阅读说明：本技术 一种用于电推力器羽流稳态离子速度测量的装置 (Device for measuring plume steady-state ion velocity of electric thruster ) 是由 汤海滨 董杨洋 章喆 于 2019-09-25 设计创作，主要内容包括：一种用于电推力器羽流稳态离子速度测量的装置,根据EXB测量离子速度的原理,采用接触式测量的方式,主要针对霍尔推力器、离子推力器、MPD等稳态推力器羽流离子速度进行诊断,测量轴线上离子速度的大小和分布规律。结构包含3层热防护设计、1层电磁屏蔽设计、1个电磁场校正结构、主体结构、排气结构等主要结构,通过改变电场电压改变筛选离子的速度,经过处理可得轴线上的离子速度分布。(A device for measuring the plume steady-state ion velocity of an electric thruster is mainly used for diagnosing the plume ion velocity of steady-state thrusters such as a Hall thruster, an ion thruster and an MPD (metal-oxide-semiconductor field-effect transistor) according to the principle of measuring the ion velocity by an EXB (acceleration-deceleration) and by adopting a contact measurement mode, and measuring the size and the distribution rule of the ion velocity on an axis. The structure comprises main structures such as 3 layers of thermal protection designs, 1 layer of electromagnetic shielding designs, 1 electromagnetic field correction structure, a main body structure, an exhaust structure and the like, the speed of screening ions is changed by changing the voltage of an electric field, and the ion speed distribution on the axis can be obtained by processing.)

1. A device for measuring steady-state ion velocity of a plume of an electric thruster is characterized by comprising a front-end rotating structure, a middle electromagnetic field structure, a tail-end acquisition structure and a front-end protection structure; the front-end rotating structure is in threaded connection with the non-metal layer of the middle electromagnetic field structure and is in clearance fit with the front-end protecting structure, and the coaxiality of the front-end rotating structure and the central plume region of the middle electromagnetic field structure is realized by the cooperation of the front-end protecting structure and the front-end rotating structure; the coaxiality of the central plume region of the intermediate electromagnetic field structure and the tail end collecting structure is realized through the matching of the lug boss and the groove.

2. The device for measuring the steady-state ion velocity of the plume of the electric thruster as claimed in claim 1, wherein the front protection structure comprises a thermal protection baffle, a left thermal insulation plate, a right thermal insulation plate and an upper thermal insulation plate, and the included angle between the left thermal insulation plate and the thermal protection baffle is 105 °.

3. The apparatus of claim 2, wherein the front rotating structure comprises an upper rotating structure shell, a transition rod, a lower rotating structure shell, an electromagnetic shielding layer, a non-metal layer, a collimator tube, and a collimator tube inlet, wherein the collimator tube is a segmented structure, and the segments are connected by screw threads.

4. The apparatus of claim 3, wherein the intermediate electromagnetic field structure comprises a non-metallic mounting plate, a non-metallic cover, a magnetic pole plate spacer, an electrode plate adaptor, a housing body side, an electrode insulating ceramic block, a housing body upper layer, a housing body base.

5. The device for measuring steady-state ion velocity of plume of electric thruster of claim 4, wherein the tail end collecting structure comprises a collecting end insulating plate, a collector, a back end electromagnetic shielding layer, a collector protecting shell and a collecting filter plate, the collector adopts a concave receiving end, and the receiving end and the outer collector protecting shell adopt a boss groove structure.

6. The apparatus of claim 5, wherein the receiving end of the trailing collection structure and the outer containment vessel have coaxial circumferential arrays of exhaust holes.

7. The device for measuring the steady-state ion velocity of the plume of the electric thruster as claimed in claim 6, wherein the electromagnetic shielding layer, the side surface of the housing main body, the upper layer of the housing main body, the base of the housing main body and the rear end electromagnetic shielding layer form an electromagnetic shielding structure, and an electrical pure iron material is used as the material of the electromagnetic shielding structure.

8. The device for measuring the steady-state ion velocity of the plume of the electric thruster as claimed in claim 7, which comprises three layers of thermal protection structures, wherein the first layer is made of a stainless steel structure and comprises a thermal protection partition plate, a left side thermal insulation plate, a right side thermal insulation plate and an upper layer thermal insulation plate, and the thermal protection structure bears the direct incidence of the plume and forms a funnel-shaped cavity structure with the bottom plate; the second layer is an outer-layer coating heat-insulating material; the third layer is a non-metal layer between the housing and the internal electromagnetic field.

9. The apparatus of claim 8, further comprising a front rotating shaft and a rear rotating shaft, wherein the front rotating shaft is connected to the front rotating structure and the middle electromagnetic field structure, and the rotation center axis of the front rotating structure coincides with the rotation axes of the front rotating shaft and the rear rotating shaft.

Technical Field

The invention belongs to the field of measurement of electrically propelled plasma, and relates to a device for measuring plume steady-state ion velocity of an electric thruster.

Background

The electric propulsion is an advanced propulsion mode which utilizes electric energy to directly heat the propellant or utilizes electromagnetic action to ionize and accelerate the propellant so as to obtain propulsion power, has higher specific impulse, thrust and efficiency, and has wide application prospect in space tasks of orbit control, deep space exploration, interstellar navigation and the like of large-scale spacecrafts.

The ion velocity in the plume of the electric thruster is closely related to the performance of the engine, and more accurate velocity diagnosis has certain influence on the performance analysis of the engine. In order to improve the measurement accuracy, it is considered to design a device for diagnosing the plume steady-state ion velocity of a thruster, such as a hall thruster, an ion thruster, or an MPD (yet to be tested).

Disclosure of Invention

The invention aims to provide a device for measuring the plume steady-state ion velocity of an electric thruster, which is mainly used for diagnosing the plume steady-state ion velocity of the electric thrusters such as a Hall thruster, an ion thruster and an MPD (currently tested).

The purpose of the invention can be realized by the following technical scheme: a device for measuring steady-state ion velocity of a plume of an electric thruster is characterized by comprising a front-end rotating structure, a middle electromagnetic field structure, a tail-end acquisition structure and a front-end protection structure; the front-end rotating structure is in threaded connection with the non-metal layer of the middle electromagnetic field structure and is in clearance fit with the front-end protecting structure, and the coaxiality of the front-end rotating structure and the central plume region of the middle electromagnetic field structure is realized by the cooperation of the front-end protecting structure and the front-end rotating structure; the coaxiality of the central plume region of the intermediate electromagnetic field structure and the tail end collecting structure is realized through the matching of the lug boss and the groove.

Furthermore, the front end protection structure comprises a heat protection clapboard, a left side heat insulation plate, a right side heat insulation plate and an upper layer heat insulation plate, and the included angle between the left side heat insulation plate and the heat protection clapboard is 105 degrees.

Furthermore, front end revolution mechanic includes revolution mechanic casing upper strata, transition pole, revolution mechanic casing lower floor, electromagnetic shield layer, nonmetal layer, collimator entry, and the collimator is the segment structure, threaded connection between each section.

Furthermore, the middle electromagnetic field structure comprises a non-metal mounting plate, a non-metal cover, a magnetic pole plate cushion block, a plate electrode adapter, a side surface of the shell body, an electrode insulating ceramic block, an upper layer of the shell body and a base of the shell body.

Further, tail end collection structure is including collecting end insulation board, collector, rear end electromagnetic shield layer, collector protective housing, collection cassette, and the collector adopts indent formula receiving terminal, and the collector protective housing in receiving terminal and the outside adopts boss groove structure.

Furthermore, the receiving end of the tail end collecting structure and the collector protecting shell on the outer side are provided with coaxial annular array exhaust holes.

Furthermore, the electromagnetic shielding layer, the side surface of the shell body, the upper layer of the shell body, the base of the shell body and the rear end electromagnetic shielding layer form an electromagnetic shielding structure, and an electrical pure iron material is adopted as an electromagnetic shielding structure material.

The device further comprises three layers of thermal protection structures, wherein the first layer is a stainless steel structure and comprises a thermal protection partition plate, a left thermal insulation plate, a right thermal insulation plate and an upper thermal insulation plate, and the thermal protection partition plate bears direct plume and forms a funnel-shaped cavity structure with the bottom plate; the second layer is an outer-layer coating heat-insulating material; the third layer is a non-metal layer between the housing and the internal electromagnetic field.

Furthermore, the electromagnetic field electromagnetic wave electromagnetic.

The invention has the advantages that:

1. the outer layer of the device surrounds an electromagnetic shielding structure formed by processing electrician pure iron, wherein the electromagnetic shielding structure comprises an electromagnetic shielding layer, a side surface of a shell body, an upper layer of the shell body, a base of the shell body and a rear end electromagnetic shielding layer, an electromagnetic field of the inner layer of the structure can be shielded, the device is guaranteed to have small influence on the movement of ions in an external plume region, and meanwhile, the electromagnetic field on the outer side cannot influence the movement of internal ions.

2. The device contains three-layer thermal protection structure, and the temperature in the inside measurement zone of greatly reduced device guarantees that magnet work is in normal operating temperature. The outmost layer is of a stainless steel structure, bears direct plume injection, forms a funnel-shaped cavity structure with the bottom plate, is not directly contacted with the device main body, is contacted only through a ball bearing on the bottom plate, and has small heat transfer quantity to the device main body in the vacuum chamber; the second layer is a common outer-layer coating type heat-insulating material and is coated outside the electromagnetic shielding shell; the third layer is a non-metal layer between the outer shell and the inner electromagnetic field, and plays a role in protecting the last layer of heat.

3. The collimator at the front end of the device adopts a sectional design and is in threaded connection, the length of the collimator can be accurately controlled, and the device is convenient to mount and dismount.

4. The device middle part is provided with the revolution mechanic who constitutes by front end rotation axis and rear end rotation axis, plays collimation pipe and the regional transitional coupling's of electromagnetic field effect, revolution mechanic rotation center axle and the coincidence of the front end thrust bearing axis of structure for revolution mechanic's rotation angle can pass through rear end thrust bearing's horizontal displacement accurate control, and rear end thrust bearing's horizontal displacement accessible small-size displacement mechanism realizes easily.

5. The tail end of the device adopts a concave receiving end, so that ions are not easy to escape after entering the receiving end.

6. The non-metal protection shell at the tail end receiving end and the outer side of the device adopts the structural design of the lug boss groove, the coaxiality precision of the tail end receiving end and the non-metal protection shell is guaranteed, and the exhaust efficiency is improved.

7. The nonmetal protective housing in device tail end receiving terminal and outside has the annular array exhaust hole design of coaxial-type, and single exhaust hole diameter 1mm, totally 48. The diameter design parameter of the collimator inlet is not more than 4mm, and the exhaust structure can meet the condition that the difference between the internal pressure and the external pressure of the instrument is not too much under the parameter. The diameter of an air vent on the nonmetal protective shell is 1.4mm, the depth of the air vent is 2.5mm, ions with the divergence angle of 15.6 degrees can be prevented from being incident into a receiving end from the outside, and the system error in collection is reduced.

8. The main theoretical basis of the device is the same as that of an EXB probe, and the ion velocity on a straight line can be accurately diagnosed through the collimating tube structure at the front end.

Drawings

The invention will be further explained with reference to the drawings.

Fig. 1 is an overall cross-sectional view of an apparatus for steady-state ion velocity measurement of an electric thruster plume.

Fig. 2 is an overall assembly diagram of an apparatus for steady state ion velocity measurement of an electric thruster plume.

Fig. 3 is an assembly view of the front end rotation structure.

Fig. 4 is an assembly view of the intermediate electromagnetic field structure.

Fig. 5 is an assembly view of the trailing acquisition structure.

In the figure:

1. a front end rotating structure; 2. an intermediate electromagnetic field structure; 3. a tail end collection structure; 4. a front end guard structure; 5. a front end rotating shaft; 6. a rear end rotating shaft; 7. a base plate; 8. a collimator clamp; 9. a collimator angle; 10. a thermal protection barrier; 11. a left side heat insulation plate; 12. a right side heat insulation plate; 13. an upper layer heat insulation board;

101. the upper layer of the rotating structure shell; 102. a transition rod; 103. a lower layer of the rotating structure shell; 104. an electromagnetic shielding layer; 105. a non-metal layer; 106. a collimator tube; 107. a collimator inlet;

201. a non-metallic mounting plate; 202. a non-metallic cover; 203. a magnetic pole plate; 204. a pole plate cushion block; 205. an electrode plate; 206. electrode plate switching; 207. a housing body side; 208. an electrode insulating ceramic block; 209. a housing body upper layer; 210. a housing body base;

301. a collection end insulating plate; 302. a collector; 303. a rear electromagnetic shielding layer; 304. a collector containment vessel; 305. and collecting the filter disc.

Detailed Description

The following detailed description of embodiments of the invention refers to the accompanying drawings.

The invention provides an overall section view of a device for measuring steady-state ion velocity of a plume of an electric thruster, which is shown in figure 1 and comprises a front-end rotating structure 1, a middle electromagnetic field structure 2, a tail-end collecting structure 3 and a front-end protecting structure 4; the front-end rotating structure 1 is in threaded connection with the non-metal layer of the middle electromagnetic field structure 2 and is in clearance fit with the front-end protection structure 3, and the front-end rotating structure 3 is matched with the front-end rotating structure 1 to realize the coaxiality of the central plume region of the front-end rotating structure and the middle electromagnetic field structure 2; the coaxiality of the central plume region of the middle electromagnetic field structure 2 and the tail end collecting structure 3 is realized through the matching of the lug boss and the groove.

The invention provides an overall assembly diagram of a device for measuring the steady-state ion velocity of a plume of an electric thruster, which is shown in figure 2 and further comprises a front-end rotating shaft 5, a rear-end rotating shaft 6, a bottom plate 7, a collimator clamping piece 8, a collimator corner piece 9, a thermal protection clapboard 10, a left-side thermal insulation plate 11, a right-side thermal insulation plate 12 and an upper-layer thermal insulation plate 13; three vertical heat insulation plates are connected through bolts and matched with the bottom plate through slotted holes, the included angle between the heat insulation plates on two sides and the heat protection partition plate is 105 degrees, and the influence on the plume is reduced as far as possible on the premise that the heat insulation plates do not interfere with each other during rotation. The four heat insulation plates and the bottom plate form a funnel-shaped structure together, and a key first layer of heat protection is provided for the main body device. The front collimator of the front rotary structure 1 is fixed to the base plate by a collimator angle 9 and a collimator holder 8, and the rotation center axis of the front rotary structure 1 coincides with the rotation axes of the front rotary shaft 5 and the rear rotary shaft 6.

The assembly diagram of the front-end rotating structure in the device for measuring the steady-state ion velocity of the plume of the electric thruster provided by the invention is shown in fig. 3, and comprises a rotating structure shell upper layer 101, a transition rod 102, a rotating structure shell lower layer 103, an electromagnetic shielding layer 104, a non-metal layer 105, a collimator 106 and a collimator inlet 107; the front-end rotating structure mainly plays a role in deflecting incident ions so as to balance system errors caused by mismatching of electromagnetic fields at the entrance of the electromagnetic field region in the middle electromagnetic field structure.

The invention provides an assembly diagram of a middle electromagnetic field structure in a device for measuring steady-state ion velocity of a plume of an electric thruster, which is shown in fig. 4 and comprises a non-metal mounting plate 201, a non-metal cover 202, a magnetic pole plate 203, a magnetic pole plate cushion block 204, an electrode plate 205, an electrode plate adapter 206, a shell body side surface 207, an electrode insulating ceramic block 208, a shell body upper layer 209 and a shell body base 210; the middle electromagnetic field structure provides a uniform electromagnetic field channel for the device, and the purpose of screening ions is achieved.

The tail end acquisition structure assembly diagram in the device for measuring the steady-state ion velocity of the plume of the electric thruster provided by the invention is shown in fig. 5, and comprises a collection end insulating plate 301, a collector 302, a rear end electromagnetic shielding layer 303, a collector protecting shell 304 and a collection filter sheet 305; the tail end acquisition structure mainly plays a role in signal collection and has a function of reducing the internal pressure of the device by exhausting.

After the three structures are installed, an electromagnetic shielding shell can be formed, the thickness of a shielding layer at any position of the shell is not less than 3mm, and 95% of electromagnetic field can be effectively filtered by adopting electrician pure iron as a shielding layer material.

The foregoing are only some embodiments of the invention. It will be apparent to those skilled in the art that various changes and modifications can be made without departing from the inventive concept thereof, and these changes and modifications can be made without departing from the spirit and scope of the invention.