CN104655417B - Device for testing high and low temperature performance of certain indexing mechanism of space station - Google Patents
Device for testing high and low temperature performance of certain indexing mechanism of space station Download PDFInfo
- Publication number
- CN104655417B CN104655417B CN201510089816.0A CN201510089816A CN104655417B CN 104655417 B CN104655417 B CN 104655417B CN 201510089816 A CN201510089816 A CN 201510089816A CN 104655417 B CN104655417 B CN 104655417B
- Authority
- CN
- China
- Prior art keywords
- indexing mechanism
- flywheel
- low temperature
- space station
- inertia
- 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.)
- Active
Links
Abstract
The invention discloses a device for testing high and low temperature performance of a certain indexing mechanism of a space station and belongs to the field of devices for testing indexing mechanisms of space stations. The device comprises a high and low temperature box, a middle support and flywheel device and a lower-end control device, wherein the middle support and flywheel device comprises an indexing mechanism body, a support body, a shafting and a flywheel; the upper end of the indexing mechanism body is placed in the high and low temperature box, the lower end of the indexing mechanism body is connected with the flywheel through the shafting, bolt holes and different ports are formed in the support body, and the indexing mechanism body is fixed on the support body through the ports; the lower-end control device comprises an air flotation platform, electric cylinders, a sliding trolley, a linear guide rail and electrical controllers, the air flotation platform is located below a top support part of the flywheel, the electric cylinders are located below the flywheel, the sliding trolley and the linear guide rail are mounted below the electric cylinders, the electric controllers are located below the whole device. The device solves the problem of lack of simulation equipment for indexing mechanisms to be lunched into the space at present.
Description
Technical field
The present invention relates to a kind of space station indexing mechanism high temperature performance test device, belong to physics facility neck
Domain.
Background technology
From the international space station that number space station of salvo of the Soviet Union is on active service still in space till now, indexing mechanism, docking
The performance and working life of the large corporation such as mechanism and development mechanism affect the Years Of Service of space station.Therefore in order to obtain
Indexing mechanism performance parameter is obtained, analysis indexing mechanism problem that may be present improves indexing to carry out being correspondingly improved optimization
The working life of mechanism, launches to before space in indexing mechanism, it is necessary to carry out ground simulating.But China currently without
Launched international space station, when international space is built, because the U.S. thinks that space station technology can be applied to military use, therefore
Refusal China adds.So, China is still short of very much in terms of indexing mechanism performance testing device at present.
Indexing mechanism indexing process high temperature performance test device is the necessary test equipment of indexing mechanism development stage, main
It is used for indexable arm indexing Process Duty simulation, the indexable detent torque of test, rotating speed, corner after the completion of indexing mechanism unit general assembly
With the data such as startup time, to examine indexing mechanism joint performance.
The content of the invention
To solve the deficiencies in the prior art, the invention provides a kind of ground simulation space station indexing mechanism high and low temperature
Can test device, can to space station indexing mechanism, the combination property of indexable process is tested in high and low temperature environment, adopt
Technical scheme is：
A kind of space station indexing mechanism high temperature performance test device, it is characterised in that including high-low temperature chamber 1, middle part
Support and flywheel gear, lower end control device；
The midfoot support includes indexing mechanism 2, supporter 3, shafting 4, flywheel 5 with flywheel gear, wherein：Indexing mechanism
2 upper ends are placed in high-low temperature chamber 1, and lower end is connected by shafting 4 with flywheel 5, and supporter 3 is provided with bolt hole and difference connects
Mouthful, indexing mechanism 2 is fixed on supporter 3 by interface；
The lower end control device includes air floating platform 6, electric cylinder 7, sliding machine 8, line slideway 9, electrical control 10,
Wherein：Air floating platform 6 is located at the lower section at the top braces position of flywheel 5, and electric cylinder 7 is located at the lower section of flywheel 5, sliding machine 8, straight line
Guide rail 9 is arranged on the lower section of electric cylinder 7；The electrical control 10 is located at the lower section of package unit.
The high-low temperature chamber 1, framework is using Thin Stainless Steel wallboard and strengthens fin, and is designed with shackle structure in upper end,
Facilitate the installation and dismounting of indexing mechanism；The high-low temperature chamber 1 is sealed, and controls height in the temperature simulation space of high-low temperature chamber
Low temperature environment.
Speed increaser is installed in the shafting 4, the size and motor demand of inertia mechanical analogue part can be reduced；It is described
Shafting 4 is the shared shafting of inertia electric simulation and inertia mechanical analogue, transmission mechanical inertia to indexing mechanism 2.The shafting 4 is pacified
Equipped with sensor and signal picker, signal is gathered, be aggregated into electric device, treatment and signal Analysis, obtain indexing mechanism
Performance parameter.
The overall structure of the flywheel 5 is combined type, and bottom is provided with the different balancing weight of quality, simulates different mechanical inertias,
Electric cylinder 7 is mounted and dismounted to balancing weight.
The flywheel 5 supports the internal motor for being provided with electric inertia simulation.
The flywheel 5 is integrally placed on air floating platform 6, the air supporting support flying wheel 5 of air floating platform 6, simulation space weightlessness.
The control whole device work of the electrical control 10, collection, process signal.
The electrical control 10 is provided with switch board, and the sensor and signal picker installed with shafting 4 are connected, and control and adopt
Collection signal, and with single measurement equipment interactive product information.
The ratio between described length of space station indexing mechanism high temperature performance test device is：It is long：It is wide：High=
9420：5055：8364.
The ratio between the diameter of the flywheel 5 and the length and width of supporter 3 are：Flywheel diameter：Supporter is long：Supporter is wide=
6550：5600：5600.
The indexing mechanism 2 of simulation when will need to carry out is arranged on supporter 3, is integrally placed in high-low temperature chamber, height
Incubator 1 is sealed, by controlling the temperature of high-low temperature chamber 1, the change of temperature in simulation space.High-low temperature chamber 1 is equally laid
On supporter 3.
The shafting 4 carries out the transmission of the inertia of moment of torsion, while being provided with speed increaser in shafting, can reduce inertia machine
The size of tool analog component and motor demand.
The supporter 3 is the basis of package unit, and supporting role is served as in package unit, and spiral shell is left on supporter 3
Keyhole and other corresponding interfaces, facilitate indexing mechanism to carry out installing/dismounting with adjustment, it would be desirable to the indexing mechanism 2 of simulation when carrying out
On supporter 3, integrally it is placed in high-low temperature chamber 1, high-low temperature chamber 1 is sealed, by the temperature for controlling high-low temperature chamber 1
Degree, the change of temperature in simulation space.
The flywheel 5 is integrally placed on air floating platform 6, when inertia simulation is carried out, is entered flywheel 5 by air floating platform 6
Promoting the circulation of qi over draft is supportted, and reduces lower end frictional force, to reach the weightlessness in simulation space.
The overall structure of the flywheel 5 makes combined type, the simulation of different inertia is carried out to facilitate, in abundant simulation space
The physics inertia of the Laboratory Module of different size；The bottom of flywheel 5 is furnished with the different balancing weight of quality, when different inertia are simulated, no
Must more changing device, need to only increase and decrease the quantity of flywheel lower end balancing weight.Flywheel counter weight block is dismantled and pacified by electric cylinder 7
Dress, when needing to change flywheel inertia simulation, it is only necessary to risen through electric cylinder 7, be reduced to proper height release or revolve
Tight corresponding bolt, without going to install by manpower, greatly facilitates installation and dismounting, considerably reduces manpower thing
The consumption of power.
In the lower part of package unit, line slideway 9 and sliding machine 8 are installed, the position of package unit can be adjusted.
The electrical equipment device of air 10 serves as control role in whole device, is responsible for the Digital Signal Analysis and Processing of package unit.
The present invention is placed in high-low temperature chamber using turn device is fixed on supporter, by changing high-low temperature chamber in
The temperature environment that different temperature is come in simulation space；Flywheel inertia analogue means is placed on air-floating apparatus, in simulation space
Weightlessness.And flywheel structure makes combined type, different mechanical inertias can be simulated, only need to change different when changing inertia
The flywheel of specification.Flywheel mechanical inertia is transferred on the indexing mechanism of space station by shafting.And in whole device
A number of sensor and signal picker are installed, the collection of signal can be carried out, and most signal is aggregated into electrically dress at last
Put, carry out the treatment and analysis of signal, to obtain the performance parameter of indexing mechanism.
Operation principle of the invention is：Inertial loads during the simulation indexing of flywheel inertia analogue means, test indexing
Startup, stop performance of the arm under flywheel inertia load.It is partly air floating platform under flywheel, is supported by air floating platform during work
Play flywheel, to reduce friction, the weightlessness in simulation space；Simultaneously inside flywheel, the motor of specific standard is installed, with
Complete electric inertia simulation；The electromagnetic clutch that electric inertia simulation passes through installation in shafting with mechanical inertia simulation；It is overall used
Amount be transferred on the indexing mechanism of upper part by shafting, indexing mechanism is placed on supporter, and with the Tongan City of supporter one
It is placed in high-low temperature chamber, the high and low temperature environment in simulation space；Switch board is used for equipment and controls and signal acquisition, and is set with single survey
It is standby to carry out product information interaction.
Beneficial effect of the present invention：
(1) in overall plan：To make indexing mechanism test process simple, convenient, cost is reduced.Package unit can be right
Different simulations are carried out in the indexing mechanism of different model, hypomere part-structure need not change, it is only necessary to end interface in change
.
(2) inertia simulation device is placed on flywheel, weightlessness in simulation space；Indexing mechanism is placed in height
In cryogenic box, by controlling the internal temperature of high-low temperature chamber, temperature change in simulation space.The mould that the present apparatus can be really true to life
Intend indexing mechanism working environment in space.
(3) mechanical analogue of different inertia can be carried out, lower end flywheel uses fabricated structure, for different inertia,
Only need to install or unload the balancing weight number of varying number, even if flywheel inertia instantly cannot still meet wanting
Ask, it is only necessary to process the flywheel of specific inertia two, without package unit is remake.
(4) lower end is designed with line slideway, can adjust the position of package unit, meets need of work.
Brief description of the drawings
Fig. 1 is the front view of overall structure installation diagram of the present invention；
(1, high-low temperature chamber；2, indexing mechanism；3, supporter；4, shafting；5, flywheel；6, air floating platform；7, electric cylinder；8,
Sliding machine；9, line slideway；10, electrical control).
Fig. 2 is the partial enlarged drawing of front view of the present invention；
(2, indexing mechanism；3, supporter；4, shafting).
Fig. 3 is the partial enlarged drawing of front view of the present invention；
(5, flywheel；6, air floating platform；7, electric cylinder；8, sliding machine；9, line slideway；10, electrical control).
Fig. 4 is the side view of overall structure installation diagram of the present invention.
Fig. 5 is the top view of overall structure installation diagram of the present invention.
Specific embodiment
Present embodiment, the space station indexing mechanism high temperature performance test of present embodiment are illustrated with reference to accompanying drawing 1-5
Device include high-low temperature chamber 1, indexing mechanism 2, supporter 3, shafting 4, flywheel 5, air floating platform 6, electric cylinder 7, sliding machine 8,
Line slideway 9, electrical control 10.The framework of high-low temperature chamber 1 is mainly constituted using Thin Stainless Steel wallboard with fin is strengthened, and in upper end
Shackle structure is designed with, facilitates the installation and dismounting of indexing mechanism.High-low temperature chamber 1 is placed on supporter 3.In whole device
In, supporter 3 is the basis of package unit, and supporter 3 serves as supporting role in package unit, and upper end has bolt hole and other are right
Interface is answered, facilitates indexing mechanism to carry out installing/dismounting with adjustment.The indexing mechanism 2 being simulated will be needed by supporter 3
Corresponding interface be arranged on supporter 3 on, be integrally placed in high-low temperature chamber, high-low temperature chamber is sealed, by control height
The temperature of incubator, high and low temperature environment in simulation space.Indexing mechanism 2 is attached with lower end flywheel part by shafting 4, shafting
Part 4 carries out the transmission of the inertia of moment of torsion.Speed increaser is installed in shafting, the size of inertia mechanical analogue part can be reduced
With motor demand.Flywheel 5 is integrally placed on air floating platform, when inertia simulation is carried out, flywheel 5 is entered into promoting the circulation of qi by air floating platform
Over draft is supportted, and reduces lower end frictional force, to reach the weightlessness in simulation space.The overall structure of flywheel 5 makes combined type, with
The simulation of different inertia is conveniently carried out, the physics inertia of the Laboratory Module of different size in abundant simulation space.It is different used in simulation
During amount, it is not necessary to more changing device, need to only increase and decrease the quantity of flywheel lower end balancing weight.Flywheel counter weight block is carried out by electric cylinder 7
Remove and install, when needing to change flywheel inertia simulation, it is only necessary to risen through electric cylinder, be reduced to proper height release
Or screw corresponding bolt.In the bottom of total, line slideway 9 is installed, can slightly adjust package unit
Position.Electric device 10 controls the work of whole device, and is responsible for the collection and treatment of signal.
Shafting 4 is that inertia electric simulation shares shafting with inertia mechanical analogue, and the motor of wherein electric inertia simulation is placed in
Flywheel support is internal；Speed increaser is installed in shafting 4, the size and motor demand of inertia mechanical analogue part can be reduced；Axle
Be 4 be inertia electric simulation and inertia mechanical analogue shared shafting, transmission mechanical inertia is to indexing mechanism 2.
Shafting 4 is provided with sensor and signal picker, gathers signal, is aggregated into electric device, treatment and signal Analysis,
Obtain the performance parameter of indexing mechanism.
Electrical control 10 is provided with switch board, and the sensor and signal picker installed with shafting 4 are connected, and control and collection are believed
Number, and with single measurement equipment interactive product information.
The ratio between length of space station indexing mechanism high temperature performance test device is：It is long：It is wide：High=9420：
5055：8364.
The ratio between the diameter of flywheel (5) and the length and width of supporter (3) are：Flywheel diameter：Supporter is long：Supporter is wide=
6550：5600：5600.
The overall structure of the flywheel 5 makes combined type, the simulation of different inertia is carried out to facilitate, in abundant simulation space
The physics inertia of the Laboratory Module of different size；The bottom of flywheel 5 is furnished with the different balancing weight of quality, when different inertia are simulated, no
Must more changing device, need to only increase and decrease the quantity of flywheel lower end balancing weight.Flywheel counter weight block is dismantled and pacified by electric cylinder 7
Dress, when needing to change flywheel inertia simulation, it is only necessary to risen through electric cylinder 7, be reduced to proper height release or revolve
Tight corresponding bolt, without going to install by manpower, greatly facilitates installation and dismounting, considerably reduces manpower thing
The consumption of power.
Operation principle：Inertial loads during the simulation indexing of flywheel inertia analogue means, the indexable arm of test is used in flywheel
Startup, stop performance under amount load.It is partly air floating platform under flywheel, flywheel is supported by air floating platform during work, with
Reduce friction, the weightlessness in simulation space.Simultaneously inside flywheel, the motor of specific standard is installed, it is used to complete electricity
Amount simulation.The electromagnetic clutch that electric inertia simulation passes through installation in shafting with mechanical inertia simulation.Overall inertia passes through axle
System is transferred on the indexing mechanism of part, and indexing mechanism is placed on supporter, and height is together placed in supporter
In incubator, the high and low temperature environment in simulation space；Switch board is used for equipment and controls and signal acquisition, and is produced with single measurement equipment
Product information exchange.
Turn device is fixed on supporter, is placed in high-low temperature chamber, by changing different temperature in high-low temperature chamber
The temperature environment come in simulation space；Flywheel inertia analogue means is placed on air-floating apparatus, the weightlessness in simulation space.And
And flywheel structure makes combined type, different mechanical inertias can be simulated, only need to change the flywheel of different size when changing inertia
.Flywheel mechanical inertia is transferred on the indexing mechanism of space station by shafting.And a fixed number is installed in whole device
The sensor and signal picker of amount, can carry out the collection of signal, and most signal is aggregated into electric device at last, carries out signal
Treatment and analysis, to obtain the performance parameter of indexing mechanism.
Although the present invention is disclosed as above with preferred embodiment, it is not limited to the present invention, any to be familiar with this skill
The people of art, without departing from the spirit and scope of the present invention, can do various changes with modification, therefore protection model of the invention
Enclose being defined of being defined by claims.
Claims (10)
1. a kind of space station indexing mechanism high temperature performance test device, it is characterised in that including high-low temperature chamber (1), middle part
Support and flywheel gear, lower end control device；
The midfoot support includes indexing mechanism (2), supporter (3), shafting (4), flywheel (5) with flywheel gear, wherein：Indexing
Mechanism (2) upper end is placed in high-low temperature chamber (1), and lower end is connected by shafting (4) with flywheel (5), and supporter (3) is provided with spiral shell
Keyhole and distinct interface, indexing mechanism (2) are fixed on supporter (3) by interface；
The lower end control device includes air floating platform (6), electric cylinder (7), sliding machine (8), line slideway (9), electric-controlled
System (10), wherein：, positioned at the lower section at flywheel (5) top braces position, electric cylinder (7) is under flywheel (5) for air floating platform (6)
Side, the lower section of sliding machine (8), line slideway (9) installed in electric cylinder (7)；The electrical control (10) is positioned at package unit
Lower section.
2. indexing mechanism high temperature performance test device in space station according to claim 1, it is characterised in that the height
Cryogenic box (1), framework is using Thin Stainless Steel wallboard and strengthens fin, and is provided with shackle structure in upper end；The high-low temperature chamber (1)
Sealed, controlled high and low temperature environment in the temperature simulation space of high-low temperature chamber.
3. indexing mechanism high temperature performance test device in space station according to claim 1, it is characterised in that the axle
System (4) is equipped with speed increaser；The shafting (4) is the shared shafting of inertia electric simulation and inertia mechanical analogue, transmits mechanical inertia
To indexing mechanism (2).
4. indexing mechanism high temperature performance test device in space station according to claim 1, it is characterised in that the axle
System (4) is provided with sensor and signal picker, gathers signal, is aggregated into electric device, treatment and signal Analysis, obtains indexing
The performance parameter of mechanism.
5. indexing mechanism high temperature performance test device in space station according to claim 1, it is characterised in that described to fly
Wheel (5) overall structure is combined type, and bottom is provided with the different balancing weight of quality, simulates different mechanical inertias, and electric cylinder (7) is to matching somebody with somebody
Pouring weight is mounted and dismounted.
6. indexing mechanism high temperature performance test device in space station according to claim 1, it is characterised in that described to fly
The internal motor for being provided with electric inertia simulation of wheel (5) support.
7. indexing mechanism high temperature performance test device in space station according to claim 1, it is characterised in that described to fly
Wheel (5) is integrally placed on air floating platform (6), air floating platform (6) air supporting support flying wheel (5), simulation space weightlessness.
8. indexing mechanism high temperature performance test device in space station according to claim 1, it is characterised in that the electricity
Gas control system (10) is provided with switch board, and the sensor and signal picker installed with shafting (4) are connected, and controls and collection signal,
And with single measurement equipment interactive product information.
9. indexing mechanism high temperature performance test device in space station according to claim 1, it is characterised in that length and width,
The ratio between height is：It is long：It is wide：High=9420：5055：8364.
10. indexing mechanism high temperature performance test device in space station according to claim 1, it is characterised in that described
The ratio between the diameter of flywheel (5) and the length and width of supporter (3) are：Flywheel diameter：Supporter is long：Supporter is wide=and 6550：5600：
5600。
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510089816.0A CN104655417B (en) | 2015-02-27 | 2015-02-27 | Device for testing high and low temperature performance of certain indexing mechanism of space station |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510089816.0A CN104655417B (en) | 2015-02-27 | 2015-02-27 | Device for testing high and low temperature performance of certain indexing mechanism of space station |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104655417A CN104655417A (en) | 2015-05-27 |
| CN104655417B true CN104655417B (en) | 2017-05-24 |
Family
ID=53246807
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510089816.0A Active CN104655417B (en) | 2015-02-27 | 2015-02-27 | Device for testing high and low temperature performance of certain indexing mechanism of space station |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104655417B (en) |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105214751B (en) * | 2015-09-16 | 2017-03-29 | 中国船舶重工集团公司第七一〇研究所 | A kind of nonmetallic single box vacuum constant temperature tank |
| CN106404248A (en) * | 2016-10-11 | 2017-02-15 | Tcl瑞智（惠州）制冷设备有限公司 | Motor starting torque testing device |
| CN110159666B (en) * | 2019-05-23 | 2020-07-24 | 哈尔滨工业大学 | Axial line switching tool of testing equipment of certain indexing mechanism of space station |
| CN111551362B (en) * | 2020-05-15 | 2021-10-08 | 河北工业大学 | Planetary gear mechanism vibration response test device for simulating weightless environment |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH08104300A (en) * | 1994-10-03 | 1996-04-23 | Nippon Sanso Kk | Space environment test device |
| JP4266977B2 (en) * | 2005-11-21 | 2009-05-27 | 大陽日酸株式会社 | Space environment test equipment |
| CN202330194U (en) * | 2011-11-18 | 2012-07-11 | 浙江工业大学 | High precision measurement system for three-dimensional microdeformation of mechanical device in high-lower temperature chamber |
| CN103091079A (en) * | 2011-10-31 | 2013-05-08 | 北京精密机电控制设备研究所 | High-low temperature vacuum environment of rotation mechanism and load simulation experiment table |
| KR101307513B1 (en) * | 2011-11-01 | 2013-09-12 | 한국항공우주연구원 | Blower device for high temperature and cryogenic gas |
| CN103969004A (en) * | 2014-05-13 | 2014-08-06 | 上海宇航系统工程研究所 | High-low temperature environment dustproof sealing ring sealing performance testing device and testing method |
| CN104181098A (en) * | 2014-09-11 | 2014-12-03 | 四川大学 | High/low-temperature slide/roll tribological property experimental table |
-
2015
- 2015-02-27 CN CN201510089816.0A patent/CN104655417B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH08104300A (en) * | 1994-10-03 | 1996-04-23 | Nippon Sanso Kk | Space environment test device |
| JP4266977B2 (en) * | 2005-11-21 | 2009-05-27 | 大陽日酸株式会社 | Space environment test equipment |
| CN103091079A (en) * | 2011-10-31 | 2013-05-08 | 北京精密机电控制设备研究所 | High-low temperature vacuum environment of rotation mechanism and load simulation experiment table |
| KR101307513B1 (en) * | 2011-11-01 | 2013-09-12 | 한국항공우주연구원 | Blower device for high temperature and cryogenic gas |
| CN202330194U (en) * | 2011-11-18 | 2012-07-11 | 浙江工业大学 | High precision measurement system for three-dimensional microdeformation of mechanical device in high-lower temperature chamber |
| CN103969004A (en) * | 2014-05-13 | 2014-08-06 | 上海宇航系统工程研究所 | High-low temperature environment dustproof sealing ring sealing performance testing device and testing method |
| CN104181098A (en) * | 2014-09-11 | 2014-12-03 | 四川大学 | High/low-temperature slide/roll tribological property experimental table |
Non-Patent Citations (1)
| Title |
|---|
| 月球着陆器用金属橡胶高低温力学性能试验研究;王少纯 等;《航空材料学报》;20040430;第24卷(第2期);第27-31页 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN104655417A (en) | 2015-05-27 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN104655417B (en) | Device for testing high and low temperature performance of certain indexing mechanism of space station | |
| CN106525450B (en) | For the matched test method of twin shaft drive electric automobile dynamical system and device | |
| CN109018430B (en) | Rotorcraft blade performance test bench | |
| CN102156047B (en) | Loading simulation device for test bed of wind turbine | |
| CN103033373B (en) | Braking system comprehensive test platform and method for braking test with platform | |
| CN204587330U (en) | Unmanned plane tractive performance test macro | |
| CN103471706B (en) | A kind of micro-vibration test system of solar wing driving mechanism | |
| CN103383306B (en) | The simulation experiment device of wind of wind-power generating yaw speed reduction unit and method thereof | |
| CN102175420A (en) | Two-degrees-of-freedom supporting system for wind tunnel test of airplane | |
| CN206531649U (en) | A kind of power system of electric automobile and controller synthesis test-bed | |
| CN202393602U (en) | Integrated loading testing table for high-power wheeled tractor | |
| CN106828972A (en) | A kind of aircraft rudder surface drive ram performance testing device | |
| CN104238548B (en) | A kind of four-wheel independence Electric Motor Wheel drives vehicle working condition simulation system and investigating method | |
| CN105551366A (en) | Ground microgravity equivalent experimental device and method of six-freedom-degree spatial mechanical arm | |
| CN205209615U (en) | Controllable formula aircraft weighting device | |
| CN206470066U (en) | A kind of power assembly of electric automobile testboard bay | |
| CN103558548A (en) | Multifunctional servo motor performance testing device and testing system thereof | |
| CN205404115U (en) | Derailleur assembly inclining test rack | |
| CN202403910U (en) | Comprehensive test device for harmonic transmission performances | |
| CN104590582B (en) | A kind of aircraft blade power imitates test device | |
| CN206292048U (en) | The experimental bench of RV decelerator transmission efficiencies | |
| CN105083585A (en) | Balance test system of four-rotor aircraft | |
| CN202083551U (en) | Testing stand simulation loading device of wind generating set | |
| CN203337187U (en) | Wind driven generator test machine case | |
| CN109490064B (en) | Annular rail wheel rail stress and base disease test device with multi-physical factor effect |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |