Dual-mode propulsion system of xenon working propellant electric propulsion and cold gas propulsion

Abstract

This invention provides a dual-mode propulsion system in the field of space propulsion technology, combining xenon propellant electric propulsion and cold gas propulsion. The system comprises a gas storage module and a pressure regulation module connected in series, with an electric propulsion module and a cold gas propulsion module connected in parallel downstream. These modules are controlled by a control and power module, which is shared by both electric and cold gas propulsion. Its advantages include solving the problem of insufficient control torque compared to a single electric propulsion system. Furthermore, because xenon is used as the working propellant, the xenon required for cold gas propulsion and electric propulsion serves as a backup for each other, resulting in high system integration. This meets the stringent limitations of satellite propulsion system size and control resources. Compared to an independent cold gas propulsion system, it achieves stable adjustment of the cold gas thruster's thrust over a wide range. Additionally, the system employs isentropic expansion decompression, reducing energy loss during decompression and lowering the power consumption required for temperature control.

Description

Technical Field

[0001] This invention relates to the field of space propulsion technology, specifically to a dual-mode propulsion system combining xenon propellant electric propulsion and cold gas propulsion. Background Technology

[0002] With the development and maturation of electric propulsion technology, its advantages of high specific impulse, long lifespan, and low thrust have led to its large-scale application in low-Earth orbit satellite constellations. Compared to traditional chemical propulsion systems that utilize multiple engines, electric propulsion technology is limited by energy, cost, and structure, requiring only a single orbit control thruster per system. Therefore, satellites using electric propulsion systems need to be coupled with magnetic rods or flywheels for attitude control. Because the torque provided by magnetic rods and flywheels is relatively small, the control time is long, affecting the establishment of the satellite's attitude, and even causing attitude control failure. Some satellites require cold gas propulsion for attitude control and flywheel unloading. Adding a separate cold gas propulsion system complicates the propulsion system, requires more telemetry, control, and temperature control resources, and results in greater weight. Summary of the Invention

[0003] To address the shortcomings of existing technologies, the purpose of this invention is to provide a dual-mode propulsion system that combines xenon propellant electric propulsion and cold gas propulsion.

[0004] The present invention provides a dual-mode propulsion system for xenon working propellant electric propulsion and cold gas propulsion, comprising a gas storage module, a pressure regulation module, an electric propulsion module, a cold gas propulsion module, and a control and power module;

[0005] The gas storage module is connected in series with one end of the pressure regulating module, and the cold air propulsion module and the electric propulsion module are connected in parallel with the other end of the pressure regulating module.

[0006] The control and power module controls the operation of the gas storage module, the pressure regulation module, the electric propulsion module, and the cold gas propulsion module, and the gas storage module, the pressure regulation module, and the control and power module are configured as multiplexed modules for electric propulsion mode and cold gas propulsion mode.

[0007] In some embodiments, the gas storage module includes a high-pressure sensor, a xenon cylinder, a filler valve, and a self-locking valve, with one outlet end of the xenon cylinder sequentially connected to the filler valve, the high-pressure sensor, and the self-locking valve.

[0008] The xenon cylinder is used to store high-pressure xenon working fluid;

[0009] The filling and emptying valve is used to fill and release the xenon cylinder during ground testing and filling.

[0010] The high-pressure sensor is used to monitor the pressure of the xenon cylinder to prevent overpressure.

[0011] The self-locking valve is used to supply high-pressure xenon working fluid to the downstream pressure regulating module.

[0012] In some embodiments, the self-locking valve one is connected in series with one end of the solenoid valve one and the solenoid valve two, and the other end of the solenoid valve one and the solenoid valve two is connected in series with one end of the inlet of the buffer tank, and one end of the outlet of the buffer tank is connected to the low-pressure sensor.

[0013] The control and power module uses the low-pressure sensor to collect the pressure signal of the buffer tank and controls the opening and closing sequence of the solenoid valve one and the solenoid valve two to enable the xenon cylinder to fill the buffer tank.

[0014] In some embodiments, the cold air propulsion module includes a second self-locking valve and a cold air thruster. One end of the outlet of the buffer tank is also connected to one end of the second self-locking valve. Multiple cold air thrusters are arranged in parallel at the other end of the second self-locking valve. The second self-locking valve is used to control the opening and closing of the air passage of the cold air propulsion module.

[0015] In some embodiments, the electric propulsion module includes a flow regulator and an electric thruster, with one end of the buffer tank connected to the flow regulator, which is connected to the electric thruster; the flow regulator is used to control and distribute the xenon gas flow rate supplied to the cathode and anode of the electric thruster.

[0016] In some embodiments, multiple cold gas thrusters and electric thrusters are disposed on the same satellite base plate, and the multiple cold gas thrusters are respectively disposed at the four corners of the satellite base plate.

[0017] The electric thruster is located at the center of the satellite base plate, and the thrust vector directions of the plurality of cold gas thrusters are set at a certain angle to the satellite base plate.

[0018] In some embodiments, the flow regulator and the self-locking valve are arranged in parallel at one end of the outlet of the buffer tank.

[0019] Compared with the prior art, the present invention has the following beneficial effects:

[0020] 1. This invention highly integrates a dual-mode propulsion system of xenon working propellant electric propulsion and cold gas propulsion by setting up a gas storage module, a pressure regulation module, a control and power module, an electric propulsion module and a cold gas propulsion module. At the same time, the gas storage, pressure regulation, control and power modules can be shared. This can simplify the system, increase the system reliability, reduce the system size and weight, reduce the control resources required for the propulsion system, and reduce production and use costs.

[0021] 2. This invention stores the xenon working propellant required for both cold gas propulsion and electric propulsion in the same cylinder, allowing the xenon required for both to serve as backups for each other, thus increasing system reliability.

[0022] 3. This invention reduces energy loss during decompression by using isentropic expansion decompression in the pressure regulation module, thereby reducing the energy demand for temperature control during propulsion system operation. Moreover, this decompression method provides stable output pressure and a wide adjustment range, thus achieving a 10-fold adjustment of the thrust of the cold gas thruster. Attached Figure Description

[0023] Other features, objects, and advantages of the present invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings:

[0024] Figure 1 This is a schematic diagram illustrating the working principle of the dual-mode propulsion system of xenon working propellant electric propulsion and cold gas propulsion of the present invention.

[0025] Figure 2 This is a bottom view schematic diagram of the electric thruster and the cold gas thruster of the dual-mode propulsion system of xenon working propellant electric propulsion and cold gas propulsion of the present invention;

[0026] Figure 3 This is a side view of the electric thruster and the cold gas thruster of the dual-mode propulsion system of xenon working propellant electric propulsion and cold gas propulsion of the present invention.

[0027] Figure label:

[0028] Gas storage module 1, low-pressure pressure sensor 24

[0029] High-pressure sensor 11, cold air propulsion module 3

[0030] Xenon cylinder 12, self-locking valve 2, 31

[0031] Add exhaust valve 13, air conditioning thruster 32

[0032] Self-locking valve 14 Electric propulsion module 4

[0033] Pressure regulating module 2 Flow regulator 41

[0034] Solenoid valve 121, electric thruster 42

[0035] Solenoid Valve 22 Control and Power Module 5

[0036] Buffer tank 23 Satellite base plate 6 Detailed Implementation

[0037] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the protection scope of the present invention.

[0038] like Figure 1 As shown, the xenon propellant electric propulsion and cold gas propulsion dual-mode propulsion system of the present invention includes a gas storage module 1, a pressure regulation module 2, a cold gas propulsion module 3, an electric propulsion module 4, and a control and power module 5. The gas storage module 1, pressure regulation module 2, and control and power module 5 are multiplexed modules for both electric and cold gas propulsion.

[0039] The gas storage module 1 consists of a xenon cylinder 12, the outlet of which is connected in sequence to a high-pressure sensor 11, a filler / release valve 13, and a self-locking valve 14. The filler / release valve 13 is used to fill and release the xenon cylinder 12 during ground testing and filling. The xenon cylinder 12 is used to store high-pressure xenon working fluid at 7-12 MPa. The self-locking valve 14 is used to supply high-pressure xenon working fluid to the downstream pressure regulating module 2. The high-pressure sensor 11 is used to monitor the pressure of the xenon cylinder 12 to prevent overpressure of the cylinder.

[0040] The pressure regulation module 2 consists of a solenoid valve 21, a solenoid valve 22, a buffer tank 23, and a low-pressure sensor 24 connected in sequence. The control and power module 5 collects the pressure of the buffer tank 23 through the low-pressure sensor 24 and performs closed-loop control based on the pressure signal. It adopts a certain control strategy to control the opening and closing sequence of solenoid valves 21 and 22 to inflate the buffer tank 23. High-pressure xenon of 7-12MPa enters the buffer tank 23 for isentropic expansion and decompression, thereby providing a high-precision stable pressure output with a 10-fold adjustable pressure range for the gas propulsion module 3 and the electric propulsion module 4. This means that the gas propulsion module 3 and the electric propulsion module 4 can be provided with a high-precision stable pressure output with ±2% fluctuation within a pressure range of 0.1-1MPa.

[0041] The cold air propulsion module 3 consists of a second self-locking valve 31 and multiple cold air thrusters 32. The second self-locking valve 31 is used to control the opening and closing of the air passage of the cold air propulsion module 3. The four cold air thrusters 32 connected in parallel downstream of the second self-locking valve 31 work in pairs to generate the required force and torque.

[0042] The electric propulsion module 4 consists of a flow regulator 41 and an electric thruster 42. The flow regulator 41 is composed of flow resistance elements and can be composed of a labyrinth throttle and a solenoid valve. It is used to control and distribute the xenon gas flow supplied to the cathode and anode in the electric thruster 42.

[0043] like Figure 2As shown, the electric thruster 42 of the present invention is arranged on the satellite base plate 6. The thrust vector of the electric thruster 42 acts on the center of mass of the artificial satellite to maintain the orbital maneuverability and stability of the artificial satellite.

[0044] Multiple cold gas thrusters 32 are arranged sequentially at the four corners of the satellite base plate 6. The center point of the satellite base plate 6 coincides with the thrust vector direction of the electric thruster 42 and the center of mass of the satellite. The thrust vector direction of the multiple cold gas thrusters 32 is set at 45° with the satellite base plate. By controlling different thrusters to work in pairs, the satellite can achieve three-axis stable control, rapid orbital maneuvering, and flywheel unloading. Furthermore, by expanding the number and position of the cold gas thrusters 32, more precise attitude control of the satellite can be achieved.

[0045] By adjusting the pressure output of the pressure regulating module 2, the thrust variation on the cold gas thruster 32 can be increased by 10 times. Specifically, the thrust variation on the cold gas thruster 32 can be increased from 2 to 20 mN by adjusting the pressure output of the pressure regulating module 2, which can be used for drag-free satellite control.

[0046] The control and power module 5 is used for remote measurement of pressure, temperature, current, voltage, etc. of the dual-mode propulsion system, power supply and remote control of valves, heaters, pressure sensors, etc., and control of power output of the anode and cathode in electric propulsion mode.

[0047] In the description of this application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application.

[0048] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. A dual-mode propulsion system combining xenon working propellant electric propulsion and cold gas propulsion, characterized in that, It includes a gas storage module (1), a pressure regulation module (2), a cold air propulsion module (3), an electric propulsion module (4), and a control and power module (5); The gas storage module (1) is connected in series with the pressure regulating module (2) at one end, and the cold air propulsion module (3) and the electric propulsion module (4) are connected in parallel at the other end of the pressure regulating module (2); The control and power module (5) controls the operation of the gas storage module (1), the pressure regulation module (2), the cold air propulsion module (3) and the electric propulsion module (4), and the gas storage module (1), the pressure regulation module (2) and the control and power module (5) are configured as multiplexing modules for electric propulsion mode and cold air propulsion mode; The gas storage module (1) includes a high pressure sensor (11), a xenon cylinder (12), a filler valve (13), and a self-locking valve (14). The outlet end of the xenon cylinder (12) is connected in sequence to the filler valve (13), the high pressure sensor (11), and the self-locking valve (14). The xenon cylinder (12) is used to store high-pressure xenon working fluid; The filling and emptying valve (13) is used to fill and empty the xenon cylinder (12) during ground testing and filling; The high-pressure sensor (11) is used to monitor the pressure of the xenon cylinder (12) to prevent overpressure. The self-locking valve (14) is used to supply high-pressure xenon working fluid to the downstream pressure regulating module (2); The pressure regulating module (2) includes a solenoid valve one (21), a solenoid valve two (22), a buffer tank (23), and a low-pressure sensor (24). The self-locking valve one (14) is connected in series with one end of the solenoid valve one (21) and the solenoid valve two (22), and the other end of the solenoid valve one (21) and the solenoid valve two (22) is connected in series with one end of the inlet of the buffer tank (23). One end of the outlet of the buffer tank (23) is connected to the low pressure sensor (24). The control and power module (5) collects the pressure signal of the buffer tank (23) through the low-pressure sensor (24) and controls the opening and closing sequence of the solenoid valve one (21) and the solenoid valve two (22) to realize the xenon cylinder (12) to fill the buffer tank (23).

2. The dual-mode propulsion system of xenon working propellant electric propulsion and cold gas propulsion according to claim 1, characterized in that, The cold air propulsion module (3) includes a self-locking valve two (31) and a cold air thruster (32). One end of the outlet of the buffer tank (23) is also connected to one end of the self-locking valve two (31). Multiple cold air thrusters (32) are arranged in parallel at the other end of the self-locking valve two (31). The self-locking valve two (31) is used to control the air passage opening and closing of the cold air propulsion module (3).

3. The dual-mode propulsion system of xenon working propellant electric propulsion and cold gas propulsion according to claim 2, characterized in that, The electric propulsion module (4) includes a flow regulator (41) and an electric thruster (42). The outlet end of the buffer tank (23) is also connected to the flow regulator (41), and the flow regulator (41) is connected to the electric thruster (42). The flow regulator (41) is used to control and distribute the xenon gas flow supplied to the cathode and anode of the electric thruster (42).

4. The dual-mode propulsion system of xenon working propellant electric propulsion and cold gas propulsion according to claim 3, characterized in that, Multiple cold gas thrusters (32) and electric thrusters (42) are disposed on the same satellite base plate (6), and multiple cold gas thrusters (32) are disposed at the four corners of the satellite base plate (6); The electric thruster (42) is located at the center of the satellite base plate (6), and the thrust vector direction of the plurality of cold gas thrusters (32) is set at a certain angle to the satellite base plate (6).

5. The dual-mode propulsion system of xenon working propellant electric propulsion and cold gas propulsion according to claim 3, characterized in that, The flow regulator (41) and the self-locking valve (31) are connected in parallel at one end of the outlet of the buffer tank (23).

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