CN104374506B - One dangles the momentum test device and method of testing that declines - Google Patents
One dangles the momentum test device and method of testing that declines Download PDFInfo
- Publication number
- CN104374506B CN104374506B CN201410647212.9A CN201410647212A CN104374506B CN 104374506 B CN104374506 B CN 104374506B CN 201410647212 A CN201410647212 A CN 201410647212A CN 104374506 B CN104374506 B CN 104374506B
- Authority
- CN
- China
- Prior art keywords
- fork
- microdriver
- momentum
- vacuum
- vacuum tank
- 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.)
- Expired - Fee Related
Links
Landscapes
- Lasers (AREA)
- Length Measuring Devices By Optical Means (AREA)
Abstract
The invention discloses one to dangle the momentum test device and method of testing that declines, the system of dangling is fixed in vacuum tank, propeller priming supply, contactor, wire and microdriver use modularity to be integrated in the system of dangling, dangle decline momentum test system work under vacuum conditions, contactor uses remote switch to be remotely controlled igniting, eliminates microdriver igniting resistance silk power supply and the wire impact on test result；Laser Doppler measuring device is arranged on outside vacuum tank, the light path of single beam laser head in regulation laser Doppler measuring device, it is allowed to and target reflecting optics centering, eliminate the bias of outgoing beam and incident beam, accurately measure angle of rake change in displacement, it is to avoid dangle and affected by air drag when swinging.Micro-momentum test device and method of testing, can test the power of microrocket engine short period work, also can test small impulse, and higher to impulse measuring accuracy.
Description
Technical field
The present invention relates to microdriver field tests, specifically, relate to one and dangle the momentum test that declines
Device and method of testing.
Background technology
Microminaturization is an important directions of modern spacecraft development.Tiny spacecraft to have quickly response,
High accuracy and the feature of high reliability, and these features all propulsion systems with tiny spacecraft have direct relation,
Thus micromass culture system is had higher requirement.General micromass culture system provides the micro thrust of milli cattle level,
And the working time is the shortest.Therefore, the performance test of process micro thruster and demarcation, need resolution high
And there is the measurement system of high frequency response.
The measurement of microdriver momentum is the work of a complexity the most difficult.On the one hand, micro-thruster work
The thrust that when making, itself produces is the least and the working time is the shortest, in this case, and the damping of circuit lead
Accurately measuring of thrust can be had a huge impact；On the other hand, microdriver generally is directed to space
Environment uses design, and microdriver impulse measurement is then to carry out in the gravitational field of the earth.At the earth
In gravitational field, the deadweight of micro-thruster is far longer than its thrust produced, and therefore carries out small in gravitational field
The measurement of thrust is necessary for the impact eliminating deadweight to measuring.Microdriver micro impulse measure to solve with
Lower two problems: the deadweight of (1) microdriver separates with thrust；(2) microdriver electric power system pair
The impact of thrust measurement.
At present, several typical cases micro-momentum test system succeeded in developing has: NASA LEWIS research center
THOMAS pulsed plasma micro-thruster momentum testboard, the high-power micro-thruster in LEWIS research center pushes away
Force test method, the rotation wire form Micro-thrust test platform of OLDDARD space research center, double pendulum measurement push system,
Laser interference measuring method measures impulse, Tokyo University's pulsed plasma microthruster testboard.From
From the point of view of structural point, micro-momentum test system can be divided into according to structure: balance-type type, rotation wire form and the formula of dangling.
The formula that dangles structure micro-momentum test system measures micro thrust and precision Gao Erying of impulse due to it
With relatively wide, but micro-momentum of the formula structure that dangles test system still suffers from some shortcomings, such as Thomas pulse
Plasma micro-thruster momentum testboard.This test system is that torsion is dangled horse structure, can test simple venation
Amount and Plasma propulsion device continuous impulse igniting average thrust in a state of excitement.Static demarcating determining, thrust is turned round with stand
Relation between pendulum displacement；The method that momentum clashes into pendulum in demarcating, determines that the stand after momentum change rings
Should, record stand maximum displacement and natural frequency.But system eliminates system damping the most as far as possible, as
Air damping is lost with pivoting friction, and system the most mathematically derives thrust or momentum and displacement
Relation, simply the most experimentally calibration system, precision is relatively low.The most double Thrust Measuring Systems that dangle,
This system is Left-side support and two swing arm structures of right side suspension, microdriver horizontal positioned；Can test quiet
Thrust, average thrust and impulse bit.When the structure of system can keep microdriver to work, propeller
Move distance is little in the vertical direction, and beneficially LVDT measures microdriver and swings displacement, this system
Being disadvantageous in that four movable joints of employing, therefore system has bigger frictional force, thus after pulse,
System vibration displacement signal is decayed quickly.
Existing micro-momentum test device is getting rid of air damping impact, system mechanics friction and circuit lead connection
There are some problem demanding prompt solutions in the drag effects aspect produced.
Summary of the invention
In order to avoid prior art exist deficiency, the present invention propose one dangle decline momentum test device and
Method of testing, dangle decline momentum test system work under vacuum conditions, by the edge of a knife and circuit remote control collection
One-tenthization design eliminates the resistance impact on measurement result；Use laser Doppler measuring device, eliminate outgoing beam
With the bias of incident beam, improve certainty of measurement.
The technical solution adopted for the present invention to solve the technical problems is: micro-momentum test device includes vacuum
Case, upright post base, column, bracer, middle cutter hold, middle cutter, flat crossbeam, balance nut, overarm brace,
Power supply, fork, remote switch, microdriver, target reflecting mirror, laser Doppler measuring device,
Transparency window, vacuum pump interface, hermatic door, described vacuum tank is rectangular structure, and vacuum tank has hermatic door,
Transparency window is embedded on vacuum tank sidewall, and the vacuum tank sidewall that transparency window is relative has vacuum pump interface, at the bottom of column
Seat is positioned at vacuum tank inner bottom part, and uprights vertical is fixed on upright post base, and a bracer is fixed on column upper end,
Middle cutter holds and is positioned at middle part on a bracer, and middle cutter is embedded in the middle of flat crossbeam, and there is balance spiral shell at flat crossbeam two ends
Mother, flat crossbeam and overarm brace be connected, and fork one end is connected with overarm brace, power supply be arranged on fork and
Overarm brace junction, remote switch is fixed on fork, and microdriver is arranged on fork, miniature propelling
Device initial thrust direction is horizontal direction, and target reflecting mirror is fixed on fork the lower section being positioned at microdriver,
Target mirror mirror is parallel with fork, and middle cutter is placed on the middle cutter at a bracer center and holds, middle cutter and middle cutter
The contact point held is the axle point that system swings that dangles, laser Doppler measuring device be arranged on the outside of vacuum tank with
Transparency window the same side, and laser Doppler measuring device and transparency window, target reflecting mirror be positioned on same axis.
A kind of use described in dangle the momentum test device method that carries out micro-momentum test that declines, it is characterised in that
Comprise the following steps:
Step 1. assembles each mechanical part, power supply, remote switch, micro-thruster and wire is carried out even
Connect, connection procedure keeps remote switch be off all the time；
The flat board bolt of step 2. adjusting post base, makes upright post base be in level, regulates flat crossbeam
The balance nut at two ends, makes fork be in vertical equilibrium position, regulates target reflecting mirror, make target reflecting mirror
Minute surface is parallel with fork；
Step 3. closes vacuum box hermetic door, it is ensured that vacuum tank starts vacuum pump after fully sealing, until vacuum
Vacuum in case reaches 10-2During Pa, closing vacuum pump, vacuum keeps 1 hour；
Step 4. carries out optical path adjusting；Check after evacuation and confirm fork state position, start laser-Doppler and survey
Measuring device, regulates single beam laser head orientation, and the laser making single beam laser hair go out reflects through target reflecting mirror
Tailing edge input path backtracking；
Step 5. opens the signal processor of laser Doppler measuring system, and the place of being allowed in working order, starts
Circuit remote switch makes igniting electric line electric current connect, and ignition voltage is 10V, and initial firing current is 0.5A；
Microdriver ignition wire works, and makes propellant fire burning produce thrust, promotes fork motion；
The data in fork motor process recorded by step 6. laser Doppler measuring device, obtain through signal processing
The displacement data of different time, and send data to computer, calculate rushing of microdriver work generation
Amount, can measure momentum is 1 μ N.s～1mN.s；
Step 7. closes test device, preserves experimental data, and the angle of rake momentum of solid micro has been tested.
Beneficial effect
The one that the present invention proposes dangles the momentum test device and method of testing that declines, and uses vacuum tank for test
System provide vacuum condition, dangle decline momentum test system be fixedly mounted in vacuum tank, the formula that dangles test
System works under vacuum conditions, the impact on test result by the edge of a knife and circuit remote control integrated elimination resistance；
Use laser Doppler measuring device, eliminate the bias of outgoing beam and incident beam, improve its measuring accuracy；
Avoiding dangling when swinging is affected by air drag.
The present invention micro-momentum test device is by propeller priming supply, contactor, wire and microdriver
Using modularity to be integrated in the system of dangling, meanwhile, contactor uses remote switch, when being remotely controlled igniting
There is no the interference of wire, eliminate the impact on test of microdriver igniting resistance silk power supply and wire.
The fulcrum that the system that dangles swings uses knife edge structure, and minimizing system swings the friction loss brought, and improves spirit
Sensitivity.Laser Doppler measuring device is placed in outside vacuum tank, and the displacement that can accurately measure microdriver becomes
Change.Use micro-momentum test device, can test the short period work power, also can test pulse momentum, and
Higher to impulse measuring accuracy.The present invention is especially suitable for the micro impulse test of microrocket engine
And development work.
Accompanying drawing explanation
Dangle to one of the present invention declining momentum test device and method of testing below in conjunction with the accompanying drawings with embodiment
It is described in further detail.
Fig. 1 be the present invention dangle decline momentum test device vacuum tank schematic diagram.
Fig. 2 be the present invention dangle decline momentum test apparatus structure schematic diagram.
In figure:
1. in 6. bracers 7. of hermatic door 2. transparency window 3. vacuum pump interface 4. upright post base 5. column, cutter holds
8. cutter 9. flat crossbeam 10. balance nut 11. overarm brace 12. power supply 13. fork 14. remote switch in
15. microdriver 16. target reflecting mirror 17. laser Doppler measuring device 18. vacuum tanks
Specific embodiments
The present embodiment is that one dangles the momentum test device and method of testing that declines.
Refering to Fig. 1, Fig. 2, the present embodiment dangle decline momentum test device, by vacuum tank 18, hermatic door 1,
Transparency window 2, vacuum pump interface 3, upright post base 4, column 5, bracer 6, middle cutter hold 7, middle cutter 8,
Flat crossbeam 9, balance nut 10, overarm brace 11, power supply 12, fork 13, remote switch 14,
Microdriver 15, target reflecting mirror 16, laser Doppler measuring device 17 form.Vacuum tank is survey of dangling
Test system provides vacuum condition, and the test system that dangles is arranged in vacuum tank, it is to avoid dangle when swinging by sky
The impact of atmidometer.Vacuum tank 18 is rectangular structure, and vacuum tank has hermatic door 1, and transparency window 2 is embedding
Entering below vacuum tank 18 sidewall, vacuum pump interface 3 is arranged on the vacuum tank sidewall that transparency window 2 is relative, very
Empty van 18 body material uses acrylic board, and transparency window 2 material is quartz glass.
Upright post base 4 is arranged on vacuum tank 18 inner bottom part, and there is regulation bolt corner, upright post base 4 bottom surface, vertical
Post 5 is vertically fixed on upright post base 4 and is bolted, and a bracer 6 is fixedly mounted on column 5 upper end
Portion, middle cutter holds 7 and is fixed on a bracer 6, and middle cutter 8 is embedded in flat crossbeam 9 middle part, flat crossbeam 9
Two ends are provided with balance nut 10, and flat crossbeam 9 is connected with overarm brace 11, and fork 13 upper end is propped up with crossbeam
Frame 11 connects.Power supply 12 is fixed on fork 13 and overarm brace 11 junction, and remote switch 14 is solid
It is scheduled on fork 13；Microdriver 15 is arranged on fork 13 lower end near fork, microdriver
15 initial thrust directions are horizontal direction.Target reflecting mirror 16 is arranged on fork and is positioned at microdriver 15
Lower section, target mirror mirror is parallel with fork, and during middle cutter 8 is placed on bracer 6, cutter holds in 7
Between, it is the axle point that system swings that dangles that middle cutter 8 and middle cutter hold the contact point of 7, and the axle point of swing can be effectively
Reducing and swing friction, resistance is reduced to negligible degree；Middle cutter 8 is all adopted with the material that middle cutter holds 7
Make of Achates.
Laser Doppler measuring device 17 is arranged on outside and transparency window 2 the same side of vacuum tank 18, and laser
Doppler measurement device 17 and transparency window 2, target reflecting mirror 16 are positioned on same axis, can accurately measure micro-
The change in displacement of type propeller 15.
Utilize the above-mentioned momentum test device method that carries out micro-momentum test that declines that dangles, sequentially include the following steps:
Step one, before test experiments, assembles mechanical component, and by power supply, remote switch,
Microdriver and wire connect into complete circuit, keep remote switch to be in disconnection shape all the time in connection procedure
State；
Step 2, regulates target reflecting mirror so that mirror mirror is parallel with fork, then adjusts at the bottom of column
The flat board regulation bolt of seat so that upright post base is in level, finally regulates the balance at flat crossbeam two ends
Nut so that fork is in vertical equilibrium position；System debug of dangling, to poised state, then arranges distant
Control device parameter；
Step 3, closes vacuum box hermetic door, after detection guarantees that vacuum tank fully seals, starts vacuum pumping
Vacuum, until the vacuum in vacuum tank reaches 10-2During Pa, closing vacuum pump, in vacuum tank, vacuum keeps 1
Hour；
Step 4, after checking evacuation, whether fork position is in VE state, after confirming VE
Start laser Doppler measuring device, regulate single beam laser head orientation so that what single beam laser hair went out swashs
Light reflects tailing edge input path backtracking through target reflecting mirror, completes optical path adjusting；
Step 5, opens the signal processor of laser Doppler test system, is allowed in running order, opens
Galvanic electricity road remote switch makes igniting electric line electric current connect, and this ignition voltage is 10V, and initial firing current is
0.5A, microdriver igniting resistance silk works so that micromass culture agent ignition produces thrust, promotes pendulum
Bar moves；
Step 6, laser Doppler measuring device is recorded the data in fork motor process, is obtained through signal processing
To the displacement data of different time, transmit the data to electronic computer and carry out calculating microdriver
The momentum that work produces；Can measure momentum scope is 1 μ N.s～1mN.s；
Step 7, closes test device, preserves experimental data, complete to dismantle after above procedure experimental provision with
Standby test next time uses, and the test experiments of solid micro-thruster momentum completes.
Claims (1)
1. dangle decline momentum test a device, including vacuum tank, transparency window, microdriver, flat crossbeam,
Column, fork, overarm brace, it is characterized in that: also include upright post base, a bracer, middle cutter hold, middle cutter,
Balance nut, power supply, remote switch, target reflecting mirror, laser Doppler measuring device, vacuum pump connect
Mouth, hermatic door, described vacuum tank is rectangular structure, and vacuum tank has hermatic door, and transparency window is embedded in very
On empty van sidewall, the vacuum tank sidewall that transparency window is relative there are vacuum pump interface, upright post base to be positioned at vacuum tank
Bottom, uprights vertical is fixed on upright post base, and a bracer is fixed on column upper end, and middle cutter holds and is positioned at support
Middle part on block, middle cutter is embedded in the middle of flat crossbeam, and there are balance nut, flat crossbeam and crossbeam in flat crossbeam two ends
Support is connected, and fork one end is connected with overarm brace, and power supply is arranged on fork and overarm brace junction,
Remote switch is fixed on fork, and microdriver is arranged on fork, microdriver initial thrust direction
For horizontal direction, target reflecting mirror is fixed on fork the lower section being positioned at microdriver, target mirror mirror
Parallel with fork, middle cutter is placed on the middle cutter at a bracer center and holds, and the contact point that middle cutter and middle cutter hold is outstanding
The axle point that oscillator system swings, laser Doppler measuring device is arranged on outside and transparency window the same side of vacuum tank,
And laser Doppler measuring device is positioned on same axis with transparency window, target reflecting mirror；Its method of testing includes
Following steps:
Step 1. assembles each mechanical part, power supply, remote switch, micro-thruster and wire is carried out even
Connect, connection procedure keeps remote switch be off all the time；
The flat board bolt of step 2. adjusting post base, makes upright post base be in level, regulates flat crossbeam
The balance nut at two ends, makes fork be in vertical equilibrium position, regulates target reflecting mirror, make target reflecting mirror
Minute surface is parallel with fork；
Step 3. closes vacuum box hermetic door, it is ensured that vacuum tank starts vacuum pump after fully sealing, until vacuum
Vacuum in case reaches 10-2During Pa, closing vacuum pump, vacuum keeps 1 hour；
Step 4. carries out optical path adjusting；Check after evacuation and confirm fork state position, start laser-Doppler and survey
Measuring device, regulates single beam laser head orientation, and the laser making single beam laser hair go out reflects through target reflecting mirror
Tailing edge input path backtracking；
Step 5. opens the signal processor of laser Doppler measuring system, and the place of being allowed in working order, starts
Circuit remote switch makes igniting electric line electric current connect, and ignition voltage is 10V, and initial firing current is 0.5A；
Microdriver ignition wire works, and makes propellant fire burning produce thrust, promotes fork motion；
The data in fork motor process recorded by step 6. laser Doppler measuring device, obtain through signal processing
The displacement data of different time, and send data to computer, calculate rushing of microdriver work generation
Amount, can measure momentum is 1 μ N.s～1mN.s；
Step 7. closes test device, preserves experimental data, and the angle of rake momentum of solid micro has been tested.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410647212.9A CN104374506B (en) | 2014-11-14 | 2014-11-14 | One dangles the momentum test device and method of testing that declines |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410647212.9A CN104374506B (en) | 2014-11-14 | 2014-11-14 | One dangles the momentum test device and method of testing that declines |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104374506A CN104374506A (en) | 2015-02-25 |
| CN104374506B true CN104374506B (en) | 2016-08-17 |
Family
ID=52553557
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410647212.9A Expired - Fee Related CN104374506B (en) | 2014-11-14 | 2014-11-14 | One dangles the momentum test device and method of testing that declines |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104374506B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109827704A (en) * | 2019-02-28 | 2019-05-31 | 西北工业大学 | Minute yardstick pinking thrust-measuring device based on the method for dangling |
Families Citing this family (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105043635A (en) * | 2015-07-14 | 2015-11-11 | 西安近代化学研究所 | Response energy and response impulse testing system of target |
| CN105115461B (en) * | 2015-09-30 | 2018-01-05 | 南京理工大学 | A kind of pendulum device for determining displacement during laser Impulse coupling |
| CN105136009B (en) * | 2015-09-30 | 2018-01-05 | 南京理工大学 | Micro-displacement dynamic measurement system and method caused by a kind of laser Impulse coupling |
| CN105352639B (en) * | 2015-09-30 | 2018-09-04 | 南京理工大学 | A kind of laser acts on Impulse coupling efficiency test system to target |
| CN106248281B (en) * | 2016-09-20 | 2018-12-11 | 哈尔滨工业大学 | A kind of plane torsion declines impulse measurement method |
| CN108414127A (en) * | 2018-02-01 | 2018-08-17 | 南京航空航天大学 | Compensation Micromass cell culture torsion balance |
| CN110646157B (en) * | 2019-09-29 | 2021-08-13 | 中国直升机设计研究所 | Sliding window limiting impact test device |
| CN110672247B (en) * | 2019-11-13 | 2021-08-20 | 西安近代化学研究所 | Swinging plate type micro-thrust measuring device |
| CN110836758B (en) * | 2019-11-21 | 2020-11-24 | 中国科学院微小卫星创新研究院 | Thimble type micro-impulse applying device |
| CN112050988B (en) * | 2020-05-29 | 2022-04-19 | 北京机械设备研究所 | Thrust measurement device and method |
| CN112985816A (en) * | 2021-03-18 | 2021-06-18 | 北京航空航天大学 | Variable-size universal miniature turbine engine test bed |
| CN113418711B (en) * | 2021-06-02 | 2022-10-28 | 北京机械设备研究所 | Micro-thrust measurement system and method |
| CN113691189B (en) * | 2021-08-26 | 2024-04-23 | 聚辰半导体股份有限公司 | Method for correcting non-linearity of zero magnetic area of magnet of closed-loop voice coil motor |
| CN116577009B (en) * | 2023-07-04 | 2023-10-20 | 华中科技大学 | Triaxial decoupling measurement device for testing mass release impulse |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101979978A (en) * | 2010-11-16 | 2011-02-23 | 北京航空航天大学 | Electromagnetic force calibrating device for micro impulse test |
| CN102072790A (en) * | 2010-11-16 | 2011-05-25 | 北京航空航天大学 | Device for measuring micro impulse |
| CN102305682A (en) * | 2011-05-31 | 2012-01-04 | 哈尔滨工业大学 | Device and method for measuring micro impulse by torsional pendulum method for modulating multi-beam laser heterodyne by using doppler galvanometer sine |
| CN102353491A (en) * | 2011-05-31 | 2012-02-15 | 哈尔滨工业大学 | Second harmonic multi-beam laser heterodyne measurement method for micro impulse based on doppler oscillating mirror sinusoidal modulation |
| CN102353490A (en) * | 2011-05-31 | 2012-02-15 | 哈尔滨工业大学 | Micro impulse measuring apparatus using torsion pendulum method of using Doppler vibrating mirror to carry out sine modulation on multiple-beam laser heterodyne and method thereof |
| CN102937496A (en) * | 2012-10-22 | 2013-02-20 | 西北工业大学 | Thrust measuring device of mini-type solid chemical thruster |
| CN103759874A (en) * | 2014-01-16 | 2014-04-30 | 徐州大亚自动装备有限公司 | Simple thrust testing device for window controller |
-
2014
- 2014-11-14 CN CN201410647212.9A patent/CN104374506B/en not_active Expired - Fee Related
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101979978A (en) * | 2010-11-16 | 2011-02-23 | 北京航空航天大学 | Electromagnetic force calibrating device for micro impulse test |
| CN102072790A (en) * | 2010-11-16 | 2011-05-25 | 北京航空航天大学 | Device for measuring micro impulse |
| CN102305682A (en) * | 2011-05-31 | 2012-01-04 | 哈尔滨工业大学 | Device and method for measuring micro impulse by torsional pendulum method for modulating multi-beam laser heterodyne by using doppler galvanometer sine |
| CN102353491A (en) * | 2011-05-31 | 2012-02-15 | 哈尔滨工业大学 | Second harmonic multi-beam laser heterodyne measurement method for micro impulse based on doppler oscillating mirror sinusoidal modulation |
| CN102353490A (en) * | 2011-05-31 | 2012-02-15 | 哈尔滨工业大学 | Micro impulse measuring apparatus using torsion pendulum method of using Doppler vibrating mirror to carry out sine modulation on multiple-beam laser heterodyne and method thereof |
| CN102937496A (en) * | 2012-10-22 | 2013-02-20 | 西北工业大学 | Thrust measuring device of mini-type solid chemical thruster |
| CN103759874A (en) * | 2014-01-16 | 2014-04-30 | 徐州大亚自动装备有限公司 | Simple thrust testing device for window controller |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109827704A (en) * | 2019-02-28 | 2019-05-31 | 西北工业大学 | Minute yardstick pinking thrust-measuring device based on the method for dangling |
Also Published As
| Publication number | Publication date |
|---|---|
| CN104374506A (en) | 2015-02-25 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN104374506B (en) | One dangles the momentum test device and method of testing that declines | |
| CN108408089B (en) | Ground physical simulation test method aiming at space spinning target capture and racemization | |
| JP5633799B2 (en) | Weather observation equipment | |
| KR102118157B1 (en) | Sensor mounting device of unmanned aerial vehicle for meteorological observation, unmanned aerial vehicle for meteorological observation and meteorological observation method thereof and sensor mounting device of unmanned aerial vehicle for meteorological observation | |
| CN106092399B (en) | Spaceflight micro thruster impulse measuring table based on torsion balance | |
| CN104597841B (en) | System and method for compensating planeness of compact field plane scanning frame | |
| EP2733075B1 (en) | Flight control device, spacecraft, and reference path correction method | |
| WO2016007275A1 (en) | Enhanced accuracy for tracking tethered airborne vehicles | |
| CN105805176A (en) | Stent, thrombelastogram instrument and supporting system | |
| JP2019026244A (en) | Ceiling travel type unmanned flight body | |
| CN103818526A (en) | Water platform with thrusters | |
| CN109781384B (en) | Multi-navigation-body parallel water-entry experimental device | |
| CN104655154A (en) | Static balance testing device and method of high-precision gyroscope suspension system | |
| US20150367966A1 (en) | Attitude determination and control system (adcs), sun sensor, and star tracker | |
| CN116224467A (en) | Ground verification testing device and method for on-orbit release of inspection quality | |
| CN208731251U (en) | Spacecraft three-dimensional zero-g simulator based on double-stage air floatation | |
| CN108945537A (en) | Spacecraft three-dimensional zero-g simulator based on double-stage air floatation | |
| CN103376092B (en) | A kind of leveling turntable device based on laser ranging and leveling method | |
| CN203758522U (en) | Unmanned aerial vehicle attitude sensor | |
| CN106705938A (en) | Method for measuring inclination of ship stern bearing through laser | |
| CN203838951U (en) | Automatic rotating inverted pendulum device based on ARM | |
| CN104457794A (en) | Gravity unloading mechanism for ground tests of control moment gyro | |
| Adamov et al. | Experimental study of aerodynamic characteristics of a reentry vehicle on a setup with free oscillations at supersonic velocities | |
| CN103115745B (en) | Hypersonic shock tunnel hanging pendulum type relief means | |
| CN102944207B (en) | Springback type angle displacement measurement device and measurement method thereof |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20160817 Termination date: 20171114 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |