Electric thruster thermal control and satellite thermal control fluid loop integrated system and implementation method thereof

Abstract

The invention provides an electric thruster thermal control and satellite thermal control fluid loop integrated system and an implementation method thereof. The system comprises a satellite internal fluid loop 1, an external fluid loop 3 and a heat exchanger 4. The satellite internal fluid loop 1 is connected with the external fluid loop 3 through the heat exchanger 4; under different working modes, the heat of the electric thruster and the heat in the satellite are efficiently utilized, the electric thruster is particularly suitable for tasks such as deep space exploration, the thermal control power consumption of the satellite body can be effectively saved, the working temperature of the electric thruster is reduced, and the working performance of the electric thruster is improved.

Description

Technical Field

[0001] The present invention relates to the field of electric propulsion thermal control and satellite thermal control, and in particular to an integrated system of electric thruster thermal control and satellite thermal control fluid circuit and a method for implementing the system. Background Art

[0002] Electric thrusters are one of the electric propulsion devices widely used in aerospace orbit. When in working state, the maximum temperature of components can reach 300-400℃, or even higher. It is necessary to perform thermal conduction treatment on high-temperature components and thermal protection treatment on heat-sensitive components. When not in working state, due to the physical characteristics of some of its components, there are special requirements for the minimum standby temperature. Therefore, electric thrusters operating in orbit need to perform thermal control management to keep each component operating within an appropriate range.

[0003] In order to prevent the high temperature heat from being transferred to the satellite body during the operation of electric propulsion, it is usually required to install insulation pads and other components between the electric thruster and the satellite for heat insulation treatment. This makes the thermal control of the thruster at high temperature more difficult, and the difficulty of heat dissipation on orbit further limits the performance improvement of the electric thruster. At the same time, some subsystems and components of the satellite have requirements for operating temperature, so the satellite thermal control subsystem needs to be equipped with multiple heaters to control the temperature of the components, which consumes a lot of power, especially for long-term large-scale deep space exploration detectors. When in cold standby for a long time, the thermal control consumes a lot of power.

[0004] During deep space exploration, the electric propulsion system of the probe will work continuously for thousands to tens of thousands of hours during deep space orbit transfer. The typical efficiency of electric thrusters is about 50% to 65%, and they lose 35% to 50% of energy, most of which is dissipated as heat energy.

[0005] Fluid circuit is an active thermal control technology based on mechanical pumps, which has the advantages of simple structure, flexible layout, high robustness and good inheritability. It has played a core role in the thermal control system of large manned spacecraft such as the Apollo lunar module, the space shuttle, the International Space Station and the Shenzhou spacecraft.

[0006] Based on this, the present invention provides an integrated design method and system for electric thruster thermal control and satellite thermal control fluid circuit, which reduces the on-orbit thermal control power consumption of the electric thruster and improves the overall thermal control efficiency of the satellite and the working performance of the electric thruster.

[0007] Patent document CN112918705B (application number: 202110273581.6) discloses a thermal control system and method for an integrated propulsion subsystem. The patent mainly designs a thermal control system for an integrated propulsion subsystem to achieve the temperature index requirements of each propulsion component, while ensuring the orbit control and attitude control capabilities of the spacecraft, and reducing the weight, power consumption, and implementation difficulty of the thermal control of the propulsion subsystem. Compared with the present invention, the patent is an independent thermal control design scheme for the thrust subsystem, which does not involve docking with the thermal control of the entire satellite;

[0008] Patent document CN101508349B (application number: 200910080237.4) discloses a fluid circuit control device suitable for a nanosatellite thermal control system. The patent mainly installs a microchannel heat exchanger 10 on the onboard equipment of an existing nanosatellite, so as to reuse the heat generated by the onboard equipment when it is working, thereby saving the energy of the nanosatellite. Compared with the present invention, the energy used in the patent is the heat generated by the onboard equipment when it is working, while the energy used in the present invention is the waste heat generated by the electric thruster, and a thermal control design of the fluid circuit is adopted.

[0009] Patent document CN113879568A (application number: 202111037827.6) discloses a pluggable satellite thermal control system and method. The patent mainly provides a pluggable satellite thermal control system, including an operating robot, a thermal insulation component and a heat dissipation component to enhance the satellite's heat dissipation capacity. Compared with the present invention, the technical means are different.

[0010] Patent document CN114408225A (application number: 202210048878.7) discloses a universal satellite cabin panel thermal design structure. This patent mainly provides a universal satellite cabin panel thermal design structure to solve the problem of poor satellite thermal design. Compared with the present invention, the technical means are different. The present invention adopts a fluid circuit solution.

[0011] Patent document CN115145325A (application number: 202210821225.8) discloses an active temperature control device and method for a high-heat-generating space device. This patent mainly provides an active temperature control method and device for a high-heat-generating space device to solve the problem of poor satellite thermal design. Compared with the present invention, the working principle is different and the heat control method is different. Summary of the invention

[0012] In view of the defects in the prior art, the object of the present invention is to provide an integrated system of electric thruster thermal control and satellite thermal control fluid circuit and a method for implementing the same.

[0013] According to the present invention, an electric thruster thermal control and satellite thermal control fluid circuit integrated system includes: a satellite internal fluid circuit 1, an external fluid circuit 3 and a heat exchanger 4;

[0014] The satellite internal fluid circuit 1 is connected to the external fluid circuit 3 via the heat exchanger 4 .

[0015] Preferably, the external fluid circuit 3 comprises: an internal fluid pipeline of the electric thruster 9, a radiation heat sink 10, a first control valve 5, a second control valve 6, a first external circuit pump 7 and a second external circuit pump 8;

[0016] One end of the electric thruster 9 is connected to one end of the radiation radiator 10 through the first control valve 5; the other end of the electric thruster 9 is connected to the other end of the radiation radiator 10 through the second external circuit pump 8 and the second control valve 6 in sequence.

[0017] Preferably, the satellite internal fluid circuit 1 comprises an internal heat transfer fluid circuit 2; the internal heat transfer fluid circuit 2 is connected to the heat exchanger 4 to form a circuit.

[0018] Preferably, the first control valve 5 in the external fluid circuit is connected to the heat exchanger 4 ; the second control valve 6 in the external fluid circuit is connected to the heat exchanger 4 via the first external circuit pump 7 .

[0019] Preferably, the first control valve 5 and the second control valve 6 are used to realize on-off and flow control between the fluid pipeline of the electric thruster 9 and the fluid pipeline of the radiant heat sink 10, and between the fluid pipeline of the electric thruster 9 and the fluid pipeline of the heat exchanger 10.

[0020] Preferably, the first external circuit pump 7 is turned on, the first control valve 5 and the second control valve 6 are adjusted, and the radiation radiator 10 and the pipelines on both sides are isolated from the external fluid circuit 3 to achieve positive and negative transfer of heat flow inside the satellite and heat flow of the electric thruster 9.

[0021] Preferably, the second external circuit pump 8 is turned on to assist in controlling the power of the first external circuit pump 7, and the first control valve 5 and the second control valve 6 are adjusted so that all pipelines of the external fluid circuit 3 are connected, so that the heat flow inside the satellite and the electric thruster 9 converges to the radiation heat sink 10.

[0022] Preferably, the exposed pipelines of the external fluid circuit 3 are all covered with multiple layers of thermal control protection measures.

[0023] According to a method for implementing an integrated system of electric thruster thermal control and satellite thermal control fluid circuit provided by the present invention, the following steps are performed using the integrated system of electric thruster thermal control and satellite thermal control fluid circuit described above:

[0024] When the heat generated in the satellite internal fluid circuit 1 is lower than a preset value, the heat of the electric inference device 9 is supplemented into the satellite internal fluid circuit 1;

[0025] When the heat generated in the external fluid circuit 3 is lower than a preset value, the heat of the internal heat-conducting fluid circuit 2 is supplemented into the external fluid circuit 3;

[0026] When the heat of the satellite internal fluid circuit 1 and the external fluid circuit 3 is higher than a preset value, the heat flows to the radiation heat sink 10 for convergence.

[0027] Preferably, when the heat value in the satellite internal fluid circuit 1 is lower than a preset value or the heat value in the external fluid circuit 3 is lower than a preset value, the first external circuit pump 7 is turned on, and the first control valve 5 and the second control valve 6 are adjusted to supplement the heat of the electric inference device 9 to the satellite internal fluid circuit 1 or supplement the heat of the internal heat transfer fluid circuit 2 to the external fluid circuit 3;

[0028] When the heat of the satellite's internal fluid circuit 1 and the external fluid circuit 3 is higher than a preset value, the second external circuit pump 8 is turned on to assist in controlling the power of the first external circuit pump 7, and the first control valve 5 and the second control valve 6 are adjusted to connect all pipelines of the external fluid circuit 3, so that the heat flow inside the satellite and the electric thruster 9 converges to the radiation heat sink 10.

[0029] Compared with the prior art, the present invention has the following beneficial effects:

[0030] 1. The present invention realizes efficient utilization of the heat of the electric thruster and the internal heat of the satellite under different working modes, and is particularly suitable for tasks such as deep space exploration, which can effectively save the thermal control power consumption of the satellite body, reduce the working temperature of the electric thruster, and improve its working performance;

[0031] 2. The present invention proposes an integrated system of electric thruster thermal control and satellite thermal control fluid circuit and its implementation method, which solves the problem of thermal control of electric thrusters in deep space exploration, converts the heat generated by the electric thrusters into an effective heat source for thermal control inside the satellite, and improves the working thermal stability of the thrusters;

[0032] 3. The present invention can effectively save the thermal control power consumption of the satellite body, reduce the operating temperature of the electric thruster, and improve its working performance. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] Other features, objects and advantages of the present invention will become more apparent from the detailed description of non-limiting embodiments made with reference to the following drawings:

[0034] Figure 1 It is a schematic diagram of the integrated design of the electric thruster and the satellite thermal control fluid circuit according to the present invention.

[0035] Figure 2It is a schematic diagram of the heat flow direction of the thermal control fluid circuit of the present invention under three different working modes. DETAILED DESCRIPTION

[0036] The present invention is described in detail below in conjunction with specific embodiments. The following embodiments will help those skilled in the art to further understand the present invention, but are not intended to limit the present invention in any form. It should be noted that, for those of ordinary skill in the art, several changes and improvements can also be made without departing from the concept of the present invention. These all belong to the protection scope of the present invention.

[0037] Example 1

[0038] According to the present invention, an integrated system of electric thruster thermal control and satellite thermal control fluid circuit is provided. Figure 1 As shown, it includes: a satellite internal fluid circuit 1, an external fluid circuit 3 and a heat exchanger 4;

[0039] The satellite internal fluid circuit 1 is connected to the external fluid circuit 3 via the heat exchanger 4 .

[0040] Specifically, the external fluid circuit 3 includes: an internal fluid pipeline of the electric thruster 9, a radiation heat sink 10, a first control valve 5, a second control valve 6, a first external circuit pump 7 and a second external circuit pump 8;

[0041] One end of the electric thruster 9 is connected to one end of the radiation radiator 10 through the first control valve 5; the other end of the electric thruster 9 is connected to the other end of the radiation radiator 10 through the second external circuit pump 8 and the second control valve 6 in sequence.

[0042] Specifically, the satellite internal fluid circuit 1 includes an internal heat transfer fluid circuit 2; the internal heat transfer fluid circuit 2 is connected to the heat exchanger 4 to form a circuit.

[0043] Specifically, the first control valve 5 in the external fluid circuit is connected to the heat exchanger 4 ; the second control valve 6 in the external fluid circuit is connected to the heat exchanger 4 through the first external circuit pump 7 .

[0044] In this embodiment, the satellite internal fluid circuit 1 and the external fluid circuit 3 are designed as segmented controllable fluid circuits, and the on-off and direction of the fluid in the external fluid circuit are controlled by the control valves on both sides of the electric thruster, so as to achieve the purpose of thermal control under different thermal states;

[0045] The fluid flow direction in the external fluid circuit can be realized in forward and reverse flow according to requirements.

[0046] According to the present invention, a method for realizing an integrated system of electric thruster thermal control and satellite thermal control fluid circuit is provided, such as Figure 2As shown, including:

[0047] Working mode 1: When the thrusters are working and the satellite body needs additional heat for thermal control, the control valves on both sides of the electric thrusters are adjusted to transfer part of the heat of the electric thrusters to the internal fluid circuit of the satellite through the external fluid circuit and the heat exchanger for thermal control of each unit inside the satellite;

[0048] Working mode 2: When the thrusters are working and the satellite body does not need external heat for thermal control but needs to dissipate heat to the outside, the control valves on both sides of the electric thrusters are adjusted to transfer the excess heat of the satellite body and the heat of the electric thrusters to the radiation radiator through the external fluid circuit;

[0049] Working mode 3: When the thruster is not working, the heat generated by the single unit inside the satellite is large and needs to be dissipated externally. The heat of the single unit is guided to the heat exchanger through the satellite fluid circuit, and the heat is transferred to the external fluid circuit through the heat exchanger. The control valves on both sides of the electric thruster are adjusted to guide the heat flow to the electric thruster for thermal control and insulation in its non-working state.

[0050] The fluid circuit can automatically control the flow rate of the fluid circuit according to the temperature of each component, and cooperate with the control valves at both ends of the electric thruster to control the fluid flow in different pipelines, ultimately realizing the function of controlling heat exchange and radiation heat dissipation according to demand.

[0051] Example 2

[0052] Embodiment 2 is a preferred embodiment of Embodiment 1

[0053] Combination Figure 1 and Figure 2 To illustrate the implementation of the thermal control fluid circuit:

[0054] According to the present invention, an electric thruster thermal control and satellite thermal control fluid circuit integrated system includes: heat exchange between an internal fluid circuit 1 and an external fluid circuit 3 of the satellite is achieved through a heat exchanger 4.

[0055] The external fluid circuit 3 includes an internal fluid pipeline of the electric thruster 9, a radiation heat sink 10, a first control valve 5 and a second control valve 6 at both ends of the electric thruster 9, a first external circuit pump 7 and a second external circuit pump 8, etc.

[0056] The control valves at both ends of the electric thruster 9 can realize the on-off and flow control of the fluid pipeline of the electric thruster 9 and the fluid pipeline of the radiation radiator 10, as well as the fluid pipeline of the electric thruster 9 and the fluid pipeline of the radiation heat exchanger 10.

[0057] By opening the first external circuit pump 7 and adjusting the first control valve 5 and the second control valve 6, the radiation radiator 10 and the pipelines on both sides are isolated from the external fluid circuit 3, the positive and negative transfer of the heat flow inside the satellite and the heat flow of the electric thruster 9 can be realized. For example, when the electric thruster works continuously for a long time to perform deep space transfer in deep space exploration, and the main single machines inside the satellite are all in the shutdown state and the heat generation is low, the heat flow of the electric thruster can be guided to the inside of the detector for temperature control; when it is in the exploration mission stage, the main loads are working, the heat generated inside the satellite is large, and the electric thruster 9 does not work for a long time, the heat is guided to the temperature-sensitive components of the electric thruster 9 through the fluid circuit to achieve temperature control and ensure its performance.

[0058] The second external circuit pump 8 is turned on to assist in controlling the power of the first external circuit pump 7, and the first control valve 5 and the second control valve 6 are adjusted to connect all the pipelines of the external fluid circuit, so that the heat flow inside the satellite and the electric thruster 9 converges to the radiation radiator 10. For example, when the electric thruster and the main heat-generating load inside the satellite are both in working state, the fluid circuit is adjusted to guide the heat of both to the radiation radiator for heat dissipation.

[0059] According to the thermal control requirements of different types of electric thrusters 9, the internal heat transfer fluid circuit 2 is designed individually, but the interface specifications connected to the external fluid circuit are designed uniformly to facilitate modular replacement.

[0060] All exposed pipes in the external fluid circuit 3 need to adopt thermal control protection measures such as multi-layer wrapping.

[0061] The fluid circuit design provided by the present invention can adapt to the heat regulation of different thermal states under various operating modes of the satellite.

[0062] The above describes the specific embodiments of the present invention. It should be understood that the present invention is not limited to the above specific embodiments, and those skilled in the art can make various changes or modifications within the scope of the claims, which does not affect the essence of the present invention. In the absence of conflict, the embodiments of the present application and the features in the embodiments can be combined with each other arbitrarily.

Claims

1. An integrated system of electric thruster thermal control and satellite thermal control fluid circuit, characterized in that: include: A satellite internal fluid circuit (1), an external fluid circuit (3) and a heat exchanger (4); The satellite internal fluid circuit (1) is connected to the external fluid circuit (3) via the heat exchanger (4).

2. The electric thruster thermal control and satellite thermal control fluid circuit integrated system according to claim 1 is characterized in that: The external fluid circuit (3) comprises: an internal fluid pipeline of the electric thruster (9), a radiation heat sink (10), a first control valve (5), a second control valve (6), a first external circuit pump (7) and a second external circuit pump (8); One end of the electric thruster (9) is connected to one end of the radiation radiator (10) via a first control valve (5); the other end of the electric thruster (9) is connected to the other end of the radiation radiator (10) via the second external circuit pump (8) and the second control valve (6) in sequence.

3. The electric thruster thermal control and satellite thermal control fluid circuit integrated system according to claim 1, characterized in that: The satellite internal fluid circuit (1) comprises an internal heat-conducting fluid circuit (2); the internal heat-conducting fluid circuit (2) is connected to the heat exchanger (4) to form a circuit.

4. The electric thruster thermal control and satellite thermal control fluid circuit integrated system according to claim 1, characterized in that: The first control valve (5) in the external fluid circuit is connected to the heat exchanger (4); the second control valve (6) in the external fluid circuit is connected to the heat exchanger (4) via the first external circuit pump (7).

5. The electric thruster thermal control and satellite thermal control fluid circuit integrated system according to claim 2, characterized in that: The first control valve (5) and the second control valve (6) are used to realize the on-off and flow control of the fluid pipeline of the electric thruster (9) and the fluid pipeline of the radiant heat sink (10), as well as the fluid pipeline of the electric thruster (9) and the fluid pipeline of the heat exchanger (10).

6. The electric thruster thermal control and satellite thermal control fluid circuit integrated system according to claim 2, characterized in that: The first external circuit pump (7) is turned on, and the first control valve (5) and the second control valve (6) are adjusted to isolate the radiation radiator (10) and the pipelines on both sides from the external fluid circuit (3), thereby achieving positive and negative transfer of heat flow inside the satellite and heat flow of the electric thruster (9).

7. The electric thruster thermal control and satellite thermal control fluid circuit integrated system according to claim 2, characterized in that: The second external circuit pump (8) is turned on to assist in controlling the power of the first external circuit pump (7), and the first control valve (5) and the second control valve (6) are adjusted so that all pipelines of the external fluid circuit (3) are connected, thereby realizing the convergence of heat flow inside the satellite and the electric thruster (9) to the radiation heat sink (10).

8. The electric thruster thermal control and satellite thermal control fluid circuit integrated system according to claim 1, characterized in that: The exposed pipelines of the external fluid circuit (3) are all protected by thermal control measures such as multiple layers of wrapping.

9. A method for realizing an integrated system of electric thruster thermal control and satellite thermal control fluid circuit, characterized in that: The following steps are performed using the integrated system of electric thruster thermal control and satellite thermal control fluid circuit as described in any one of claims 1 to 8: When the heat generated in the satellite internal fluid circuit (1) is lower than a preset value, the heat of the electric inference device (9) is supplemented into the satellite internal fluid circuit (1); When the heat generated in the external fluid circuit (3) is lower than a preset value, the heat of the internal heat-conducting fluid circuit (2) is supplemented into the external fluid circuit (3); When the heat of the satellite internal fluid circuit (1) and the external fluid circuit (3) is higher than a preset value, the heat flows to the radiation heat sink (10) for convergence.

10. The method for realizing the integrated system of electric thruster thermal control and satellite thermal control fluid circuit according to claim 9, characterized in that: When the heat generated in the satellite internal fluid circuit (1) is lower than a preset value or the heat generated in the external fluid circuit (3) is lower than a preset value, the first external circuit pump (7) is turned on, the first control valve (5) and the second control valve (6) are adjusted, and the heat of the electric inference device (9) is supplemented to the satellite internal fluid circuit (1) or the heat of the internal heat transfer fluid circuit (2) is supplemented to the external fluid circuit (3); When the heat of the satellite's internal fluid circuit (1) and the external fluid circuit (3) is higher than a preset value, the second external circuit pump (8) is turned on to assist in controlling the power of the first external circuit pump (7), and the first control valve (5) and the second control valve (6) are adjusted so that all pipelines of the external fluid circuit (3) are connected, thereby realizing the convergence of heat flow from the satellite's interior and the electric thruster (9) to the radiation heat sink (10).

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