阅读说明：本技术 一种阵列式同轴型真空电弧推力器装置 (Array coaxial type vacuum arc thruster device ) 是由 王红霞 于新爱 沈震宇 于 2020-06-24 设计创作，主要内容包括：本发明涉及一种阵列式同轴型真空电弧推力器装置,属于微纳卫星电推进技术领域。所述装置中的推力器头数量处于3到50个之间；且有多种排列方式,这些排列方式统称为阵列式,如圆形排列、矩形排列以及三角形排列方式。同轴型推力器头由圆柱状的阳极,绝缘器和阴极沿径向依次向外排列组成,阴极在外的结构增加了有效工质,提高了推力器的总冲；阴极采用了弹簧推进装置,当阴极端面的金属材料被烧蚀后,弹簧会推动阴极向远端面方向移动,直至工质烧蚀完；这种阵列式同轴型真空电弧推力器装置可以通过CPU控制点火时序,可根据要求产生不同的推力；多数量的推力器头之间配合工作不仅使电推力器增加了寿命还使其获得了较高的总冲。(The invention relates to an array type coaxial vacuum arc thruster device, and belongs to the technical field of electric propulsion of micro-nano satellites. The number of thruster heads in the device is between 3 and 50; there are various arrangements, which are collectively called an array, such as a circular arrangement, a rectangular arrangement, and a triangular arrangement. The coaxial thruster head is formed by sequentially arranging a cylindrical anode, an insulator and a cathode outwards along the radial direction, and the structure with the cathode outside increases effective working media, so that the total impact of the thruster is improved; the cathode adopts a spring propelling device, and after the metal material on the end surface of the cathode is ablated, the spring can push the cathode to move towards the direction of the far end surface until the working medium is ablated; the array type coaxial vacuum arc thruster device can control the ignition time sequence through the CPU and can generate different thrusts according to requirements; the cooperation between a plurality of thruster heads not only prolongs the service life of the electric thruster but also obtains higher total impact.)

1. The utility model provides an array coaxial type vacuum arc thrustor device which characterized in that: the device is positioned in a micro-nano satellite and comprises a plurality of thruster heads;

each thruster head is of a coaxial type and comprises an anode, a cathode, an insulator, a shell and a spring, and the arrangement mode of the thruster heads is one of circular arrangement, rectangular arrangement, triangular arrangement, trapezoidal arrangement and polygonal arrangement;

the array type coaxial vacuum arc thruster device is controlled by an array type control circuit;

wherein the electromechanical transmission is one of an electromechanical motor, a piezoelectric motor, and a rotary motor;

the array control circuit comprises a power supply conversion module, an energy storage and discharge module, a pulse control module, a switch driving module, a thruster module and a power supply module;

in each thruster head, the anode is cylindrical, and the insulator and the cathode are sequentially arranged outwards along the radial direction; the insulator is coaxial with the spring and has the same radius;

the anode is connected with the insulator, and the insulator is connected with the cathode; the cathode is connected with the shell; the insulator is connected with the spring;

the structure of the cathode outside can lead the cathode material to be ablated uniformly.

2. The array type coaxial vacuum arc thruster device of claim 1, wherein: the thruster head is a coaxial arc thruster head.

3. The array type coaxial vacuum arc thruster device of claim 1, wherein: the number of thruster heads ranges from 3 to 50.

4. The array type coaxial vacuum arc thruster device of claim 1, wherein: the pusher head may also be of the stack type or the ring type.

5. The array type coaxial vacuum arc thruster device of claim 1, wherein: the pulse control module comprises a power supply processing unit PPU and a CPU;

the power supply processing unit PPU comprises an inductor charged by a semiconductor switch, the working frequency and the pulse width of the on-off of the semiconductor switch are controlled by a pulse signal generator, and the working process is as follows:

when the semiconductor switch is closed, the power supply voltage is directly applied to the inductor for pre-charging;

when the semiconductor switch is turned off, an induced voltage peak pulse LdI/dt generated by Lenz's law induces an initial arcing of the plasma.

6. The array type coaxial vacuum arc thruster device of claim 1, wherein: the array control circuit adopts an inductance energy storage IES flyback topological structure to generate pulse voltage to excite plasma initial arc discharge.

7. The array type coaxial vacuum arc thruster device of claim 1, wherein: the current loop of the array control circuit is converted to a thruster head branch from a semiconductor switch branch, a conductive film is plated on the surface of an insulator between an anode and a cathode, pulse voltage is concentrated to two ends of a contact point of the conductive film and the cathode, high voltage electricity generated at a tiny gap induces current breakdown discharge, metal of the cathode is evaporated due to heat generated by a current heating effect, metal atom vapor diffused in a vacuum area is ionized into micro plasma, a low-impedance channel between two electrodes is formed, current is rapidly switched to a low-impedance plasma discharge path from the surface discharge of an initial electrode with high impedance, and finally most of magnetic field energy stored in an inductor is released to generate plasma pulse thrust.

8. The array type coaxial vacuum arc thruster device of claim 1, wherein: the connection and information transmission relationship of each part in the array control circuit is as follows:

the power supply module transmits voltage and current to the power supply conversion module; the power supply conversion module transmits the current and the voltage to the energy storage discharge module, the pulse control module and the switch driving module; after receiving the current and the voltage, the pulse discharge module transmits the discharged electric power to the thruster module and feeds back the instantaneous current of the controllable switch to the pulse control module; the pulse control module transmits the rectangular signal to the switch driving module; the switch control module controls the pulse discharge module through a rectangular pulse signal; the pulse control module is connected with the CAN bus interface, and a CPU in the pulse control module controls the frequency and the discharge frequency of the rectangular wave and the working state of the thruster head.

9. The array type coaxial vacuum arc thruster device of claim 1, wherein: the pulse control module controls the ignition time sequence; the CPU controls the thruster module based on the ignition time sequence so as to generate different thrusts; the array type coaxial vacuum arc thruster device provided with the micro-nano satellite is controlled by a switch driving module of an array type control circuit to start and close different numbers of thruster heads to complete the flight tasks of orbit lifting and position keeping; the micro-nano satellites of a plurality of thruster heads can improve the task completion rate and reduce the loss caused by faults; when the micro-nano satellite executes a task, a certain thruster head is failed and does not catch fire or abnormally extinguishes fire under the condition of ignition, and other thruster heads are started to continue to finish the task at the moment.

10. The array type coaxial vacuum arc thruster device of claim 1, wherein: the spring is a cathodic propulsion device including, but not limited to, a spring, an elastic propulsion device, an elastic mechanism, or an electromechanical transmission.

Technical Field

The invention relates to an array type coaxial vacuum arc thruster device, and belongs to the technical field of electric propulsion of microsatellites.

Background

The power source of the micro-nano satellite is mainly various propulsion systems such as cold air propulsion, chemical propulsion, electric propulsion, nuclear propulsion and anti-substance propulsion, solar sail propulsion, beam energy propulsion, micro propulsion, rope system propulsion and the like. Among them, the chemical propulsion system is the most commonly used propulsion system at present, and develops from a single-component propulsion system to a double-component propulsion system, and then to a double-component and double-mode propulsion system, and matures gradually. The space chemical propulsion system is mainly applied to the orbit migration task of the micro-nano satellite. More than 80% of the total fuel on the micro-nano satellite needs to be consumed by a chemical propulsion system in the orbit transfer stage, so that the final service life of the satellite is directly determined by the limited fuel carried by the micro-nano satellite. At present, a propulsion system of few micro-nano satellites in China is cold air propulsion, and the cold air propulsion system has the advantages of simple structure, low energy consumption, no pollution and the like. However, whereas chilled and chemical propulsion systems require large volume fuel tanks and heavy mass low leak rate valve lines, scaled-down conventional electric propulsion systems are often limited by satellite power. Due to the limitation of conditions and factors such as power, volume and weight, the traditional propulsion system cannot meet the use requirement of a platform of the micro-nano satellite. The electric propulsion system is increasingly considered as a power source of the micro-nano satellite due to the advantages of small volume, light weight, low cost, micro thrust, high efficiency, high specific impulse, long service life, adjustable thrust and the like.

With the development of the aerospace technology and the deep space exploration technology, higher requirements are put forward on a micro-nano satellite propulsion module, for example, the micro-nano satellite for long-term monitoring needs the propulsion module to have higher total impulse so as to provide long-time power, and smaller element impulse is provided for good precision approximation. The micro-nano propulsion mainly can meet the propulsion requirements of micro-nano satellites and mainly comprises the following steps: damping compensation, rail lifting, position keeping and maneuvering, attitude control, launching error correction, thrust adjustable fast in a wide range, drag-free control, precise formation flying and the like.

Today, electric propulsion systems need to provide not only longer life but also greater total thrust and a variety of different thrusts. The service life of the micro-nano satellite mainly depends on the service life of a propulsion system, and the service life of each electric propulsion is uncertain and mainly determined by cathode materials, ablation conditions and the like; the thrust provided by each electric propulsion is also limited and deterministic. In order to solve the problem that the service life of the micro-nano satellite is influenced by certain electric propulsion, an array type electric propulsion device needs to be designed.

Disclosure of Invention

The invention aims to provide an array type coaxial vacuum arc thruster device aiming at the technical current situations of uncontrollable thrust, limited service life and the like in the coaxial vacuum arc thruster device.

The array type coaxial vacuum arc thruster device is positioned in a micro-nano satellite and comprises a plurality of thruster heads;

wherein, the thruster heads are coaxial arc thruster heads, and the number of the thruster heads ranges from 3 to 50;

each thruster head is of a coaxial type and comprises an anode, a cathode, an insulator, a shell and a spring, and the arrangement mode of the thruster heads is one of circular arrangement, rectangular arrangement, triangular arrangement, trapezoidal arrangement and polygonal arrangement;

the thruster head can also be of a stack type or a ring type;

the array type coaxial vacuum arc thruster device is controlled by an array type control circuit;

wherein, the spring is a cathode propelling device, and the propelling device comprises but is not limited to a spring, an elastic propelling device, an elastic mechanism or an electromechanical transmission device;

wherein the electromechanical transmission is one of an electromechanical motor, a piezoelectric motor, and a rotary motor;

the array control circuit comprises a power supply conversion module, an energy storage and discharge module, a pulse control module, a switch driving module, a thruster module and a power supply module;

the pulse control module comprises a power supply processing unit PPU and a CPU;

the array control circuit adopts an inductance energy storage IES flyback topological structure to generate pulse voltage to excite plasma initial arc discharge;

the power supply processing unit PPU comprises an inductor charged by a semiconductor switch, the working frequency and the pulse width of the on-off of the semiconductor switch are controlled by a pulse signal generator, and the working process is as follows:

when the semiconductor switch is closed, the power supply voltage is directly applied to the inductor for pre-charging;

when the semiconductor switch is switched off, an induced voltage peak pulse LdI/dt generated by Lenz's law induces plasma initial arc discharge;

the current loop of the array control circuit is converted to a thruster head branch from a semiconductor switch branch, a conductive film is plated on the surface of an insulator between an anode and a cathode, pulse voltage is concentrated to two ends of a contact point of the conductive film and the cathode, high voltage electricity generated at a tiny gap induces current breakdown discharge, metal of the cathode is evaporated due to heat generated by a current heating effect, metal atom vapor diffused in a vacuum area is ionized into micro plasma, a low-impedance channel between two electrodes is formed, current is rapidly switched to a low-impedance plasma discharge path from the surface discharge of an initial electrode with high impedance, and finally most of magnetic field energy stored in an inductor is released to generate plasma pulse thrust;

in each thruster head, the anode is cylindrical, and the insulator and the cathode are sequentially arranged outwards along the radial direction; the insulator is coaxial with the spring and has the same radius;

the anode is connected with the insulator, and the insulator is connected with the cathode; the cathode is connected with the shell; the insulator is connected with the spring;

the structure of the cathode outside can lead the cathode material to be ablated uniformly;

the connection and information transmission relationship of each part in the array control circuit is as follows:

the power supply module transmits voltage and current to the power supply conversion module; the power supply conversion module transmits the current and the voltage to the energy storage discharge module, the pulse control module and the switch driving module; after receiving the current and the voltage, the pulse discharge module transmits the discharged electric power to the thruster module and feeds back the instantaneous current of the controllable switch to the pulse control module; the pulse control module transmits the rectangular signal to the switch driving module; the switch control module controls the pulse discharge module through a rectangular pulse signal; the pulse control module is connected with the CAN bus interface, and a CPU in the pulse control module controls the frequency and the discharge frequency of the rectangular wave and the working state of the thruster head;

the pulse control module controls the ignition time sequence; the CPU controls the thruster module based on the ignition time sequence so as to generate different thrusts; the array type coaxial vacuum arc thruster device provided with the micro-nano satellite is controlled by a switch driving module of an array type control circuit to start and close different numbers of thruster heads to complete the flight tasks of orbit lifting and position keeping; the micro-nano satellites of a plurality of thruster heads can improve the task completion rate and reduce the loss caused by faults; when the micro-nano satellite executes a task, a certain thruster head is failed and does not catch fire or abnormally extinguishes fire under the condition of ignition, and other thruster heads are started to continue to finish the task at the moment.

Advantageous effects

Compared with the conventional coaxial vacuum arc thruster device, the array coaxial vacuum arc thruster device has the following beneficial effects:

1. the thruster device is controlled by a CPU, and the ignition time sequence can be controlled by an array control mode to generate different thrusts and total impacts; in the flight process of the satellite, different thrust and total impulse required by different flight stages can be controlled through the ignition time sequence function of the CPU, so that the flight of the satellite is more flexible;

2. the array type coaxial vacuum arc thruster device effectively prolongs the service life of the micro-nano satellite.

Drawings

Fig. 1 is a composition view of a thruster head in the array-type coaxial vacuum arc thruster apparatus;

fig. 2 is a circular arrangement of the array type coaxial type vacuum arc thruster apparatus;

fig. 3 is a rectangular arrangement of the array type coaxial type vacuum arc thruster apparatus;

fig. 4 is a structural composition diagram of the array type coaxial vacuum arc thruster device according to the present invention;

illustration of the drawings:

1-anode, 2-shell, 3-spring, 4-cathode, 5-insulator, 6-semiconductor switch, 7-resistor, 8-inductor, 9-power supply, 10-thruster head and 11-micro-nano satellite.

Detailed Description

The array type coaxial vacuum arc thruster device of the present invention is described in detail below with reference to the accompanying drawings and specific embodiments.