CN101614606B - Measuring device and method of thrust vector of detection space plasma thruster - Google Patents
Measuring device and method of thrust vector of detection space plasma thruster Download PDFInfo
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- CN101614606B CN101614606B CN200910089133XA CN200910089133A CN101614606B CN 101614606 B CN101614606 B CN 101614606B CN 200910089133X A CN200910089133X A CN 200910089133XA CN 200910089133 A CN200910089133 A CN 200910089133A CN 101614606 B CN101614606 B CN 101614606B
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Abstract
The invention relates to a measuring device and a method of the thrust vector of a detection space plasma thruster. The measuring device of the thrust vector mainly comprises an electrostatic probe, an electrostatic probe regulating mechanism, a locating piece and a data acquisition and processing system. The method comprises the following steps: first fixing the electrostatic probe on a movable platform, simultaneously regulating the position of the electrostatic probe, installing the locating piece on the position which the probe can contact when the axis of the probe coincides with that of the plasma thruster, collecting the electrons jetted on the local position by the thruster in real time by the electrostatic probe on which positive bias voltage is applied when the movable platform moves at a constant speed along the direction vertical to the axis of the thruster, thus collecting the voltage signals at both ends of sample resistance in real time by the data acquisition and processing system when current flows through a probe circuit, and educing deflection of the actual thrust vector from the design objective by comparing the differences between the time corresponding to the vertex of the voltage signals at both ends of the sample resistance and the sudden change time of the voltage signals at both ends of the locating piece according to the moving speed of a translation stage and the distance from the electrostatic probe to the exit of the thruster.
Description
Technical field
The present invention relates to a kind of measurement mechanism and method that detects the space plasma thruster thrust vectoring.
Background technology
Along with development of times, space restriction ability is to an effect that the nation's security play more and more is important.The chemical fuel weight that chemical rocket carries accounts for more than 90% of vehicle general assembly (TW), and useful load only accounts for about 1%, and is subjected to the restriction of propellant chemistry energy, and its specific impulse is difficult to improve.Therefore chemical propellant is applicable to the propelling task of short time, high thrust.Comparatively speaking, the electrical rocket Push Technology can obtain higher delivery efficient, is applicable to the propelling task of long-time, middle low thrust, high specific impulse.At present, for the satellite of various uses, for reducing weight and size, raising bearing accuracy, prolonging operation life, usage space electric propulsion technology has become a kind of valid approach.No matter be that recent space technology is used, still following scientific research to deep space all needs to develop high efficiency space electric propulsion technology.This is that the electric propulsion mode has the outstanding advantage of high specific impulse because compare with traditional appearance control/rail control chemical rocket.Electric propulsion technology in space roughly can be divided into: 1) electroheating type comprises resistance heated mode of jet and arcjet mode; 2) static accelerating type is as ion engine; 3) plasma propulsion type comprises that Hall engine, pulsed plasma engine, magnetoplasmadynamics engine and variable ratio are towards the magnetopasma engine.Up to now, existing in the world hundreds of satellites have used electric propulsion system, have accumulated a large amount of useful datas.But China also reaches without any the electric propulsion engine of kind or near the integrated performance index of practical application.
The rocket engine of any kind of before the operation of really can going up to the sky, all must carry out a large amount of performance studies and reliability simulated experiment on ground.Wherein, the measurement of thrust is absolutely necessary, for example, for gross thrust only is the multikilowatt arc-plasma thruster of hundreds of milli ox, except that the resistance of dynamometric system itself, be connected in the air supply pipe of thruster and accurate measurement that the service cable setting seriously influences thrust and the reliability of measurement result.Therefore, people have proposed the dynamometer of various different principle, pendulum model, double pendulum type are for example arranged down, rock formula, measuring method such as multi-arm type; The force measuring method that directly thruster is sitting on the balance is also arranged, or on the basis that thruster is sitting on the balance, do the processing or the compensation of a little gravity balances again; The measuring method of also useful laser interference principle.But above method all is that the size of thrust is measured, in other words conj.or perhaps to measuring along the thrust component of thruster axis direction, but whether absolute parallel is in engine axis for the thrust direction that thruster produces, be whether deflection of thrust vectoring, also be the important parameter that needs are accurately measured, also can not find out relevant open report at present.
Summary of the invention
The objective of the invention is to: propose a kind of device that detects the space plasma thruster thrust vectoring, and use this device and carry out the thrust vectoring measurement, inquire into the method for actual thrust vector and design object deflection situation.
The object of the present invention is achieved like this:
A kind of method that detects space plasma thruster actual thrust vector and design object deflection situation provided by the invention, be specially: utilize the electric signal in the thrust vectoring measurement mechanism collection space plasma thruster jet flow field, compare by skew, obtain the deflection of actual thrust vector and design object the electric signal peak space plasma thruster axis that collects.
Further, may further comprise the steps: 1) regulate electrostatic probe, when its axis and plasma thruster dead in line, but the electrostatic probe position contacting is provided with keeper, when the moment of electrostatic probe contact keeper, the signal that is applied on the keeper can be undergone mutation; 2) the described electrostatic probe of along continuous straight runs uniform motion, electrostatic probe is gathered the electronics of jet flow in local position in real time, and data acquisition processing system is gathered the electric signal of keeper and electrostatic probe simultaneously; 3) the pairing moment of electric signal peak of comparison electrostatic probe and keeper electric signal sudden change difference constantly, according to electrostatic probe translational speed and electrostatic probe distance, draw the deflection of the relative design object of thrust vectoring in the horizontal direction apart from the thruster outlet; 4) change the electrostatic probe moving direction, make it vertically at the uniform velocity mobile, gather the electronics of jet flow in real time, repeating step 3) in local position; 5) comprehensively measure deflection angle at level, vertical direction, its resultant vector direction is actual thrust vectoring deflection angle.
Further, the movement velocity of described moveable platform needs to determine according to the steady change cycle of plasma jet, guarantees that electrostatic probe can inswept whole jet flow radial section in single stable period.
A kind of device that detects the space plasma thruster thrust vectoring comprises electrostatic probe, electrostatic probe governor motion, keeper and data acquisition processing system, the electronics in the described electrostatic probe real-time collecting space plasma thruster jet flow; Described electrostatic probe governor motion is used to control electrostatic probe in level or vertical direction motion, and regulates the depth of parallelism between electrostatic probe axis and thruster axis; Described data acquisition processing system is used for electrostatic probe is applied positive bias, gather the electric signal of each point in the jet flow that electrostatic probe records and the electric signal of keeper output simultaneously, by analyzing the thrust vectoring deflection angle that two electric signal relatively draw thruster reality.
Further, the device of described detection space plasma thruster thrust vectoring, it is applicable to and has electronics and the electrical characteristics situation with respect to jet flow axis symmetry in the jet flow that thruster produces.
Further, described electrostatic probe governor motion comprises probe supporting seat, shock absorber part, moveable platform and universal stage, fixing moveable platform on the rotation platform, fixing shock absorber part on the moveable platform, set up the probe supporting seat on the shock absorber part, described electrostatic probe is fixed in the probe supporting seat, and insulation with it, and an end links to each other with described data acquisition processing system; Described moveable platform is used to control electrostatic probe in level or vertical direction motion, and described rotation platform is used to regulate the depth of parallelism between electrostatic probe axis and thruster axis.
Further, described data acquisition processing system comprises sampling resistor, grid bias power supply and reference electrode and data collector, and described electrostatic probe, sampling resistor, grid bias power supply and reference electrode constitute electric loop; Grid bias power supply is used for applying bias voltage to described electrostatic probe two ends, controls described electrostatic probe and gathers electronics in the described thruster jet flow field, thereby flow through electric current in the electric loop that is constituted; Data collector is used to gather the voltage signal at sampling resistor two ends.
Further, described electrostatic probe silk footpath determines that according to the radial extension and the measuring accuracy of jet flow diffusion the radial extension of the jet flow diffusion of described thruster and the ratio of probe filament diameter are greater than 30.
Further, described electrostatic probe is fixed in moveable platform by shock absorber part, guarantees that electrostatic probe measures real-time actual signal, and shock absorber part is adjusted the height of described electrostatic probe by adjusting its length.
Further, described moveable platform is controlled by step motor drive.
Further, need think over shielding, the problem with grounding of described thrust vectoring measurement mechanism link circuit, to obtain authentic and valid signal.
Characteristics of the present invention are:
1) voltage signal and the keeper both end voltage signal by sampling resistor two ends in the measurement of electrostatic probe loop, the pairing moment of voltage signal maximal value and keeper both end voltage sudden change difference constantly according to the sampling resistor two ends, with reference to translation stage translational speed and electrostatic probe distance, obtain the deflection of the relative design object of plasma thruster thrust vectoring apart from the thruster outlet.This measuring method novelty, measuring equipment is simple, has good operability.
2) moveable platform has stable, low vibration, high position precision and at the uniform velocity mobile characteristics.The characteristics of stable, low vibration that universal stage has, high position precision.Data collector has high sample frequency and precision, makes that detected voltage signal is undistorted, improves accuracy of detection.
Description of drawings
Fig. 1 is a thrust vectoring measurement mechanism synoptic diagram of the present invention;
Fig. 2 is a thrust vectoring deflection instrumentation plan of the present invention;
Fig. 3 is the measurement result figure of electrostatic probe loop current signals of the present invention (voltage signal at resistance two ends obtains divided by resistance value).
Embodiment
With reference to Fig. 1, make plasma thruster thrust vectoring measurement mechanism, this device comprises: 1. electrostatic probe, 2. insulating sleeve, 3. probe supporting seat, 4. sampling resistor, 5. grid bias power supply, 6. data collector, 7. reference electrode, 8, keeper, 9. shock absorber part, 10. moveable platform, 11. universal stages.
To adopt diameter be that the tungsten filament of 0.3mm is made for electrostatic probe 1 in the present embodiment, and stretch out insulating sleeve 2mm, and insulating sleeve 2 external diameters are 1mm, length is 35mm, to reduce the disturbance to jet flow as far as possible, thin tungsten filament diameter makes measurement result have higher spatial resolution again; Probe supporting seat 3 adopts high temperature ceramic material to make; Grid bias power supply 5 is set to 10V, and the resistance of sampling resistor 4 is 1 ohm, and data collector 6 can reach the digital oscilloscope of 100MHz for sample frequency; Reference electrode 7 can make the probe loop that one stable potential reference point is arranged; Shock absorber part 9 can be adjusted the height of electrostatic probe 1 up and down, and has shock-absorbing function.Moveable platform 10 is selected the high precision electronic control translation stage of using in the optical measurement for use, the characteristics that it has stable, low vibration, at the uniform velocity moves, universal stage 11 is selected the automatically controlled universal stage of the high precision of using in the optical measurement for use, it has characteristics stable, low vibration, guarantees to test to have good precision and repeatability.Keeper 8 is selected limit switch for use, is generally long switch, when probe moves to thruster axis place, touches the moment of limit switch, and the output voltage of limit switch suddenlys change to 1.5V by 0.
As shown in Figure 2, when using above-mentioned measurement mechanism and measuring the plasma thruster thrust vectoring, 1) earlier electrostatic probe 1 is fixed in moveable platform 10 by shock absorber part 9, moveable platform 10 is fixed in universal stage 11, universal stage 11 is fixed in stable platform 12; 2) whole device is placed 13 of plasma thruster jet flows; 3) regulate electrostatic probe 1 position by universal stage 11, make the parallel axes of electrostatic probe 1 axis and thruster 14, regulate electrostatic probes and space plasma thruster axis at sustained height by moveable platform 10, guarantee that simultaneously the tangential movement direction of electrostatic probe 1 axis and moveable platform 10 is vertical; 4) but when electrostatic probe 1 moves to the thruster axis position contacting one limit switch 8 is set, when probe 1 touches moment of this limit switch 8, the voltage that is applied on this limit switch 8 can suddenly change; 5) by moveable platform 10 electrostatic probe is moved on to position away from the thruster axis; Open bias voltage, apply positive bias voltage for electrostatic probe 1; 6) plasma thruster produces jet flow 13; 7) edge is perpendicular to the at the uniform velocity mobile moveable platform 10 of the direction level of thruster 14 axis, and electrostatic probe will be at the uniform velocity mobile thereupon; 8) apply the electrostatic probe of positive bias voltage simultaneously with the electronics of real-time collecting plasma thruster jet flow in local position, thereby flow through electric current at probe circuit, data collector is gathered the voltage signal (voltage signal at sampling resistor two ends can obtain the current value that loop stream is crossed divided by resistance value, and it directly reflects the electrical characteristics of jet flow) at sampling resistor two ends in real time; 9) change the probe moving direction, make it vertically at the uniform velocity mobile, repeating step 8); 10) deflection angle at level, vertical direction that comprehensively measures, its resultant vector direction is the thrust vectoring deflection angle that finally obtains.
Figure 3 shows that and adopt the resulting measurement result figure of above-mentioned measurement mechanism, solid line is an electrostatic probe loop current measurement result among the figure, and dotted line is represented the jet flow center.By the current data symmetry of analytic centre line both sides, thereby obtain the degree of deflection of thrust vectoring.The method that stretches into the electrostatic probe loop current in the plasma thruster jet flow of measuring is adopted in this embodiment explanation, and the deflection of inquiring into thrust vectoring is a kind of simple, feasible, effective method.
It is to be noted any type of distortion of making according to the specific embodiment of the present invention, all do not break away from the protection domain of spirit of the present invention and claim.
Claims (7)
1. method that detects space plasma thruster actual thrust vector and design object deflection situation, be specially: utilize the thrust vectoring measurement mechanism to gather the electric signal of each point in the space plasma thruster jet flow field, analyze by skew the electric signal peak space plasma thruster axis that collects, obtain the deflection of actual thrust vector and design object, it specifically may further comprise the steps: 1) regulate electrostatic probe, when its axis and plasma thruster dead in line, but the electrostatic probe position contacting is provided with keeper, when the moment of electrostatic probe contact keeper, the signal that is applied on the keeper can be undergone mutation; 2) edge and the at the uniform velocity mobile electrostatic probe of the orthogonal horizontal direction of described electrostatic probe axis, electrostatic probe is gathered the electronics of jet flow in local position in real time, and data acquisition processing system is gathered the electric signal of keeper and electrostatic probe simultaneously; 3) the pairing moment of electric signal peak of comparison electrostatic probe and keeper electric signal sudden change difference constantly, according to electrostatic probe translational speed and electrostatic probe distance, draw the deflection of the relative design object of thrust vectoring in the horizontal direction apart from the thruster outlet; 4) change the electrostatic probe moving direction, make it vertically at the uniform velocity mobile, gather the electronics of jet flow in real time, repeating step 3) in local position; 5) comprehensively measure deflection angle at level, vertical direction, its resultant vector direction is actual thrust vectoring deflection angle.
2. the method for detection space plasma thruster actual thrust vector as claimed in claim 1 and design object deflection situation, it is characterized in that, described electrostatic probe translational speed needs to determine according to the steady change cycle of plasma jet, guarantees that electrostatic probe can inswept whole jet flow radial section in single stable period.
3. device that detects the space plasma thruster thrust vectoring, it is characterized in that, comprise electrostatic probe, electrostatic probe governor motion, keeper and data acquisition processing system, the electronics in the described electrostatic probe real-time collecting space plasma thruster jet flow; Described electrostatic probe governor motion be used to control electrostatic probe with perpendicular horizontal direction or the vertical direction motion of electrostatic probe axis, regulate electrostatic probe axis and thruster parallel axes; When described keeper is arranged on electrostatic probe axis and plasma thruster dead in line, but the electrostatic probe position contacting; Electrostatic probe moves to the moment of plasma thruster axis, and electrostatic probe is touched described keeper, produces the sudden change electric signal on keeper; Described data acquisition processing system is used for probe is applied positive bias, and the while is gathered the electric signal of electrostatic probe and keeper output in real time, and analyzes and compare the thrust vectoring deflection angle that two voltage signals draw thruster reality.
4. the device of detection space plasma thruster thrust vectoring as claimed in claim 3, it is characterized in that, described electrostatic probe governor motion comprises probe supporting seat, shock absorber part, moveable platform and rotation platform, fixing moveable platform on the rotation platform, fixing shock absorber part on the moveable platform sets up the probe supporting seat on the shock absorber part, described electrostatic probe is fixed in the probe supporting seat, and insulation with it, and an end links to each other with described data acquisition processing system; Described moveable platform be used to control electrostatic probe with perpendicular horizontal direction or the vertical direction motion of electrostatic probe axis, described rotation platform is used to regulate the electrostatic probe axis and the plasma thruster axis parallels.
5. the device of detection space plasma thruster thrust vectoring as claimed in claim 3, it is characterized in that, described data acquisition processing system comprises sampling resistor, grid bias power supply, reference electrode and data collector, described electrostatic probe, sampling resistor, grid bias power supply and reference electrode constitute electric loop, and data collector is used to gather the electric signal of sampling resistor two ends and keeper.
6. the device of detection space plasma thruster thrust vectoring as claimed in claim 3, it is characterized in that, described electrostatic probe silk footpath determines that according to the radial extension and the measuring accuracy of jet flow diffusion the radial extension of the jet flow diffusion of described thruster and the ratio in electrostatic probe silk footpath are greater than 30.
7. the device of detection space plasma thruster thrust vectoring as claimed in claim 3 is characterized in that, the device of described detection space plasma thruster thrust vectoring need shield, ground connection.
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| CN200910089133XA CN101614606B (en) | 2009-07-30 | 2009-07-30 | Measuring device and method of thrust vector of detection space plasma thruster |
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| CN106802125A (en) * | 2017-01-24 | 2017-06-06 | 上海空间推进研究所 | The spacecraft eccentric determination method of electric thruster thrust vectoring |
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