阅读说明：本技术 一种能够产生可控力矩的霍尔推力器 (Hall thruster capable of generating controllable torque ) 是由 苏宏博 林滢 魏鑫 王奕臣 温正 崔宁 王珏 刘杰 张旭 于 2021-06-30 设计创作，主要内容包括：本发明涉及一种能够产生可控力矩的霍尔推力器,属于霍尔电推进技术领域。本发明将传统单一的环型气体分配器进行分段设计,将气体分配器的内部缓冲腔利用缓冲腔隔板分割为若干段,采用主体结构为分瓣式结构,使得气体分配器的气密性更好,每一段分配器都分别由一条管路供气,通过控制每条管路供气的气体流量,从而达到通道各区域内氙工质密度不同的目的,本发明的分段设计采用阳极-多段气体分配器一体化的设计思路,将分段结构作为一个整体施加阳极电压,保证阳极放电电压的一致,使得电压不会做为变量影响放电。(The invention relates to a Hall thruster capable of generating controllable torque, and belongs to the technical field of Hall electric propulsion. The invention carries on the sectional design to the traditional single ring-shaped gas distributor, the internal buffer cavity of the gas distributor is divided into several sections by the baffle of the buffer cavity, the main structure is the split structure, the gas tightness of the gas distributor is better, each section of distributor is supplied with gas by a pipeline, the gas flow of each pipeline is controlled, thus the purpose of different xenon working medium density in each area of the channel is achieved.)

1. The utility model provides a hall thruster that can produce controllable moment which characterized in that: the gas distributor of the Hall thruster comprises a gas supply pipe, a buffer cavity partition plate and a main body structure;

the number of the buffer cavity partition plates is n, and n is not less than 3;

the main structure comprises an inner ring cylinder, an outer ring cylinder, an upper layer clapboard and a lower layer clapboard, wherein the outer ring cylinder is sleeved outside the inner ring cylinder, the upper layer clapboard and the lower layer clapboard are arranged between the inner ring cylinder and the outer ring cylinder, and the inner ring cylinder, the outer ring cylinder, the upper layer clapboard and the lower layer clapboard surround an annular cavity as a buffer cavity;

a plurality of air outlets are uniformly distributed on the upper layer clapboard;

the buffer cavity partition plates are uniformly distributed in the buffer cavity to uniformly divide the buffer cavity into n +1 small cavities, and the gas between every two adjacent small cavities is not communicated;

the air supply pipe is n +1, and air supply pipe fixed connection can be with gaseous input to the cushion chamber in through the air supply pipe on the baffle of lower floor.

2. The Hall thruster capable of generating controllable torque according to claim 1, wherein:

each air supply pipe is positioned in the center of the small chamber, and sixteen air outlets are uniformly distributed on the upper-layer partition plate.

3. The Hall thruster capable of generating controllable torque according to claim 1, wherein:

the material of the buffer chamber partition is the same as the material of the gas distributor.

4. The Hall thruster capable of generating controllable torque according to claim 3, wherein:

the buffer cavity partition plate is made of nonmagnetic stainless steel.

5. The Hall thruster capable of generating controllable torque according to claim 1, wherein:

each air supply pipe is independently controlled in flow by one thermal throttle valve, and when the Hall thruster is required to provide torque in the pitch or roll axis direction, the air supply of the corresponding subsection area is changed by controlling the valves, so that the air density of the area is improved, local ionization is increased, uneven thrust is generated in the circumferential direction, and torque with controllable size and position is achieved.

6. The Hall thruster capable of generating controllable torque according to claim 5, wherein: when the amount of air supplied to a certain area is increased, the amount of ventilation needs to be decreased in the remaining areas.

7. The utility model provides a hall thruster that can produce controllable moment which characterized in that: the gas distributor of the Hall thruster comprises a gas supply pipe and a main body structure;

the main structure is a split structure and is divided into m lobes, and the main structure forms an annular structure by the m lobes;

each valve of the main body structure comprises an inner ring cylinder, an outer ring cylinder, an upper layer clapboard, a lower layer clapboard, a left buffer cavity clapboard and a right buffer cavity clapboard, wherein the outer ring cylinder is sleeved outside the inner ring cylinder, the upper layer clapboard and the lower layer clapboard are arranged between the inner ring cylinder and the outer ring cylinder, and the left buffer cavity clapboard and the right buffer cavity clapboard are used for sealing after being arranged;

a plurality of air outlets 4 are uniformly distributed on the upper layer clapboard;

the gas between each valve divided by the main body structure is not communicated;

the air supply pipe is m, and air supply pipe fixed connection can be with gaseous input to fan-shaped buffering intracavity on the lower floor's baffle through the air supply pipe, and every air supply pipe all is located the central point of every lamella that the major structure at place divide into and puts.

8. The Hall thruster of claim 7, wherein:

each air supply pipe is positioned in the center of the small chamber, and sixteen air outlets are uniformly distributed on the upper-layer partition plate.

9. The Hall thruster of claim 7, wherein:

the material of the buffer cavity partition plate is the same as that of the gas distributor, and the material of the buffer cavity partition plate is nonmagnetic stainless steel.

10. The Hall thruster of claim 7, wherein:

each air supply pipe is independently controlled in flow by one thermal throttle valve, when a Hall thruster is required to provide moment in the pitch or roll axis direction, the air supply of a corresponding subsection area is changed by controlling the valves, the air density of the area is improved, local ionization is increased, uneven thrust is generated in the circumferential direction, moment with controllable size and position is further realized, and when the air supply quantity of a certain area is improved, the ventilation quantity of other areas is required to be reduced.

Technical Field

The invention relates to a Hall thruster capable of generating controllable torque, and belongs to the technical field of Hall electric propulsion.

Background

Compared with the traditional chemical propulsion, the electric propulsion technology is more and more widely applied to the flying tasks of spacecraft, such as north-south position maintenance, orbit transfer, deep space exploration and the like by virtue of the characteristics of high specific impulse, long service life, light weight and the like. The Hall electric propulsion technology is the most mature and widely applied, and most foreign in-orbit electric propulsion spacecrafts adopt Hall thrusters for position maintenance, such as typical SPT-100 Hall thrusters, and the number of in-orbit electric propulsion spacecrafts is close to 500 at present.

The basic working principle of the Hall thruster is as follows: after entering the thruster channel, electrons emitted from the cathode are influenced by an orthogonal electromagnetic field to carry out circumferential Hall drift, meanwhile, xenon working medium discharged from the anode region collides and ionizes with the circumferentially drifting electrons, and then xenon ions are accelerated and emitted under the action of an electric field formed by plasma self-consistency, so that axial thrust is formed.

Generally, the Hall thruster adopts a single gas supply pipe for supplying gas, and xenon working medium is homogenized by an integral gas distributor and then discharged into an annular channel to participate in ionization. Because of this, the initial xenon atoms in the annular channel are uniformly distributed, and therefore the ionized accelerated xenon ions are also uniformly emitted, which is macroscopically reflected as the total axial thrust generated passing through the center of the exit section of the thruster. On the other hand, a slight uncontrollable moment is caused by a thrust deflection due to a machining error and an electron circumferential drift. However, the uncontrollable moment generated by a single well-designed hall thruster is very small and is usually ignored. Therefore, it is generally considered that a single hall thruster does not generate a significant moment, so that the conventional hall thruster can only provide directional thrust, and if attitude control of an aircraft is to be provided, a layout of multiple thrusters must be adopted, so that the design increases the power load and weight of the whole satellite, and has a great influence on the reliability of the whole satellite. Therefore, in order to further expand the service range of the Hall thruster, so that the Hall thruster can not only provide directional thrust, but also provide obvious and controllable torque, and further a single Hall thruster can control the attitude of an aircraft, the invention provides a Hall thruster design capable of generating controllable torque.

Disclosure of Invention

The technical problem to be solved by the invention is as follows: the Hall thruster overcomes the defects of the prior art and can generate controllable torque.

The technical solution of the invention is as follows:

a Hall thruster capable of generating controllable torque comprises a gas supply pipe, a buffer cavity partition plate and a main body structure;

the gas supply pipe also serves as an anode electrode;

the number of the buffer cavity partition plates is n, and n is not less than 3;

the main structure comprises an inner ring cylinder, an outer ring cylinder, an upper layer clapboard and a lower layer clapboard, wherein the outer ring cylinder is sleeved outside the inner ring cylinder, the upper layer clapboard and the lower layer clapboard are arranged between the inner ring cylinder and the outer ring cylinder, and the inner ring cylinder, the outer ring cylinder, the upper layer clapboard and the lower layer clapboard surround an annular cavity as a buffer cavity;

a plurality of air outlets are uniformly distributed on the upper-layer clapboard, and the number of the air outlets is dozens;

the buffer cavity partition plates are uniformly distributed in the buffer cavity to uniformly divide the buffer cavity into n +1 small cavities, and the gas between every two adjacent small cavities is not communicated;

the number of the gas supply pipes is n +1, the gas supply pipes are fixedly connected to the lower-layer partition plate, gas can be input into the buffer cavity through the gas supply pipes, and each gas supply pipe is located in the center of the small cavity;

a Hall thruster capable of generating controllable torque comprises a gas supply pipe and a main body structure, wherein the gas supply pipe is connected with the main body structure;

the gas supply pipe also serves as an anode electrode;

the main structure is a split structure and is divided into m lobes, and the main structure forms an annular structure by the m lobes;

each valve of the main body structure comprises an inner ring cylinder, an outer ring cylinder, an upper layer clapboard, a lower layer clapboard, a left buffer cavity clapboard and a right buffer cavity clapboard, wherein the outer ring cylinder is sleeved outside the inner ring cylinder, the upper layer clapboard and the lower layer clapboard are arranged between the inner ring cylinder and the outer ring cylinder, and the left buffer cavity clapboard and the right buffer cavity clapboard are used for sealing after being arranged;

a plurality of air outlets are uniformly distributed on the upper layer of partition plate, and the number of the air outlets is generally dozens, for example 16;

the gas between each valve divided by the main body structure is not communicated;

the air supply pipe is m, and air supply pipe fixed connection can be with gaseous input to fan-shaped buffering intracavity on the lower floor's baffle through the air supply pipe, and every air supply pipe all is located the central point of every lamella that the major structure at place divide into and puts.

Considering the problem of thermal expansion of the buffer chamber partition plate, the material of the buffer chamber partition plate is the same as that of the gas distributor, and the buffer chamber partition plate is usually non-magnetic stainless steel;

the working process of the Hall thruster comprises the following steps: the generation of the thrust is positively correlated with the xenon atom density, and as a result, each gas supply pipe is independently controlled by one thermal throttle valve to control the flow, and when the Hall thruster is required to provide the moment in the pitch or rolling axis direction, the gas supply of the corresponding segment area is changed by the control valve, so that the gas density of the area is improved, the local ionization is increased, the uneven thrust is generated in the circumferential direction, and the moment with controllable size and position is further realized. In order to ensure that the Hall drift of electrons in the discharge channel is not influenced by the segmented uneven gas supply, when the gas supply quantity of a certain area is increased, the rest areas also need to be ventilated a little, but only the most basic ionization and electron conduction are ensured.

Advantageous effects

(1) The traditional single annular gas distributor is designed in a segmented manner, and an internal buffer cavity of the gas distributor is divided into a plurality of segments by buffer cavity clapboards;

(2) the main body structure 3 is a split structure, so that the air tightness of the air distributor is better;

(3) in the invention, each section of distributor is respectively supplied with gas by one pipeline, and the purpose of different xenon working medium densities in each area of a channel is achieved by controlling the gas flow supplied by each pipeline;

(4) the segmented design of the invention adopts the design idea of integrating the anode and the multi-segment gas distributor, and applies anode voltage to the segmented structure as a whole, thereby ensuring the consistency of anode discharge voltage and preventing the voltage from being used as a variable to influence discharge;

(5) the invention covers Hall thrusters with various power levels, particularly, when the designed power of the thruster is higher, the geometric dimension of the thruster is larger, the diameter of the gas distributor is larger, the generated moment is more obvious, and when the thruster is required to provide pitching or rolling moment, an obvious and independently controllable moment can be generated through non-uniform gas supply of a plurality of gas supply pipelines, so that the application range of the Hall electric propulsion technology is further expanded.

Drawings

FIG. 1 shows the configuration and gas flow law of a gas distributor of a conventional Hall thruster;

FIG. 2 is a sectional gas distributor configuration and gas flow pattern according to the present invention;

FIG. 3 is a schematic view of another sectional gas distributor configuration and gas flow pattern according to the present invention;

figure 4 shows the characteristics of two thrusters generating thrust.

Detailed Description

The invention is further illustrated by the following figures and examples.

In general, a conventional well-designed single hall thruster can only generate negligible and uncontrollable torque. In order to further improve the function of a single Hall thruster, the invention provides a design scheme of a sectional air supply mode, so that the single Hall thruster can generate obvious and controllable torque, and the task range of the Hall electric propulsion technology is further expanded.

(1) According to the neutral gas dynamics, the working medium utilization rate can be expressed by the length of an ionization region and an average collision ionization free path:

wherein L is_ionIs the ionization region length, λ_iFor the average collision ionization free path, the average free path is in inverse proportion to the initial neutral atom density, and when the initial atom density is increased, the utilization rate of the working medium is increased, so that the ion density in the region is increased, more ions are accelerated under the same acceleration voltage, and the generated thrust is increased finally.

By adjusting the density of the neutral gas in different areas of the discharge channel, a controllable torque is generated.

(2) The invention firstly redesigns the traditional gas supply device, and the traditional single ring-shaped gas distributor (figure 1) enters the distributor through a single gas supply pipe, is uniformly discharged after being homogenized, thereby forming uniform neutral gas in the circumferential direction and finally generating uniform thrust. Therefore, in order to generate uneven thrust, the distributor is designed in a segmented mode, and the internal buffer cavity of the gas distributor is divided into a plurality of buffer cavities by buffer cavity partition plates, as shown in fig. 2.

(3) Considering the problem of thermal expansion of the buffer chamber partition plate, the material of the buffer chamber partition plate is the same as that of the gas distributor, and the distributor is usually welded by nonmagnetic stainless steel, so the buffer chamber partition plate is also made of nonmagnetic stainless steel.

(4) In addition, the segmented design can also be welded by a plurality of split gas distributors in consideration of the thermal expansion of the baffle of the buffer chamber and the complexity and air tightness of the welding, as shown in fig. 3.

(5) No matter which type of subsection design is adopted, each distributor section is supplied with gas by one pipeline respectively, and n gas supply pipes are counted, so that the aim of different densities of xenon working media in all areas of the channel is fulfilled.

(6) As shown in fig. 1, the conventional distributor is fixed to a base plate by a plurality of fixing rods and an air supply pipe in a screw manner. Similar to the traditional fixing mode, the root of each gas supply pipe is required to be threaded, so that the whole gas distributor is fixed on the bottom plate of the thruster through the threaded connection of each gas supply pipe.

(7) The conventional hall thruster, such as SPT series, adopts an anode-gas distributor integrated design, i.e. the gas distributor directly applies anode voltage as anode to realize the function of receiving electrons. The segmented design of the invention still adopts the design idea of integrating the anode and the multi-segment gas distributors, and applies anode voltage to the segmented structure as a whole, thereby ensuring the consistency of anode discharge voltage, avoiding causing different anode voltage of each segment of distributor and further avoiding influencing discharge by taking the voltage as a variable.

(8) As analyzed in embodiment (1), the thrust generation is positively correlated with the xenon atom density. Therefore, each air supply pipe is individually controlled in flow by a flow meter or a thermal throttle valve, so that a difference in thrust is generated in the circumferential direction, as shown in fig. 4. When the Hall thruster is required to provide torque in the pitch or rolling axis direction, the gas supply of the corresponding segment area is changed by controlling the valve, and the gas density of the area is improved, so that local ionization is increased, uneven thrust is generated in the circumferential direction, and torque with controllable size and position is realized. Naturally, in order to control the over-tolerance of the total power of the thruster, the flow supply of the rest areas is required to be correspondingly reduced, in addition, in order to ensure that the Hall drift of electrons in the discharge channel is not influenced by the sectional uneven gas supply, when the gas supply amount of a certain area is increased, the rest areas are required to be not stopped, but a small amount of gas supply is required, but only the most basic ionization and electron conduction are required to be ensured, so the value is the theoretical maximum value.

In addition, reducing the flow in each pipe also improves the stability and reliability of the piping and valves.

(9) The invention covers Hall thrusters with various power levels, and particularly, when the design power of the thrusters is higher, the geometrical size of the thrusters is larger, the diameter of the gas distributor is larger, and the generated moment is more remarkable.

Example 1

A Hall thruster capable of generating controllable torque comprises a gas supply pipe 1, a buffer cavity partition plate 2 and a main body structure 3;

the gas supply pipe 1 also serves as an anode electrode;

three buffer cavity partition plates 2 are arranged;

the main structure 3 comprises an inner ring cylinder, an outer ring cylinder, an upper layer clapboard and a lower layer clapboard, wherein the outer ring cylinder is sleeved outside the inner ring cylinder, the upper layer clapboard and the lower layer clapboard are arranged between the inner ring cylinder and the outer ring cylinder, and the inner ring cylinder, the outer ring cylinder, the upper layer clapboard and the lower layer clapboard surround to form an annular cavity as a buffer cavity 3;

forty air outlets 4 are uniformly distributed on the upper layer of the clapboard;

the buffer cavity partition plates 2 are uniformly distributed in the buffer cavity 3 and are used for uniformly dividing the buffer cavity 3 into four small cavities, and the gas between every two adjacent small cavities is not communicated;

the gas supply pipe 1 is four, and gas supply pipe 1 fixed connection can be with gaseous input 3 in the cushion chamber through gas supply pipe 1 on the lower floor's baffle, and every gas supply pipe 1 all is located the central point of the little cavity at place and puts.

Taking SPT-100 as an example, the rated power is 1.35kW, the rated flow is 5.5mg/s, and the rated thrust is 82 mN. Any of these may be exemplified by: when 4mg/s of flow is supplied to one of the air supply pipes, 0.5mg/s of flow is supplied to the other three air supply pipes in order to ensure that the total rated power and the flow are constant, and the flow and the thrust are in a fixed proportional relation, the buffer cavity on the side of supplying 4mg/s can generate 60mN of thrust, and the other three buffer cavities respectively generate 7mN of thrust, so that a significant thrust deviation can be generated, and the deviation can be controlled through the flow. For the value of the generated moment, data of the specific type of satellite mass center and Hall thruster layout can be determined, so that the value of the whole satellite moment cannot be given, and only the difference of the generated force is provided.

Example 2

A Hall thruster capable of generating controllable torque comprises a gas supply pipe 1 and a main body structure 3;

the gas supply pipe 1 also serves as an anode electrode;

the main structure 3 is a split structure, the main structure 3 is divided into four lobes, and the main structure 3 forms an annular structure by the four lobes;

each valve divided by the main structure 3 comprises an inner ring cylinder, an outer ring cylinder, an upper layer clapboard, a lower layer clapboard, a left buffer cavity clapboard and a right buffer cavity clapboard, the outer ring cylinder is sleeved outside the inner ring cylinder, the upper layer clapboard and the lower layer clapboard are arranged between the inner ring cylinder and the outer ring cylinder, the left buffer cavity clapboard and the right buffer cavity clapboard are used for sealing after being arranged, the inner ring cylinder, the outer ring cylinder, the upper layer clapboard, the lower layer clapboard, the left buffer cavity clapboard and the right buffer cavity clapboard enclose a fan-shaped cavity as a fan-shaped buffer cavity, the main structure 3 totally forms four fan-shaped buffer cavities, and the four fan-shaped buffer cavities form an annular buffer cavity;

ten air outlets 4 are uniformly distributed on the upper layer clapboard;

the gas among each valve divided by the main body structure 3 is not communicated;

the gas supply pipe 1 is four, and gas supply pipe 1 fixed connection can be with gaseous input to fan-shaped buffering intracavity on the lower floor's baffle through gas supply pipe 1, and every gas supply pipe 1 all is located the central point of every lamella that the major structure 3 at place divide into and puts.

Taking SPT-100 as an example, the rated power is 1.35kW, the rated flow is 5.5mg/s, and the rated thrust is 82 mN. Any of these may be exemplified by: when 4mg/s of flow is supplied to one of the air supply pipes, 0.5mg/s of flow is supplied to the other three air supply pipes in order to ensure that the total rated power and the flow are constant, and the flow and the thrust are in a fixed proportional relation, the buffer cavity on the side of supplying 4mg/s can generate 60mN of thrust, and the other three buffer cavities respectively generate 7mN of thrust, so that a significant thrust deviation can be generated, and the deviation can be controlled through the flow. For the value of the generated moment, data of the specific type of satellite mass center and Hall thruster layout can be determined, so that the value of the whole satellite moment cannot be given, and only the difference of the generated force is provided.