Novel micro-flow control system imitating Tesla valve structure for satellite

Abstract

The invention provides a Tesla valve structure imitating novel micro-flow control system for satellites, which comprises a xenon gas circuit control system and a circuit control system, and the xenon gas circuit control system comprises a Tesla valve structure imitating novel micro-flow controller for satellites. The Tesla valve structure imitating type novel micro-flow controller for the satellite comprises a sealed cavity provided with a xenon inlet and a xenon outlet, and a plurality of flow channels communicated with the xenon inlet and the xenon outlet are formed in the sealed cavity. Based on the step-by-step throttling characteristic of a Tesla valve structure during reverse flow, the micro-channel type flow controller is used for flow channel design of the micro-channel type flow controller, nearly perfect precise regulation and control of xenon pressure and flow can be theoretically achieved, and the smooth implementation of the micro-channel type flow controller has the advantages of improving the xenon management level of a space Hall electric propeller, improving the flow rate of the space Hall electric propeller and improving the flow rate of the space Hall electric propeller. The method has important strategic significance in improving micro flow distribution and coordination control precision and enhancing maneuverability.

Description

Technical Field

[0001] The invention relates to the field of space propulsion technology, in particular to a novel micro-flow control system with a Tesla-like valve structure for satellites. Background Art

[0002] Hall effect propulsion is a typical spacecraft electric propulsion system with advantages such as high thrust-to-power ratio, high thrust density, high specific impulse, simple and reliable system (Zhang Guangke, Shan Shihua, Fan Chao, Overview of the Development Trend of Satellite Propellant Technology, Chemical Propellants and Polymer Materials 2012, 10: 71-74.). Xenon (high purity Xe) is the most commonly used propellant for Hall thrusters, with many advantages such as no pollution, no toxicity, and no chemical reaction with spacecraft surface materials. In order to improve storage efficiency, the storage pressure of xenon in the space electric propulsion system is about 15MPa, and the inlet pressure of the flow regulating module in the propellant supply unit is relatively low, usually about 0.2MPa. Hall electric thrusters have very strict requirements on propellant flow control. The inlet pressure is high and the output flow is very small. How to reduce the outlet pressure to 5~10kPa and ensure the outlet flow is 0.1~20mg / s is the key to the stable operation of the Hall thruster (Hou Xiao, Li Yong, Wu Zhiwen, Lin Qingguo, Wang Xiaowei, Geng Hai, Huang Tiankun, Thoughts and Suggestions on the Development of Space Propulsion Technology in my country, China Engineering Science 2024, 26: 217-225.).

[0003] At present, electric propulsion systems at home and abroad mostly use micro-flow controllers such as metal capillaries and porous metal materials for flow control, such as: SH Collicott, Convergence behavior of surface evolver applied to agenic propellant-management device, Journal of Propulsion and Power 2001,17: 845-851, Wang Xiaoyong, Zhang Hongpeng, Hu Jing, Li Xingkun, Development of propellant supply technology for foreign electric propulsion systems, Vacuum and Cryogenics 2022, 28: 497-506, J. Cassady, B. Boyce, B. Kearney, D. Herman, P.Peterson, Development of 12 kw hall thrusters for nasa lunar gateway power and propulsion element, SPACE PROPULSION 2022, ESTORIL, PORTUGAL | 09 – 13MAY 2022. The capillary micro-flow controller uses a capillary as a throttling element, and achieves micro-flow control by precisely controlling the diameter and length of the capillary, as well as monitoring and regulating the pressure, temperature and other parameters of the fluid in the capillary. The porous metal material micro-flow controller uses the characteristics of porous metal materials to achieve micro-flow control by precisely controlling and monitoring the parameters of the fluid passing through the material. Although adjusting the inlet pressure and temperature can correct the xenon flow rate on orbit, it has fundamental defects such as flow resistance and unsatisfactory flow control. How to improve the xenon control capability of the flow controller is crucial to improving the level of space propellant distribution and control.

[0004] The Tesla valve structure has the excellent performance of achieving unidirectional conduction of fluid without any auxiliary structure (FK Forster, RL Bardell, M. Afromowitz, NR Sharma, A. Blanchard, Design, fabrication and testing of fixed-valve micro-pumps, Proceedings of the ASME Fluids Engineering Division 1995, 234: 39–44.). The Tesla valve structure is usually used in liquid fluids. The application of the Tesla valve structure in Hall thrusters has not been found in the prior art. Summary of the invention

[0005] In order to solve the problems of the prior art, the present invention provides a novel micro-flow control system with a Tesla-like valve structure for satellites. Based on the step-by-step throttling characteristics of the Tesla valve structure during reverse flow, it is used in the flow channel design of a microfluidic flow controller. In theory, nearly perfect xenon pressure and flow rate regulation can be achieved. The successful implementation of the present invention is of great strategic significance for improving the xenon management level of space Hall electric thrusters, enhancing the accuracy of micro-flow distribution and coordinated control, and enhancing their maneuverability.

[0006] The invention provides a novel micro-flow control system with Tesla-like valve structure for satellite, comprising a xenon gas path control system and a circuit control system, characterized in that: the xenon gas path control system comprises a novel micro-flow controller with Tesla-like valve structure for satellite connected between a xenon gas storage box and a Hall thruster, the xenon gas storage box is connected to the inlet of the novel micro-flow controller with Tesla-like valve structure for satellite through a filter and a stop valve in sequence, the outlet of the novel micro-flow controller with Tesla-like valve structure for satellite is respectively connected to the anode and cathode of the Hall thruster through two controllable stop valves, and low-pressure gas valves are respectively arranged in the anode and cathode of the Hall thruster; the novel micro-flow controller with Tesla-like valve structure for satellite comprises a sealed cavity with a xenon gas inlet and a xenon gas outlet, a plurality of flow channels connecting the xenon gas inlet and the xenon gas outlet are present in the sealed cavity, the flow channels adopt a plurality of Tesla valve wing-shaped structural unit arrays, the xenon gas inlet pressure is 0.1-0.3MPa, the xenon gas outlet pressure is 5-10 kPa, and the flow channel flow is 0.1-30mg / s; The circuit control system is respectively connected to the filter, the stop valve, the controllable stop valve, and the low-pressure gas valve. The low-pressure gas valve is arranged inside the anode and cathode of the Hall thruster. The flow at the inlet of the new micro-flow controller with Tesla valve structure for satellite is controlled by the filter and the stop valve. The high-pressure gas flow entering the cathode and anode of the Hall thruster is controlled by the controllable stop valve. The low-pressure gas flow entering the cathode and anode of the Hall thruster is controlled by the low-pressure gas valve.

[0007] As a further improvement, the number of Tesla valve wing-shaped structural unit arrays in the new micro-flow controller with Tesla valve-like structure for satellite is 3 to 10 groups.

[0008] As a further improvement, the Tesla valve wing-shaped structural unit array in the novel micro-flow controller with Tesla valve-like structure for satellite is a plurality of Tesla valve wing-shaped structures arranged in an array, and the array modes include single-sided array, double-sided array, single-sided and double-sided combination, and positive and negative combination array, the connection modes include divergent and convergent types, and the combination forms include single-column or multi-column combination.

[0009] As a further improvement, the Tesla valve wing-shaped structural unit array includes 1 to 10 Tesla valve wing-shaped structural units, and the Tesla valve wing-shaped structural units include an entrance and exit position, a wing front position, a wing rear position and a wingspan angle.

[0010] As a further improvement, the cross-sectional shape of the entrance and exit is rectangular, the width and depth of the entrance and exit are 0.2~2mm, and the width and depth of the wing front and wing rear are 0.2~2mm.

[0011] As a further improvement, the cross-section of the entrance and exit is circular, the diameter of the entrance and exit is 0.2~2mm, and the wingspan angle is 20~70°.

[0012] The present invention also provides a method for manufacturing and packaging a novel micro-flow control system with a Tesla-like valve structure for satellites, which is characterized by: adopting diffusion welding packaging technology and 3D printing technology to manufacture the novel micro-flow controller with a Tesla-like valve structure for satellites, and connecting the novel micro-flow controller with a Tesla-like valve structure for satellites between a xenon storage tank and a Hall thruster; the diffusion welding packaging technology specifically includes the following steps: a) Surface pretreatment: The micro flow controller mainly consists of two parts: the upper and lower substrates. The substrate material can be made of 304 stainless steel or TC4 titanium alloy and other metal materials. The upper and lower substrate samples are polished with 120#, 100#, 60#, 36#, and 24# metallographic sandpaper respectively, and then polished with a grinding and polishing machine to ensure that the surface roughness Ra is below 50nm; b) Tesla valve structure processing: micro-machining, micro-electrolysis, and laser etching processing methods are used to process a new type of micro-flow control system structure for satellites that imitates the Tesla valve structure on the lower substrate surface. The size error of the processed structure is controlled within 10%; c) Fixing hole processing: Use mechanical drilling method to process bolt holes on the upper and lower substrates. The specific number is determined according to the brazing effect and the overall structural size of the micro flow controller; d) Surface polishing: Use a grinding and polishing machine to polish the surface to ensure that the surface roughness is below Ra50nm; e) Surface coating preparation: magnetron sputtering technology or physical vapor deposition is used to deposit Ti thin films on the upper and lower substrate surfaces as the intermediate layer for subsequent diffusion welding. The film thickness is controlled at 3~10nm and the film roughness is less than 5nm; f) Diffusion welding packaging: Press the upper and lower substrates together and place them in a vacuum or protective atmosphere furnace for heating and pressurization. The surfaces to be welded will undergo microscopic plastic deformation and come into close contact, thus achieving micro flow controller packaging; g) Bolt connection reinforcement: For the packaged micro flow controller, the bolt holes processed in step c) are connected with fine thread bolts.

[0013] The present invention also provides a working method of a novel micro-flow control system with a Tesla-like valve structure for satellites, comprising the following steps: connecting the novel micro-flow control system with a Tesla-like valve structure for satellites between a xenon storage tank and a Hall thruster, allowing xenon gas output from the xenon storage tank to enter the novel micro-flow control system with a Tesla-like valve structure for satellites through a filter and a stop valve, the novel micro-flow control system with a Tesla-like valve structure for satellites regulating the pressure and flow of the xenon gas, and flowing into the anode and cathode of the Hall thruster through two controllable stop valves to realize xenon supply; during the working process, the filter, the stop valve, and the controllable stop valve are automatically controlled by the circuit control system.

[0014] The beneficial effects of the present invention are: utilizing the Tesla valve structure to achieve the excellent characteristic of one-way conduction of the fluid without any auxiliary structure, designing a new micro-flow control system for satellites with a Tesla valve-like structure to improve the regulation level of xenon pressure and flow of xenon (Xe), and better meet the use requirements of the Hall propulsion system of the entire satellite. In theory, nearly perfect precise regulation of xenon pressure and flow can be achieved. The smooth implementation of the present invention has important strategic significance for improving the xenon management level of space Hall electric thrusters, improving the accuracy of micro-flow distribution and coordinated control, and enhancing their maneuverability. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings required for use in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0016] Figure 1 It is the characteristic of Tesla valve wing-shaped structural unit; Figure 2 Design for the array, connection and combination of structural units; Figure 3 Manufacturing and packaging of a new type of micro flow controller imitating the Tesla valve structure; Figure 4 This is a schematic diagram of a new micro-flow control system that imitates the Tesla valve structure. DETAILED DESCRIPTION

[0017] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0018] The technical implementation plan of the new micro-flow controller with Tesla valve structure mainly includes: Tesla valve wing-shaped structural unit design, array, connection and combination design, manufacturing and packaging of the new micro-flow controller with Tesla valve structure, control method implementation and other core parts. The specific technical details are as follows: 1) Tesla valve wing structure unit design: Tesla valve wing structure unit Figure 1 As shown, its characteristic parameters include key positions such as entrance / exit, front / rear position of the wing, and wingspan angle. For structural units with a rectangular cross-sectional shape, the width and depth dimensions of the entrance / exit position are guaranteed to be 0.2~2mm, the width and depth dimensions of the front / rear position of the wing are guaranteed to be 0.2~2mm, and for structural units with a circular cross-sectional shape, the diameter dimensions of the above positions are guaranteed to be 0.2~2mm, and the wingspan angle is 20~70°.

[0019] 2) Tesla valve wing structure unit array, connection and combination design: Taking the xenon propellant parameters in the Hall electric thrusters in different types of small satellites as the target (specifically including: inlet pressure 0.1~0.3MPa, outlet pressure 5~10kPa, flow rate 0.1~30mg / s), based on the size of the Tesla valve wing structure unit obtained in step 1), the Tesla valve wing structure unit array, connection and combination method are designed, such as Figure 2 As shown, the number of wing-shaped structure units is controlled at 1 to 10, the wing-shaped structure array modes include single-side array, double-side array, single / double-side combination and forward and reverse combination array, the connection modes include divergent and convergent types, the combination forms include single-row or multi-row combination (3 to 10 groups), and the specific structural parameters are determined according to the actual needs of the use and control of xenon propellant in the Hall electric thruster in the small satellite.

[0020] 3) Micro flow controller manufacturing and packaging: There are two types of manufacturing and packaging: ① Processing the structure scheme obtained in step 2) on the surface of the metal substrate and packaging it using diffusion welding technology; ② Using 3D printing technology to print the Tesla valve wing structure combination scheme obtained in step 2) in one piece. Here, only the technical details of the first type of manufacturing and packaging are elaborated in detail, as follows: a) Surface pretreatment: The micro flow controller mainly consists of two parts: the upper and lower substrates. The substrate material can be made of metal materials such as 304 stainless steel or TC4 titanium alloy. Since the surface roughness of the substrate has a great influence on the final packaging effect, the upper and lower substrate samples are polished with 120#, 100#, 60#, 36#, and 24# metallographic sandpaper respectively, and then polished with a grinding / polishing machine to ensure that the surface roughness Ra is below 50nm; b) Tesla valve structure processing: using micromachining, micro electrolysis, laser etching and other processing methods, such as Figure 3 As shown, the specific structure obtained in step 2) is processed on the lower substrate surface, and the size error of the processed structure is controlled within 10%; c) Fixing hole processing: Use mechanical drilling method to drill holes on the upper and lower substrates Figure 3 Bolt holes (maximum M4 bolts) are machined at the positions shown. The specific number is determined according to the brazing effect and the overall structural size of the micro-flow controller (the maximum size of the controller is determined according to the Hall electric thrusters used in the specific model of satellites, and the number is 8 to 20); d) Surface polishing: Since steps b) and c) will produce machining burrs on the surface, a grinding / polishing machine is further used to polish the surface to ensure that the surface roughness is below Ra50nm; e) Surface coating preparation: magnetron sputtering technology (physical vapor deposition) is used to deposit Ti thin films on the upper and lower substrate surfaces as intermediate layers for subsequent diffusion welding. The film thickness is controlled at 3-10 nm and the film roughness is less than 5 nm to improve the diffusion welding effect; f) Diffusion welding packaging: Press the upper and lower substrates together and place them in a vacuum or protective atmosphere furnace for heating and pressurization. The surfaces to be welded will undergo microscopic plastic deformation and come into close contact, thus achieving micro flow controller packaging; g) Bolt connection reinforcement: Considering the instability of the packaging interface caused by extreme working conditions such as impact during satellite launch and space service, the bolt holes processed in step c) of the packaged micro flow controller are connected with fine thread bolts to ensure the stability of the controller.

[0021] At this point, the micro flow controller is manufactured and packaged, and its structure is shown in the figure below. Figure 3 shown.

[0022] 4) Control method implementation: Figure 4 The diagram shows a new type of micro-flow control system with a Tesla-like valve structure. It mainly includes two parts: a xenon gas path control system and a circuit control system. The working principle is as follows: the xenon gas in the xenon storage tank flows into the new type of micro-flow controller with a Tesla-like valve structure through a filter and a stop valve. The pressure and flow are regulated by the Tesla-like valve structure, and then flows into the anode and cathode of the Hall thruster through the controllable stop valve A / B to realize the xenon supply. As for the control circuit part, the satellite solar panels mainly provide power for the main components. The control system automatically controls the filter, stop valve, controllable stop valve A / B, the anode and cathode of the Hall thruster, and the low-pressure gas valve according to the instructions. The functions of the main components are as follows: Filter: used to filter micro-nano particles in storage tanks and pipelines; Stop valve: cuts off the propeller (xenon) supply in special circumstances; Controllable stop valve A / B: controls the propellant (xenon) supply to the Hall anode and cathode; Solar panels: provide power for the system; Control system: perform corresponding operations according to instructions; Low-pressure gas valve: It serves as the second gas valve after the controllable stop valve A / B to control the propellant (xenon) supply to the Hall anode and cathode; Hall thruster: The final execution unit that completes the propulsion function based on the Hall effect.

[0023] Each embodiment in this specification is described in a progressive manner, and the same or similar parts between the embodiments can be referred to each other, and each embodiment focuses on the differences from other embodiments. In particular, for the device embodiment, the above is only a preferred embodiment of the present invention. Since it is basically similar to the method embodiment, the description is relatively simple, and the relevant parts can be referred to the partial description of the method embodiment. The above is only a specific embodiment of the present invention, but the protection scope of the present invention is not limited to this. Any technician familiar with the technical field is within the technical scope disclosed by the present invention. For ordinary technicians in the technical field, changes or replacements that can be easily thought of should be covered within the protection scope of the present invention without departing from the principle of the present invention. Therefore, the protection scope of the present invention should be based on the protection scope of the claims.

Claims

1. A new type of micro-flow control system with Tesla-like valve structure for satellite, including a xenon gas path control system and a circuit control system, characterized in that: The xenon gas path control system includes a satellite-use Tesla-like valve structure novel micro-flow controller connected between a xenon gas storage tank and a Hall thruster, the xenon gas storage tank is connected to the inlet of the satellite-use Tesla-like valve structure novel micro-flow controller through a filter and a stop valve in sequence, the outlet of the satellite-use Tesla-like valve structure novel micro-flow controller is connected to the anode and cathode of the Hall thruster respectively through two controllable stop valves, and the anode and cathode of the Hall thruster are respectively provided with low-pressure gas valves; the satellite-use Tesla-like valve structure novel micro-flow controller includes a sealed cavity with a xenon gas inlet and a xenon gas outlet, and there are a plurality of flow channels connecting the xenon gas inlet and the xenon gas outlet in the sealed cavity, the flow channels adopt a plurality of Tesla valve wing-shaped structural unit arrays, the xenon gas inlet pressure is 0.1-0.3 MPa, the xenon gas outlet pressure is 5-10 kPa, and the flow channel flow is 0.1-30 mg / s; The circuit control system is respectively connected to the filter, the stop valve, the controllable stop valve, and the low-pressure gas valve. The low-pressure gas valve is arranged inside the anode and cathode of the Hall thruster. The flow at the inlet of the new micro-flow controller with Tesla valve structure for satellite is controlled by the filter and the stop valve. The high-pressure gas flow entering the cathode and anode of the Hall thruster is controlled by the controllable stop valve. The low-pressure gas flow entering the cathode and anode of the Hall thruster is controlled by the low-pressure gas valve.

2. The novel micro-flow control system of the Tesla-like valve structure for satellite according to claim 1 is characterized in that: The number of Tesla valve wing-shaped structural unit arrays in the novel micro-flow controller imitating Tesla valve structure for satellite is 3 to 10 groups.

3. The novel micro-flow control system of the Tesla-like valve structure for satellite according to claim 1 is characterized in that: The Tesla valve wing-shaped structural unit array in the novel micro-flow controller with Tesla valve-like structure for satellite is a plurality of Tesla valve wing-shaped structures arranged in an array. The array modes include single-side array, double-side array, single-side and double-side combination, and positive and negative combination array. The connection modes include divergent and convergent types. The combination forms include single-column or multi-column combination.

4. The novel micro-flow control system of the Tesla-like valve structure for satellite according to claim 3 is characterized by: The Tesla valve wing-shaped structural unit array includes 1 to 10 Tesla valve wing-shaped structural units, and the Tesla valve wing-shaped structural unit includes an entrance and exit position, a wing front position, a wing rear position and a wingspan angle.

5. The novel micro-flow control system of the Tesla-like valve structure for satellites according to claim 4 is characterized by: The cross-sectional shape of the entrance and exit is rectangular, the width and depth of the entrance and exit are 0.2-2 mm, and the width and depth of the wing front and wing rear are 0.2-2 mm.

6. The novel micro-flow control system of the Tesla-like valve structure for satellite according to claim 4 is characterized by: The cross-sectional shape of the entrance and exit is circular, the diameter of the entrance and exit is 0.2~2 mm, and the wingspan angle is 20~70°.

7. A method for manufacturing and packaging a novel micro-flow control system of a satellite with a Tesla-like valve structure as claimed in any one of claims 1 to 6, characterized in that: A new type of micro flow controller with Tesla-like valve structure for satellite is manufactured by diffusion welding packaging and 3D printing technology, and the new type of micro flow controller with Tesla-like valve structure for satellite is connected between the xenon storage tank and the Hall thruster; the diffusion welding packaging specifically includes the following steps: a) Surface pretreatment: The micro flow controller mainly consists of two parts, the upper and lower substrates. The substrate material is made of metal. The upper and lower substrate samples are polished with 120#, 100#, 60#, 36#, and 24# metallographic sandpaper respectively, and then polished with a grinding and polishing machine to ensure that the surface roughness Ra is below 50 nm; b) Tesla valve structure processing: micro-machining, micro-electrolysis, and laser etching processing methods are used to process a new type of micro-flow control system structure for satellites that imitates the Tesla valve structure on the lower substrate surface. The size error of the processed structure is controlled within 10%; c) Fixing hole processing: Use mechanical drilling method to process bolt holes on the upper and lower substrates. The specific number is determined according to the brazing effect and the overall structural size of the micro flow controller; d) Surface polishing: Use a grinding and polishing machine to polish the surface to ensure that the surface roughness is below Ra 50 nm; e) Surface coating preparation: magnetron sputtering technology or physical vapor deposition is used to deposit Ti thin films on the upper and lower substrate surfaces as the intermediate layer for subsequent diffusion welding. The film thickness is controlled at 3~10 nm and the film roughness is less than 5nm; f) Diffusion welding packaging: Press the upper and lower substrates together and place them in a vacuum or protective atmosphere furnace for heating and pressurization. The surfaces to be welded will undergo microscopic plastic deformation and come into close contact, thus achieving micro flow controller packaging; g) Bolt connection reinforcement: For the packaged micro flow controller, the bolt holes processed in step c) are connected with fine thread bolts.

8. A method for operating the novel micro-flow control system of the Tesla-like valve structure for satellites as claimed in any one of claims 1 to 6, characterized in that The following steps are involved: A new micro-flow control system with a Tesla-like valve structure for satellite is connected between a xenon storage tank and a Hall thruster. The xenon gas output from the xenon storage tank enters the new micro-flow control system with a Tesla-like valve structure for satellite through a filter and a stop valve. The new micro-flow control system with a Tesla-like valve structure for satellite regulates the pressure and flow of the xenon gas, and flows into the anode and cathode of the Hall thruster through two controllable stop valves to realize the xenon supply. During the working process, the filter, the stop valve, the controllable stop valve and the low-pressure gas valve are automatically controlled by the circuit control system.

Images