CN105181221A - Cold air nozzle thrust calibration device and installation method thereof - Google Patents
Cold air nozzle thrust calibration device and installation method thereof Download PDFInfo
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- CN105181221A CN105181221A CN201510616865.5A CN201510616865A CN105181221A CN 105181221 A CN105181221 A CN 105181221A CN 201510616865 A CN201510616865 A CN 201510616865A CN 105181221 A CN105181221 A CN 105181221A
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Abstract
The present invention provides a cold air nozzle thrust calibration device and an installation method thereof. The cold air nozzle thrust calibration device includes an air channel part and a testing part. The air channel part includes an air source, a pressure-reducing valve, an air capacitor, a flowmeter and a switching valve. The testing part includes a micro-miniature nozzle, a testing tool, a marble platform and a PC. An air inlet and the nozzle are mounted separately so that the accuracy of the nozzle thrust measurement is increased and the interference to the thrust measurement is eliminated, wherein, the interference is caused by the pressure change when the air enters an air pipe. The nozzle is fixed on a nozzle mounting port in a vertical screw thread fitting manner so that the accuracy of the nozzle thrust measurement is increased and the skew force interference is eliminated when a sensor measures force. The marble platform is used as a testing platform so that the stability of a nozzle force measurement tool is increased and the vibration interference is eliminated when the sensor measures force.
Description
Technical field
The present invention relates to a kind of thrust calibration, particularly a kind of cold air nozzle thrust calibration device and installation method thereof.
Background technology
Air supporting simulator can be gone out the space operation of spacecraft microgravity under space environment, zero friction by approximate simulation, can verify actual functional capability and the performance of spacecraft control intuitively.And the realization of the propelling of air supporting simulator, pitching, yawing rotation all will rely on the thrust of cold air nozzle to realize.Also have the propelling of part minitype spacecraft and gesture stability that the thrust of cold air nozzle also will be relied on to realize.Therefore, cold air nozzle dynamic and static thrust response curve is studied extremely important.
The static characteristics of cold air nozzle generally can be calculated by mathematical modeling or flow field simulation obtains, and is also more conveniently drawn by experimental test.The dynamic perfromance of cold air nozzle, namely produces or eliminates time delay of reacting force after the electromagnetic switch valve of Control Nozzle receives switch order, for more important control system.But the dynamic characteristic measuring of cold air nozzle is general more difficult, needing to coordinate with sensitive force snesor, also needing stable experiment porch to reduce vibrations to measuring the impact brought.Meanwhile, because generally sensitive force snesor all has certain requirement to the verticality of force direction, therefore how to fix cold air nozzle, the verticality ensureing itself and force snesor is also for extremely important thrust measurement.
The main method of domestic gaging nozzle thrust is strain gauge method.The thin-wall copper pipe of given shape sticks foil gauge, and the thrust of nozzle makes thin-wall copper pipe be out of shape, and foil gauge just has signal to export, and extrapolates the thrust of nozzle thus.But this kind of measurement of method to high thrust value is feasible, microminiature nozzle thrust magnitude is all generally 10mN level, measures just there is certain problem by this kind of method.Therefore, utilizing force cell directly to measure is the common method measuring microminiature nozzle thrust.But low thrust measuring technique has following difficult points and defect at present:
(1) jet pipe is directly connected with pipe adapter, tracheae, and produce in thrust process at jet pipe, the gaseous tension in tracheae and the low thrust of jet pipe are superimposed;
(2) jet pipe is when blowing, and the verticality of thrust and sensor changes;
(3) in process of the test, vibration environment is to thrust measurement result, and especially dynamic measurement results interference ratio is larger.
Summary of the invention
The object of the invention is to the above-mentioned deficiency overcoming prior art, provide a kind of cold air nozzle thrust calibration device, this cold air nozzle thrust calibration device improves the degree of accuracy of thrust calibration, achieves and to eliminate in tracheae variations in flow to the interference of nozzle thrust measurement; Improve the accuracy of thrust calibration, achieve and eliminate skew force to the interference of sensor; Improve the sensitivity of thrust calibration, achieve the real-time measurement of high sensitivity LOAD CELLS to thrust.
Above-mentioned purpose of the present invention is achieved by following technical solution:
A kind of cold air nozzle thrust calibration device, comprises air path part and part of detecting; Wherein air path part comprises source of the gas, reduction valve, air-capacitor, flowmeter and switch valve, source of the gas provides gases at high pressure for whole gas circuit, reduction valve is connected with source of the gas, realize the decompression to the gases at high pressure in gas circuit, air-capacitor is connected with reduction valve, ensures steady air current in gas circuit, flowmeter is connected with air-capacitor, carry out record to entering orifice gas flow, switch valve is connected with flowmeter, realizes the control to entering microminiature orifice gas; Part of detecting comprises microminiature nozzle, test fixture, marble plane and PC; Microminiature nozzle is arranged on test fixture, and test fixture is connected with PC, and test fixture is fixedly mounted in marble plane; Air path part is connected with part of detecting.
At above-mentioned a kind of cold air nozzle thrust calibration device, test fixture comprises LOAD CELLS, sensor installed surface, dynamometry pallet, nozzle installing port, nozzle mounting tool and air intake opening composition; Wherein nozzle installing port is positioned at nozzle mounting tool upper end, air intake opening is positioned at nozzle mounting tool side, the switch valve of air path part is connected with the air intake opening of part of detecting, sensor installed surface is positioned in marble plane, LOAD CELLS is fixedly mounted on sensor installed surface top, LOAD CELLS is connected with PC, and dynamometry pallet is positioned at LOAD CELLS top, and nozzle mounting tool is fixedly mounted on dynamometry pallet.
At above-mentioned a kind of cold air nozzle thrust calibration device, nozzle mounting tool is cubic shaped, and dynamometry pallet is disc-shape, and sensor installed surface is circular.
At above-mentioned a kind of cold air nozzle thrust calibration device, microminiature nozzle is fixedly mounted on nozzle installing port.
At above-mentioned a kind of cold air nozzle thrust calibration device, LOAD CELLS sensitivity is not less than 10mN level; The flatness of marble plane is not more than 14 μm; The requirement for horizontality of sensor installed surface upper and lower surface is not more than 2 μm; Nozzle installing port inwall and nozzle mounting tool lower surface verticality require to be not more than 2 μm.
At above-mentioned a kind of cold air nozzle thrust calibration device, the installation method of described test fixture mainly comprises the following steps:
Step (one), be fixedly mounted on sensor installed surface by LOAD CELLS level, LOAD CELLS dynamometry is towards upper;
Step (two), nozzle mounting tool is fixed on dynamometry tray upper surface home position, nozzle installing port and dynamometry pallet vertical, air intake opening and dynamometry pallet level;
Step (three), dynamometry pallet is fixed on LOAD CELLS dynamometry face;
Step (four), a whole set of test fixture are placed in marble platform and test;
Step (five), LOAD CELLS to be connected with PC.
At the scaling method of above-mentioned a kind of cold air nozzle thrust calibration device, it is characterized in that: described step (five) is when LOAD CELLS is connected with PC, conveniently PC image data, Tandem amplifier and USB collecting cassette between LOAD CELLS and PC.
The present invention compared with prior art tool has the following advantages:
(1) the innovative design of the present invention test fixture of cold air nozzle thrust calibration device, have employed design air intake opening and nozzle are installed separately, improve the degree of accuracy of nozzle thrust measurement, achieve the interference of pressure change to thrust measurement when eliminating tracheae air inlet;
(2) present invention employs method fixing for the cooperation of nozzle normal thread, improve the accuracy of nozzle thrust measurement, achieve skew force interference when eliminating sensor dynamometry;
(3) present invention employs marble platform as test platform, improve the stability of nozzle dynamometry frock, achieve vibration interference when eliminating sensor dynamometry.
Accompanying drawing explanation
Fig. 1 is the structural representation of a kind of cold air nozzle of the present invention thrust calibration device;
Fig. 2 is test fixture schematic diagram of the present invention.
Embodiment
Below in conjunction with the drawings and specific embodiments, the present invention is described in further detail:
Be illustrated in figure 1 a kind of structural representation of cold air nozzle thrust calibration device, comprise source of the gas 1, reduction valve 2, air-capacitor 3, flowmeter 4, switch valve 5, microminiature nozzle 6, test fixture 7, bearing sensor 8, marble plane 9 and PC 10 as seen from the figure.
Cold air nozzle thrust calibration device forms in two sub-sections primarily of air path part and test department.Air path part and part of detecting are coupled together by the air intake opening 15 on test fixture 7.Source of the gas 1 is connected successively with reduction valve 2, air-capacitor 3, flowmeter 4, switch valve 5, forms the air path part of cold air nozzle thrust calibration device.Source of the gas 1 provides gases at high pressure for whole gas circuit, reduction valve 2 is the high pressure air reducing in gas circuit, the working pressure at adjustment nozzle entrance place, serial connection air-capacitor 3 can ensure steady air current in gas circuit, serial connection flowmeter 4 can record the gas flow entering nozzle, and switch valve 5 can control the presence or absence entering orifice gas.The Main Function of whole air path part is exactly for microminiature nozzle provides the gas of regime flow under certain working pressure.Microminiature nozzle 6 is arranged on test fixture 7, and test fixture 7 to be placed in marble plane 9 and LOAD CELLS 8 to be connected with PC 10, they constitutes the part of detecting of thrust calibration device.
Be illustrated in figure 2 the detailed maps of test fixture 7 of the present invention, comprise sensor installed surface 11, LOAD CELLS 8, dynamometry pallet 12, nozzle installing port 13, nozzle mounting tool 14, air intake opening 15 as seen from the figure.
Test fixture 7 is made up of sensor installed surface 11, LOAD CELLS 8, dynamometry pallet 12, nozzle installing port 13, nozzle mounting tool 14, air intake opening 15.The air supply pipe of air path part, for being microminiature nozzle 6 air feed, is arranged on air intake opening 15 by air intake opening 15.Nozzle installing port 13 is for fixing microminiature nozzle 6, and nozzle 6 is arranged on nozzle installing port 13 by threaded engagement, ensures that the jet direction of nozzle 6 is vertical with LOAD CELLS 8.To the reacting force of nozzle mounting tool 14 1 equivalence vertically downward when nozzle 6 is upwards blown, LOAD CELLS 8 is for measuring the size of this reacting force.Sensor installed surface 11 is for fixing LOAD CELLS 8.Dynamometry pallet 12 is for being fixed on LOAD CELLS 8 by nozzle mounting tool 14.Marble platform 9 can reduce the interference of vibration to test, can also ensure the levelness of LOAD CELLS 8.PC 10 can control the switch of electromagnetic switch valve, by sending the presence or absence of command signal Control Nozzle inlet air flow to switch valve, gathers simultaneously and records the size of reacting force.Concrete grammar is exactly amplified by the voltage signal of LOAD CELLS 8 by signal amplifier, imports signal into PC 10 by USB collecting cassette.By real-time data acquisition program, voltage signal is converted into power, and thrust output response curve.The effect of whole part of detecting be exactly Real-time Collection and recording nozzles blow time thrust size variation.
Described mouth mounting tool 14 is cubic shaped, and dynamometry pallet 12 is disc-shape, and sensor installed surface 11 is circular.
Microminiature nozzle 6 is fixedly mounted on nozzle installing port 13.
The sensitivity of described LOAD CELLS 8 is not less than 10mN level; The flatness of marble plane 9 is not more than 14 μm; The requirement for horizontality of sensor installed surface 11 upper and lower surface is not more than 2 μm; Nozzle installing port 3 inwall and nozzle mounting tool 14 lower surface verticality require to be not more than 2 μm.
Be illustrated in figure 2 test fixture schematic diagram, test fixture 7 is installed and is mainly comprised the following steps:
Step (one), be fixedly mounted on sensor installed surface 11 by LOAD CELLS 8 level, LOAD CELLS 8 dynamometry is towards upper;
Step (two), nozzle mounting tool 14 is fixed on dynamometry pallet 12 upper surface home position, nozzle installing port 13 is vertical with dynamometry pallet 12, air intake opening 15 and dynamometry pallet 12 level, nozzle mounting tool 14 is for fixing microminiature nozzle 6, ensure that the jet direction of microminiature nozzle 6 is vertical with LOAD CELLS 8, to the reacting force of test fixture 7 one equivalence vertically downward when microminiature nozzle 6 is upwards blown, LOAD CELLS 8 is for measuring the size of this reacting force;
Step (three), dynamometry pallet 12 is fixed on LOAD CELLS 8 dynamometry face, notes the dynamometry face of protection LOAD CELLS 8 in installation process, be not applied above the pressure of range, or the pressure tilted.
Step (four), LOAD CELLS 8 to be connected with PC 10, conveniently PC 10 image data, Tandem amplifier and USB collecting cassette between LOAD CELLS 8 and PC 10, PC 10 can control the switch of electromagnetic switch valve, gathers simultaneously and records the size of reacting force.
Step (five), a whole set of test fixture 7 are placed in marble platform 9 and test, and marble plane 9 can reduce the interference of vibration to test, and ensure that the requirements such as the stability of test platform and levelness.Nozzle is arranged on nozzle installing port by threaded engagement, and air intake opening connects the air supply pipe in gas circuit.Dynamometry pallet is fixed in LOAD CELLS, ensure that the verticality in reacting force when nozzle is blown and LOAD CELLS dynamometry face.Air intake opening in the horizontal direction simultaneously, avoids the measuring error that air-flow brings.
Described step (five) is when LOAD CELLS 8 is connected with PC 10, conveniently PC 10 image data, Tandem amplifier and USB collecting cassette between LOAD CELLS 8 and PC 10, the voltage signal of LOAD CELLS is amplified by signal amplifier by part of data acquisition, imports signal into PC by USB collecting cassette.By real-time data acquisition program, voltage signal is converted into power, and thrust output response curve.
The content be not described in detail in instructions of the present invention belongs to the known technology of those skilled in the art.
Claims (7)
1. a cold air nozzle thrust calibration device, is characterized in that: comprise air path part and part of detecting, wherein air path part comprises source of the gas (1), reduction valve (2), air-capacitor (3), flowmeter (4) and switch valve (5), source of the gas (1) provides gases at high pressure for whole gas circuit, reduction valve (2) is connected with source of the gas (1), realize the decompression to the gases at high pressure in gas circuit, air-capacitor (3) is connected with reduction valve (2), ensure steady air current in gas circuit, flowmeter (4) is connected with air-capacitor (3), record is carried out to entering orifice gas flow, switch valve (5) is connected with flowmeter (4), realize the control entering microminiature nozzle (6) gas, part of detecting comprises microminiature nozzle (6), test fixture (7), marble plane (9) and PC (10), microminiature nozzle (6) is arranged on test fixture (7), and test fixture (7) is connected with PC (10), and test fixture (7) is fixedly mounted in marble plane (9), air path part is connected with part of detecting.
2. a kind of cold air nozzle thrust calibration device according to claim 1, is characterized in that: test fixture (7) comprises LOAD CELLS (8), sensor installed surface (11), dynamometry pallet (12), nozzle installing port (13), nozzle mounting tool (14) and air intake opening (15) composition, wherein nozzle installing port (13) is positioned at nozzle mounting tool (14) upper end, air intake opening (15) is positioned at nozzle mounting tool (14) side, the switch valve (5) of air path part is connected with the air intake opening (15) of part of detecting, sensor installed surface (11) is positioned in marble plane (9), LOAD CELLS (8) is fixedly mounted on sensor installed surface (11) top, LOAD CELLS (8) is connected with PC (10), dynamometry pallet (12) is positioned at LOAD CELLS (8) top, nozzle mounting tool (14) is fixedly mounted on dynamometry pallet (12).
3. a kind of cold air nozzle thrust calibration device according to claim 2, it is characterized in that: nozzle mounting tool (14) is cubic shaped, dynamometry pallet (12) is disc-shape, and sensor installed surface (11) is circular.
4. a kind of cold air nozzle thrust calibration device according to claim 1, is characterized in that: microminiature nozzle (6) is fixedly mounted on nozzle installing port (13).
5. a kind of cold air nozzle thrust calibration device according to claim 1, is characterized in that: described LOAD CELLS (8) sensitivity is not less than 10mN level; The flatness of marble plane (9) is not more than 14 μm; The requirement for horizontality of sensor installed surface (11) upper and lower surface is not more than 2 μm; Nozzle installing port (3) inwall and nozzle mounting tool (14) lower surface verticality require to be not more than 2 μm.
6. a kind of cold air nozzle thrust calibration device according to claim 1, is characterized in that: the installation method of described test fixture (7) mainly comprises the following steps:
Step (one), be fixedly mounted on sensor installed surface (11) by LOAD CELLS (8) level, LOAD CELLS (8) dynamometry is towards upper;
Step (two), nozzle mounting tool (14) is fixed on dynamometry pallet (12) upper surface home position, nozzle installing port (13) is vertical with dynamometry pallet (12), air intake opening (15) and dynamometry pallet (12) level;
Step (three), dynamometry pallet (12) is fixed on LOAD CELLS (8) dynamometry face;
Step (four), a whole set of test fixture (7) are placed in marble platform (9) and test;
Step (five), LOAD CELLS (8) to be connected with PC (10).
7. the scaling method of a kind of cold air nozzle thrust calibration device according to claim 6, it is characterized in that: described step (five) is when LOAD CELLS (8) is connected with PC (10), conveniently PC (10) image data, Tandem amplifier and USB collecting cassette between LOAD CELLS (8) and PC (10).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201510616865.5A CN105181221A (en) | 2015-09-24 | 2015-09-24 | Cold air nozzle thrust calibration device and installation method thereof |
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| CN201510616865.5A CN105181221A (en) | 2015-09-24 | 2015-09-24 | Cold air nozzle thrust calibration device and installation method thereof |
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| CN201510616865.5A Pending CN105181221A (en) | 2015-09-24 | 2015-09-24 | Cold air nozzle thrust calibration device and installation method thereof |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105651522A (en) * | 2016-04-12 | 2016-06-08 | 中国工程物理研究院总体工程研究所 | Shooting position test device for piston cooling nozzle performance test bench |
| CN109357885A (en) * | 2018-11-02 | 2019-02-19 | 天津航宇卓然科技有限公司 | A kind of discharge coefficient Intelligent Calibration system of multichannel nozzle |
| CN112284593A (en) * | 2020-10-21 | 2021-01-29 | 北京航空航天大学 | Torsional pendulum type micro-nozzle thrust measuring device |
| CN114235246A (en) * | 2021-11-15 | 2022-03-25 | 上海空间推进研究所 | Gravitational method micro-thrust measuring device and pipeline stress interference elimination method thereof |
| CN115901233A (en) * | 2022-12-12 | 2023-04-04 | 武汉智目智能技术合伙企业(有限合伙) | Spout valve and spout power testing arrangement |
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| CN103674379A (en) * | 2013-11-18 | 2014-03-26 | 北京宇航系统工程研究所 | Nozzle thrust measurement test system |
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| SU1659753A1 (en) * | 1989-07-26 | 1991-06-30 | Предприятие П/Я А-1928 | Installation for measuring thrust of inclined nozzle in multinozzle unit |
| CN1255627A (en) * | 1999-10-22 | 2000-06-07 | 中国航天工业总公司第一计量测试研究所 | Automatic measurer with low dynamic push |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105651522A (en) * | 2016-04-12 | 2016-06-08 | 中国工程物理研究院总体工程研究所 | Shooting position test device for piston cooling nozzle performance test bench |
| CN109357885A (en) * | 2018-11-02 | 2019-02-19 | 天津航宇卓然科技有限公司 | A kind of discharge coefficient Intelligent Calibration system of multichannel nozzle |
| CN112284593A (en) * | 2020-10-21 | 2021-01-29 | 北京航空航天大学 | Torsional pendulum type micro-nozzle thrust measuring device |
| CN114235246A (en) * | 2021-11-15 | 2022-03-25 | 上海空间推进研究所 | Gravitational method micro-thrust measuring device and pipeline stress interference elimination method thereof |
| CN114235246B (en) * | 2021-11-15 | 2023-11-17 | 上海空间推进研究所 | Gravity method micro-thrust measuring device and pipeline stress interference eliminating method thereof |
| CN115901233A (en) * | 2022-12-12 | 2023-04-04 | 武汉智目智能技术合伙企业(有限合伙) | Spout valve and spout power testing arrangement |
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Application publication date: 20151223 |
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