CN204389169U - The device of test solid fuel micro-thruster ignition characteristic and propulsive performance - Google Patents
The device of test solid fuel micro-thruster ignition characteristic and propulsive performance Download PDFInfo
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- CN204389169U CN204389169U CN201520022487.3U CN201520022487U CN204389169U CN 204389169 U CN204389169 U CN 204389169U CN 201520022487 U CN201520022487 U CN 201520022487U CN 204389169 U CN204389169 U CN 204389169U
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- 239000004449 solid propellant Substances 0.000 title claims abstract description 33
- 238000012360 testing method Methods 0.000 title claims abstract description 31
- 230000001141 propulsive effect Effects 0.000 title claims abstract description 27
- 239000000835 fiber Substances 0.000 claims abstract description 33
- 230000001360 synchronised effect Effects 0.000 claims abstract description 21
- 238000002485 combustion reaction Methods 0.000 claims abstract description 11
- 239000003380 propellant Substances 0.000 claims abstract description 7
- 238000012544 monitoring process Methods 0.000 claims description 10
- 238000005259 measurement Methods 0.000 claims description 9
- 238000012546 transfer Methods 0.000 claims description 9
- 238000004458 analytical method Methods 0.000 claims description 4
- 238000011056 performance test Methods 0.000 claims description 4
- 239000000565 sealant Substances 0.000 claims description 4
- 230000005611 electricity Effects 0.000 claims description 3
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 3
- 230000005540 biological transmission Effects 0.000 claims description 2
- 238000010438 heat treatment Methods 0.000 abstract description 4
- 238000011160 research Methods 0.000 abstract description 4
- 238000000034 method Methods 0.000 abstract description 3
- 230000006872 improvement Effects 0.000 description 6
- 230000008859 change Effects 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 4
- 238000012935 Averaging Methods 0.000 description 3
- 230000008901 benefit Effects 0.000 description 2
- 238000000295 emission spectrum Methods 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 238000010998 test method Methods 0.000 description 2
- 241000168254 Siro Species 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000004364 calculation method Methods 0.000 description 1
- 238000013481 data capture Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000003745 diagnosis Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
- VIKNJXKGJWUCNN-XGXHKTLJSA-N norethisterone Chemical compound O=C1CC[C@@H]2[C@H]3CC[C@](C)([C@](CC4)(O)C#C)[C@@H]4[C@@H]3CCC2=C1 VIKNJXKGJWUCNN-XGXHKTLJSA-N 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 238000004088 simulation Methods 0.000 description 1
- 238000009987 spinning Methods 0.000 description 1
- 230000009466 transformation Effects 0.000 description 1
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Abstract
The utility model relates to the test unit of test igniting combustion characteristics and propulsive performance, aims to provide the device of test solid fuel micro-thruster ignition characteristic and propulsive performance.The device of this test solid fuel micro-thruster ignition characteristic and propulsive performance comprises laser instrument, reactor, vacuum pump, high-speed camera, high speed temperature measurer, fiber spectrometer, data collecting card, synchronous trigger switch and computing machine, and reactor comprises withstand voltage cloche, micro-thruster fixed rack, O-ring seal, base, tensimeter, high quick pressure transducer.The utility model adopts the mode of laser ignition to light a fire to the propellant in thruster, its ignition energy, ignition temperature and heating rate and actual hot-wire ignition basically identical, but cost reduces greatly, technique simplifies greatly, and job stability is better, be applicable to very much laboratory testing research work.
Description
Technical field
The utility model is the test unit about test igniting combustion characteristics and propulsive performance, particularly tests the device of solid fuel micro-thruster ignition characteristic and propulsive performance.
Background technology
Because launch cost is low, stability, dirigibility good and be applicable to far, a series of advantage such as deep space mission, the miniaturization of spacecraft has become aerospace industry development trend.Along with the miniaturization of spacecraft, original propulsion system is difficult to the demand meeting small-sized spacecraft, and therefore, the research of micro-thruster has very urgent and important meaning.In various micro-thruster, the solid fuel propeller based on MEMS is simple, compact because having structure, without moving member, reveals the advantages such as possibility is little, has become the focus of research.The performance study of MEMS base solid fuel propeller, mainly studies for the ignition characteristic of propellant in the thruster of ad hoc structure moulding and propulsive performance.
At present, the mode being applied to realize the igniting of MEMS base solid fuel propeller is mainly heating wire igniting.But due to heating wire material expensive, and manufacture, assembling and Controlling Technology are numerous and diverse, bring great difficulty to the correlative study work in laboratory.Therefore find a kind of cheapness, the convenient sparking mode that can meet again true micro-thruster operating environment requirements is very important.
Because solid fuel micro-thruster is short for burning time, temperature, the combustion ignition characteristic such as speed, emission spectrum, thrust and the change of propulsive performance index are fast, carry out effectively monitoring very difficult to its Changing Pattern in combustion.Particularly its thrust range is very little, is generally only 1-100 milli ox, is difficult to measure fast and accurately.Therefore how test is carried out to the ignition characteristic of solid fuel micro-thruster and propulsive performance and seem particularly important.At present, the researcher of association area adopts mono-pendulum type propulsion test device to measure its thrust usually.The ultimate principle of this proving installation utilizes swing arm around the rotation of fulcrum, is gravitional force by angle of rake kinetic transformation, according to the angle calculation thrust size that swing arm is rotated.But this method of testing is by the factor serious interference such as friction, thruster mass change, and its measuring accuracy is poor, and due to thruster be move in test process, be difficult to carry out real-time combustion diagnosis to it.Therefore need to find new propulsive performance method of testing, overcome these shortcoming and defect.
Utility model content
Fundamental purpose of the present utility model is to overcome deficiency of the prior art, provides the device of test solid fuel micro-thruster ignition characteristic and propulsive performance.For solving the problems of the technologies described above, solution of the present utility model is:
The device of test solid fuel micro-thruster ignition characteristic and propulsive performance is provided, for carrying out performance test to micro-thruster, be mounted with solid propellant in micro-thruster, the device of described test solid fuel micro-thruster ignition characteristic and propulsive performance comprises laser instrument, reactor, vacuum pump, high-speed camera, high speed temperature measurer, fiber spectrometer, data collecting card, synchronous trigger switch and computing machine;
Described reactor comprises withstand voltage cloche, micro-thruster fixed rack, O-ring seal, base, tensimeter, high quick pressure transducer; Withstand voltage cloche is bell cloche, the top of withstand voltage cloche has circular hole, circular hole is used for the exit portal of connecting laser, and ensures that the exit portal of laser instrument and circular hole are tightly connected, and described laser instrument is used for the propellant in micro-thruster to be heated to more than its ignition temperature; The lower end of withstand voltage cloche is combined with base seal by O-ring seal, is provided with a gas passage in base, and gas passage is communicated with withstand voltage cloche inside and vacuum pump, and described vacuum pump is for extracting the air of withstand voltage cloche inside; A tensimeter is equipped with in the side of base, for monitoring the pressure of withstand voltage cloche inside; The upper strata of base is provided with micro-thruster fixed rack, for micro-thruster being fixed in withstand voltage cloche, a Tai Gaomin pressure transducer is provided with immediately below micro-thruster fixed rack, high quick pressure transducer is connected with data collecting card, the thrust signal that micro-thruster produces can be converted to voltage signal and transfer to data collecting card by high quick pressure transducer, and data collecting card is used for the voltage signal received being converted to digital signal and transferring to computing machine;
The contactor of described high-speed camera, high speed temperature measurer, fiber spectrometer, data collecting card and laser instrument, be connected with computing machine respectively by signal line, and calculating function utilizes synchronous trigger switch, control high-speed camera, high speed temperature measurer, fiber spectrometer, data collecting card and Laser synchronisation and start; High-speed camera, high speed temperature measurer, data collecting card and fiber spectrometer are separately positioned on the outside of reactor, for the combustion process of Real-Time Monitoring micro-thruster, and by data transfer to computing machine; Laser instrument, high-speed camera, high speed temperature measurer, fiber spectrometer also carry out physics manual triggers by synchronous trigger switch;
Described synchronous trigger switch respectively with the power supply of computing machine, laser instrument, and high-speed camera, high speed temperature measurer, fiber spectrometer outside electricity frequently trigger port association, and can manually to trigger with computing machine two kinds of mode gauge tap;
Centralized control module is provided with in described computing machine, centralized control module energy centralized displaying high-speed camera, high speed temperature measurer, fiber spectrometer, the control of data collecting card and laser instrument, the control of the paired synchronous trigger switch of union, for to laser instrument, high-speed camera, high speed temperature measurer, the start and stop of fiber spectrometer and data collecting card control, realize parameter (power simultaneously, heat time and sample frequency etc.) centralized operation that arranges, and to high-speed camera, high speed temperature measurer, fiber spectrometer, the data of data collecting card transmission carry out preserving and subsequent analysis.
As further improvement, the quick pressure transducer of described height adopts minimum range in 1 below μ N, highest measurement frequency at the pressure transducer of more than 1000Hz.
As further improvement, the power of described laser instrument can regulate, and range of adjustment is 10 ~ 150W.
As further improvement, the circular hole of described laser emitting mouth and withstand voltage cloche is connected and sealed by sealant tape.
As further improvement, the highest measurement frequency of described high-speed camera, high speed temperature measurer and fiber spectrometer is 1000Hz.
As further improvement, described centralized control module adopts WSP-D806 type logging and I-1075 type D/A converter module.
As further improvement, described reactor water placing flat, and the exit portal of laser instrument and reactor keep vertical.
Compared with prior art, the beneficial effects of the utility model are:
1, the utility model adopts the mode of laser ignition to light a fire to the propellant in thruster, its ignition energy, ignition temperature and heating rate and actual hot-wire ignition basically identical, but cost reduces greatly, technique simplifies greatly, and job stability is better, be applicable to very much laboratory testing research work.
2, the utility model controls fine adjustment laser power by computing machine, and can realize the linear change of laser power in experimentation, for experimenter provides abundanter ignition schemes.
3, the utility model can carry out the micro-thruster of different structure and the performance test of different types of propellant.
4, the reactor in the utility model is connected with vacuum pump, can simulation space actual environment, realizes the performance test of thruster under varying environment pressure condition.
5, the utility model is by advanced measurement means, achieve the quick and precisely measurement to the ignition characteristics such as temperature, burning, emission spectrum, thrust, momentum and specific impulse in micro-thruster ignition combustion event and propulsive performance index, survey frequency is up to 1000Hz.
6, the utility model adopts the propulsive performance of high quick pressure transducer to micro-thruster to test, and eliminates the measurement system error such as mobile friction, the time delay of traditional mono-pendulum type propulsion test device, improves measuring accuracy.
7, the utility model is by synchronous trigger switch, and measuring equipment and Laser synchronisation are opened, and can measure the ignition characteristic index such as the ignition delay time of micro-thruster and burning time.
8, the utility model is by computer integrated control, for safe, convenient the carrying out of test provides guarantee.
Accompanying drawing explanation
Fig. 1 is the structure of reactor figure in the utility model.
Fig. 2 is the installation drawing of the utility model test micro-thruster ignition characteristic and propulsive performance.
Reference numeral in figure is: 1 withstand voltage cloche; 2 micro-thruster fixed racks; 3 O-ring seals; 4 bases; 5 tensimeters; 6 high quick pressure transducers; 7 laser instruments; 8 sealant tapes; 9 micro-thrusters; 10 solid propellants; 11 vacuum pumps; 12 data collecting cards; 13 high-speed cameras; 14 high speed temperature measurers; 15 fiber spectrometers; 16 synchronous trigger switches; 17 computing machines.
Embodiment
Below in conjunction with accompanying drawing and embodiment, the utility model is described in further detail:
The device of test solid fuel micro-thruster ignition characteristic and propulsive performance comprises laser instrument 7, reactor, vacuum pump 11, high-speed camera 13, high speed temperature measurer 14, fiber spectrometer 15, data collecting card 12, synchronous trigger switch 16 and computing machine 17, the solid propellant 10 in laser instrument 7 pairs of micro-thrusters 9 can be utilized to heat, realize propellant fire and burning under varying environment pressure, by multiple instrument and equipment, the ignition characteristic of micro-thruster 9 and propulsive performance are observed, measure and analyzed.
Micro-thruster 9 ignition in the reactor in the utility model, as shown in Figure 1, reactor comprises withstand voltage cloche 1, micro-thruster fixed rack 2, O-ring seal 3, base 4, tensimeter 5, high quick pressure transducer 6, reactor water placing flat.Withstand voltage cloche 1 is bell, for ensureing the structural strength of reactor, is convenient to monitor the ignition characteristic of solid propellant 10 simultaneously.The top of withstand voltage cloche 1 has circular hole, and circular hole is used for the exit portal of connecting laser 7, and the exit portal of laser instrument 7 and reactor keep vertical, and ensures that the exit portal of laser instrument 7 and circular hole are tightly connected by sealant tape 8.Laser instrument 7 is for being heated to more than its ignition temperature (being generally 500-1000 DEG C) by the solid propellant 10 in micro-thruster 9, the power of laser instrument 7 can regulate, range of adjustment is 10 ~ 150W, laser instrument 7 power is generally tens watts, and the hot-wire ignition device used in ignition temperature and energy and practical application is close.The lower end of withstand voltage cloche 1 is sealed by O-ring seal 3 and base 4 and combines, and is provided with a gas passage in base 4, and gas passage is communicated with withstand voltage cloche 1 inside and vacuum pump 11, and described vacuum pump 11 is for extracting the air of withstand voltage cloche 1 inside.A tensimeter 5 is equipped with in the side of base 4, for monitoring the pressure of withstand voltage cloche 1 inside.The upper strata of base 4 is provided with micro-thruster fixed rack 2, for being fixed on by micro-thruster 9 in withstand voltage cloche 1; Micro-thruster fixed rack 2 can be used for the fixing of the micro-thruster 9 of different structure, and can change different micro-thrusters 9 as required and be fixed.Be provided with a Tai Gaomin pressure transducer 6 immediately below micro-thruster fixed rack 2, high quick pressure transducer 6 adopts minimum range in 1 below μ N, highest measurement frequency at the pressure transducer of more than 1000Hz.High quick pressure transducer 6 is connected with supporting data collecting card 12, the thrust signal that micro-thruster 9 produces can be converted to voltage signal and transfer to data collecting card 12 by high quick pressure transducer 6, and data collecting card 12 is for being converted to digital signal by the voltage signal received and transferring to computing machine 17.
As shown in Figure 2, the contactor of high-speed camera 13, high speed temperature measurer 14, fiber spectrometer 15, data collecting card 12 and laser instrument 7, be connected with computing machine 17 respectively by signal line, and computing machine 17 can utilize synchronous trigger switch 16, control high-speed camera 13, high speed temperature measurer 14, fiber spectrometer 15, data collecting card 12 and laser instrument 7 synchronous averaging.High-speed camera 13, high speed temperature measurer 14, data collecting card 12 and fiber spectrometer 15 are separately positioned on the outside of reactor, for the combustion process of Real-Time Monitoring micro-thruster 9, and by data transfer to computing machine 17, wherein, the highest measurement frequency of high-speed camera 13, high speed temperature measurer 14 and fiber spectrometer 15 all reaches 1000Hz.Laser instrument 7, high-speed camera 13, high speed temperature measurer 14, fiber spectrometer 15 also synchronously trigger by physical switch.
Synchronous trigger switch 16 specifically refers to: frequently triggers with the outside electricity of laser instrument 7 power supply, high-speed camera 13, high speed temperature measurer 14, fiber spectrometer 15 that port associates with computing machine 17 simultaneously, and the trigger switch that can control with manual and computing machine 17 two kinds of modes.
Be provided with centralized control module in computing machine 17, be made up of WSP-D806 type logging and I-1075 type D/A converter module; Centralized control module is used for controlling the start and stop of laser instrument 7, high-speed camera 13, high speed temperature measurer 14, fiber spectrometer 15 and data collecting card 12, for realizing centralized control to the optimum configurations of power, heat time and sample frequency etc., and the data that high-speed camera 13, high speed temperature measurer 14, fiber spectrometer 15, data collecting card 12 transmit are preserved and subsequent analysis.
During test, first the micro-thruster 9 filling solid propellant 10 is fixed on micro-thruster fixed rack 2, and withstand voltage cloche 1 is installed, keep it and between laser instrument 7 and base 4 after compact siro spinning technology, open vacuum pump 11, after the registration of tensimeter 5 reaches the operating mode designed in advance, circuit is connected by the sequence check switch in computing machine 17, laser tube exit portal from laser instrument 7 penetrates by laser, light the solid propellant 10 in micro-thruster 9, after solid propellant 10 is lighted, laser instrument 7 power supply cuts off automatically.Simultaneously, synchronous trigger switch 16 is opened by computing machine 17, control high-speed camera 13, high speed temperature measurer 14, fiber spectrometer 15 and laser instrument 7 synchronous averaging, enforcement monitoring is carried out to the whole combustion process of solid propellant 10, and by data transfer to computing machine 17.Simultaneously, synchronous trigger switch 16 is opened by computing machine 17, control data capture card 12 and laser instrument 7 synchronous averaging, Real-Time Monitoring is carried out to the thrust that solid propellant 10 combustion process produces, during monitoring, the thrust signal that micro-thruster 9 produces is converted to voltage signal and transfers to data collecting card 12 by high quick pressure transducer 6, and voltage signal is converted to digital signal and transfers to computing machine 17 by data collecting card 12.
Experimenter can utilize the centralized control module in computing machine 17 to realize centralized control to the start and stop of laser instrument 7, high-speed camera 13, high speed temperature measurer 14, fiber spectrometer 15 and data collecting card 12 and optimum configurations, and to observing the data obtained preserve and subsequent analysis.
Finally, it should be noted that above what enumerate is only specific embodiment of the utility model.Obviously, the utility model is not limited to above embodiment, can also have a lot of distortion.All distortion that those of ordinary skill in the art can directly derive or associate from content disclosed in the utility model, all should think protection domain of the present utility model.
Claims (7)
1. test the device of solid fuel micro-thruster ignition characteristic and propulsive performance, for carrying out performance test to micro-thruster, solid propellant is mounted with in micro-thruster, it is characterized in that, the device of described test solid fuel micro-thruster ignition characteristic and propulsive performance comprises laser instrument, reactor, vacuum pump, high-speed camera, high speed temperature measurer, fiber spectrometer, data collecting card, synchronous trigger switch and computing machine;
Described reactor comprises withstand voltage cloche, micro-thruster fixed rack, O-ring seal, base, tensimeter, high quick pressure transducer; Withstand voltage cloche is bell cloche, the top of withstand voltage cloche has circular hole, circular hole is used for the exit portal of connecting laser, and ensures that the exit portal of laser instrument and circular hole are tightly connected, and described laser instrument is used for the propellant in micro-thruster to be heated to more than its ignition temperature; The lower end of withstand voltage cloche is combined with base seal by O-ring seal, is provided with a gas passage in base, and gas passage is communicated with withstand voltage cloche inside and vacuum pump, and described vacuum pump is for extracting the air of withstand voltage cloche inside; A tensimeter is equipped with in the side of base, for monitoring the pressure of withstand voltage cloche inside; The upper strata of base is provided with micro-thruster fixed rack, for micro-thruster being fixed in withstand voltage cloche, a Tai Gaomin pressure transducer is provided with immediately below micro-thruster fixed rack, high quick pressure transducer is connected with data collecting card, the thrust signal that micro-thruster produces can be converted to voltage signal and transfer to data collecting card by high quick pressure transducer, and data collecting card is used for the voltage signal received being converted to digital signal and transferring to computing machine;
The contactor of described high-speed camera, high speed temperature measurer, fiber spectrometer, data collecting card and laser instrument, be connected with computing machine respectively by signal line, and calculating function utilizes synchronous trigger switch, control high-speed camera, high speed temperature measurer, fiber spectrometer, data collecting card and Laser synchronisation and start; High-speed camera, high speed temperature measurer, data collecting card and fiber spectrometer are separately positioned on the outside of reactor, for the combustion process of Real-Time Monitoring micro-thruster, and by data transfer to computing machine; Laser instrument, high-speed camera, high speed temperature measurer, fiber spectrometer also carry out physics manual triggers by synchronous trigger switch;
Described synchronous trigger switch respectively with the power supply of computing machine, laser instrument, and high-speed camera, high speed temperature measurer, fiber spectrometer outside electricity frequently trigger port association, and can manually to trigger with computing machine two kinds of mode gauge tap;
Centralized control module is provided with in described computing machine, the control of centralized control module energy centralized displaying high-speed camera, high speed temperature measurer, fiber spectrometer, data collecting card and laser instrument, the control of the paired synchronous trigger switch of union, for controlling the start and stop of laser instrument, high-speed camera, high speed temperature measurer, fiber spectrometer and data collecting card, realize the centralized operation to optimum configurations simultaneously, and the data of high-speed camera, high speed temperature measurer, fiber spectrometer, data collecting card transmission are preserved and subsequent analysis.
2. the device of test solid fuel micro-thruster ignition characteristic according to claim 1 and propulsive performance, it is characterized in that, the quick pressure transducer of described height adopts minimum range in 1 below μ N, highest measurement frequency at the pressure transducer of more than 1000Hz.
3. the device of test solid fuel micro-thruster ignition characteristic according to claim 1 and propulsive performance, is characterized in that, the power of described laser instrument can regulate, and range of adjustment is 10 ~ 150W.
4. the device of test solid fuel micro-thruster ignition characteristic according to claim 1 and propulsive performance, is characterized in that, the circular hole of described laser emitting mouth and withstand voltage cloche is connected and sealed by sealant tape.
5. the device of test solid fuel micro-thruster ignition characteristic according to claim 1 and propulsive performance, is characterized in that, the highest measurement frequency of described high-speed camera, high speed temperature measurer and fiber spectrometer is 1000Hz.
6. the device of test solid fuel micro-thruster ignition characteristic according to claim 1 and propulsive performance, is characterized in that, described centralized control module adopts WSP-D806 type logging and I-1075 type D/A converter module.
7. the test solid fuel micro-thruster ignition characteristic according to claim 1 to 6 any one and the device of propulsive performance, it is characterized in that, described reactor water placing flat, and the exit portal of laser instrument and reactor keep vertical.
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| CN201520022487.3U CN204389169U (en) | 2015-01-13 | 2015-01-13 | The device of test solid fuel micro-thruster ignition characteristic and propulsive performance |
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| CN201520022487.3U CN204389169U (en) | 2015-01-13 | 2015-01-13 | The device of test solid fuel micro-thruster ignition characteristic and propulsive performance |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104596768A (en) * | 2015-01-13 | 2015-05-06 | 浙江大学 | Device for testing ignition combustion characteristics and propulsive performance of solid fuel micro-thruster |
| CN105067523A (en) * | 2015-08-03 | 2015-11-18 | 南京理工大学 | Solid propellant flame segmentation device |
| CN106092587A (en) * | 2016-07-22 | 2016-11-09 | 北京航空航天大学 | A kind of ion thruster installing rack with pipeline protection device |
| CN106680612A (en) * | 2015-11-11 | 2017-05-17 | 北京卫星环境工程研究所 | Performance test device for emitter of field emission electric thruster of satellite |
| CN107860863A (en) * | 2017-10-30 | 2018-03-30 | 西安近代化学研究所 | A kind of method of testing of the high activity metal reactivity based on combustion reaction |
| CN109578170A (en) * | 2018-12-11 | 2019-04-05 | 上海新力动力设备研究所 | A kind of low pressure laser ignition test macro |
-
2015
- 2015-01-13 CN CN201520022487.3U patent/CN204389169U/en not_active Withdrawn - After Issue
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104596768A (en) * | 2015-01-13 | 2015-05-06 | 浙江大学 | Device for testing ignition combustion characteristics and propulsive performance of solid fuel micro-thruster |
| CN104596768B (en) * | 2015-01-13 | 2017-04-12 | 浙江大学 | Device for testing ignition combustion characteristics and propulsive performance of solid fuel micro-thruster |
| CN105067523A (en) * | 2015-08-03 | 2015-11-18 | 南京理工大学 | Solid propellant flame segmentation device |
| CN105067523B (en) * | 2015-08-03 | 2017-09-15 | 南京理工大学 | A kind of Flame of Solid Propellant segmenting device |
| CN106680612A (en) * | 2015-11-11 | 2017-05-17 | 北京卫星环境工程研究所 | Performance test device for emitter of field emission electric thruster of satellite |
| CN106680612B (en) * | 2015-11-11 | 2019-08-06 | 北京卫星环境工程研究所 | The performance testing device of satellite field emission electric thruster emitter |
| CN106092587A (en) * | 2016-07-22 | 2016-11-09 | 北京航空航天大学 | A kind of ion thruster installing rack with pipeline protection device |
| CN106092587B (en) * | 2016-07-22 | 2018-10-30 | 北京航空航天大学 | A kind of ion thruster mounting bracket with pipeline protective device |
| CN107860863A (en) * | 2017-10-30 | 2018-03-30 | 西安近代化学研究所 | A kind of method of testing of the high activity metal reactivity based on combustion reaction |
| CN109578170A (en) * | 2018-12-11 | 2019-04-05 | 上海新力动力设备研究所 | A kind of low pressure laser ignition test macro |
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