CN104535256A - Measuring device for measuring micro thrust - Google Patents
Measuring device for measuring micro thrust Download PDFInfo
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- CN104535256A CN104535256A CN201410818411.1A CN201410818411A CN104535256A CN 104535256 A CN104535256 A CN 104535256A CN 201410818411 A CN201410818411 A CN 201410818411A CN 104535256 A CN104535256 A CN 104535256A
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Abstract
The invention discloses a measuring device for measuring micro thrust. The measuring device for measuring micro thrust comprises a target system, a displacement sensor system and a target mounting block, wherein the target system comprises a target, an elastic beam and vertical angle aluminum; the displacement sensor system comprises a displacement sensor and a sensor mounting rod. In the target system, the elastic beam and the target mounting block are connected and located through the right-angle aluminum, and therefore the perpendicularity of the elastic beam is guaranteed; the target is mounted at the bottom end of the elastic beam. In the displacement sensor system, the sensor mounting rod is vertically arranged, and the top end of the sensor mounting rod is fixed to the bottom face of the target mounting block; the bottom end of the sensor mounting rod is provided with the displacement sensor through a sensor mounting plate, so that the measuring end of the displacement sensor is aligned with the middle of the elastic beam. The measuring device for measuring micro thrust has the advantages that integration of the whole measuring device is achieved through the target mounting block, so the distance between the measuring device and an engine can be measured conveniently, and even continuous and automatic adjustment can be conducted in the measuring process.
Description
Technical field
The invention belongs to space micro thrust thruster technical field, specifically, being a kind of measurement mechanism for measuring micro-thrust, is a part for measuring micro-thrust system.
Background technology
Along with the development of electric propulsion technology, increasing electric thruster is devised, but the thrust of a lot of electric thruster is all mN level, and the method that normal thrust is measured is difficult to accurately measure so small thrust.And thrust is a very important parameter of thruster, if cannot determine thrust, some important performance parameters of thruster, such as specific impulse also cannot be determined, this can bring very burden for the practical application of thruster.In order to accurately measure the thrust of electric thruster, measuring micro-thrust system has been devised.
Measuring micro-thrust system can be divided into directly to be measured and indirect inspection two kinds.In general directly measure simpler in principle, design comparison is easy, measurement result is also more reliable, and the measuring system of " a kind of Thrust Measuring System for thrust engine with tiny space " by name that such as BJ University of Aeronautics & Astronautics develops just belongs to the one directly measured.But directly measure and require thruster to be directly installed in the moving frame of measuring system, and complementary field plasma thruster quality is large, complex structure, be only used for providing the mass of coil of complementary field just more than 50kg, and during engine operation, need 4 water routes, tunnel, 2 tunnel gas circuits and 4 road circuit.If carry out measurement by direct method engine and coil to be all arranged on thrust frame, also will ensure that the water route of engine and circuit do not cause interference to measurement, this is difficult to realize simultaneously.In view of complementary field plasma thruster quality is large, baroque feature, is difficult to adopt existing direct measuring system to carry out thrust measurement to it.Comparatively ideal mode adopts indirect thrust measurement.
Just complicated engine system can be separated with measuring system during indirect inspection, measuring system only needs to test the plume of engine ejection.According to available data, domestic Tsing-Hua University developed the target method thrust-measuring device for micro-nozzle device, and the mounting means that this device hits is suspension type, during measurement, target is considered as the particle of single pendulum.Use the prerequisite of Pendulum Model be the suspender of target length relative to target surface characteristic length enough large, so this measurement mechanism needs larger space, and the target hanging installation certainly exists a rotating shaft, the force of sliding friction of rotating shaft place can have a certain impact to measurement result.And this measurement mechanism for thruster be a kind of miniature cold air thruster, the combustion gas of ejection is nitrogen, and temperature is lower, and the ejection of complementary field plasma thruster is the plume of high temperature, and operating mode is very severe.Sensor in addition for displacement measurement in this system is eddy current displacement sensor, and this sensor is difficult to normally work in the strong electromagnetic environment of complementary field plasma thruster plume.There is the throwing target method thrust-measuring device for ion thruster abroad, but the method for external throwing target method measurement mechanism laser reflection when measuring the displacement of target, and this method is easily subject to the interference of the high light that engine sends.And this system hits and displacement measuring device separates, the position of each running target all needs again to demarcate thrust frame.So these devices are all not suitable for the thrust measurement of complementary field plasma thruster.
Summary of the invention
According to the problems referred to above, the present invention, specially for complementary field plasma thruster, designs a kind of measurement mechanism for measuring micro-thrust, as the core of throwing target method measuring micro-thrust system,
The present invention is used for the measurement mechanism of measuring micro-thrust, comprises target system, displacement transducer system and target mounting blocks; Wherein, target system comprises target, elastic beam and vertical aluminum corner brace; Displacement transducer system comprises displacement transducer, sensor mounting rod and sensor installing plate;
In described target system, vertical aluminum corner brace is the cross section be made up of transverse slat and stringer board is L-type aluminum component; The lower surface of transverse slat and target mounting blocks is fitted, and transverse slat end face realizes the location on fore-and-aft direction by the positioning step that target mounting blocks designs; The lateral surface of stringer board has vertical detent; Elastic beam and detent are equipped with in detent, and the location realizing elastic beam is fixed; And make elastic beam top withstand target mounting blocks bottom surface; Elastic beam bottom is provided with target; In institute's displacement sensors system, sensor mounting rod is vertically arranged, and top and target mounting blocks bottom surface are fixed; Sensor mounting rod bottom is provided with displacement transducer by sensor installing plate, and the measurement of displacement transducer is rectified in the middle part of elastic beam.
Applying when thrust-measuring device of the present invention is measured is fixed on target mounting blocks on the mobile platform of external displacement mechanism, utilize target to bear the shock of engine plume, because target and elastic beam are connected, and the stiffness coefficient of elastic beam is less, easily bend, therefore will there is obvious movement in target after being subject to plume and clashing into.The displacement transducer being positioned at target rear is used to the displacement of measuring elastic beam generation; Displacement transducer can measure himself to the spacing between elastic beam, just can measure the displacement of elastic beam like this when elastic beam bends.Because engine plume has certain decay in the process of spraying, so can by measuring the thrust at diverse location place, the then value of the true thrust of com-parison and analysis.
Advantage of the present invention is:
1, thrust-measuring device of the present invention, the integration whole measurement mechanism being realized by target mounting blocks, the spacing adjusted like this between measurement mechanism and engine is just very convenient, even automatically can adjust continuously in measuring process;
2, thrust-measuring device of the present invention, the mobile platform of the meeting of target mounting blocks and a displacement mechanism is connected in use, whole like this measurement mechanism just can move very easily, relative position can also be kept constant with timer various components inside, as long as this just makes once to demarcate the reliability that just can ensure measurement result in whole experimentation on pretreatment;
3, thrust-measuring device of the present invention, high-intensity magnetic field is had around when considering that complementary field plasma thruster works, and have a lot of charged particle in the plume of its ejection, so engine environment has stronger electromagnetic field, the electric vortex type displacement sensor crossed of prerequisite be difficult to normal work under such conditions, therefore select laser position sensors to measure, the impact himself be subject to can be ignored;
4, thrust-measuring device of the present invention, consider that target is in plume center, temperature can be higher, and laser sensor is at high temperature cisco unity malfunction, lower for the temperature of sensor present position after measurement point moves, also be convenient to carry out other thermal protections to sensor, what therefore the test point of displacement transducer was selected is elastic beam instead of target surface simultaneously;
5, thrust-measuring device of the present invention, target adopts aluminum alloy framework good rigidity, and quality is little; Adopt copper coin energy high temperature resistant, and sputtering amount is little when Ions Bombardment, and then makes measurement sensitiveer.
Accompanying drawing explanation
Fig. 1 is measurement mechanism one-piece construction schematic diagram of the present invention;
Fig. 2 is that measurement mechanism of the present invention hits mounting blocks structural representation;
Fig. 3 is sensor mounting rod structural representation in measurement mechanism of the present invention;
Fig. 4 is that in measurement mechanism of the present invention, top board structure schematic diagram installed by sensor;
Fig. 5 is vertical angle constructed of aluminium schematic diagram in measurement mechanism of the present invention.
In figure:
1-target system 2-displacement transducer system 3-target mounting blocks
The vertical aluminum corner brace of 101-target 102-elastic beam 103-
104-positioning step 105-detent 201-displacement transducer
202-sensor installing plate 203-displacement transducer 204-detent
205-shoulder hole
Embodiment
Below in conjunction with accompanying drawing, the invention will be further described.
The present invention is used for the measurement mechanism of measuring micro-thrust, comprises target system 1, displacement transducer system 2 and target mounting blocks 3, as shown in Figure 1; Wherein, target system 1 comprises target 101, elastic beam 102 and vertical aluminum corner brace 103; Displacement transducer system 2 comprises displacement transducer 201, sensor mounting rod 202 and sensor installing plate 203; Target mounting blocks 3 is installation foundation of target system 1 and sensing system 2, fixing between the mobile platform being used for realizing both target system 1 and sensing system 2 and external displacement mechanism.
In described target system 1, vertical aluminum corner brace 103 is the cross section be made up of transverse slat and stringer board is L-type aluminum component, and as shown in Figure 2, what be used for realizing between elastic beam 102 with target mounting blocks 3 is relative fixing.The transverse slat of vertical aluminum corner brace 103 and the lower surface of target mounting blocks 3 are fitted, and fitting in positioning step 104 side that transverse slat end face and target mounting blocks 3 design, realizes vertical aluminum corner brace 103 location upwards, front and back on target mounting blocks 3, as shown in Figure 3.The lateral surface of stringer board has vertical detent 204, be used for positioning elastic beam 102, as shown in Figure 2, elastic beam 102 and detent 204 are equipped with in detent 204, realize the location on elastic beam 102 fore-and-aft direction and left and right directions, by screw by fixing between elastic beam 102 and stringer board; And make elastic beam 102 top withstand target mounting blocks bottom surface, realize the location of elastic beam in the vertical direction, now, by screw by fixing between transverse slat and target mounting blocks 3, realize fixing between elastic beam 102 and target mounting blocks 3, and the verticality of elastic beam 102 can be ensured by vertical aluminum corner brace 103 and positioning step 104.Elastic beam 102 bottom is provided with target 101; The covering skeleton construction that target 101 is made up of copper coin and aluminum alloy framework; Skeleton is fixed on elastic beam 102 bottom; Copper coin is vertically arranged, and is fixed on skeleton.Above-mentioned elastic beam 102 carries out thermal protection by temperature barrier, prevents hot environment during engine operation from beam temperature is raised, causes the change of elasticity coefficient, even have influence on thrust measurement because of overheated generation thermal deformation.
In institute's displacement sensors system 2, sensor mounting rod 201 is used for connection bit displacement sensor 203 and target mounting blocks 3; Sensor mounting rod 201 is cylindrical bar, and diameter is comparatively large, and stiffness coefficient is much larger than the stiffness coefficient of elastic beam 102; Therefore, can think that the mobile platform of displacement transducer 203 and external displacement mechanism is rigidly connected.Sensor mounting rod 201 is vertically arranged, and top is stretched in fixing slotted eye that target mounting blocks 3 bottom surface sidewall is offered, is fitted in end face and fixing slotted eye bottom surface, realizes the location of the vertical direction of sensor mounting rod 201.Sensor mounting rod 201 top sidewall has detent 204, detent 204 is screwed into by the fixed threaded hole offered by target mounting blocks 3 side of spiral shell, hold out against in sensor mounting rod 201 top and detent 204, realize fixing between sensor mounting rod 201 and target mounting blocks 3.Described sensor mounting rod 201 is connected by sensor installing plate 202 with between displacement transducer 203, sensor mounting rod 201 bottom is provided with displacement transducer 201 by sensor installing plate 202, and the fore-and-aft direction position of displacement transducer is adjusted, concrete mode is: sensor mounting rod 201 bottom end face has threaded hole vertically, sensor installing plate 202 center has bar shaped shoulder hole 205, pass bar shaped shoulder hole 205 by screw by below sensor installing plate 203, screw thread is connected with sensor mounting rod 202 bottom threaded hole.Installation position displacement sensor 201 on sensor installing plate 203 lower surface; Thus, the position at fore-and-aft direction that can realize displacement transducer 201 by adjusting the position of screw residing for shoulder hole 205 adjusts.Upper displacement sensors 201 adopts laser displacement sensor, require there is suitable gap between measured object and sensor during this working sensor, and Laser emission window will just in the middle part of elastic beam, Laser emission direction is perpendicular to target, and launch window will remain on about 35mm to the distance of elastic beam; And the sectional area of displacement transducer 201 on plume direction is less, its area is only 5% of target, and the position residing for displacement transducer 201 is away from the central area of plume, thus, is negligible in the displacement of the effect bottom offset sensor 201 of plume.
Applying when thrust-measuring device of the present invention is measured is fixed on target mounting blocks 3 on the mobile platform of external displacement mechanism, utilize target 101 to bear the shock of engine plume, because target 101 and elastic beam 102 are connected, and the stiffness coefficient of elastic beam 102 is less, easily bend, therefore will there is obvious movement in target 101 after being subject to plume and clashing into.The displacement transducer 201 being positioned at target 101 rear is used to the displacement of measuring elastic beam 102 generation; Displacement transducer 201 can measure the spacing himself arrived between preceding object thing (elastic beam 102), just can measure the displacement of elastic beam 102 like this when elastic beam 102 bends.Because engine plume has certain decay in the process of spraying, so can by measuring the thrust at diverse location place, the then value of the true thrust of com-parison and analysis.
Claims (6)
1. for a measurement mechanism for measuring micro-thrust, it is characterized in that: comprise target system, displacement transducer system and target mounting blocks; Wherein, target system comprises target, elastic beam and vertical aluminum corner brace; Displacement transducer system comprises displacement transducer, sensor mounting rod;
In described target system, vertical aluminum corner brace is the cross section be made up of transverse slat and stringer board is L-type aluminum component; The lower surface of transverse slat and target mounting blocks is fitted, and transverse slat end face realizes the location on fore-and-aft direction by the positioning step that target mounting blocks designs; The lateral surface of stringer board has vertical detent; Elastic beam and detent are equipped with in detent, and the location realizing elastic beam is fixed; And make elastic beam top withstand target mounting blocks bottom surface; Elastic beam bottom is provided with target; In institute's displacement sensors system, sensor mounting rod is vertically arranged, and top and target mounting blocks bottom surface are fixed; Sensor mounting rod bottom is provided with displacement transducer by sensor installing plate, and the measurement of displacement transducer is rectified in the middle part of elastic beam.
2. a kind of measurement mechanism for measuring micro-thrust as claimed in claim 1, is characterized in that: described elastic beam and sensor carry out thermal protection by temperature barrier.
3. a kind of measurement mechanism for measuring micro-thrust as claimed in claim 1, it is characterized in that: described sensor mounting rod bottom end face has threaded hole vertically, sensor installing plate center has bar shaped shoulder hole, pass bar shaped shoulder hole by screw by below sensor installing plate, be threaded with sensor mounting rod bottom threaded hole; Thus, the position at fore-and-aft direction that can realize displacement transducer by adjusting the position of screw residing for shoulder hole adjusts.
4. a kind of measurement mechanism for measuring micro-thrust as claimed in claim 1, is characterized in that: institute's displacement sensors adopts laser displacement sensor.
5. a kind of measurement mechanism for measuring micro-thrust as claimed in claim 1, is characterized in that: the measuring junction of institute's displacement sensors is 35mm to the distance of elastic beam.
6. a kind of measurement mechanism for measuring micro-thrust as claimed in claim 1, is characterized in that: the sectional area of institute's displacement sensors is 5% of target.
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| CN201410818411.1A CN104535256B (en) | 2014-12-24 | 2014-12-24 | Measuring device for measuring micro thrust |
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| CN201410818411.1A CN104535256B (en) | 2014-12-24 | 2014-12-24 | Measuring device for measuring micro thrust |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105784232A (en) * | 2016-03-24 | 2016-07-20 | 北京航空航天大学 | Micro thrust measurement device with damping system |
| CN106525311A (en) * | 2016-12-16 | 2017-03-22 | 哈尔滨工业大学 | Electric-thruster specific impulse measurement method and system thereof |
| CN107515095A (en) * | 2017-08-24 | 2017-12-26 | 北京航空航天大学 | A kind of target target assembly and suitable for milli ox level vacuum plume aerodynamic force system |
| CN107543642A (en) * | 2017-08-24 | 2018-01-05 | 北京航空航天大学 | A kind of device and milli ox level vacuum plume aerodynamic force system of target method measurement electric thruster thrust |
| CN110333019A (en) * | 2019-07-03 | 2019-10-15 | 北京航空航天大学 | It is a kind of for measuring the pressure probe and measuring system of electric thruster dynamic pressure performance |
| CN111964912A (en) * | 2020-09-01 | 2020-11-20 | 北京航空航天大学 | Calibration device and thrust test system |
| CN111964828A (en) * | 2020-07-29 | 2020-11-20 | 北京机械设备研究所 | Device and method for measuring thrust and specific impulse of micro-electric thruster |
| CN112268704A (en) * | 2020-10-13 | 2021-01-26 | 西北工业大学 | Device and method for combined measurement of thrust flow and current of electric thruster |
| CN112326253A (en) * | 2020-10-28 | 2021-02-05 | 哈尔滨工业大学 | Thrust vector eccentricity diagnostic device |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH07120334A (en) * | 1993-10-21 | 1995-05-12 | Nippon Seiko Kk | Apparatus for measuring thrust load at rotary supporting part |
| CN1916580A (en) * | 2006-07-31 | 2007-02-21 | 北京航空航天大学 | System for measuring thrust suitable to thrust engine with tiny space |
| CN101514927A (en) * | 2009-03-20 | 2009-08-26 | 北京航空航天大学 | Elastic micro-Newton level low thrust measuring system |
| CN102072790A (en) * | 2010-11-16 | 2011-05-25 | 北京航空航天大学 | Device for measuring micro impulse |
| CN103712723A (en) * | 2013-12-19 | 2014-04-09 | 江苏大学 | Laser cavitation jet flow force impact effect detecting method and apparatus |
-
2014
- 2014-12-24 CN CN201410818411.1A patent/CN104535256B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH07120334A (en) * | 1993-10-21 | 1995-05-12 | Nippon Seiko Kk | Apparatus for measuring thrust load at rotary supporting part |
| CN1916580A (en) * | 2006-07-31 | 2007-02-21 | 北京航空航天大学 | System for measuring thrust suitable to thrust engine with tiny space |
| CN101514927A (en) * | 2009-03-20 | 2009-08-26 | 北京航空航天大学 | Elastic micro-Newton level low thrust measuring system |
| CN102072790A (en) * | 2010-11-16 | 2011-05-25 | 北京航空航天大学 | Device for measuring micro impulse |
| CN103712723A (en) * | 2013-12-19 | 2014-04-09 | 江苏大学 | Laser cavitation jet flow force impact effect detecting method and apparatus |
Non-Patent Citations (1)
| Title |
|---|
| 汤海滨等: "微推力全弹性测量装置", 《推进技术》 * |
Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105784232A (en) * | 2016-03-24 | 2016-07-20 | 北京航空航天大学 | Micro thrust measurement device with damping system |
| CN105784232B (en) * | 2016-03-24 | 2019-05-03 | 北京航空航天大学 | A kind of device for measuring micro-thrust with damping system |
| CN106525311A (en) * | 2016-12-16 | 2017-03-22 | 哈尔滨工业大学 | Electric-thruster specific impulse measurement method and system thereof |
| CN107543642A (en) * | 2017-08-24 | 2018-01-05 | 北京航空航天大学 | A kind of device and milli ox level vacuum plume aerodynamic force system of target method measurement electric thruster thrust |
| CN107515095B (en) * | 2017-08-24 | 2018-09-18 | 北京航空航天大学 | A kind of target target assembly and it is suitable for milli ox grade vacuum plume aerodynamic force system |
| CN107543642B (en) * | 2017-08-24 | 2018-09-21 | 北京航空航天大学 | A kind of target method measures the device and milli ox grade vacuum plume aerodynamic force system of electric thruster thrust |
| CN107515095A (en) * | 2017-08-24 | 2017-12-26 | 北京航空航天大学 | A kind of target target assembly and suitable for milli ox level vacuum plume aerodynamic force system |
| CN110333019A (en) * | 2019-07-03 | 2019-10-15 | 北京航空航天大学 | It is a kind of for measuring the pressure probe and measuring system of electric thruster dynamic pressure performance |
| CN111964828A (en) * | 2020-07-29 | 2020-11-20 | 北京机械设备研究所 | Device and method for measuring thrust and specific impulse of micro-electric thruster |
| CN111964828B (en) * | 2020-07-29 | 2022-03-29 | 北京机械设备研究所 | Device and method for measuring thrust and specific impulse of micro-electric thruster |
| CN111964912A (en) * | 2020-09-01 | 2020-11-20 | 北京航空航天大学 | Calibration device and thrust test system |
| CN111964912B (en) * | 2020-09-01 | 2021-09-17 | 北京航空航天大学 | Calibration device and thrust test system |
| CN112268704A (en) * | 2020-10-13 | 2021-01-26 | 西北工业大学 | Device and method for combined measurement of thrust flow and current of electric thruster |
| CN112326253A (en) * | 2020-10-28 | 2021-02-05 | 哈尔滨工业大学 | Thrust vector eccentricity diagnostic device |
| CN112326253B (en) * | 2020-10-28 | 2022-08-16 | 哈尔滨工业大学 | Thrust vector eccentricity diagnostic device |
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