CN108303206A - Simulate the microthruster Thrust Measuring System under vacuum environment - Google Patents
Simulate the microthruster Thrust Measuring System under vacuum environment Download PDFInfo
- Publication number
- CN108303206A CN108303206A CN201710017540.4A CN201710017540A CN108303206A CN 108303206 A CN108303206 A CN 108303206A CN 201710017540 A CN201710017540 A CN 201710017540A CN 108303206 A CN108303206 A CN 108303206A
- Authority
- CN
- China
- Prior art keywords
- microthruster
- vacuum
- thrust
- right angle
- hole
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
- G01L5/00—Apparatus for, or methods of, measuring force, work, mechanical power, or torque, specially adapted for specific purposes
- G01L5/12—Apparatus for, or methods of, measuring force, work, mechanical power, or torque, specially adapted for specific purposes for measuring axial thrust in a rotary shaft, e.g. of propulsion plants
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Combustion & Propulsion (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Measuring Fluid Pressure (AREA)
Abstract
The invention discloses the microthruster Thrust Measuring Systems under a kind of simulation vacuum environment, including vacuum thrust measuring device (1), data processor (2), gas cylinder (3), vacuum pump (4), thrust pickup (9), microthruster (20)；Thrust pickup (9) is fixed on vacuum thrust measuring device (1) bottom, right angle adapter (10) is fixedly mounted thereon, one end of right angle adapter (10) is perpendicularly fixed at the top of microthruster (20)；Hose (19) connects gas cylinder (3), and the other end stretches into right angle adapter (10) connection microthruster (20)；Microthruster (20) sprays gas and generates thrust, thrust pickup (9) measures thrust data and is transferred to data processor (2), by measuring microthruster (20) thrust magnitude and ambient value under different vacuum degrees, after experimental data is carried out Function Fitting reckoning, it can show that the actual thrust value under vacuum condition, measurement result are more accurate, objective.
Description
Technical field
The invention belongs to Micromass cell culture technical field, the microthruster thrust under especially a kind of simulation vacuum environment is surveyed
Amount system.
Background technology
Microthruster is a kind of low thrust gesture stability power plant applied to fields such as aerospaces, general using empty
The compressed gas such as gas, nitrogen, helium are as propellant.During the research and development of micro-thruster, thrust measurement technology plays
One vital effect, wherein Thrust Measuring System under simulation vacuum environment can it is most objective, precisely measure out
Thrust size in the case of microthruster real work.
Currently, microthruster Thrust Measuring System generally uses balance-type type or full elastic construction to measure microthrust.
Such as Chinese invention patent (patent No. CN200610089041) discloses a kind of pushing away suitable for thrust engine with tiny space
Force measuring system, it carries out thrust measurement using full elastic construction to electric arc microthruster, and propellant pipeline uses stainless steel tube
It is larger to Micromass cell culture interference, and system structure is complicated, it is inconvenient for operation.Chinese invention patent (the patent No.
CN200910312194 a kind of device for measuring micro-thrust) is disclosed, it is overcome in propulsion system using balance-type type structure and is supplied
The influence that air pipe deformation generates thrust measurement, but without carrying out structure design for the thrust measurement under vacuum environment,
The thrust size under vacuum environment can not accurately be measured.
Invention content
It is an object of the invention to establish a kind of experimental system for simulating progress microthruster thrust measurement under vacuum environment.
The Thrust Measuring System can simulate the vacuum environment of aerospace microthruster real work, directly be surveyed using force snesor
Microthruster thrust magnitude and the ambient value under different vacuum degrees are measured, after experimental data is calculated by Function Fitting, can be obtained
Go out the actual thrust value under vacuum condition, measurement result is more accurate, objective, credible.
The present invention is a kind of microthruster Thrust Measuring System simulated under vacuum environment, including vacuum thrust measurement dress
It sets, data processor, gas cylinder, vacuum pump, vacuum pressure sensor, thrust pickup, right angle adapter, vacuum pump connect
Head, pressure release valve union, relief valve, power cord connector, signal wire joint, hose coupling, microthruster power cord, probe power
Line, signal wire, hose, microthruster, power supply；
Wherein, the vacuum thrust measuring device includes the vacuum cavity of open top, for sealing at the top of vacuum cavity
The sealing cover of opening, the pedestal for being fixed on cavity bottom, vacuum cavity outer wall reserved through hole are respectively used to installation vacuum pump and connect
Head, pressure release valve union, power cord connector, signal wire joint, hose coupling.
The thrust pickup is fixed on the base, and top is fixedly connected with right angle adapter, fixed at the top of microthruster
It is connected to an interface of right angle adapter, top down is perpendicular to the bottom surface of vacuum cavity；Hose passes through right angle adapter
Another interface stretch into connection microthruster, the other end is stretched out from preformed hole via hose coupling to be connect with gas cylinder, height
Air bottle is by hose to microthruster output high-pressure gas to generate thrust；
The vacuum pump is connect by vacuum pump adapter with vacuum cavity, is used for cavity vacuum state；Relief valve
It is mounted on pressure release valve union with vacuum pressure sensor, removes and measure microthruster for letting out gas is discharged in vacuum cavity
Generated environmental pressure；
The microthruster power cord and sensor power supply line are stretched into via power cord connector in vacuum cavity respectively to be connected
Microthruster and thrust pickup, power supply are used for microthruster power supply and thrust pickup power supply；Signal wire is via signal wire
Connector stretches into and connects thrust pickup in vacuum cavity, data processor of the other end connection for acquisition process measurement data.
Compared with prior art, advantages of the present invention is：
(1) present invention uses direct measuring method, simulates vacuum experiment environment, and the thrust generated to microthruster is surveyed
Amount, measurement result are more accurate objective；
(2) it uses right angle adapter to ensure that the installation site of hose is vertical with microthruster axis, so that hose is pressurized and generate
Additional force direction it is consistent with force sensor measuring thrust direction, reduce experimental error.
(3) good airproof performance can extract room air out in very short time, reach the vacuum degree of requirement of experiment, pass through
Relief valve accurately adjusts vacuum degree in vacuum cavity, measures the thrust magnitude under different vacuum degrees, by analyzing thrust magnitude variation rule
Rule carries out Function Fitting to experimental data and extrapolates vacuum thrust.
Description of the drawings
Fig. 1 is the general illustration of invention.
Fig. 2 is the front view of vacuum thrust measuring device 1 of the present invention.
Fig. 3 is the front view of vacuum cavity 5 described in the specific embodiment of the invention.
Fig. 4 is the 3 plenum system schematic diagram of gas cylinder described in the specific embodiment of the invention.
Specific implementation mode
In the following, in conjunction with attached drawing 1~4, the specific implementation mode to the present invention is expanded on further.
The present invention is a kind of microthruster Thrust Measuring System simulated under vacuum environment, including vacuum thrust measuring device
1, data processor 2, gas cylinder 3, vacuum pump 4, vacuum pressure sensor 8, thrust pickup 9, right angle adapter 10, vacuum
Pump joint 11, pressure release valve union 12, relief valve 13, power cord connector 14, signal wire joint 15, hose coupling 16, microthruster
Power cord 17, sensor power supply line 171, signal wire 18, hose 19, microthruster 20, power supply 24；
Wherein, the vacuum thrust measuring device include vacuum cavity 5, sealing cover 6, the pedestal 7 for being fixed on cavity bottom,
Vacuum cavity outer wall distinguishes reserved through hole 111,121,141,151,161, and wherein first through hole 111 is for installing vacuum pump adapter
11, the second through-hole 121 is for installing pressure release valve union 12, and third through-hole 141 is for installing power cord connector 14, fourth hole
151 for installing signal wire joint 15, and fifth hole 161 is for installing hose coupling 16；
The thrust pickup 9 is fixed on pedestal 7, and top is threadably secured with right angle adapter 10 and connect, micro- to push away
20 top of power device is threadably secured an interface for being connected to right angle adapter 10, and top down is perpendicular to vacuum cavity 5
Bottom surface；Hose 19 stretches into connection microthruster 20 by another interface of right angle adapter 10, and the other end is from preformed hole 161
Stretch out via hose coupling 16 and connect with gas cylinder 3, gas cylinder 3 by hose 19 to microthruster output high-pressure gas with
Generate thrust；
The vacuum pump 4 is connect by vacuum pump adapter 11 with vacuum cavity 5, is used for cavity vacuum state；It lets out
Pressure valve 13 and vacuum pressure sensor 8 are mounted on pressure release valve union 12, and microthruster 20 is removed and measure in vacuum chamber for letting out
Environmental pressure caused by discharge gas in body 5；
The microthruster power cord 17 and sensor power supply line 171 are stretched into via power cord connector 14 respectively connects micro- push away
Power device 20 and thrust pickup 9, the other end connect power supply 24 and are used to power to the power supply of microthruster 20 and thrust pickup 9；Letter
Number line 18 stretches into connection thrust pickup 9, number of the other end connection for acquisition process measurement data via signal wire joint 15
According to processor 2.
As shown in figure 3, in order to make to keep better vacuum sealing effect in vacuum cavity 5, such sealing can be taken
Structure：The pre-groove 502 i.e. on the 5 unlimited circular hole 501 of top setting protrusion of vacuum cavity, 501 diameter wall of circular hole, and be symmetrical arranged
More than two non-through screw holes 503；140 size of sealing cover be more than 501 area of circular hole, thereon setting with it is pre-embossed on 501 diameter wall of circular hole
503 quantity of non-through screw hole is equal, the corresponding tapped through hole in position；Washer 61 is first positioned over 501 diameter of circular hole by sealing cover when installing
On wall in pre-embossed groove 502, then sealing cover covered on circular hole 501, installation bolt is sealed solid in non through hole 503
It is fixed.
As shown in figure 4, in order to reach better measurement effect, propellant gas supply flow situation is grasped, can be taken in this way
Plenum system：Pressure reducing valve 21, flow control valve 22, flowmeter 23 are placed in gas cylinder 3 and microthruster 20, use hose
19 are sequentially connected, and pressure reducing valve 21 adjusts gas outlet pressure, can be adjusted and be surveyed in real time by flow control valve 22 and flowmeter 23
Try the quality of filling gas flow rate of microthruster jet pipe.
Measurement experiment process is as follows：
(1) adjustment and installation and vacuumizing phase.Microthruster 20 and thrust pickup 9 are fixedly mounted on vacuum cavity 5
Bottom is sealed vacuum cavity with sealing cover 140, confirms that vacuum pump, sensor, power cord connect just with each component such as signal wire
Often, ensure that microthruster 20 and thrust pickup 9 are in and be powered on state.After each section installation and debugging are good, vacuum pump 4 is started
Air is extracted, environmental pressure in vacuum cavity 5 is made to reach 1kpa and keep its vacuum degree.
(2) test phase is supplied.The media such as nitrogen or helium are inputted microthruster 20 by gas cylinder, and pass through flow tune
It saves valve 22 and controls inlet pressure, gas supply flow is read by flowmeter 23, propulsive medium is sprayed from Laval nozzle generates thrust.
Data processor 2 can acquire the voltage signal changing value that thrust pickup 9 exports in real time.The gas that microthruster 20 is sprayed from jet pipe
Knowing from experience influences environmental pressure, 8 real-time measuring environment pressure changing of vacuum pressure sensor.
(3) experimental result and finishing phase are obtained.By measuring under inlet pressure certain condition, when varying environment pressure, is micro-
The thrust size that thruster 20 generates, then extrapolate by Function Fitting the actual thrust of microthruster 20 under space condition of high vacuum degree
Value, to reduce experimental error.After the completion of experiment, pressure release is carried out to vacuum cavity 5 by relief valve 12.
Claims (3)
1. the microthruster Thrust Measuring System under a kind of simulation vacuum environment, it is characterised in that including vacuum thrust measuring device
(1), data processor (2), gas cylinder (3), vacuum pump (4), vacuum pressure sensor (8), thrust pickup (9), right angle
Adapter (10), vacuum pump adapter (11), pressure release valve union (12), relief valve (13), power cord connector (14), signal wire joint
(15), hose coupling (16), microthruster power cord (17), sensor power supply line (171), signal conductor (18), hose (19),
Microthruster (20), probe power (24)；
Wherein, the vacuum thrust measuring device includes vacuum cavity (5), sealing cover (6), the pedestal for being fixed on cavity bottom
(7), the reserved through-hole (111) of vacuum cavity (5) outer wall, (121), (141), (151), (161) are respectively used to installation vacuum pump
Connector (11), pressure release valve union (12), power cord connector (14), signal wire joint (15), hose coupling (16)；
The thrust pickup (9) is fixed on pedestal (7), and top is fixedly connected with right angle adapter (10), microthruster
(20) top down is fixedly connected on an interface of right angle adapter (10), and perpendicular to the bottom surface of vacuum cavity (5)；It is soft
Pipe (19) stretches into connection microthruster (20) by another interface of right angle adapter (10), and the other end is from preformed hole (161)
It stretches out via hose coupling (16) and is connect with gas cylinder (3)；
The vacuum pump (4) is connect by vacuum pump adapter (11) with vacuum cavity (5)；Relief valve (13) and vacuum pressure sensing
Device (8) is mounted on pressure release valve union (12)；
It is micro- that the microthruster power cord (17) and sensor power supply line (171) stretch into connection via power cord connector (14) respectively
Thruster (20) and thrust pickup (9), the other end connect power supply (24)；Signal wire (18) is stretched into via signal wire joint (15)
Thrust pickup (9) is connected, the other end connects data processor (2).
2. the microthruster Thrust Measuring System under simulation vacuum environment according to claim 1, it is characterised in that vacuum
Setting, which is protruded, at the top of cavity (5) opens wide circular hole (501), pre-groove (502) on circular hole (501) diameter wall, and is symmetrical arranged two
The above non-through screw hole (503)；Sealing cover (140) size is more than circular hole (501) area, thereon in setting and circular hole (501) diameter wall
Non-through screw hole (503) quantity is equal, the corresponding tapped through hole in position；Washer (61) is first positioned over by sealing cover (140) when installing
On circular hole (501) diameter wall in pre-embossed groove (502), then sealing cover (140) covered on circular hole (501), in non through hole (503)
Middle installation bolt is sealed fixation.
3. the microthruster Thrust Measuring System under simulation vacuum environment according to claim 1 or claim 2, special
Sign is：Pressure reducing valve (21), flow control valve (22), flowmeter (23) are placed in gas cylinder (3) and microthruster (20),
It is sequentially connected with hose (19).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710017540.4A CN108303206A (en) | 2017-01-11 | 2017-01-11 | Simulate the microthruster Thrust Measuring System under vacuum environment |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710017540.4A CN108303206A (en) | 2017-01-11 | 2017-01-11 | Simulate the microthruster Thrust Measuring System under vacuum environment |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108303206A true CN108303206A (en) | 2018-07-20 |
Family
ID=62871450
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710017540.4A Pending CN108303206A (en) | 2017-01-11 | 2017-01-11 | Simulate the microthruster Thrust Measuring System under vacuum environment |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108303206A (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109470447A (en) * | 2018-11-09 | 2019-03-15 | 中国船舶工业集团公司第七0八研究所 | A kind of cycloid thruster experimental rig |
| CN111089674A (en) * | 2019-12-26 | 2020-05-01 | 兰州空间技术物理研究所 | Thrust measuring device of ion thruster |
| 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 |
| CN116007892A (en) * | 2023-03-27 | 2023-04-25 | 中国人民解放***箭军工程大学 | Jet propulsion micro-thrust testing method |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101435728A (en) * | 2008-12-18 | 2009-05-20 | 中国科学院力学研究所 | Apparatus and method for measuring small rocket engine thrust force vector in vacuum |
| CN101514927A (en) * | 2009-03-20 | 2009-08-26 | 北京航空航天大学 | Elastic micro-Newton level low thrust measuring system |
| CN101539482A (en) * | 2009-04-21 | 2009-09-23 | 北京航空航天大学 | Electric propulsion testing platform gaseous-propellant supply device |
| CN107182257B (en) * | 2010-12-31 | 2014-01-22 | 兰州空间技术物理研究所 | The calibrating installation and method of a kind of measuring micro-thrust system |
| US20160202131A1 (en) * | 2013-08-26 | 2016-07-14 | University Of Florida Research Foundation Inc. | Method and Apparatus for Measuring Thrust |
-
2017
- 2017-01-11 CN CN201710017540.4A patent/CN108303206A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101435728A (en) * | 2008-12-18 | 2009-05-20 | 中国科学院力学研究所 | Apparatus and method for measuring small rocket engine thrust force vector in vacuum |
| CN101514927A (en) * | 2009-03-20 | 2009-08-26 | 北京航空航天大学 | Elastic micro-Newton level low thrust measuring system |
| CN101539482A (en) * | 2009-04-21 | 2009-09-23 | 北京航空航天大学 | Electric propulsion testing platform gaseous-propellant supply device |
| CN107182257B (en) * | 2010-12-31 | 2014-01-22 | 兰州空间技术物理研究所 | The calibrating installation and method of a kind of measuring micro-thrust system |
| US20160202131A1 (en) * | 2013-08-26 | 2016-07-14 | University Of Florida Research Foundation Inc. | Method and Apparatus for Measuring Thrust |
Non-Patent Citations (1)
| Title |
|---|
| 岑继文，徐进良: "真空环境下微推力测量的研究", 《宇航学报》 * |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109470447A (en) * | 2018-11-09 | 2019-03-15 | 中国船舶工业集团公司第七0八研究所 | A kind of cycloid thruster experimental rig |
| CN111089674A (en) * | 2019-12-26 | 2020-05-01 | 兰州空间技术物理研究所 | Thrust measuring device of ion thruster |
| 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 |
| CN116007892A (en) * | 2023-03-27 | 2023-04-25 | 中国人民解放***箭军工程大学 | Jet propulsion micro-thrust testing method |
| CN116007892B (en) * | 2023-03-27 | 2023-08-15 | 中国人民解放***箭军工程大学 | Jet propulsion micro-thrust testing method |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN108303206A (en) | Simulate the microthruster Thrust Measuring System under vacuum environment | |
| CN110793746B (en) | Wind tunnel test device for measuring thrust of oblique cutting spray pipe of hypersonic vehicle | |
| CN105605371A (en) | Building pipeline overhauling device | |
| CN105675224B (en) | The detection method of encapsulating package sealing propertytest system | |
| CN202255802U (en) | Airtight pressurization test set for cabin | |
| CN208060103U (en) | A kind of exhaust system quantity of gas leakage detection device | |
| CN104501917B (en) | Super large caliber sonic nozzle group formula gas flowmeter calibrating installation | |
| CN202171525U (en) | Device for measuring coefficient of air resistance | |
| RU2381471C1 (en) | Device for identification of traction characteristics in imitators of air-feed jet engines (afje), method for detection of traction characteristics of afje imitators and method for control of validity in detection of traction characteristics of afje imitators | |
| CN109655228A (en) | A kind of jet flow thrust school survey device for different shaped face jet pipe | |
| CN205562162U (en) | Semi -automatic carbon tank control valve flow testing arrangement | |
| CN205157158U (en) | Hypersonic wind tunnel pressure measurement structure | |
| CN103852392B (en) | A kind of test unit of simulating the erosion of gas well Y type X-tree | |
| CN103940581A (en) | Experimental method for monitoring tracer gas concentration value and measuring jet entrainment amount | |
| CN110567673A (en) | Wind tunnel test method for thrust measurement of oblique cutting nozzle of hypersonic vehicle | |
| CN109084968B (en) | Air valve dynamic performance testing device and testing method | |
| CN207198045U (en) | A kind of gas-detecting device for GIS device fault gas chamber fast positioning | |
| CN205262537U (en) | Measure device of irregular solid volume | |
| CN209198482U (en) | A kind of Pitot tube and anemobiagraph probe fixture | |
| CN103424229A (en) | Device and method for detecting leakproofness of vehicle exhaust system | |
| CN106644262A (en) | Field pressure calibration test valve and test method for railway vehicles | |
| CN208858550U (en) | A kind of water pump delivery test system | |
| CN107131922B (en) | Fuel spray nozzle flow test system | |
| CN209164111U (en) | A kind of pump test system | |
| CN109521217A (en) | Pitot tube and anemobiagraph probe fixing device |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20180720 |