CN100429496C - Method and device for measuring jet thrust - Google Patents
Method and device for measuring jet thrust Download PDFInfo
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- CN100429496C CN100429496C CNB2006100721744A CN200610072174A CN100429496C CN 100429496 C CN100429496 C CN 100429496C CN B2006100721744 A CNB2006100721744 A CN B2006100721744A CN 200610072174 A CN200610072174 A CN 200610072174A CN 100429496 C CN100429496 C CN 100429496C
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Abstract
The invention relates to a device for measuring jet thrust which includes a guiding mechanism supported by a first bracket mounted on the base and a second bracket, and provided with a bearings group which is fixed together with the support base having a thruster of measured thrust disposed by screws thereon; A trust measurement mechanism comprising a socle girder opened an aligning hole on one end and fixed on the bracket by a fastener through the aligning hole, the top end of which is suspended and higher than the support base, a sensor adhibited on the surface of the suspension girder is electrically connected with acquisition, process and display system outside through signal lines. The measurement device for the invention is independent of operational sensation of mounting and debugging persons, so as to guaranty repetitive calibration and reproducibility of experiment measurement result, and good comparability of thrust measurement result for different operating parameters.
Description
Technical field
The present invention relates to a kind of measuring method and device thereof of jet thrust, particularly a kind of at measuring method and the device thereof of rail spacecraft attitude control with the jet thrust of track control usefulness.
Background technology
Along with development of times, space restriction ability is to a nation's security and development play more and more crucial effects.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 or the spacecraft of various uses, for reducing weight and size, raising bearing accuracy, prolonging operation life, usage space electric propulsion technology has become requisite effective way.No matter be development and national economy, national security, or following scientific research, all need to develop high efficiency space electric propulsion technology deep space.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 thruster; 3) plasma propulsion type comprises that Hall thruster, pulsed plasma thruster, magnetoplasmadynamics thruster and variable ratio are towards the magnetopasma thruster.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 thruster of kind or near the integrated performance index of practical application.
The electric propulsion thruster 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, and especially the accurate measurement to the thrust of low thrust thruster is vital.One of the characteristics that are used for the thruster of space electric propulsion are exactly that thrust is smaller, thereby one of the very crucial technology of electric propulsion thruster ground test is the measuring micro-thrust of thruster.Can not survey thrust, just can't verify the key property of thruster.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; Also have directly thruster seat force measuring method of (being that thrust direction is consistent with gravity direction) on balance, or remake the processing or the compensation of a little gravity balances on the basis of being present up; The measuring method of also useful laser interference principle.These methods all exist be provided with the debugging and alignment requirements very high, especially some needs counterweight and transfers the metering system of center of gravity, need carry out dynamometer structural design and debugging at the thrust thruster of variety classes, weight, shape, and same measuring instrument is to the thruster of same shape and weight, the subtle change that is difficult to hold in the time of also can be because of each debugging and produce the measuring error that can't estimate.In this case, proposing certain measuring principle or ergographic precision or measuring error, is nonsensical when practical application.The so difficult basic reason of surveying of electric propulsion thruster micro thrust is because ground test is to carry out in the gravity field of the earth, and the characteristics of electric propulsion thruster are the thrust that its deadweight is far longer than its generation.External existing electrical rocket is delivered to space go to measure, but such measurement is inevitable very expensive and be difficult to bear for developing electric thrust thruster.The vacuum environment of electric power system, air supply system, thruster work heating itself, measurement is also very big to the influence of thrust measurement in addition, and for this reason, people are seeking a kind of desirable high precision jet thrust measuring method always.
Summary of the invention
The objective of the invention is to be easy to generate the defective of measuring error, a kind of simple force measuring method is provided, and has provided the measurement mechanism of realizing this method in order to overcome existing dynamometry principle debugging and alignment requirements height when measuring jet thrust.
The measurement mechanism of realizing this method comprises: pedestal 15 and be vertically fixed on first support 1, second support 14 on the pedestal 15, and force measuring machine; Force measuring machine comprises that sensor 11, one ends that are connected with signal wire 13 have the semi-girder 10 of pilot hole 24, and the dynamometry that is fixed on the upper end of semi-girder 10 is propped up part 21, by pilot hole 24 semi-girder 10 is fixed on securing member 12 on the support.The upper end of described semi-girder 10 suspends and is higher than described supporting seat 3, and described sensor 11 is attached to the surface of overarm arm 10, and is electrically connected by collection, processing and the display system of signal wire 13 with the outside.Measurement mechanism is characterised in that, also comprises thruster carrying stand and stationary positioned mechanism that guiding mechanism 2, bearing pack 16, supporting seat 3 are formed; Wherein said first support 1 and the described guiding mechanism 2 of second support, 14 apical support, bearing pack 16 are by guiding mechanism 2 constrained motions, and supporting seat 3 is fixed together with bearing pack 16, and the thruster 6 of tested thrust is fixed on the supporting seat 3.
In the above-mentioned technical scheme, described sensor 11 can be the ess-strain sheet.And another kind of technical scheme is that described sensor 11 is the vortex induction displacement transducer.
In the technique scheme, bearing pack is made up of 2 above bearings, locatees mutually by guiding mechanism 2, and is connected with supporting seat 3.Make the supporting seat 3 that loads thruster 6 reach stable and balance.
In the technique scheme, guiding mechanism 2 makes bearing pack 16 move as straight line in definite direction, and moving direction is parallel with thrust direction, and the horizontal slip resistance between bearing pack 16 and the guiding mechanism 2 is less than 1mN.
In the technique scheme, load the supporting seat 3 of thruster, as the chassis of directed rectilinear translation, moving direction is vertical with the dynamometry semi-girder.
In the technique scheme, when the design of the pattern of supporting seat can be implemented in the locking thruster, make the thruster thrust direction parallel with the bearing pack moving direction.
In the technique scheme, adjust the levelness of pedestal 15, make thrust direction and gravity direction angle be equal to or slightly less than 90 degree, eliminate when thrust direction is slided additional drag by the gravity generation.
The invention has the advantages that:
1, because electric propulsion rocket thrust device and bearing pack is affixed, as long as the bearing of selecting suitable dimension and load-bearing capacity according to the weight and the size of thruster when making, the processing fit dimension is reasonable, during assembling the resistance of bearing slippage is transferred to minimum, the thruster supporting seat is just as the vehicle seat stably that is contained on the minimum slide rail of resistance, with thruster and vehicle seat when affixed, do not require the adjusting of noting thruster centre of gravity place and fuselage balance, the glide direction that only needs to guarantee thrust and linear bearing is parallel to each other, and just can realize high-precision measurement.
2, guarantee thrust (the thruster axis just) condition parallel with the bearing pack guiding mechanism, be when the design of supporting seat and support and guiding mechanism, just considered alignment restrictions when fixed according to the structure of thruster, thereby do not rely on and install and commissioning staff's operation feeling, so can not vary with each individual yet, when more not needing to install at every turn miscellaneous careful and can not guarantee repeatability calibration, so the favorable repeatability of experimental measurements, the comparability of the thrust measurement result during thruster difference operational factor is strong.
Description of drawings
Fig. 1 is the structural representation of jet thrust measurement mechanism of the present invention;
When Fig. 2 selects the ess-strain sheet for use for sensor of the present invention, the mutual relationship synoptic diagram of sensor and semi-girder;
When Fig. 3 selects the vortex induction sensor for use for sensor of the present invention, the mutual relationship synoptic diagram of sensor and semi-girder;
Fig. 4 is the system schematic of thrust calibration of the present invention and verification.
The drawing explanation
1 first support, 2 guiding mechanisms, 3 supporting seats, 4 high velocity airs, 5 arrows
6 thrusters 7 are supplied with gas circuit 8 power leads 9 tops 10 semi-girders
11 sensors, 12 securing members, 13 signal wires, 14 second supports, 15 pedestals
16 bearing pack, 21 dynamometry are propped up part 24 pilot holes 30 web members 31 force transmission elements
39 40 counterweights of 33 displacement sensing spare 37 optical fiber, 38 precision bearings
Embodiment
Be elaborated below in conjunction with the measurement mechanism of drawings and Examples to jet thrust of the present invention.
Embodiment 1:
With reference to figure 1, make the measurement mechanism of the jet thrust of playscript with stage directions invention.First support 1 and second support 14 are fixed on the pedestal 15 first support 1 and second support, 14 apical support, one guiding mechanism 2.Bearing pack 16 and guiding mechanism 2 constitute kinematic pair, and supporting seat 3 is fixed together with bearing pack 16, and the thruster 6 of tested thrust is fixed on the supporting seat 3, thereby realization and bearing pack 16 is fixing.Described supporting seat 3 is made by the good material of thermal insulation.
As shown in Figure 2, a bonding jumper is as semi-girder 10, semi-girder 10 1 ends of this bonding jumper have pilot hole 24, securing member 12 is fixed on semi-girder 10 on second support 14 by pilot hole 24, also can be fixed on first support 1, securing member 12 can be fixed on the positions different on the support, with the thrust measurement of the thruster that is fit to different size.The sensor 11 applied stress foil gauges of present embodiment, this ess-strain sheet are attached to the surface of overarm arm 10, and the ess-strain sheet is electrically connected by collection, processing and the display system of signal wire 13 with the outside, the deflection of ess-strain sheet induction overarm arm 10.
When utilizing the measurement mechanism of jet thrust of the present invention that the jet thrust of thruster is measured, thruster 6 infeeds the thruster propellant by supplying with gas circuit 7, by power lead 8 to the thruster power supply, so that propellant is heated.The nozzle of thruster 6 ejection high temperature and high speed air-flow 4 during work, simultaneously thruster is produced the thrust of direction shown in the arrow 5, as illustrated in fig. 1 and 2, the top 9 of this thrust by being fixed in thruster 6, the dynamometry that acts on the suspension end of measurement mechanism semi-girder 10 is propped up part 21.Semi-girder 10 produces deformation under the effect of thrust, ess-strain sheet induction deformation quantity, and the output electric signal also is converted to corresponding to the voltage of power size and by charactron through circuit board by signal wire 13 and is shown as the dynamometry reading.
Embodiment 2:
As shown in Figure 1, make the measurement mechanism of the jet thrust of playscript with stage directions invention.Make a pedestal 15, on pedestal 15, fix the apical support guiding mechanism 2 of first support 1 and second support, 14, the first supports 1 and second support 14.Bearing pack 16 and guiding mechanism 2 constitutes kinematic pairs, and supporting seat 3 is fixed together with bearing pack 16, the thruster 6 of tested thrust by screw retention on supporting seat 3, thereby realize fixing with bearing pack 16.Described supporting seat 3 is made by the good material of thermal insulation.As shown in Figure 2, on the end of semi-girder 10 pilot hole 24 is arranged, securing member 12 is fixed on semi-girder 10 on second support 14 by pilot hole 24, and securing member 12 can be fixed in the diverse location of second support 14, with the thrust measurement of the thruster that is fit to different size.Near the suspension end of overarm arm 10 sensor 11 is arranged, described sensor 11 adopts the vortex induction displacement transducer.
Utilize the measurement mechanism of jet thrust of the present invention that the jet thrust of thruster is measured, before measurement, as shown in Figure 3, thruster 6 is fixed by a web member 30 and an end of force transmission element 31, and the other end of force transmission element 31 is connected with displacement sensing spare 33.Described vortex induction displacement transducer should align with displacement sensing spare 33 when mounted, has certain distance between the two.During measurement, thruster 6 infeeds the thruster propellant by supplying with gas circuit 7, power to thruster by power lead 8, propellant is in thruster 6 heating and by nozzle ejection formation high temperature and high speed air-flow 4, simultaneously thruster is produced the thrust of direction shown in the arrow 5, thrust acts on semi-girder 10 by force transmission element 31, semi-girder 10 produces distortion under thrust, so that produce move parallel with the action direction of power with the displacement sensing spare 33 that force transmission element 31 connects, gap between displacement sensing spare 33 and the vortex induction sensor changes, this gap changes by the vortex induction sensor senses and is transformed to electric signal, by signal wire 13 input signal treatment circuit plates, concern the size that can obtain acting force again according to circuit board output voltage and demarcation.
Embodiment 3:
Fig. 4 is the static demarcating synoptic diagram of the measurement mechanism of jet thrust of the present invention, be formed centrally aperture in the thruster 6,200 micron diameter optical fiber, 37 1 ends are fixedly connected at the thruster spout, the other end runs through the central axis hole of aperture and electric thrust thruster 6, and from coming directly towards 9, pass in the semi-girder 10, ride at last on the precision bearing 38.The center fixation of precision bearing 38 is on axle 39, axle 39 then is fixed on the pedestal 15 of measurement mechanism, optical fiber is installed near an end of precision bearing 38 can unload counterweight 40, with identical as shown in arrow 5 the acting on the semi-girder 10 of thrust of the gravity of counterweight 40 size, sensor 11 detection effect stressed on semi-girder 10.The acting force that contrast records via sensor and the gravity of counterweight 40 can be demarcated the measurement mechanism of jet thrust of the present invention.
Claims (6)
1, a kind of measurement mechanism of jet thrust comprises: pedestal (15) and be vertically fixed on first support (1), second support (14) on the pedestal (15), and force measuring machine; Force measuring machine comprises the sensor (11) that is connected with signal wire (13), one end has the semi-girder (10) of pilot hole (24), the dynamometry that is fixed on the upper end of semi-girder (10) is propped up part (21), by pilot hole (24) semi-girder (10) is fixed on securing member (12) on the support; The upper end suspension of described semi-girder (10) also is higher than described supporting seat (3), and described sensor (11) is attached to the surface of overarm arm (10) and is electrically connected by collection, processing and the display system of signal wire (13) with the outside; It is characterized in that, also comprise thruster carrying stand and stationary positioned mechanism that guiding mechanism (2), bearing pack (16), supporting seat (3) are formed; Wherein said first support (1) and the described guiding mechanism of second support (14) apical support (2), bearing pack (16) is by guiding mechanism (2) constrained motion, supporting seat (3) is fixed together with bearing pack (16), and the thruster of tested thrust (6) is fixed on the supporting seat (3).
2, the measurement mechanism of jet thrust according to claim 1 is characterized in that: bearing pack is made up of 2 above bearings, locatees mutually by guiding mechanism, and is connected with supporting seat.
3, the measurement mechanism of jet thrust according to claim 2, it is characterized in that: guiding mechanism makes bearing pack move as straight line in definite direction, moving direction is parallel with thrust direction, and the horizontal slip resistance between bearing pack and the guiding mechanism is less than 1mN.
4, the measurement mechanism of jet thrust according to claim 2 is characterized in that: the described supporting seat that loads thruster is the chassis of directed rectilinear translation, and moving direction is vertical with the dynamometry semi-girder.
5, the measurement mechanism of jet thrust according to claim 2 is characterized in that: when the pattern design of supporting seat can be implemented in the locking thruster, make the thruster thrust direction parallel with the bearing pack moving direction.
6, the measurement mechanism of jet thrust according to claim 1, it is characterized in that: the horizontal adjusting mechanism of adjusting pedestal, make thrust direction and gravity direction angle be equal to or slightly less than 90 degree, eliminate mechanism's additional drag by the gravity generation when thrust direction is slided.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2006100721744A CN100429496C (en) | 2006-04-14 | 2006-04-14 | Method and device for measuring jet thrust |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2006100721744A CN100429496C (en) | 2006-04-14 | 2006-04-14 | Method and device for measuring jet thrust |
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| CN101055215A CN101055215A (en) | 2007-10-17 |
| CN100429496C true CN100429496C (en) | 2008-10-29 |
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| CNB2006100721744A Expired - Fee Related CN100429496C (en) | 2006-04-14 | 2006-04-14 | Method and device for measuring jet thrust |
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