CN106742089B - Three-axis air-bearing table variable bit rate Satellite General orbital simulation device and method - Google Patents
Three-axis air-bearing table variable bit rate Satellite General orbital simulation device and method Download PDFInfo
- Publication number
- CN106742089B CN106742089B CN201611030980.5A CN201611030980A CN106742089B CN 106742089 B CN106742089 B CN 106742089B CN 201611030980 A CN201611030980 A CN 201611030980A CN 106742089 B CN106742089 B CN 106742089B
- Authority
- CN
- China
- Prior art keywords
- earth
- satellite
- platform
- rotary working
- bit rate
- 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
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G7/00—Simulating cosmonautic conditions, e.g. for conditioning crews
Landscapes
- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
The invention discloses a kind of three-axis air-bearing table variable bit rate Satellite General orbital simulation device and method, which includes rotary working platform, equipment base etc.；Wherein, the equipment base is used to support entire analog satellite track motion simulator, bears system pressure and torque tension, its underpart are butted against and fixed with vibrating isolation foundation, upper Middle face docks fixation with attitude motion simulation platform structure.Structure of the invention is compact, large carrying capacity, and stability is high, and 360 degree of Star Simulator rotation simulations may be implemented；Orbital simulation device meets extremely low fast high-precision orbital speed regulation rotation demand；Orbital simulation device and method fully take into account the arrangement states and use of each attitude sensor of satellite；Simulation precision is high, and it is convenient to test application；Can simulate it is low, in, highly elliptic orbit and geostationary orbit satellite Orbit revolutionary, carry out the test of rail control performance simulation.
Description
Technical field
The present invention relates to a kind of full physical test device and methods of remote sensing of the earth satellite, more particularly to a kind of three axis air bearings
Platform variable bit rate Satellite General orbital simulation device and method.
Background technique
Three-axis air-bearing table zero-gravity simulation, friction free space environment, are freely rotated using three axis and are widely used in spacecraft
Ground full physical simulation test.General three-axis air-bearing table is only capable of the attitudes vibration under analog orbit coordinate system, in order to guarantee ground
The validity or task of face l-G simulation test, which extend, to be needed, and variable bit rate Satellite General orbital simulation device and method has very much must
It wants.
Introduced at present about three-axis air-bearing table orbital simulation device it is less, by literature search, Chinese invention patent number
201520154332.5, patent name is " a kind of arc guide rail structure of emulation platform ", gives a kind of semicircle arc guide rail knot
Structure be embodied as large-scale experiment part various motion states provide movement environment simulation, the shape and structure size which provides compared with
Greatly, sliding block is fixed, and solves large-scale, heavily loaded loading scheme by multi-track, it is impossible to be used in the satellite orbit mould of three-axis air-bearing table
It is quasi-.
Summary of the invention
For the defects in the prior art, the object of the present invention is to provide a kind of three-axis air-bearing table variable bit rate Satellite Generals
Orbital simulation device and method is able to carry out low orbit, middle orbit, highly elliptic orbit and geostationary orbit satellite track and becomes
The simulation of change carries out the test of rail control performance simulation.
According to an aspect of the present invention, a kind of three-axis air-bearing table variable bit rate Satellite General orbital simulation device is provided,
It is characterized in that, the three-axis air-bearing table variable bit rate Satellite General orbital simulation device includes rotary working platform, equipment base
Seat, annular rolling guide, pulley mechanism, gear reduction mechanism, attitude motion emulation platform, vibrating isolation foundation, earth simulator for earth, too
Positive simulator, driving control system；
Wherein, the equipment base is used to support entire analog satellite track motion simulator, bear system pressure and
Torque tension, its underpart are butted against and fixed with vibrating isolation foundation, and upper Middle face docks fixation with attitude motion simulation platform structure；
The annular rolling guide is for realizing 360 degree of trackwork platform and 0.00417 °/s~0.07 °/s variable angle
Rate rotatory power has six groups of pulley mechanisms to be evenly arranged by equiangularly spaced on annular rolling guide；
The pulley mechanism together with rotary working platform for rotating；Above pulley mechanism with rotary working platform lower end
Annulus is connected, and makees rolling movement by ball or roller with annular rolling guide below；
The rotary working platform installs earth simulator for earth, the variation of analog satellite orbit angular velocity；Under rotary working platform
Hold annulus that bull gear is housed, bull gear is meshed with pinion gear, and pinion gear is driven by driving motor by gear reduction mechanism, band
Dynamic rotary working platform rotation；
The gear reduction mechanism has the function of big retarding than meeting extremely low fast high-precision orbital speed regulation rotation demand；
The attitude motion emulation platform is used for analog satellite attitudes vibration, and installation satellite earth sensor, the sun are sensitive
Device carries out the rail control performance verification under the conditions of Orbit revolutionary；
The earth simulator for earth is mounted on rotary table, and rotary simulation satellite is revolved around the earth together with rotary table
Transformationization；
The solar simulator is mounted on vibrating isolation foundation, is not rotated together with rotary table, and simulation inertial space is too
Sunlight is incident；
The vibrating isolation foundation has vibration isolation ditch, there is design in the middle part of vibrating isolation foundation for extraneous vibration to be isolated between workshop periphery
Foundation pit, entire variable bit rate Satellite General orbital simulation device are located in foundation pit；
The driving control system is mounted in gear reduction mechanism, for acquiring driving motor working condition and host computer
Instruction, provides rotary working platform motion control instruction accordingly, handles the failure being likely to occur, system real-time detection is worked as
Preceding speed, current location, limit information, motor operating state, power supply status and host computer communication state.
Preferably, the big retarding provides accordingly than function for acquiring driving motor working condition and host computer instruction
Rotary working platform motion control instruction handles the failure being likely to occur, system real-time detection present speed, present bit
Set, limit information, motor operating state, power supply status, host computer communication state.
Preferably, the equipment base uses cast steel reinforced structure form, has two circle anchor (bolt) holes and vibrating isolation foundation solid
Fixed connection；Planar design has the positioning convex platform of a fixed pose movement simulation platform structure and fixed circle to lead on equipment base
The positioning convex platform of rail.
Preferably, using three main beam structure supports, each girder support construction bottom extends the rotary working platform
Two auxiliary support beam structures are fixedly connected with adjacent girder top out, and three girders support corresponding platform laminate progress structure to add
Strong design, for fixing earth simulator for earth, while three girder support construction bottoms are that equiangularly spaced roll positioned at annular is led
On three pulley mechanisms of rail, the variation of rotary working platform analog satellite orbit angular velocity.
Preferably, six groups of pulley mechanisms carrying rotary working platform moves together, using helical gear and worm and gear
In conjunction with big retarding compare integrated transmission；The driving control system peace is furnished with brake sticking brake, needs tightly once encountering limit
When emergency stop vehicle, the driving control system is by automatic band-type brake brake electric under a motor, once stalling, output end turns motor
Speed is lower, close to halted state.
Preferably, the vibrating isolation foundation is by the sandstone damping bed course group under integrated poured reinforced concrete plinth and pedestal
At, it in order to improve the bearing capacity of foundation pit, prevents differential settlement, squeezes into big square pile and tubular pole in vibrating isolation foundation bottom,
Surrounding has vibration isolation ditch.
Preferably, the attitude motion emulation platform be used for analog satellite attitudes vibration, and fixed satellite earth sensor,
Sun sensor carries out the rail control performance verification under the conditions of Orbit revolutionary；Solar simulator simulation inertial space sunlight enters
It penetrates.
The present invention also provides a kind of three-axis air-bearing table variable bit rate Satellite General orbital simulation methods, which is characterized in that packet
Include following steps:
Step 1: it according to the tested in-orbit orbit angular velocity change curve of satellite, works out driving motor motion control and refers to
Order is stored on host computer；
Step 2: rational deployment adjusts the earth simulator for earth on rotary working platform, the solar simulator on vibrating isolation foundation,
And the direction of the earth sensor and sun sensor on attitude motion emulation platform, setting test original state, when necessary
It controls rotary working platform and rotates an angle；
Step 3: starting solar simulator air cooling system opens solar simulator and provides uniform and stable sun optical mode
It is quasi-；It opens earth simulator for earth and uniform and stable earth heat radiation simulation is provided；
Step 4: being arranged according to operating condition of test, and program-controlled rotary working platform is pressed in orbit angular velocity variation control instruction fortune
Then row carries out test and data collection and analysis.
Compared with prior art, the present invention has following the utility model has the advantages that structure of the invention is compact, large carrying capacity, surely
360 degree of Star Simulator rotation simulations may be implemented in qualitative height；Orbital simulation device meets extremely low fast high-precision orbital speed regulation rotation need
It asks；Orbital simulation device and method fully take into account the arrangement states and use of each attitude sensor of satellite；Simulation precision is high, and
Test application is convenient.
Detailed description of the invention
Fig. 1 is the device of the invention structural schematic diagram.
Specific embodiment
The present invention is described in detail combined with specific embodiments below.Following embodiment will be helpful to the technology of this field
Personnel further understand the present invention, but the invention is not limited in any way.It should be pointed out that the ordinary skill of this field
For personnel, without departing from the inventive concept of the premise, various modifications and improvements can be made.These belong to the present invention
Protection scope.
As shown in Figure 1, in the present embodiment, a kind of three-axis air-bearing table variable bit rate Satellite General track provided by the invention
Simulator includes rotary working platform 1, equipment base 2, annular rolling guide 3, pulley mechanism 4, gear reduction mechanism 5, appearance
State movement simulation platform 9, vibrating isolation foundation 6, earth simulator for earth 7, solar simulator 8, driving control system 11, equipment base 2 are adopted
With cast steel reinforced structure form, positioning convex platform, i.e., two circle anchor (bolt) holes guarantee its stiffness and strength, meet bearing capacity, adjust
Flat and stability requirement.
Equipment base 2 needs level-off in assembling.Planar design has the convex of a vertical columns on equipment base 2
The positioning convex platform of platform and fixed circular guideway, to guarantee the air-bearing vertical centre and rotary working platform 1 of three-axis air-bearing table
Rotation center have enough concentricitys.The equipment base is used to support entire three-axis air-bearing table variable bit rate Satellite General
Orbital simulation device, both bears system pressure, is also subjected to torque tension, and its underpart is butted against and fixed with vibrating isolation foundation, above in
Fixation is docked with attitude motion simulation platform structure in portion.
Rotary working platform 1 is made of pulley mechanism 4, gear reduction mechanism 5, annular rolling guide 3, gear reduction mechanism
5 are fixed on equipment base 2, and the pulley mechanism 4 that rotary working platform 1 is made up of several sliding blocks is fixed on guide rail.It is described
Rotary working platform using the support of three main beam structures, each girder support construction bottom extend two auxiliary support beam structures with
Adjacent girder top is connected.Three girders support corresponding platform laminate to carry out structural strengthening design, for installing earth simulation
Device etc., while three girder support construction bottoms are on equiangularly spaced three pulley mechanisms for being located at annular rolling guide,
The variation of rotary working platform analog satellite orbit angular velocity.
The annular rolling guide is for realizing 360 degree of trackwork platform and 0.00417 °/s~0.07 °/s variable angle
Rate rotatory power has six groups of pulley mechanisms to be evenly arranged by equiangularly spaced on annular rolling guide, and six groups of pulley mechanisms are held
It carries rotary working platform to move together, integrated transmission is compared using big retarding of the helical gear in conjunction with worm and gear.Specifically, ring
Six groups of pulley mechanisms 4 are fixed on shape rolling guide 3, six groups of pulley mechanisms 4 are connected with the lower end annulus of rotary working platform 1
It connects, fixes bull gear on the lower end annulus of rotary working platform 1, bull gear is matched with pinion gear, and pinion gear is passed through by motor
Speed reducer driving is crossed, rotary working platform 1 is driven to rotate.For guarantee bull gear and circular guideway concentricity, in rotary work
4 stationary positioned boss of bull gear and pulley mechanism is respectively designed on the lower end annulus of platform 1.Annular rolling guide 3 and coaster
Rolling movement is done by rolling elements such as ball or rollers between mechanism 4, substantially reduces kinetic friction force.
The pulley mechanism 4 together with rotary working platform for rotating.Above pulley mechanism and under rotary working platform
It holds annulus to be connected, makees rolling movement by rolling elements such as balls or roller with annular rolling guide below.
According to the reduction ratio of system and driving torque requirement, the driving moment requirement of driving motor is smaller, but needs to have
Biggish rotation speed change demand.Design of Speed Reducer of the invention considers that transmission ratio and return difference will be oblique using worm type of reduction gearing
Gear integrally combines with worm and gear, high transmission accuracy, small in size, and reduction ratio is big, and structure is more compact, saves space.
Described rotary working platform installation earth simulator for earth etc., the variation of analog satellite orbit angular velocity.Rotary working platform
Lower end annulus is equipped with bull gear, and bull gear is meshed with pinion gear, and pinion gear is driven by driving motor by gear reduction mechanism,
Drive rotary working platform rotation.
The gear reduction mechanism has the function of big retarding than meeting extremely low fast high-precision orbital speed regulation rotation demand, using
In acquisition driving motor working condition and host computer instruction, rotary working platform motion control instruction is provided accordingly, to may go out
Existing failure is handled, system real-time detection present speed, current location, limit information, motor operating state, power supply shape
The communication state of state, host computer.
Earth simulator for earth 7 is fixed on rotary working platform 1, with rotary working platform 1 together rotary simulation satellite around ground
Ball rotation variation, provides heat radiation input signal for earth sensor；Earth simulator for earth 7 mainly by emulation terrestrial radiation plate and
Temperature control equipment composition, the function of emulation terrestrial radiation plate are to simulate the heat radiation of the earth, the main function of temperature control equipment
Can realize that the real-time surface temperature of terrestrial radiation plate is accurately measured and controlled.
Solar simulator 8 is fixed on vibrating isolation foundation 6, is not rotated together with rotary working platform 1, and simulation inertial space is too
Sunlight is incident.The output beam angle of collimation of solar simulator 8 is consistent with sunlight, output spectrum 0.35 μm of visible light~
It is very close with solar spectrum in 0.75 μ m, irradiation uniformity with higher and stabilization in specified effective irradiation face
Property.In addition, azimuth and the pitch angle of the adjustable output collimated light beam of solar simulator 8, it can also be manual in a small range
The position of vertical direction is adjusted, in order to the alignment of solar simulator 8 output beam and sun sensor.
The vibrating isolation foundation has vibration isolation ditch, there is design in the middle part of vibrating isolation foundation for extraneous vibration to be isolated between workshop periphery
Foundation pit, entire variable bit rate Satellite General orbital simulation device are located in foundation pit.Vibrating isolation foundation 6 is mixed by integrated poured reinforcing bar
Sandstone damping bed course composition under solidifying soil matrix seat and pedestal, in order to improve the bearing capacity of foundation pit, prevents differential settlement,
Big square pile and tubular pole are squeezed into bottom of foundation ditch, there is vibration isolation ditch between surrounding and foundation pit.
The attitude motion emulation platform is used for analog satellite attitudes vibration, and installation satellite earth sensor, the sun are sensitive
Device etc. carries out the rail control performance verification under the conditions of Orbit revolutionary.
The driving control system is mounted in gear reduction mechanism, for acquiring driving motor working condition and host computer
Instruction, provides rotary working platform motion control instruction accordingly, handles the failure being likely to occur, system real-time detection is worked as
Preceding speed, current location, limit information, motor operating state, power supply status and communication state of host computer etc..
Driving control system peace is furnished with brake sticking brake, described when encountering limit etc. and needing to stop in emergency
Driving control system is by automatic band-type brake brake electric under a motor, and for motor once stalling, output end revolving speed is lower, close to
Halted state.In addition, the reduction ratio for the retarder that motor output end connects is very big, motor is once stalled, the revolving speed of output end
Will be very low, close to halted state, depending merely on friction can be enough to stop rapidly.
The present invention also provides a kind of three-axis air-bearing table variable bit rate Satellite General orbital simulation methods, include the following steps:
Step 1: according to the tested in-orbit orbit angular velocity change curve of satellite (low orbit, middle orbit, big oval rail
Road and geostationary orbit satellite track etc.), establishment driving motor motion control instruction is stored on host computer；
Step 2: rational deployment adjusts the earth simulator for earth on rotary working platform, the solar simulator on vibrating isolation foundation,
And the direction of the earth sensor and sun sensor on attitude motion simulation platform structure, setting test original state must
Rotary working platform is controlled when wanting rotates an angle；
Step 3: starting solar simulator air cooling system opens solar simulator and provides uniform and stable sun optical mode
It is quasi-；It opens earth simulator for earth and uniform and stable earth heat radiation simulation is provided；
Step 4: being arranged according to operating condition of test, and program-controlled rotary working platform changes control instruction by in-orbit orbit angular velocity
Operation carries out Test Data Collecting and analysis.
In conclusion structure of the invention is compact, large carrying capacity, stability is high, and 360 degree of Star Simulator rotation moulds may be implemented
It is quasi-；Orbital simulation device meets extremely low fast high-precision orbital speed regulation rotation demand；Orbital simulation device and method fully take into account
The arrangement states and use of each attitude sensor of satellite；Simulation precision is high, and it is convenient to test application.The present invention can carry out low rail
The simulations such as road, middle orbit, highly elliptic orbit and geostationary orbit satellite Orbit revolutionary carry out the test of rail control performance simulation.
Specific embodiments of the present invention are described above.It is to be appreciated that the invention is not limited to above-mentioned
Particular implementation, those skilled in the art can make various deformations or amendments within the scope of the claims, this not shadow
Ring substantive content of the invention.
Claims (8)
1. a kind of three-axis air-bearing table variable bit rate Satellite General orbital simulation device, which is characterized in that the three-axis air-bearing table can
Variable Rate Satellite General orbital simulation device includes rotary working platform, equipment base, annular rolling guide, pulley mechanism, biography
Dynamic deceleration mechanism, attitude motion emulation platform, vibrating isolation foundation, earth simulator for earth, solar simulator, driving control system；
Wherein, the equipment base is used to support entire analog satellite track motion simulator, bears system pressure and torque
Pulling force, its underpart are butted against and fixed with vibrating isolation foundation, and upper Middle face docks fixation with attitude motion simulation platform structure；
The annular rolling guide can be changed angular speed for realizing 360 degree of trackwork platform and 0.00417 °/s~0.07 °/s
Rotatory power has six groups of pulley mechanisms to be evenly arranged by equiangularly spaced on annular rolling guide；
The pulley mechanism together with rotary working platform for rotating；Above pulley mechanism with rotary working platform lower end annulus
It is connected, rolling movement is made by ball or roller with annular rolling guide below；
The rotary working platform installs earth simulator for earth, the variation of analog satellite orbit angular velocity；Rotary working platform lower end circle
Ring is equipped with bull gear, and bull gear is meshed with pinion gear, and pinion gear is driven by driving motor by gear reduction mechanism, drives rotation
Turn workbench rotation；
The gear reduction mechanism has the function of big retarding than meeting extremely low fast high-precision orbital speed regulation rotation demand；
The attitude motion emulation platform be used for analog satellite attitudes vibration, installation satellite earth sensor, sun sensor into
Rail control performance verification under the conditions of row Orbit revolutionary；
The earth simulator for earth is mounted on rotary table, and rotary simulation satellite becomes around earth rotation together with rotary table
Change；
The solar simulator is mounted on vibrating isolation foundation, is not rotated together with rotary table, and inertial space sunlight is simulated
It is incident；
The vibrating isolation foundation has vibration isolation ditch for extraneous vibration to be isolated between workshop periphery, and design has foundation pit in the middle part of vibrating isolation foundation,
Entire variable bit rate Satellite General orbital simulation device is located in foundation pit；
The driving control system is mounted in gear reduction mechanism, is referred to for acquiring driving motor working condition and host computer
It enables, provides rotary working platform motion control instruction accordingly, the failure being likely to occur is handled, system real-time detection is current
Speed, current location, limit information, motor operating state, power supply status and host computer communication state.
2. three-axis air-bearing table variable bit rate Satellite General orbital simulation device according to claim 1, which is characterized in that institute
Big retarding is stated than function for acquiring driving motor working condition and host computer instruction, provides rotary working platform movement control accordingly
System instruction, handles the failure being likely to occur, system real-time detection present speed, current location, limit information, motor fortune
Row state, power supply status, host computer communication state.
3. three-axis air-bearing table variable bit rate Satellite General orbital simulation device according to claim 1, which is characterized in that institute
Equipment base is stated using cast steel reinforced structure form, there are two circle anchor (bolt) holes to be fixedly connected with vibrating isolation foundation；On equipment base
Planar design has the positioning convex platform of a fixed pose movement simulation platform structure and the positioning convex platform of fixed circular guideway.
4. three-axis air-bearing table variable bit rate Satellite General orbital simulation device according to claim 1, which is characterized in that institute
Rotary working platform is stated using three main beam structure supports, two auxiliary support beam structures are extended in each girder support construction bottom
It is fixedly connected with adjacent girder top, three girders support corresponding platform laminate to carry out structural strengthening design, for fixedly
Ball simulator, while three girder support construction bottoms are equiangularly spaced three pulley mechanisms for being located at annular rolling guide
On, the variation of rotary working platform analog satellite orbit angular velocity.
5. three-axis air-bearing table variable bit rate Satellite General orbital simulation device according to claim 1, which is characterized in that institute
It states six groups of pulley mechanism carrying rotary working platforms to move together, using big retarding of the helical gear in conjunction with worm and gear than one
Transmission；Driving control system peace is furnished with brake sticking brake, and when encountering limit and needing to stop in emergency, the driving is controlled
System processed passes through electric automatic band-type brake brake under a motor, and for motor once stalling, output end revolving speed is lower, close to stopping shape
State.
6. three-axis air-bearing table variable bit rate Satellite General orbital simulation device according to claim 1, which is characterized in that institute
It states vibrating isolation foundation to be made of the sandstone damping bed course under integrated poured reinforced concrete plinth and pedestal, in order to improve foundation pit
Bearing capacity prevents differential settlement, squeezes into big square pile and tubular pole in vibrating isolation foundation bottom, surrounding has vibration isolation ditch.
7. three-axis air-bearing table variable bit rate Satellite General orbital simulation device according to claim 1, which is characterized in that institute
Attitude motion emulation platform is stated for analog satellite attitudes vibration, and fixed satellite earth sensor, sun sensor carry out rail
Rail control performance verification under road change condition；It is incident that solar simulator simulates inertial space sunlight.
8. a kind of such as the three of the described in any item three-axis air-bearing table variable bit rate Satellite General orbital simulation devices of claim 1-7
Axis air floating table variable bit rate Satellite General orbital simulation method, which comprises the steps of:
Step 1: it according to the tested in-orbit orbit angular velocity change curve of satellite, works out driving motor motion control instruction and protects
There are on host computer；
Step 2: rational deployment adjusts the earth simulator for earth on rotary working platform, the solar simulator on vibrating isolation foundation, and
The direction of earth sensor and sun sensor on attitude motion emulation platform, setting test original state, controls when necessary
Rotary working platform rotates an angle；
Step 3: starting solar simulator air cooling system opens solar simulator and provides uniform and stable sun optical analog；It beats
It opens earth simulator for earth and uniform and stable earth heat radiation simulation is provided；
Step 4: being arranged according to operating condition of test, and program-controlled rotary working platform is pressed in orbit angular velocity variation control instruction operation, so
After carry out test and data collection and analysis.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611030980.5A CN106742089B (en) | 2016-11-16 | 2016-11-16 | Three-axis air-bearing table variable bit rate Satellite General orbital simulation device and method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611030980.5A CN106742089B (en) | 2016-11-16 | 2016-11-16 | Three-axis air-bearing table variable bit rate Satellite General orbital simulation device and method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106742089A CN106742089A (en) | 2017-05-31 |
| CN106742089B true CN106742089B (en) | 2019-06-28 |
Family
ID=58970931
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611030980.5A Active CN106742089B (en) | 2016-11-16 | 2016-11-16 | Three-axis air-bearing table variable bit rate Satellite General orbital simulation device and method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106742089B (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110060552B (en) * | 2019-03-26 | 2021-07-20 | 南京航空航天大学 | Satellite constellation orbit physical simulation experiment platform |
| CN113479355B (en) * | 2021-08-12 | 2022-04-29 | 哈尔滨工业大学 | Ground variable-centroid zero-gravity simulation device and method |
| CN114162354B (en) * | 2021-09-30 | 2024-03-29 | 哈尔滨工业大学 | Executing device for simulating Mars attraction |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101551301A (en) * | 2009-04-24 | 2009-10-07 | 哈尔滨工业大学 | Satellite orbit motion ground simulation system and method |
| CN102354123A (en) * | 2011-07-18 | 2012-02-15 | 北京航空航天大学 | Cross-platform extendible satellite dynamic simulation test system |
| CN102520719A (en) * | 2011-12-06 | 2012-06-27 | 北京邮电大学 | Microgravity air floatation target satellite simulator system with five degrees of freedom |
| CN105182798A (en) * | 2015-09-10 | 2015-12-23 | 哈尔滨工业大学 | Ground motion full-physical simulation system for spacecraft |
| CN105480440A (en) * | 2015-11-23 | 2016-04-13 | 上海卫星装备研究所 | Open earth simulator applied to three-axis air bearing table |
| CN105936339A (en) * | 2016-06-14 | 2016-09-14 | 南京航空航天大学 | Micro-gravity environment ground air flotation simulation mechanism and system and working method thereof |
| CN106005497A (en) * | 2016-06-13 | 2016-10-12 | 北京航空航天大学 | Suspension type six-degree-of-freedom micro-gravity environment simulating system |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR100835656B1 (en) * | 2007-08-13 | 2008-06-05 | 한국항공우주연구원 | Deployment test apparatus of solar array |
-
2016
- 2016-11-16 CN CN201611030980.5A patent/CN106742089B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101551301A (en) * | 2009-04-24 | 2009-10-07 | 哈尔滨工业大学 | Satellite orbit motion ground simulation system and method |
| CN102354123A (en) * | 2011-07-18 | 2012-02-15 | 北京航空航天大学 | Cross-platform extendible satellite dynamic simulation test system |
| CN102520719A (en) * | 2011-12-06 | 2012-06-27 | 北京邮电大学 | Microgravity air floatation target satellite simulator system with five degrees of freedom |
| CN105182798A (en) * | 2015-09-10 | 2015-12-23 | 哈尔滨工业大学 | Ground motion full-physical simulation system for spacecraft |
| CN105480440A (en) * | 2015-11-23 | 2016-04-13 | 上海卫星装备研究所 | Open earth simulator applied to three-axis air bearing table |
| CN106005497A (en) * | 2016-06-13 | 2016-10-12 | 北京航空航天大学 | Suspension type six-degree-of-freedom micro-gravity environment simulating system |
| CN105936339A (en) * | 2016-06-14 | 2016-09-14 | 南京航空航天大学 | Micro-gravity environment ground air flotation simulation mechanism and system and working method thereof |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106742089A (en) | 2017-05-31 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN205352219U (en) | Three -dimensional test turntable of guided missile | |
| CN106742089B (en) | Three-axis air-bearing table variable bit rate Satellite General orbital simulation device and method | |
| CN102393213B (en) | Space-based detecting and tracking imaging system testing device and testing method | |
| CN106134364B (en) | A kind of satellite automated mounting plate | |
| CN103085992A (en) | Spatial microgravity simulation experiment system | |
| CN104443448A (en) | Cable drive robot device for simulating zero-gravity and low-gravity environment | |
| CN102556363B (en) | Servo motor type undercarriage retractile follow-up loading system and loading method of loading system | |
| CN204188800U (en) | With the servo platform of motion compensation | |
| CN102530264B (en) | Pneumatic load simulator for undercarriage control test | |
| CN105652684A (en) | Novel large-size four-freedom attitude simulation structure | |
| CN104477420A (en) | Nine-rope driving robot device for simulating zero gravity and low gravity | |
| CN105217058B (en) | Aircraft simulation air floating table mass property adjusting apparatus and method | |
| CN112067313B (en) | Low-gravity simulation test device and method for solar wing of mars vehicle | |
| CN104931219A (en) | Landing impact test device and test method thereof | |
| CN103662109A (en) | Device for simulating microgravity on lunar surface | |
| CN102087104A (en) | Three-coordinate conversion machine for measuring aircraft quality characteristics, test system and method | |
| CN212556849U (en) | High-precision double-shaft simulation turntable with no shielding of clearance of pitching shaft | |
| CN103149227B (en) | Precise main body movement device for high-resolution powder diffractometer | |
| CN104932559A (en) | Six-degree-of-freedom air bearing table mass center adjustment mechanism and adjustment method | |
| CN202807109U (en) | Space target simulation system used for on-orbit service | |
| CN103018100B (en) | Horizontal loading device for geotechnical centrifuge modeling test | |
| CN102072796A (en) | Solar battery array dynamic-measurement system | |
| CN102789241B (en) | Device and method for simulating solar illumination with autoregulative elevation angle | |
| CN103869835A (en) | Device for adjusting mass center of three-axis air bearing table based on non-orthogonal structure | |
| CN102141463A (en) | Slewing mechanism of swing test bench |
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 | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |