a maximum steady-state working time of 100s.

[0034] This method solves the technical challenge of the start-up life of single-component thrusters in green propulsion systems. The green HAN propulsion system based on this method has been applied to a micro-nano experimental satellite, successfully realizing satellite maneuvering and orbit maintenance. The thrust of the HAN thruster is 0.5N.

[0035] Example 2: The difference from Example 1 is as follows:

[0036] The steps and methods for using the system in orbit are as follows:

[0037] S1: Temperature control method of propulsion system after entering orbit with the whole satellite: The catalyst bed and nozzle of the single-component thrust chamber 4 are placed outside the whole satellite compartment and no temperature control is applied; the injector, tank, valve, pressure sensor and other components of the single-component thrust chamber 4 are placed inside the whole satellite compartment and the temperature is controlled within the range of 5℃~60℃.

[0038] S2: Preheating method for the catalyst bed in the single-component thrust chamber 4 before the first start-up: 1.5 hours before the start-up of the single-component thrust chamber 4, start the heater of the single-component thrust chamber 4 to preheat the catalyst bed so that the temperature of the catalyst bed is not lower than 300℃;

[0039] S3: Method for removing the anti-inversion membrane during the first start-up of the monocomponent thrust chamber 4: Start the monocomponent thrust chamber 4, with an opening time of 0.05s and a closing time of 2s, and repeat 10 times; then proceed with the catalytic bed heating program: opening time of 0.1s and a closing time of 1s, and repeat 20 times to raise the temperature of the catalytic bed in the monocomponent thrust chamber 4 to above 400℃. At this temperature, the functional material will completely decompose.

[0040] S4: Propulsion system for satellite attitude control: The start-up temperature of the single-component thrust chamber 4 catalytic bed is not lower than 300℃, the working pulse width is 25ms, the shutdown time interval is 100ms, and the duty cycle and number of cycles are controlled and adjusted by the control system according to the attitude of the aircraft.

[0041] S5: Propulsion system satellite orbit control adjustment method: The start-up temperature of the single-component thrust chamber 4 catalytic bed is not lower than 300℃. First, start the catalytic bed heating program: start-up time 0.1s, shutdown time interval 1s, cycle 10 times, then perform the steady-state start-up program. The steady-state working time is controlled and adjusted by the control system according to the attitude of the spacecraft.

[0042] S6: During the standby phase of the propulsion system, the minimum insulation temperature of the catalyst bed in the single-component thrust chamber 4 is not lower than 50℃. The temperature of the single-component thrust chamber 4 is increased by the onboard autonomous heater. The heating duration is controlled and adjusted by the control system according to the onboard energy situation. The temperature control range of components other than the single-component thrust chamber 4, such as tanks, valves, and pressure sensors, is 5℃~35℃.

[0043] Using the above method, the system can achieve 200 warm starts, a warm start temperature of not less than 300℃, 20,000 pulses, and a maximum steady-state working time of 300s.

[0044] The above method is applicable to green single-component ADN propulsion systems, where the thrust level of the thrust chamber is 5N.

[0045] Example 3: The difference from Example 1 is that:

[0046] The steps and methods for using the system in orbit are as follows:

[0047] S1: Temperature control method of propulsion system after entering orbit with the whole satellite: The catalyst bed and nozzle of the single-component thrust chamber 4 are placed outside the whole satellite compartment and no temperature control is applied; the injector, tank, valve, pressure sensor and other components of the single-component thrust chamber 4 are placed inside the whole satellite compartment and the temperature is controlled within the range of 15℃~60℃.

[0048] S2: Preheating method for the catalyst bed in the single-component thrust chamber 4 before the first start-up: 1.5 hours before the start-up of the single-component thrust chamber 4, start the heater of the single-component thrust chamber 4 to preheat the catalyst bed so that the temperature of the catalyst bed is not lower than 200℃;

[0049] S3: Method for removing the anti-inversion membrane during the first start-up of the monocomponent thrust chamber 4: Start the monocomponent thrust chamber 4, with an opening time of 0.05s and a closing time of 2s, and repeat 10 times; then proceed with the catalytic bed heating program: opening time of 0.1s and a closing time of 1s, and repeat 20 times to raise the temperature of the catalytic bed in the monocomponent thrust chamber 4 to above 400℃. At this temperature, the functional material will completely decompose.

[0050] S4: Propulsion system for satellite attitude control: The start-up temperature of the single-component thrust chamber 4 catalytic bed is not lower than 200℃, the working pulse width is 25ms, the shutdown time interval is 50ms, and the duty cycle and number of cycles are controlled and adjusted by the control system according to the aircraft attitude.

[0051] S5: Propulsion system satellite orbit control adjustment method: The start-up temperature of the single-component thrust chamber 4 catalytic bed is not lower than 200℃. First, start the catalytic bed heating program: start-up time 0.1s, shutdown time interval 1s, cycle 10 times, then perform the steady-state start-up program. The steady-state working time is controlled and adjusted by the control system according to the attitude of the spacecraft.

[0052] S6: During the standby phase of the propulsion system, the minimum insulation temperature of the catalyst bed in the single-component thrust chamber 4 is not lower than 140℃. The temperature of the single-component thrust chamber 4 is increased by the onboard autonomous heater. The heating duration is controlled and adjusted by the control system according to the onboard energy situation. The temperature control range of components other than the single-component thrust chamber 4, such as tanks, valves, and pressure sensors, is 15℃~60℃.

[0053] Using the above method, the system can achieve 500 warm starts, a warm start temperature of not less than 200℃, 50,000 pulses, and a maximum steady-state working time of 1200s.

[0054] The above method is applicable to green single-component ADN propulsion systems, where the thrust level of the thrust chamber 4 is 1N.

[0055] The above description is only a preferred embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any equivalent substitutions or modifications made by those skilled in the art within the scope of the technology disclosed in the present invention, based on the technical solution and inventive concept of the present invention, should be covered within the scope of protection of the present invention.

Claims

1. A novel green single-component propulsion system's on-orbit application method, characterized in that: The propulsion system includes a propellant tank (1), a front-end solenoid valve (2), a start-up solenoid valve (3), a single-component thrust chamber (4), and a pressure sensor (5). The single-component thrust chamber (4) is equipped with an anti-inversion function membrane, which controls the propulsion system to be installed at any angle on the entire satellite. The on-orbit operation steps of the single-component propulsion system are as follows: S1: The temperature control process of the propulsion system after the entire satellite enters orbit is as follows: the catalyst bed and nozzle of the single-component thrust chamber (4) are placed outside the entire satellite cabin and no temperature control is applied. The injector, storage tank, valve and pressure sensor components of the single-component thrust chamber (4) are placed inside the entire satellite cabin and the temperature range is controlled to be 5℃-60℃. S2: Preheat the catalyst bed of the single-component thrust chamber (4) before the first start-up: For a period of time before the start-up of the single-component thrust chamber (4), 1h-1.5h, start the heater of the single-component thrust chamber (4) to preheat the catalyst bed so that the temperature of the catalyst bed is not lower than 200℃; S3: The first start-up anti-inversion membrane removal method of the single-component thrust chamber (4) is as follows: start the single-component thrust chamber (4), start time 0.05s, stop time 1s, repeat multiple times; then carry out the catalytic bed heating program: start time 0.1s, stop time 1s, repeat multiple times, raise the temperature of the single-component thrust chamber (4) catalytic bed to above 400℃, at this temperature, the functional material will be completely decomposed; S4: The satellite attitude control process of the propulsion system is as follows: the starting temperature of the catalyst bed of the single-component thrust chamber (4) is not lower than 200℃, the working pulse width is not less than 25ms, the shutdown time interval is not less than 100ms, and the duty cycle and cycle number are controlled and adjusted by the control system according to the attitude of the aircraft. S5: The satellite orbit control adjustment process of the propulsion system is as follows: the starting temperature of the catalyst bed of the single-component thrust chamber (4) is not lower than 200℃. The catalyst bed heating process is started first: the start time is 0.1s, the shutdown time interval is 1s, and the cycle is repeated multiple times. Then the steady-state start-up procedure is performed. The steady-state working time is controlled and adjusted by the control system according to the attitude of the spacecraft. S6: During the standby phase of the propulsion system, the minimum insulation temperature of the catalyst bed of the single-component thrust chamber (4) is not lower than 20°C. The temperature of the single-component thrust chamber (4) is increased by the onboard autonomous start heater. The heating time is controlled and adjusted by the control system according to the onboard energy situation. The temperature range of the tank, valves and pressure sensor components other than the single-component thrust chamber (4) is 5°C-60°C.

2. The method for on-orbit use of a novel green single-component propulsion system according to claim 1, characterized in that: The number of warm starts of the single-component thrust chamber (4) shall not be less than 60, the warm start temperature shall not be less than 200℃, the number of pulses shall not be less than 2000, and the longest steady-state working time of a single start shall not be less than 100s.

3. The method for on-orbit use of a novel green single-component propulsion system according to claim 1, characterized in that: This method is applicable to green single-component HAN and ADN propulsion systems where the thrust level of the thrust chamber (4) is no greater than 5N.

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