CN109080851A - Cube star moment of mass disymmetry is laid out attitude-control device - Google Patents
Cube star moment of mass disymmetry is laid out attitude-control device Download PDFInfo
- Publication number
- CN109080851A CN109080851A CN201810752986.6A CN201810752986A CN109080851A CN 109080851 A CN109080851 A CN 109080851A CN 201810752986 A CN201810752986 A CN 201810752986A CN 109080851 A CN109080851 A CN 109080851A
- Authority
- CN
- China
- Prior art keywords
- fixed
- linear motor
- moment
- clump weight
- cube
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 230000007246 mechanism Effects 0.000 claims abstract description 24
- NJPPVKZQTLUDBO-UHFFFAOYSA-N novaluron Chemical compound C1=C(Cl)C(OC(F)(F)C(OC(F)(F)F)F)=CC=C1NC(=O)NC(=O)C1=C(F)C=CC=C1F NJPPVKZQTLUDBO-UHFFFAOYSA-N 0.000 claims description 12
- 230000006870 function Effects 0.000 claims description 4
- 230000008450 motivation Effects 0.000 claims 1
- 238000013519 translation Methods 0.000 abstract description 6
- 238000005516 engineering process Methods 0.000 description 8
- 239000007787 solid Substances 0.000 description 8
- 238000013461 design Methods 0.000 description 7
- 238000011160 research Methods 0.000 description 5
- 238000000034 method Methods 0.000 description 4
- 238000011161 development Methods 0.000 description 3
- 239000004449 solid propellant Substances 0.000 description 3
- 230000006641 stabilisation Effects 0.000 description 3
- 238000011105 stabilization Methods 0.000 description 3
- 230000008901 benefit Effects 0.000 description 2
- 238000004880 explosion Methods 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 238000009987 spinning Methods 0.000 description 2
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 238000011217 control strategy Methods 0.000 description 1
- 238000013016 damping Methods 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005265 energy consumption Methods 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/10—Artificial satellites; Systems of such satellites; Interplanetary vehicles
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/24—Guiding or controlling apparatus, e.g. for attitude control
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/24—Guiding or controlling apparatus, e.g. for attitude control
- B64G1/244—Spacecraft control systems
- B64G1/245—Attitude control algorithms for spacecraft attitude control
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/10—Geometric CAD
- G06F30/15—Vehicle, aircraft or watercraft design
Abstract
The invention discloses a kind of cube of star moment of mass disymmetrys to be laid out attitude-control device, including control module, movement mechanism and fixed device, control module includes system control panel and motor driving plate, 4 motor driving plates are fixed in system control panel, it is connect by soft arranging wire with linear motor, 4 linear motors are parallel two-by-two, vertical symmetry arrangement, linear motor and clump weight constitute movement mechanism, fixed device limits movement mechanism freedom of motion, and fixed straight line motor shaft, linear motor can in guide-track groove free translation, it fixes device and control module and relative positional relationship is determined by quadrangle through-hole and stud.The present invention uses the clump weight layout type of disymmetry, reduces present apparatus occupied space, simplifies the kinematics and dynamics modeling of satellite, realizes effective control of executing agency.
Description
Technical field
The invention belongs to Spacecraft Attitude Control fields, and in particular to a kind of cube of star moment of mass disymmetry is laid out posture control
Device processed.
Background technique
With the continuous development of space technology, various countries' transmitting spacecraft quantity is more and more, but current cube of star platform
Orbit maneuver ability with respect to showing slightly insufficient for other platform technologys such as attitude control, communication, be suitable for cube star track machine at present
The propulsion system of dynamic task mainly has the modes such as cold air propulsion, liquid propulsion, solid propellant propulsion, electric propulsion and solar sail propulsion.Its
Middle solid propellant propulsion is since density impulse is high, occupy small volume in star, structure is simple, the working time is short, reliable performance etc. is excellent
Gesture is used compared with lesser cube of star platform of suitable volume power consumption, and with a cube development for star technology, solid thruster is in a cube star
Fast railway is motor-driven, quickly leave the right or normal track and the advantage of track deployment etc. also highlights, and is with a wide range of applications.
The shortcomings that becoming rail using solid thruster is to be easy to cause the attitude of satellite there are biggish thrust eccentric torque
Overturning, and the control of the angular momentum of satellite platform itself or magnetic control mode absorb the scarce capacity of disturbing moment.For this problem,
It can be given by modes such as the pneumatic rudder of design engine, vector nozzle, multiinjectors generally for for large-sized solid engine
It solves；And more generally using spinning stability or using three-axis stabilization attitude control engine for Small Solid Rocket Motor
Method, but both modes come with some shortcomings: and spinning stability is untwisted for cube star and is difficult to realize, and due to starting
The presence of machine jet-damping torque may be such that satellite, and there are nutating wild effects, and use three-axis stabilization attitude control engine
If will increase dramatically the complexity of cube star.
The basic principle of moment of mass attitude control technology be using the movement of several movable mass blocks in carrier inside come
Change centroid position, the outer arm of force of the corrective action on carrier realizes carrier maneuvering flight, with the appearance using three-axis stabilization
Control engine is compared, and this mode of moment of mass gesture stability greatly reduces the cost and complexity of satellite gravity anomaly, and
Since tail portion thrust is larger, movable mass block only needs the displacement of a very little that can generate biggish control moment to realize appearance
The adjustment of state.
Moment of mass technology is mainly applied and reenters bullet and anti-missile interceptor field.Bullet field is being reentered, it is open earliest
Moving Mass Trim Control is reported in 1984, the scientist Regan in USN's water surface war research center et al. is in order to improve again
The terminal guidance precision for entering bullet designs a kind of single-degree-of-freedom movable mass body trim control, can be when close to target pair
Axial symmetry ballistic missile trajectory does appropriate amendment.In anti-missile interception field, interceptor Moving Mass Trim Control is also obtained
Extensive concern.Disclosed document shows the scientist Chadwick in USN's water surface war research center in 2000 et al. earliest
Moment of mass technology is used in the Guidance and control of anti-missile system kinetic interception, and points out that the U.S. makees Moving Mass Trim Control
Control method for endoatmosphere and exoatmosphere kinetic interception weapon is studied.
Northwestern Polytechnical University Zhou Fengqi professor and its seminar have carried out research in this respect earlier, have done many valuable
The work of value, team have done many mainly using reentry vehicle as research background in terms of control mechanism and design of control law
Work；Long-living, Li Ruikang of height of Harbin Institute of Technology et al. to based on Moving Mass Trim Control reentry vehicle modeling, hold
The key technologies such as total arrangement, model affineization, control strategy, the reentry guidance control of row mechanism have all carried out system research,
The development of China's Moving Mass Trim Control is effectively pushed.The Second Academy of Aerospace Science and Industry Corporation is also the section that China is more early engaged in the technology
Unit is ground, using the mass moment control of anti-missile interceptor as research background, biases toward Mass Moment Missile movement mechanism and population parameter
The research of design.
Designed quality moment device out at present, is mostly applied in terms of missile guidance, volume is larger, is not suitable for size
Only 1U or 2U cubes of star, due to spaces compact in star, quality moment device, which will fully consider, occupies volume and power consumption, so needing
For the structure size feature of cube star, the layout type of quality moment device is rethought, the present invention uses disymmetry
Clump weight layout type.
Summary of the invention
The purpose of the present invention is to provide a kind of cube of star moment of mass disymmetrys to be laid out attitude-control device, is suitable for track
The gesture stability of cube star in the motor-driven solid propellant propulsion course of work can not only solve and exist when becoming rail using solid thruster
The problem of biggish thrust eccentric torque causes the attitude of satellite to be flipped, but also solve vertical symmetry in the same plane and pacify
Fill the problem of movement that two linear motors encounter interferes with each other.
The technical solution for realizing the aim of the invention is as follows: a kind of cube star disymmetry moment of mass attitude-control device leads to
It crosses quadrangle through-hole and stud realizes that position of the quality moment device inside cube star is fixed；Its main part occupancy 100mm ×
The space of 100mm × 40mm, described cube of star moment of mass attitude-control device include control module, movement mechanism and fixed dress
It sets, movement mechanism is fixed on the top surface of fixed device, and control module is fixed on the surface of fixed device, and control module is located at
The surface of movement mechanism.
The control module includes system control panel, 4 motor driving plates and 4 linear motor connectors, and 4 motors drive
Movable plate is arranged in system control panel top surface, is connected by contact pin pin, 4 linear motor connectors are symmetrically welded at system control
The bottom surface of plate, connect with movement mechanism.
The movement mechanism include 4 straight-line electric arbors, 4 linear motor shells, two identical first clump weights and
Two identical second clump weights；A linear motor shell, two adjacent linear motors are cased on every straight-line electric arbor 6
There are difference in height between axis, 4 linear motor axial projections constitute rectangular, symmetrical two straight-line electrics arbor height in the horizontal plane
Equal, two identical first clump weights are fixed on two high linear motor outer casing bottoms of height, and two identical second are matched
Pouring weight is fixed on two low linear motor outer casing bottoms of height, and the first clump weight and the second clump weight bottom are equipped with boss,
Enable the first clump weight and the second clump weight along fixed device sliding.
First clump weight includes the first U-shaped fixture block and the first sliding block, the open end of the first U-shaped fixture block and linear motor
Shell is connected, and the first sliding block is fixed on the first U-shaped fixture block bottom centre, and boss is at the first slider bottom center, and boss is along fixed
Device sliding.
Second clump weight includes the second U-shaped fixture block, and the open end of the second U-shaped fixture block and linear motor shell are connected,
Boss is along fixed device sliding.
The fixed device includes pedestal, 4 studs and 4 mounting bases, and the pedestal includes 4 guide-track grooves and 4 limits
Position block, the generally square frame of pedestal 12, four limited blocks are located at four angles of frame, are limited adjacent two by guide-track groove
Position block connection, 4 mounting bases are separately fixed at 4 limited block top surfaces, and straight-line electric arbor is fixed on two adjacent limited blocks,
The both ends of straight-line electric arbor are inserted into respectively in the shaft through-hole of mounting base, have fastening thread hole for fastener shaft in each through-hole
End；First clump weight, the second clump weight are slided along 4 guide-track grooves respectively, and guide-track groove limits the rotation of linear motor shell, and 4
The bottom of root stud respectively corresponds the top surface for being fixed on limited block, and control module is fixed on the top surface of 4 studs, and stud is to control
Module plays support fixed function.
The corresponding linear motor shell of each linear motor connector is matched in same vertical plane with reducing first
Frictional force between pouring weight, the second clump weight and guide-track groove.
Compared with prior art, the present invention its remarkable advantage is:
(1) present invention occupy it is small in size, comply fully with the miniaturization of cube star, lightweight requirements, reduce to other systems quality and
The limitation in space improves the functional density of cube star.
(2) present invention uses the clump weight layout type of disymmetry, realizes clump weight freely putting down in centroid of satellite plane
It is dynamic, avoid the problem of movement that vertical symmetry installs that two linear motors encounter in same level interferes with each other.
(3) present invention using clump weight difference design, guarantee 4 counterweight mass centers and centroid of satellite in same level,
Greatly simplify the kinematics and dynamics modeling of satellite.
(4) present invention arranges linear motor and motor connector in the same vertical plane, avoids connection linear motor
Soft arranging wire lateral force and rotating torque are generated to linear motor, when reducing clump weight movement the friction between guide-track groove
Power reduces the energy consumption in motion process.
(5) guide-track groove is designed on pedestal of the present invention, avoids rotation of the linear motor relative to satellite body, limitation movement
Mechanism is single-degree-of-freedom translation, realizes effective control of executing agency.
Detailed description of the invention
Fig. 1 is cube star quality moment device entirety tomograph of the invention.
Fig. 2 is cube star quality moment device stereochemical structure perspective view of the explosion of the invention.
Fig. 3 is cube star moment of mass device control module top view of the invention.
Fig. 4 is cube star quality moment device movement mechanism stereochemical structure bottom view of the invention.
Fig. 5 is the fixed device stereochemical structure main view of the present invention cube star quality moment device.
Fig. 6 is cube star quality moment device installation relation perspective view of the explosion of the invention.
Specific embodiment
Present invention is further described in detail with reference to the accompanying drawing.
In conjunction with Fig. 1, Fig. 2 and Fig. 6, a kind of cube star disymmetry moment of mass attitude-control device, main part is occupied
The space 100mm × 100mm × 40mm realizes that position of the quality moment device inside cube star is solid by quadrangle through-hole and stud
It is fixed.
Described cube of star moment of mass attitude-control device includes control module 1, movement mechanism 2 and fixed device 3, fitness machine
Structure 2 is fixed on the top surface of fixed device 3, and control module 1 is fixed on the surface of fixed device, and control module 1 is located at movement
The surface of mechanism 2.
In conjunction with Fig. 3, the control module 1 includes that 5,4 motor driving plate 4 and 4 linear motors of system control panel patch
20,4 motor driving plates 4 of part are arranged in 5 top surface of system control panel, are connected by contact pin pin, the distribution of 5 surrounding of system control panel
Multiple posture control system connectors 14 are connect by posture control system connector 14 with the other systems of satellite, quadrangle in system control panel 5
There are 4 first through hole 13 to play positioning and fixed function, 4 linear motor connectors 20 are symmetrically welded at system control panel 5
Bottom surface is connect with the linear motor shell 7 of movement mechanism 2.
In conjunction with Fig. 4, movement mechanism 2 includes that 47, two, linear motor shells of straight-line electric arbor 6,4 identical first are matched
Pouring weight 8 and two identical second clump weights 9；It is cased with a linear motor shell 7 on every straight-line electric arbor 6, adjacent two
There are difference in height between root straight-line electric arbor 6,4 projections of straight-line electric arbors 6 constitute rectangular in the horizontal plane, and symmetrical two straight
The height of line motor shaft 6 is equal, and two identical first clump weights 8 are fixed on two high 7 bottoms of linear motor shell of height, and two
A identical second clump weight 9 is fixed on two low 7 bottoms of linear motor shell of height, the first clump weight 8 and the second counterweight
9 bottom of block is equipped with boss, and the first clump weight 8 and the second clump weight 9 are slided along fixed device 3.
First clump weight 8 includes the first U-shaped fixture block and the first sliding block, the open end of the first U-shaped fixture block and straight-line electric
Machine shell 7 is connected, and the first sliding block is fixed on the first U-shaped fixture block bottom centre, and boss is fixed on the first slider bottom center, boss
It is slided in guide-track groove 16.
Second clump weight 9 includes the second U-shaped fixture block, and the open end of the second U-shaped fixture block and linear motor shell 7 are solid
Even, boss is fixed on the second U-shaped fixture block bottom centre, and boss slides in guide-track groove 16.
The movement of the movement mechanism 2 is linear motor shell 7 and the first clump weight 8, the second clump weight 9 in respective straight line
Single-degree-of-freedom translation on 6 direction of motor shaft, motor translation range are limited by 6 length of straight-line electric arbor.Threaded hole 15 is used
It is fixed on corresponding linear motor shell 7 in by the first clump weight 8, the second clump weight 9.In the first clump weight 8, the second counterweight
Boss is designed on block 9 moves it on guide-track groove 16, avoids rotation of the linear motor shell 7 relative to satellite body, limits
Movement mechanism processed is single-degree-of-freedom translation, realizes effective control of executing agency.It is installed due to adjacent straight line motor shaft 6 and there is height
It is poor to spend, therefore the difference design of the first clump weight 8, the second clump weight 9 makes counterweight mass center in same level.
In conjunction with Fig. 5, fixed device 3 includes 12,4 stud 10 and 4 mounting bases 11 of pedestal, and the pedestal 12 includes 4
Guide-track groove 16 and 4 limited block 19, the generally square frame of pedestal 12, four limited blocks 19 are located at four angles of frame, pass through
Guide-track groove 16 connects two adjacent limited blocks 19, and 4 mounting bases 11 are separately fixed at 4 limited blocks 19 by bolt and push up
Face, straight-line electric arbor 6 are fixed on two adjacent limited blocks 19, and mounting base 11 is inserted at the both ends of straight-line electric arbor 6 respectively
In shaft through-hole 18, there is fastening thread hole 17 for fastening shaft end in each through-hole 18.First clump weight 8, the second clump weight 9 divide
It is not slided along 4 guide-track grooves 16, guide-track groove 16 limits the rotation of linear motor shell 7, and the bottom of 4 studs 10 respectively corresponds
It is fixed on the top surface of limited block 19, control module 1 is fixed on the top surface of 4 studs 10,10 pairs of stud controls by first through hole 13
Molding block 1 plays support fixed function.
The corresponding linear motor shell 7 of each linear motor connector 20 is in same vertical plane, to reduce
Frictional force between one clump weight 8, the second clump weight 9 and guide-track groove 16.
Job description
A kind of cube of star moment of mass disymmetry of the present invention is laid out attitude-control device, the system control in control module 1
Plate 5 receives the control signal from attitude control computer, and sends control signal, motor driving plate 4 to corresponding motor driving plate 4
It is connected by motor connector 20 and its soft arranging wire with linear motor shell 7 corresponding in movement mechanism 2, is achieved in device fortune
Dynamic control route.
The present invention is installed on a cube star centroidal planes, cube star become a trailer it is dynamic before, using motor is internally-damped will be straight
The position of line motor housing 7 and the first clump weight 8, the second clump weight 9 on straight-line electric arbor 6 is fixed, and the present apparatus does not influence to stand
The normal in-orbit task of square star.When need to become trailer it is dynamic when, Solid propeller works first, then thrust eccentric inevitably occurs
Lead to a cube star overturning, attitude sensor measurement at this time obtains attitude offsets amount, is calculated accordingly by gesture stability algorithm
Linear motor shell 7 on straight-line electric arbor 6 position control signal, real-time control linear motor shell 7 and the first clump weight
8, the real-time amendment of cube star posture is realized so as to adjust the centroid position of cube star in the position of the second clump weight 9.
In conclusion cube star disymmetry moment of mass attitude-control device of the invention is small in size, light weight is complied fully with
Cube star will not influence the running of other systems to the device miniaturization, lightweight requirements of leaving the right or normal track, modularization, independent, and
And requirements at the higher level are not proposed to the service life of other subsystems.In addition, the present invention uses the clump weight layout type of disymmetry, it is real
In the free translation of centroid of satellite plane, it is vertical right in same level to avoid for existing first clump weight 8, the second clump weight 9
The problem of claiming the installation movement that two linear motors encounter to interfere with each other.Meanwhile the present invention is matched using the first clump weight 8, second
The difference design of pouring weight 9, the first clump weight 8 of guarantee, 9 mass center of the second clump weight and centroid of satellite are in same level, greatly letter
The kinematics and dynamics modeling of satellite is changed.Moreover, designing guide-track groove 16 on pedestal 12 of the present invention, avoid outside linear motor
Rotation of the shell 7 relative to satellite body, limiting mechanism movement are that single-degree-of-freedom is translatable, and realize effective control of executing agency.
Claims (7)
1. a kind of cube star disymmetry moment of mass attitude-control device realizes quality moment device vertical by quadrangle through-hole and stud
Position inside Fang Xing is fixed；It is characterized by: its main part occupancy space 100mm × 100mm × 40mm, described cube
Star moment of mass attitude-control device includes control module (1), movement mechanism (2) and fixes device (3), and movement mechanism (2) is fixed
In the top surface of fixed device (3), control module (1) is fixed on the surface of fixed device, and control module (1) is located at fitness machine
The surface of structure (2).
2. according to claim 1 cube of star disymmetry moment of mass attitude-control device, it is characterised in that: the control mould
Block (1) includes system control panel (5), 4 motor driving plates (4) and 4 linear motor connectors (20), 4 motor driving plates
(4) it is arranged in system control panel (5) top surface, is connected by contact pin pin, 4 linear motor connectors (20) are symmetrically welded at and are
The bottom surface of system control panel (5), connect with movement mechanism (2).
3. according to claim 1 or 2 cube of star disymmetry moment of mass attitude-control device, it is characterised in that: the fortune
Motivation structure (2) includes 4 straight-line electric arbors (6), 4 linear motor shells (7), two identical first clump weights (8) and two
A identical second clump weight (9)；A linear motor shell (7), two adjacent straight lines are cased on every straight-line electric arbor 6
There are difference in height between motor shaft (6), 4 straight-line electric arbor (6) projections constitute rectangular, symmetrical two straight lines in the horizontal plane
Motor shaft (6) height is equal, and two identical first clump weights (8) are fixed on two high linear motor shell (7) bottoms of height
Portion, two identical second clump weights (9) are fixed on two low linear motor shell (7) bottoms of height, the first clump weight (8)
It is equipped with boss with the second clump weight (9) bottom, so that the first clump weight (8) and the second clump weight (9) can be along fixed devices
(3) it slides.
4. according to claim 3 cube of star disymmetry moment of mass attitude-control device, it is characterised in that: described first matches
Pouring weight (8) includes the first U-shaped fixture block and the first sliding block, and the open end and linear motor shell (7) of the first U-shaped fixture block are connected, the
One sliding block is fixed on the first U-shaped fixture block bottom centre, and boss is at the first slider bottom center, and boss is along fixed device (3) sliding.
5. according to claim 3 cube of star disymmetry moment of mass attitude-control device, it is characterised in that: described second matches
Pouring weight (9) includes the second U-shaped fixture block, and the open end and linear motor shell (7) of the second U-shaped fixture block are connected, and boss is along fixed dress
Set (3) sliding.
6. according to claim 3 cube of star disymmetry moment of mass attitude-control device, it is characterised in that: the fixed dress
Setting (3) includes pedestal (12), 4 studs (10) and 4 mounting bases (11), and the pedestal (12) includes 4 guide-track grooves (16) and 4
A limited block (19), the generally square frame of pedestal 12, four limited blocks (19) are located at four angles of frame, pass through guide-track groove
(16) two adjacent limited blocks (19) are connected, 4 mounting bases (11) are separately fixed at 4 limited block (19) top surfaces, straight line
Motor shaft (6) is fixed on two adjacent limited blocks (19), and mounting base (11) is inserted at the both ends of straight-line electric arbor (6) respectively
In shaft through-hole (18), there are fastening thread hole (17) for fastening shaft end in each through-hole (18)；First clump weight (8), second
Clump weight (9) is slided along 4 guide-track grooves (16) respectively, and guide-track groove (16) limits the rotation of linear motor shell (7), 4 spiral shells
The bottom of column (10) respectively corresponds the top surface for being fixed on limited block (19), and control module (1) is fixed on the top of 4 studs (10)
Face, stud (10) play support fixed function to control module (1).
7. according to claim 6 cube of star disymmetry moment of mass attitude-control device, it is characterised in that: each straight-line electric
The corresponding linear motor shell (7) of machine connector (20) is in same vertical plane, to reduce the first clump weight (8), the
Frictional force between two clump weights (9) and guide-track groove (16).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810752986.6A CN109080851A (en) | 2018-07-10 | 2018-07-10 | Cube star moment of mass disymmetry is laid out attitude-control device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810752986.6A CN109080851A (en) | 2018-07-10 | 2018-07-10 | Cube star moment of mass disymmetry is laid out attitude-control device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109080851A true CN109080851A (en) | 2018-12-25 |
Family
ID=64837502
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810752986.6A Pending CN109080851A (en) | 2018-07-10 | 2018-07-10 | Cube star moment of mass disymmetry is laid out attitude-control device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109080851A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110562495A (en) * | 2019-08-15 | 2019-12-13 | 南京理工大学 | Cube star offset momentum attitude control system |
| CN110562494A (en) * | 2019-09-19 | 2019-12-13 | 中国人民解放军国防科技大学 | satellite thrust eccentric moment control device and method |
| CN111776200A (en) * | 2020-07-13 | 2020-10-16 | 中山大学 | Sliding mass moment control device and aircraft using same |
| CN112591156A (en) * | 2020-12-21 | 2021-04-02 | 星众空间(北京)科技有限公司 | 1U cube star quality simulator |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103121514A (en) * | 2011-11-18 | 2013-05-29 | 上海宇航系统工程研究所 | Attitude control method applied to centroid transverse moving spacecraft |
| CN104401506A (en) * | 2014-10-23 | 2015-03-11 | 上海卫星工程研究所 | Zero-counterweight barycenter deploying method for parallel tiling tank satellite |
| CN104477410A (en) * | 2014-11-03 | 2015-04-01 | 上海卫星工程研究所 | Motion and still isolation master-slave cooperative control double superior satellite platform |
| US9296494B1 (en) * | 2012-08-10 | 2016-03-29 | Lockheed Martin Corporation | Thruster orbit control method and configuration |
| CN105620792A (en) * | 2016-02-05 | 2016-06-01 | 上海微小卫星工程中心 | Method for controlling attitude and orbit of satellite by adopting obliquely-arranged thrusters |
-
2018
- 2018-07-10 CN CN201810752986.6A patent/CN109080851A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103121514A (en) * | 2011-11-18 | 2013-05-29 | 上海宇航系统工程研究所 | Attitude control method applied to centroid transverse moving spacecraft |
| US9296494B1 (en) * | 2012-08-10 | 2016-03-29 | Lockheed Martin Corporation | Thruster orbit control method and configuration |
| CN104401506A (en) * | 2014-10-23 | 2015-03-11 | 上海卫星工程研究所 | Zero-counterweight barycenter deploying method for parallel tiling tank satellite |
| CN104477410A (en) * | 2014-11-03 | 2015-04-01 | 上海卫星工程研究所 | Motion and still isolation master-slave cooperative control double superior satellite platform |
| CN105620792A (en) * | 2016-02-05 | 2016-06-01 | 上海微小卫星工程中心 | Method for controlling attitude and orbit of satellite by adopting obliquely-arranged thrusters |
Non-Patent Citations (1)
| Title |
|---|
| 陆正亮等: "立方体卫星质量矩姿态控制建模与布局优化", 《系统工程与电子技术》 * |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110562495A (en) * | 2019-08-15 | 2019-12-13 | 南京理工大学 | Cube star offset momentum attitude control system |
| CN110562495B (en) * | 2019-08-15 | 2021-04-13 | 南京理工大学 | Cube star offset momentum attitude control system |
| CN110562494A (en) * | 2019-09-19 | 2019-12-13 | 中国人民解放军国防科技大学 | satellite thrust eccentric moment control device and method |
| CN110562494B (en) * | 2019-09-19 | 2021-04-06 | 中国人民解放军国防科技大学 | Satellite thrust eccentric moment control device and method |
| CN111776200A (en) * | 2020-07-13 | 2020-10-16 | 中山大学 | Sliding mass moment control device and aircraft using same |
| CN112591156A (en) * | 2020-12-21 | 2021-04-02 | 星众空间(北京)科技有限公司 | 1U cube star quality simulator |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN109080851A (en) | Cube star moment of mass disymmetry is laid out attitude-control device | |
| JP7100780B2 (en) | Service satellites for providing orbital services with variable thruster control | |
| CN107792393B (en) | Master-slave non-contact embedded satellite ground verification system and verification method thereof | |
| US6454218B1 (en) | Integrated system for providing 3-axis attitude-control, energy-storage, and electrical power | |
| CN108750144B (en) | Three-dimensional coordinated type rope system satellite | |
| US7118075B2 (en) | System and method for attitude control and station keeping | |
| WO2018061226A1 (en) | Pointing mechanism | |
| CN110502024B (en) | Quasi-universal attitude executing mechanism based on space parallel mechanism | |
| CN104163251A (en) | Eight-rod connecting type non-contact satellite platform load pose adjusting device and method | |
| EP2223035A2 (en) | Torsional spring aided control actuator for a rolling missile | |
| CN107839900B (en) | Formation layout and installation system for triaxial stabilized satellites | |
| Reubush | Hyper-X stage separation-background and status | |
| Eun et al. | Design and development of ground-based 5-dof spacecraft formation flying testbed | |
| Seweryn et al. | Dynamics of space robotic arm during interactions with non-cooperative objects | |
| CN112722224B (en) | Over-constrained double-branch two-rotating spherical parallel vector propeller | |
| Brown | Control moment gyros as space-robotics actuators | |
| Dong et al. | Self-assembling wireless autonomously reconfigurable module design concept | |
| CN114139283A (en) | Method for designing overall parameters of extraterrestrial celestial body penetrator | |
| Yin et al. | Simulation and Analysis of Short Rail Launch for UAV with Rocket Booster | |
| CN113608539B (en) | Space rolling target non-contact racemization method based on double-star electromagnetic formation satellite | |
| Notti et al. | Integrated power/attitude control system (ipacs) | |
| Alifanov et al. | An approach to forming the design performance of the attitude control system for small spacecraft | |
| Sorokin et al. | Control Moment Gyroscopes for Spacecraft Attitude Control Systems: History of Development | |
| US9926886B2 (en) | Magneto-rheologic damper for electromechanical actuator | |
| Zhang et al. | Feasibility study on SSTO rocket with an initial velocity given by EML |
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 | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20181225 |