CN101813537A - Micro-thruster array testing table - Google Patents
Micro-thruster array testing table Download PDFInfo
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- CN101813537A CN101813537A CN 201010126964 CN201010126964A CN101813537A CN 101813537 A CN101813537 A CN 101813537A CN 201010126964 CN201010126964 CN 201010126964 CN 201010126964 A CN201010126964 A CN 201010126964A CN 101813537 A CN101813537 A CN 101813537A
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- thruster array
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Abstract
The invention relates to a thrust testing table for a thruster array formed by micro solid rocket engines. The thrust testing table comprises a platform, stand columns, supports, a base and piezoelectric force transducers. Peripheral devices comprise a micro-thruster array and an amplifier. The platform for placing the micro-thruster array is an X-shaped plate. The number of the stand columns is at least four. One end of each stand column is used for installing one corner of the thruster array and the other end of each stand column is connected with the X-shaped plate through a hollow bolt. A Z-shaped support is respectively arranged at the positions of the four corners of the X-shaped plate, wherein the supporting surfaces of the supports on one diagonal line are arranged at the upper part of the X-shaped plate and the supporting surfaces of the supports on the other diagonal line are arranged at the lower part of the X-shaped plate. The supporting surfaces are connected with the X-shaped plate respectively through the piezoelectric force transducers. The testing table can be used for testing the overall thrust effect of a plurality of solid rocket engines of the micro-thruster array when the solid rocket engines are simultaneously ignited, and theoretically the positions of the ignited engines can be obtained through a reverse method.
Description
Technical field
The present invention relates to a kind of stand of miniature solid rocket engine thrust test, the thrust testboard bay of the thruster array that particularly a kind of miniature solid rocket engine is formed.
Background technology
Flourish along with Aero-Space cause in recent years also is more and more higher to the requirement of the accurate test of motor power performance.The advantage that solid propellant rocket has is simple in structure, do not have moving-member, energy conversion efficiency is high is so be chosen as the roll booster of micro-satellite.Yet solid-rocket can not be reused, and the roll booster of micro-satellite uses the tiny engine group of array will become trend.If microsatellite is become rail and posture adjustment control accurately, thruster is had higher requirement, require to produce the thrust of controlled little ox magnitude, just test is had higher requirement to microthrust.
Stand about the test of solid propellant rocket thrust has much both at home and abroad, as the thrust of falling the pendulum testing jig of two turntable test boards, six component test boards, reaction balance test board, the U.S..These testboard bays only are only applicable to the test of the thrust of single solid propellant rocket.And for the investigation of miniature solid rocket engine array overall performance, generally be to obtain by the mathematical computations mode, the coupled relation between the solid propellant rocket also all is a theoretical analysis, can't verify its correctness.On the other hand, because the distance in the thruster array between adjacent two solid propellant rockets is very near, whether the high temperature that igniting produces can cause that the mistake combustion also only is to carry out theoretical analysis with flow field analysis software, and correctness can't be verified with conventional testboard bay.
Shown in Figure 1 is French cantilevered microthrust testboard bay.Solid propellant rocket is installed in the pendulum lower end that printed circuit board (PCB) connects, pendulum can be around top axle rotation, the Lorentz force that electric current in the coil produces is in the magnetic field of permanent magnet, the position of pendulum is obtained by position transducer, size by electric current in the quick adjustment coil makes pendulum remain vertical position, so, find out the funtcional relationship of the size of current in thrust size and the coil, just can test by demarcating.But this testboard bay only can be tested the thrust effect of single solid propellant rocket, is one dimension, when not analyzing a plurality of solid propellant rockets and lighting a fire simultaneously, produces the method for solving of trust engine position.
Summary of the invention
The objective of the invention is at the problems of the prior art, provide a kind of and can test the whole thrust effect of thruster array and can obtain the testboard bay of igniter motor position simultaneously.
Micro-thruster array testing table of the present invention comprises platform, column, bearing, base, bullet ball, piezoelectric force transducer, and peripherals comprises miniature thruster array, amplifier, it is characterized in that, the platform of placing miniature thruster array is the X-shaped plate; Described column has four at least, be installed respectively a jiao of miniature thruster array of one end, and the other end connects by hollow bolt with the X-shaped plate; The position at four angles of X-shaped plate is provided with a Z-shaped bearing of fixedlying connected with base respectively, the supporting plane of one of them diagonal line bearing is arranged on X-shaped plate top, under two supporting planes, connect a piezoelectric force transducer by regulating bolt thread respectively, the supporting plane of another one diagonal line bearing is arranged on X-shaped plate bottom, connects a piezoelectric force transducer by regulating bolt thread respectively on two supporting planes; The position difference interference corresponding with piezoelectric force transducer of four angles of X-shaped plate connects a bullet ball; Described bullet ball comprises cylindrical bomb body and semisphere bullet, its cylindrical bomb body and X-shaped plate interference fit, and the semisphere bullet withstands on the stress surface of contact of piezoelectric force transducer; Each piezoelectric force transducer links to each other with an amplifier respectively.
Testboard bay of the present invention can be tested the whole thrust effect that a plurality of solid propellant rockets of microthrust device array are lighted a fire simultaneously, and can instead in theory obtain the igniter motor position.
Description of drawings
Fig. 1 is French cantilevered microthrust testboard bay.
Fig. 2 is for realizing testboard bay structural drawing of the present invention.
Fig. 3 for the X-shaped plate with withstand on it under sensor between put the synoptic diagram contact.
Fig. 4 be the X-shaped plate with the sensor of pressing thereon between the synoptic diagram that contacts of point.
Fig. 5 is the structural drawing of X-shaped plate.
Fig. 6 is for using the test system module figure of this testboard bay.
Fig. 7 is an ignition location algorithm principle coordinate diagram.
Wherein, 1 is rotating shaft, and 2 is pendulum, and 3 is the copper dish, and 4 is the miniature solid rocket engine, and 5 is coil, and 6 is base, and 7 is Z-shaped bearing, and 8 is the X-shaped plate, and 9 is column, and 10 for regulating bolt, and 11 is miniature thruster array, and 12 is sensor, and 13 is bullet ball.
Embodiment
Below in conjunction with accompanying drawing, describe preferred implementation of the present invention in detail.
The tested object of this testboard bay is that 100 solid engines are evenly distributed on the thruster array on the 100x100x3mm rectangular parallelepiped flat board, and the thrust peak value of its single engine is 10mN, thrust time 100ms.
Fig. 2 is for realizing testboard bay structural drawing of the present invention.Miniature thruster array 11 is installed on four little foursquare columns 9.X-shaped plate 8 is the key-way shape holes that can move horizontally among a small circle with column 9 coupling parts, in order to test the miniature thruster array 11 of the different length of sides, opens eight dowel holes altogether, divides two groups to test the different square miniature thruster array 11 of the length of side respectively.Column 9 among a small circle slip in the key-way shape hole of X-shaped plate 8 below realizes the clamping to miniature thruster array 11.The purpose of adding four columns 9 is to have huger ignition circuit board that the space is provided below the thick thin plate of miniature thruster array 113mm.Two piezoelectric force transducers 12 are installed to pressing down on the diagonal line bearing 7 of X-shaped plate 8, two piezoelectric force transducers 12 on the another one diagonal line bearing 7 are the top upwards, the other end of piezoelectric force transducer 12 stress surface of contact is threaded by regulating bolt 10 on Z-shaped bearing 7, regulate bolt 10 by rotation, move up and down the axial location of piezoelectric force transducer 12 on bearing 7, realize loading X-shaped plate 8 pretightning forces.So far, miniature thruster array 11 is just supported by four piezoelectric force transducers 12 fully, and loading in the small thrust on the miniature thruster array 11 all can have output on four piezoelectric force transducers 12.
Fig. 3 and Fig. 4 are the synoptic diagram of some contact between the stress surface of contact of piezoelectric force transducer 12 and the X-shaped plate 8.Contact with millet cake by ball between the stress surface of contact of piezoelectric force transducer 12 and the X-shaped plate 8, can subdue greatly because the influence that 7 processing of Z bearing and error in mounting position bring, guarantee thrust forever perpendicular to the stress surface of piezoelectric force transducer 12, effectively removal level is disturbed.Realize that by tolerance interference fit, the stress surface of contact of bullet ball spherical part and piezoelectric force transducer 12 are to contact between the column part of bullet ball and the X-shaped plate 8, can realize stressedly, subdue the testing level direction and disturb all the time perpendicular to the X board plane.
One end of piezoelectric force transducer 12 non-stress faces is connected with bearing 7 with regulating double-screw bolt, by regulating double-screw bolt, axially interior among a small circle the moving of piezoelectric force transducer 12 be can realize, bolt 10, fixedly ends of piezoelectric force transducer 12 regulated with two nut locks after the stand pretension.
Because the rise time of thrust is approximately 10ms, so will distinguish, the structure of system must be light, and rigidity should be big as far as possible.The signal of piezoelectric force transducer 12 is that the distortion by X-shaped plate 8 obtains, and wherein X-shaped plate 8 is test thrust key components of testboard bay, and material can be elected titanium alloy or aluminium alloy as, considers cost, has selected aluminium alloy.In order to make X-shaped plate 8 weight lighter to greatest extent, with ANSYS it have been carried out optimizing analysis, the center that has finally formed as Fig. 5 is empty, is the version of the thick reinforcement of 2mm below.
Piezoelectric quartz crystal possesses high rigidity, high sensitivity, high natural frequency and good stable, in addition, its Curie point height, temperature stability is good, is very suitable for very significantly environment of the such temperature variation of engine ignition.So, finally selected piezoelectric quartz crystal quick in the present embodiment as the power of this test macro.
Fig. 6 is for using the test macro of this testboard bay.The voltage that can be obtained four sensors by testboard bay is exported, because thrust is smaller, the voltage signal of acquisition is also very faint, so need to connect a four-way amplifier, then the signal of amplifier is exported to oscillograph or card reader.Ce Shi signal inputs to computer and analyzes with MATLAB the most at last.
The test macro analytic process is briefly as follows: the mode of cutting off cord by the lifting counterweight adds step signal for test board x shape plate, reads oscillographic four-way output, and it is asked vector and computing; To the signal Fast Fourier Transform (FFT) of dispersing, the natural frequency that obtains stand distributes; At frequency distribution design bandpass filter original signal is carried out Filtering Processing, and compare analysis with original signal; Bandpass signal is carried out match, obtain the identification parameter of system; Design compensation circuit or software compensation algorithm compensate, and finish the demarcation to the standard step force.
Fig. 7 is an ignition location algorithm principle coordinate diagram.Test philosophy during single engine ignition: as shown in Figure 7, the xy plane is the plane at thruster array place, F
1And F
4Be a diagonal line upper sensor applied force of square ceramic wafer, point to z axle positive dirction, F
2And F
3Be the power on its another diagonal line, point to Z axle negative direction.With matrix cluster engine flat board is research object, and the regulation positive dirction is a Z axle positive dirction, the position coordinates of supposing igniter motor for (a, b), L is the distance between adjacent two sensors, then has:
Single engine main thrust F is :-F=F
1+ F
4-F
2-F
31.
X-axis is got square then to be had: Mx=-F*a=(F
1+ f
3-F
4-F
2) * L/2 2.
Y-axis is got square then to be had: My=F*b=(F
1+ F
2-F
3-F
4) * L/2 3.
2. 3. can get by equation:
a＝-(F
1+F
3-F
4-F
2)*L/(2*F)
b＝(F
1+F
2-F
3-F
4)*L/(2*F)
Test philosophy when a plurality of rockets are lighted a fire simultaneously: the size by total thrust body can draw the number n of the rocket of igniting simultaneously.When n=2, obtain the application point of total thrust earlier, principle determines that with single engine coordinate position method is consistent.The gross thrust of making a concerted effort to be of while igniter motor thrust.Suppose gross thrust second quadrant (other quadrant reasons are the same), slope of application point work of crossing gross thrust is 1 straight line, and then the upper and lower of this straight line must respectively have a solid-rocket igniting.Suppose a upper left engine α successively in order
1Be igniter motor, then with the gross thrust application point be the center symmetric points another the point near an engine β must be arranged
1Igniting is by α
1, β
1The theoretical reading that thrust stack calculates four sensors is carried out in igniting, if consistent with the actual reading that records then igniter motor is α
1, β
1,, above straight line, get another engine α successively if inconsistent
2Suppose its igniting, draw centrosymmetric another engine β
2The position, checking again, so circulation just can be obtained two position coordinateses of igniter motor simultaneously.Get limiting case, suppose that thrust with joint efforts at coordinate origin, then circulates at most 50 times, can find out the position of igniter motor.
When n=3, find out the position that thrust is made a concerted effort earlier, suppose that at third quadrant slope of effect strokes and dots is-1 straight line excessively, online below is supposed an engine α successively
1Igniting, α
1Igniter motor is d apart from point of resultant force, and then the position of the d/2 that the opposing party of point of resultant force distance is on straight line is two other solid-rocket β
1, γ
1The thrust application point of making a concerted effort, ask β
1, γ
1The method of position such as the situation of n=2, checking circulation then.N＞3 o'clock, in like manner.
So far, just finished the counter of igniter motor position asked.
Claims (6)
1. micro-thruster array testing table, comprise platform (8), column (9), bearing (7), base (6), bullet ball (13), piezoelectric force transducer (12), peripherals comprises miniature thruster array (11), test macro, it is characterized in that the platform (8) of placing miniature thruster array (11) is the X-shaped plate; Described column (9) has four at least, be installed respectively a jiao of miniature thruster array (11) of one end, and the other end connects by hollow bolt with X-shaped plate (8); The position at (8) four angles of X-shaped plate is provided with a Z-shaped bearing (7) of fixedlying connected with base (6) respectively, the supporting plane of one of them diagonal line bearing (7) is arranged on X-shaped plate (8) top, under two supporting planes respectively by regulating bolt (10) piezoelectric force transducer (12) that is threaded, the supporting plane of another one diagonal line bearing (7) is arranged on X-shaped plate (8) bottom, on two supporting planes respectively by regulating bolt (10) piezoelectric force transducer (12) that is threaded; (8) four positions that the angle is corresponding with piezoelectric force transducer of X-shaped plate interference respectively connect a bullet ball (13); Described bullet ball (13) comprises cylindrical bomb body and semisphere bullet, its cylindrical bomb body and X-shaped plate (8) interference fit, and the semisphere bullet withstands on the stress surface of contact of piezoelectric force transducer (12); Each piezoelectric force transducer (12) is connected respectively to test macro.
2. micro-thruster array testing table according to claim 1 is characterized in that, X-shaped plate (8) is the key-way shape hole with column (9) coupling part.
3. micro-thruster array testing table according to claim 2 is characterized in that, described key-way shape hole has 8.
4. micro-thruster array testing table according to claim 1 is characterized in that, the material of described X-shaped plate (8) is titanium alloy or aluminium alloy.
5. micro-thruster array testing table according to claim 1 is characterized in that, described X-shaped plate (8) center is empty, and reinforcement is arranged below.
6. micro-thruster array testing table according to claim 1 is characterized in that, described piezoelectric force transducer (12) is a piezoelectric quartz crystal.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010101269642A CN101813537B (en) | 2010-03-18 | 2010-03-18 | Micro-thruster array testing table |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010101269642A CN101813537B (en) | 2010-03-18 | 2010-03-18 | Micro-thruster array testing table |
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| CN101813537B CN101813537B (en) | 2011-06-22 |
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Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102261996A (en) * | 2011-04-27 | 2011-11-30 | 北京航空航天大学 | Micro jet engine test bench |
| CN102455279A (en) * | 2010-10-20 | 2012-05-16 | 北京卫星环境工程研究所 | Combined operation platform structure used for large spacecraft thermal vacuum tests |
| CN103935531A (en) * | 2014-04-15 | 2014-07-23 | 北京控制工程研究所 | Two-dimensional vector adjusting mechanism |
| CN104791136A (en) * | 2015-03-11 | 2015-07-22 | 北京控制工程研究所 | Solid micro-thruster array structure for experiments |
| CN105003358A (en) * | 2015-06-29 | 2015-10-28 | 西安航天动力测控技术研究所 | Mounting method of embedded miniature stress sensor for solid rocket engine |
| CN106441675A (en) * | 2016-11-08 | 2017-02-22 | 烟台职业学院 | Non-load-sharing piezoelectric thrust test device |
| CN107631817A (en) * | 2017-08-14 | 2018-01-26 | 中国科学院力学研究所 | A kind of micro-ox level Micro-thrust test system and method for testing |
| CN108279085A (en) * | 2018-04-02 | 2018-07-13 | 中北大学 | A kind of array of pressure sensors and pressure wave test system |
| CN109834667A (en) * | 2019-04-04 | 2019-06-04 | 北京宇航推进科技有限公司 | A kind of rocket engine sheet-beam structure ground run rack |
| CN110413015A (en) * | 2019-06-27 | 2019-11-05 | 北京控制工程研究所 | Micro- ox magnitude microthrust dynamic testboard and test method based on closed-loop control |
| CN113418711A (en) * | 2021-06-02 | 2021-09-21 | 北京机械设备研究所 | Micro-thrust measurement system and method |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS5772035A (en) * | 1980-10-23 | 1982-05-06 | Nissan Motor Co Ltd | Rocket motor testing stand |
| RU2091736C1 (en) * | 1994-09-27 | 1997-09-27 | Конструкторское бюро приборостроения | Method of measurement of rocket engine thrust momentum and test bench for its realization |
| CN101464215A (en) * | 2009-01-15 | 2009-06-24 | 大连理工大学 | Propulsion test device of piezo-electricity type rocket motor |
| CN101598616A (en) * | 2008-06-06 | 2009-12-09 | 中国科学院力学研究所 | A kind of low thrust dynamometer and measuring method of measuring based on pneumatic low thrust |
-
2010
- 2010-03-18 CN CN2010101269642A patent/CN101813537B/en not_active Expired - Fee Related
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS5772035A (en) * | 1980-10-23 | 1982-05-06 | Nissan Motor Co Ltd | Rocket motor testing stand |
| RU2091736C1 (en) * | 1994-09-27 | 1997-09-27 | Конструкторское бюро приборостроения | Method of measurement of rocket engine thrust momentum and test bench for its realization |
| CN101598616A (en) * | 2008-06-06 | 2009-12-09 | 中国科学院力学研究所 | A kind of low thrust dynamometer and measuring method of measuring based on pneumatic low thrust |
| CN101464215A (en) * | 2009-01-15 | 2009-06-24 | 大连理工大学 | Propulsion test device of piezo-electricity type rocket motor |
Cited By (17)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102455279A (en) * | 2010-10-20 | 2012-05-16 | 北京卫星环境工程研究所 | Combined operation platform structure used for large spacecraft thermal vacuum tests |
| CN102261996A (en) * | 2011-04-27 | 2011-11-30 | 北京航空航天大学 | Micro jet engine test bench |
| CN103935531A (en) * | 2014-04-15 | 2014-07-23 | 北京控制工程研究所 | Two-dimensional vector adjusting mechanism |
| CN103935531B (en) * | 2014-04-15 | 2016-01-20 | 北京控制工程研究所 | A kind of two-dimensional vector regulating mechanism |
| CN104791136A (en) * | 2015-03-11 | 2015-07-22 | 北京控制工程研究所 | Solid micro-thruster array structure for experiments |
| CN104791136B (en) * | 2015-03-11 | 2016-06-29 | 北京控制工程研究所 | Solid micro-thruster array structure is used in a kind of test |
| CN105003358A (en) * | 2015-06-29 | 2015-10-28 | 西安航天动力测控技术研究所 | Mounting method of embedded miniature stress sensor for solid rocket engine |
| CN105003358B (en) * | 2015-06-29 | 2017-01-11 | 西安航天动力测控技术研究所 | Mounting method of embedded miniature stress sensor for solid rocket engine |
| CN106441675A (en) * | 2016-11-08 | 2017-02-22 | 烟台职业学院 | Non-load-sharing piezoelectric thrust test device |
| CN106441675B (en) * | 2016-11-08 | 2019-02-26 | 烟台职业学院 | A kind of no load sharing piezoelectric type propulsion test device |
| CN107631817A (en) * | 2017-08-14 | 2018-01-26 | 中国科学院力学研究所 | A kind of micro-ox level Micro-thrust test system and method for testing |
| CN108279085A (en) * | 2018-04-02 | 2018-07-13 | 中北大学 | A kind of array of pressure sensors and pressure wave test system |
| CN108279085B (en) * | 2018-04-02 | 2020-03-10 | 中北大学 | Pressure sensor array and pressure wave test system |
| CN109834667A (en) * | 2019-04-04 | 2019-06-04 | 北京宇航推进科技有限公司 | A kind of rocket engine sheet-beam structure ground run rack |
| CN109834667B (en) * | 2019-04-04 | 2024-04-19 | 北京宇航推进科技有限公司 | Ground test stand with rocket engine plate rib structure |
| CN110413015A (en) * | 2019-06-27 | 2019-11-05 | 北京控制工程研究所 | Micro- ox magnitude microthrust dynamic testboard and test method based on closed-loop control |
| CN113418711A (en) * | 2021-06-02 | 2021-09-21 | 北京机械设备研究所 | Micro-thrust measurement system and method |
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