CN107585328A - The multi-functional manned spacecraft that can be flown for a long time - Google Patents
The multi-functional manned spacecraft that can be flown for a long time Download PDFInfo
- Publication number
- CN107585328A CN107585328A CN201710721913.6A CN201710721913A CN107585328A CN 107585328 A CN107585328 A CN 107585328A CN 201710721913 A CN201710721913 A CN 201710721913A CN 107585328 A CN107585328 A CN 107585328A
- Authority
- CN
- China
- Prior art keywords
- cabin
- rotatable
- rotatable cabin
- flown
- main
- 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
Landscapes
- Magnetic Bearings And Hydrostatic Bearings (AREA)
Abstract
The present invention provides a kind of multi-functional manned spacecraft that can be flown for a long time, the spacecraft includes main cabin, the first rotatable cabin, the second rotatable cabin, main cabin is elongate configuration, and the first rotatable cabin and the second rotatable cabin are annular flat configuration, and first and second rotatable cabin is respectively sleeved on main cabin vertically；Between the inner ring surface of the first rotatable cabin and main cabin, between the inner ring surface of the second rotatable cabin and main cabin, two magnetic bearings and a motor are respectively arranged with, drives the first rotatable cabin and the second rotatable cabin to be rotated relative to main cabin by motor.Fixing device is installed on the end face of the first rotatable cabin, for fixing extravehicular space suit.Dockingundocking device is installed on the outer ring surface of the first rotatable cabin or/and the second rotatable cabin, moonlet is connected by dockingundocking device.The spacecraft of the present invention can provide artificial gravity environment, attitude control, energy-storage system long-life, it is notable without consumption priming system or working medium, level of integrated system height, bulking value advantage can launch microsatellite, very moonlet.
Description
Technical field
The invention belongs to spacecraft field, and in particular to a kind of multi-functional manned spacecraft that can be flown for a long time.
Background technology
The space station that various countries have been carried out or will realized at present, problems be present during long-term flight：
(1) chemical cell energy storage is used, because space station electrical energy demands amount is huge, battery volume weight is huge, and charge and discharge
Electric number is limited, and in space station, life span domestic demand is frequently changed, and is unfavorable for space station long term maintenance.
(2) using control-moment gyro control posture, and control-moment gyro needs to rotate at a high speed by rotor and frame
Frame rotary output force square, life-span are difficult to long enough, also need frequently to change in the life span of space station.
(3) the weightless influence to spacefarer's body is one of principal element for restricting the in-orbit residence time of spacefarer.Space flight
The in-orbit residence time of member is short, and the round frequency in the world is fast, and space station operation cost is just high.Centrifuge is that space station provides artificial gravity
The approach implemented is easiest to, but device diameters are at least in more than 3.5m, it is difficult to be laid out in the very limited amount of space in space station.
(4) launch batch microsatellite, very moonlet from space station, form constellation, it is new to be increasingly becoming space station one
Application.But emitter either firer's ejector, it is disposable；Either air jet system, consume source of the gas.Shortcoming is all
The bulking value cost for launching more stars is very big.
The survey of deep space manned spacecraft of various countries just under study for action at present, following ask be present during long-term flight
Topic：
(1) regenerative fuel cell is used, bulky, capacity usage ratio is low；Using nuclear battery, can not charge and discharge cycles make
With.
(2) using control-moment gyro control posture, it can not be changed compared to space station, extra backup can only be carried,
Bulking value cost is big.
(3) because orbit altitude height of entering the orbit, the volume weight of survey of deep space manned spacecraft are restricted strong by carrying capacity
It is strong, therefore space station is compared, centrifuge is more inapplicable.
(4) because Orbit revolutionary is complicated, survey of deep space spacecraft has launches microsatellite, very moonlet development space on the way
The demand of Research of Environmental Sciences.The shortcomings that same with space station be present in emitter.
Therefore, space station of new generation or survey of deep space manned spacecraft in-orbit flight urgent need to resolve above mentioned problem for a long time.
The content of the invention
The technical problems to be solved by the invention are：In view of the shortcomings of the prior art, it is proposed that a kind of to fly for a long time
Multi-functional manned spacecraft, attitude control, energy-storage system long-life, it is possible to provide artificial gravity environment, batch microsatellite, very can be launched
Moonlet is without consuming priming system or working medium, and spacecraft realizes above-mentioned function by integrated design, and bulking value advantage shows
Write.
The technical solution used in the present invention is as follows：
A kind of multi-functional manned spacecraft that can be flown for a long time, including main cabin, the first rotatable cabin, the second rotatable cabin, it is described
Main cabin is elongate configuration, and first rotatable cabin and second rotatable cabin are annular flat configuration, first and second rotatable cabin
It is respectively sleeved in vertically on the main cabin；Between the inner ring surface of first rotatable cabin and the main cabin, second rotation
Between the inner ring surface in cabin and the main cabin, two magnetic bearings and a motor between two magnetic bearings are respectively arranged with,
First rotatable cabin and second rotatable cabin is driven to be rotated relative to the main cabin by the motor, the magnetic bearing is determined
Sub to be arranged on the stator of the motor on the main cabin, the rotor of the rotor of the magnetic bearing and the motor is installed in described
On the inner ring surface of first and second rotatable cabin.
As the improvement of the above-mentioned multi-functional manned spacecraft that can be flown for a long time of the present invention, at the end of first rotatable cabin
Fixing device is installed, the fixing device is used to fix extravehicular space suit on face.
As the improvement of the above-mentioned multi-functional manned spacecraft that can be flown for a long time of the present invention, first rotatable cabin or/
Dockingundocking device is installed with the outer ring surface of second rotatable cabin, moonlet is connected by the dockingundocking device,
The dockingundocking device is one or more.
As the improvement of the above-mentioned multi-functional manned spacecraft that can be flown for a long time of the present invention, on the main cabin, positioned at institute
The both sides of the first rotatable cabin are stated, fix a protection bearing respectively；On the main cabin, positioned at the two of second rotatable cabin
Side, a protection bearing is also fixed respectively；Installed respectively in the both ends of the surface of first rotatable cabin and second rotatable cabin
There is protective case, during spacecraft assembles the stage and magnetic bearing does not work, the protection bearing is socketed with the protection respectively
Touch, protect between the stator and rotor of the magnetic bearing and do not contacted between the stator and rotor of the motor, normally transported in spacecraft
Between the departure date, by the magnetic bearings control, make it is described protect bearing not contacted with the protective case, make first and second rotation
The relatively described main cabin in cabin is in suspended state.
As the improvement of the above-mentioned multi-functional manned spacecraft that can be flown for a long time of the present invention, equipped with end on the main cabin
Circle, the protection bearing are spacing by the nacelle of end circle and the main cabin.
As the improvement of the above-mentioned multi-functional manned spacecraft that can be flown for a long time of the present invention, the stator of the magnetic bearing is to have
The torus of salient pole, mosaic magnet in the torus, wound around coil on the salient pole, the rotor of the magnetic bearing is soft magnetism
The torus that material is formed；The torus for having salient pole that the rotor of the motor is formed for soft magnetic materials, the stator of the motor
Also it is the torus for having salient pole of soft magnetic materials composition, armature winding is wound on the salient pole of the motor stator.
As the improvement of the above-mentioned multi-functional manned spacecraft that can be flown for a long time of the present invention, the magnetic bearing is permanent magnet bias
Radial direction magnetic bearing, the motor are switched reluctance machines.
As the improvement of the above-mentioned multi-functional manned spacecraft that can be flown for a long time of the present invention, the maximum gauge in the main cabin is
4.5m, the axial overall length in the main cabin is 12m；The external diameter of first and second rotatable cabin is 10m, first and second rotatable cabin
Axial length be 3m.
The present invention has the following advantages that compared with prior art：
The invention provides a kind of multi-functional manned spacecraft that can be flown for a long time, can be sky with space station spacecrafts rendezvous
Between stand energy storage, control posture, provide gravity environment, layout microsatellite constellation；Or as independent survey of deep space manned space flight
Device, there is single-degree-of-freedom pose control and energy storing one, do not need the easily loss equipment such as battery or CMG, there is provided gravity environment, transmitting are micro-
Moonlet.Level of integrated system is high, easy to maintain.
Brief description of the drawings
Fig. 1 is the multi-functional manned spacecraft structural representation of the present invention；
Fig. 2 is the A-A structure sectional views of multi-functional manned spacecraft；
Fig. 3 is the B-B structure sectional views of multi-functional manned spacecraft；
Fig. 4 is the physical dimension of multi-functional manned spacecraft specific implementation.
Embodiment
The present invention is described further below in conjunction with the accompanying drawings.
As shown in figure 1, the present invention the multi-functional manned spacecraft that can be flown for a long time, including main cabin 1, the first rotatable cabin 2,
Second rotatable cabin 3.Wherein main cabin 1 is elongate configuration, and the first rotatable cabin 2 and the second rotatable cabin 3 are annular flat configuration, first,
Two rotatable cabins 2,3 are respectively sleeved in main 1 outer both ends of cabin vertically.Magnetic bearing rotor 8,9 is arranged on the first rotation with rotor 12
On the inner ring surface in cabin 2, the magnetic bearing stator 14,15 and the motor stator 18 that are engaged are arranged on main cabin；Magnetic bearing rotor 10,11
It is arranged on rotor 13 on the inner ring surface of second rotatable cabin 3, the magnetic bearing stator 16,17 and the motor stator 19 that are engaged are pacified
On main cabin.Protection bearing 4,5 is located at the both ends of the first rotatable cabin 2 respectively, is fixed on main cabin 1, by holding circle 18 and main cabin 1
Nacelle is spacing；Protection bearing 6,7 is located at the both ends of the second rotatable cabin 3 respectively, is fixed on main cabin 1, by holding circle 19 and the cabin of main cabin 1
Body is spacing.
During spacecraft assembles the stage and magnetic bearing does not work, the protective case with rotatable cabin respectively of bearing 4~7 is protected
20~23 contacts, protect between magnetic bearing rotor, do not contacted between electric machine rotor；In spacecraft during normal operation, lead to
Magnetic bearings control is crossed, makes to protect bearing 4~7 not contact with protective case 20~23, it is relative so as to reach first and second rotatable cabin 2,3
The effect that main cabin suspends.
Moonlet 25 is laid out the outer ring surface in the first rotatable cabin 2, is connected by dockingundocking device 24 and the first rotatable cabin 2
Connect.When spacecraft reaches planned orbit, moonlet to be launched rotation precalculated position, dockingundocking device 24 is turned by connection status
For disengaged position, moonlet 25 using relative velocity as connection status under linear velocity separated with spacecraft.
The outer ring surface of second rotatable cabin 3 can also install moonlet 25, and first and second rotatable cabin 2,3 can be in outer ring surface
Some microsatellites are installed at equal intervals, launched successively at a time interval according to rail conditions., can also be after battery has fired
Rail installs new microsatellite, carries out the transmitting of a new round.
Fixing device is installed on the end face of the first rotatable cabin 2, for fixing extravehicular space suit 26.Spacefarer goes out cabin,
Extravehicular space suit 26 is fixed on the end face of the first rotatable cabin 2, the first rotatable cabin 2 rotates, and spacefarer is made by artificial gravity
With.
Using magnetic bearing without using traditional mechanical bearing, the reliability of bearing can be effectively improved and the in-orbit life-span, subtracted
Vibration and noise caused by small nacelle rotation.Each rotatable cabin is supported by two permanent magnet offset radial magnetic bearings, is realized radially
Translation and the active control for rotating 4 frees degree；Radial direction magnetic bearing produces simultaneously axially replys rigidity, realizes axially passive steady
It is fixed.As shown in Fig. 2 magnetic bearing rotor 8~11 is the torus that soft magnetic materials is formed, magnetic bearing stator 14~17 is to have salient pole
Torus, wherein mosaic magnet 26, wound around coil 27 on salient pole.The motor control axial-rotation free degree, both exportable control
Torque, it can generate electricity again.It is simple and reliable using switched reluctance machines, it is suitable for being exposed in space environment and runs for a long time.Such as figure
Shown in 3, rotor 12,13 is the torus for having salient pole that soft magnetic materials is formed, what stator 18,19 was also formed for soft magnetic materials
There is the torus of salient pole, armature winding 28 is wound in stator salient poles.
Multi-functional manned spacecraft has following mode of operation：
(1) energy storage pattern
In Yang Zhao areas, the first rotatable cabin 2 and the second rotatable cabin 3 accelerate to rotate using electric energy caused by the solar cell wing, electricity
Machine stator end electric energy is converted into rotor-end mechanical energy, and maximum speed is reached before shadow region is entered；Into after shadow region, the first rotation
Cabin 2 is rotated in deceleration with the second rotatable cabin 3, and rotor end mechanical energy is converted into stator terminal electric energy, to main cabin 1 platform device with
Load provides electric energy.Although two rotatable cabins accelerate while slowed down simultaneously, the two direction of rotation is on the contrary, therefore will not be to cabin
Body posture has an impact.First rotatable cabin 2 and the rotating speed control law of the second rotatable cabin 3 are as shown in Equation 1.
In formula, ω2、ω3The rotating speed of the first rotatable cabin 2 and rotatable cabin 3 is represented respectively,The first rotation is represented respectively
The angle of the rotatable cabin 3 of cabin 2 and second adds rotating speed, J2、J3The rotary inertia of the first rotatable cabin 2 and the second rotatable cabin 3, W tables are represented respectively
Show the rotation function of rotatable cabin nacelle storage.
(2) attitude control pattern
In the case of axially having disturbance along nacelle, the first rotatable cabin 2 accelerates, the second rotatable cabin 3 slows down, or the first rotatable cabin
2 slow down, the second rotatable cabin 3 accelerates, and generation and the reverse control moment of disturbing moment, eliminate the influence of disturbance.First rotatable cabin 2
It is as shown in Equation 2 with the rotating speed control law of rotatable cabin 3.The electric energy provided using deceleration nacelle accelerates acceleration nacelle.
In formula, TcRepresent the control moment for offsetting disturbance torque.
(3) gravity simulation pattern
The relatively main cabin of first rotatable cabin 2 is static.Spacefarer goes out cabin, and extravehicular space suit is fixed on into the end face of the first rotatable cabin 2
On, as shown in Figure 1.First rotatable cabin 2, which accelerates to, it is expected that rotating speed keeps constant, and stable simulated gravity ring is provided for spacefarer
Border.
(4) satellite mode is launched
Microsatellite 20 is installed at the edge of first rotatable cabin 2, connects the dockingundocking device of the rotatable cabin 2 of moonlet 20 and first
21 are in connection status.First rotatable cabin 2 is rotated around main cabin 1 with constant expectation rotating speed, multi-functional manned in planned orbit position
Spacecraft adjusts posture, and it is desired moonlet separating rate direction to make the rotating speed tangential direction of the first rotatable cabin 2, and dockingundocking fills
Put and be in disengaged position, moonlet is separated using the linear velocity of connection status as initial velocity with rotatable cabin.First and second rotatable cabin 2,3
At edge some microsatellites can be installed at equal intervals, be launched successively at a time interval according to rail conditions.Launch
Bi Hou, the transmitting of a new round can be carried out with the new microsatellite of in-orbit installation.
Multi-functional manned spacecraft can realize energy storage, gravity simulation or transmitting satellite function while attitude control is realized, i.e.,
There is following combination mode of operation：
(1) energy storage-attitude control pattern
Because energy storage pattern and control of the attitude control pattern to rotatable cabin rotating speed are decouplings, therefore can be by controlling two
The rotating speed of rotatable cabin realizes energy storage and attitude control function simultaneously.First rotatable cabin 2 and the rotating speed control law of the second rotatable cabin 3 such as institute of formula 3
Show.
(2) gravity simulation-attitude control pattern
Spacefarer is fixed on the end face of the first rotatable cabin 2.First rotatable cabin 2 and the second rotatable cabin 3, which start simultaneously at, reversely to be added
Speed.Because two rotatable cabin inertia are different, to keep spacecraft attitude stabilization, the angular speed of the second rotatable cabin 3, which remains, to be faster than
First rotatable cabin 2.Period utilizes the feed speed control spacecraft axial direction posture of the second rotatable cabin 3.First rotatable cabin 2 reaches satisfaction weight
Kept after the desired speed of the force environment analogue value, the second rotatable cabin 3 adjustment rotating speed, to absorb whole device axial direction disturbance torque.
Similar, the first rotatable cabin 2 and the second rotatable cabin 3 start simultaneously at reverse deceleration, until the rotating speed of the first rotatable cabin 2 is zero, spacefarer
Leave the first rotatable cabin 2.
(3) satellite-attitude control pattern is launched
Moonlet is arranged on the first rotatable cabin 2.First rotatable cabin 2 and the second rotatable cabin 3 start simultaneously at reverse acceleration.By
Different in two rotatable cabin inertia, to keep spacecraft attitude stabilization, the angular speed of the second rotatable cabin 3, which remains, is faster than the first rotation
Turn cabin 2.Period utilizes the feed speed control spacecraft axial direction posture of the second rotatable cabin 3.First rotatable cabin 2 reaches desired speed, i.e.
After the linear velocity at rotatable cabin edge meets the initial velocity increment needed for satellite launch, the connection of satellite and nacelle disconnects, satellite
Launch.According to principle of conservation of momentum, the faster rotational speed of the first rotatable cabin 2, but rotation function reduce.First rotatable cabin 2 afterwards
Identical with the inertia of the second rotatable cabin 3, spacecraft enters normal energy storage-attitude control pattern.
As shown in figure 4, multi-functional manned spacecraft includes 1 main cabin and two rotatable cabins.Rotatable cabin by magnetic bearing with
Main cabin connection, rotated by motor driving relative to main cabin.To meet the constraint of fairing of launch vehicle, main cabin maximum gauge
4.5m.Main cabin axial overall length 12m.Rotatable cabin external diameter 10m, axial length 3m.Using a pair of permanent magnet bias installed vertically
Radial direction magnetic bearing, radial load rigidity are 5 × 104N/A, deflection stiffness 105Nm/A, while can provide and axially reply rigidity 100N/
Mm, realize the active control of radial direction translation and deflection；The control of rotary freedom is realized by motor.Rotatable cabin axial rotation is used to
Measure as 107kgm2, maximum speed 200r/min.
When multi-functional manned spacecraft is in energy storage-attitude control pattern, rotating speed is down to 150r/min, it is possible to provide and electric energy 8 ×
108J, it is ensured that be the demand of 300kW load supplyings in shadow region, while angular momentum 5 vertically positively or negatively can be provided
× 107Nms, can meet the needs of space station overcomes alternation disturbance torque in an orbital period；When multi-functional manned
Spacecraft is under gravity simulation pattern, and the rotating speed of the first rotatable cabin 2 remains 16r/min, can be the boat positioned at the first rotatable cabin 2
Its member provides the gravity environment of 1 terrestrial gravitation acceleration；In the case where launching satellite mode, multi-functional manned spacecraft is gone off course 90 °,
Rotary shaft is perpendicular to orbital plane, when the rotating speed of the first rotatable cabin 2 reaches 200r/min, moonlet rotate to relatively main cabin linear velocity with
The transmitting of orbital velocity position in the same direction, moonlet can be made with 105m/s relative velocity along orbital velocity direction and the first rotatable cabin 2
Rail lift separates；Launch if moonlet is rotated to relatively main cabin linear velocity and orbital velocity reverse position, may be such that moonlet with
105m/s relative velocity separates along orbital velocity direction with the first rotatable cabin 2 drop rail.
When the present invention is used as space station survey of deep space manned spacecraft, rotatable cabin is by protecting bearing to pacify during transmitting
On main cabin.To avoid launching shock from causing rotatable cabin impact protector bearing with vibration, rotatable cabin is pressed on guarantor by pull bar
Protect on bearing.After entering the orbit, pull bar is cut off using firer's cutter, starts magnetic bearing, the i.e. relatively main cabin of rotatable cabin suspends.
Unspecified part of the present invention belongs to general knowledge as well known to those skilled in the art.
Embodiments of the present invention are explained in detail above in association with accompanying drawing, but the present invention is not limited to described reality
Apply mode.For a person skilled in the art, without departing from the principles and spirit of the present invention to embodiment
A variety of change, modification, replacement and modification are carried out to still fall within protection scope of the present invention.
Claims (10)
- A kind of 1. multi-functional manned spacecraft that can be flown for a long time, it is characterised in that including main cabin (1), the first rotatable cabin (2), Second rotatable cabin (3), the main cabin (1) is elongate configuration, and first rotatable cabin (2) and second rotatable cabin (3) are ring Shape flat configuration, first and second rotatable cabin (2,3) are respectively sleeved on the main cabin (1) vertically；In first rotatable cabin (2) between inner ring surface and the main cabin (1), between the inner ring surface of second rotatable cabin (3) and the main cabin (1), fill There are two magnetic bearings and a motor between two magnetic bearings, first rotatable cabin is driven by the motor (3) rotated with second rotatable cabin (3) relative to the main cabin (1), the stator (14,15,16,17) of the magnetic bearing with it is described The stator (18,19) of motor is arranged on the main cabin (1), the rotor (8,9,10,11) of the magnetic bearing and the motor Rotor (12,13) is arranged on the inner ring surface of first and second rotatable cabin (2,3).
- 2. the multi-functional manned spacecraft according to claim 1 that can be flown for a long time, it is characterised in that in the described first rotation Turn that fixing device is installed on the end face of cabin (2), the fixing device is used to fix extravehicular space suit (26).
- 3. the multi-functional manned spacecraft according to claim 1 or 2 that can be flown for a long time, it is characterised in that described Dockingundocking device (24) is installed on the outer ring surface of one rotatable cabin (2) or/and second rotatable cabin (3), passes through the company Release unit (24) connection moonlet (25) is connect, the dockingundocking device (24) is one or more.
- 4. the multi-functional manned spacecraft according to claim 1 or 2 that can be flown for a long time, it is characterised in that in the master On cabin (1), positioned at the both sides of first rotatable cabin (2), a protection bearing (4,5) is fixed respectively；In the main cabin (1) On, positioned at the both sides of second rotatable cabin (3), a protection bearing (6,7) is also fixed respectively；In first rotatable cabin (2) and in the both ends of the surface of second rotatable cabin (3) be separately installed with protective case (20~23), spacecraft assemble the stage and During magnetic bearing does not work, the protection bearing (4~7) contacts with the protective case (20~23) respectively, protects the magnetic axis Do not contacted between the stator and rotor held and between the stator and rotor of the motor, by described in spacecraft during normal operation Magnetic bearings control, make it is described protect bearing (4~7) not contacted with the protective case (20~23), make first and second rotatable cabin (2,3) relatively described main cabin (1) is in suspended state.
- 5. the multi-functional manned spacecraft according to claim 3 that can be flown for a long time, it is characterised in that in the main cabin (1) on, positioned at the both sides of first rotatable cabin (2), a protection bearing (4,5) is fixed respectively；On the main cabin (1), Positioned at the both sides of second rotatable cabin (3), a protection bearing (6,7) is also fixed respectively；In first rotatable cabin (2) and Protective case (20~23) is separately installed with the both ends of the surface of second rotatable cabin (3), stage and magnetic axis are assembled in spacecraft Hold during not working, the protection bearing (4~7) contacts with the protective case (20~23) respectively, protects the magnetic bearing Do not contacted between stator and rotor and between the stator and rotor of the motor, pass through the magnetic axis in spacecraft during normal operation Hold control, make it is described protect bearing (4~7) not contacted with the protective case (20~23), make first and second rotatable cabin (2, 3) relatively described main cabin (1) is in suspended state.
- 6. the multi-functional manned spacecraft according to claim 5 that can be flown for a long time, it is characterised in that in the main cabin (1) end circle (18,19) and the main cabin (1) are passed through equipped with end circle (18,19), the protection bearing (4,5,6,7) on Nacelle is spacing.
- 7. the multi-functional manned spacecraft according to claim 5 that can be flown for a long time, it is characterised in that the magnetic bearing Stator (14~17) is to have the torus of salient pole, mosaic magnet (26) in the torus, wound around coil on the salient pole (27), the rotor (8~11) of the magnetic bearing is the torus that soft magnetic materials is formed；The rotor (12,13) of the motor is soft The torus for having salient pole that magnetic material is formed, the stator (18,19) of the motor is also the circle for having salient pole of soft magnetic materials composition Ring body, armature winding (28) is wound on the salient pole of the motor stator.
- 8. the multi-functional manned spacecraft that can be flown for a long time according to any one of claim 1,2,5,6,7, its feature It is, the magnetic bearing is permanent magnet offset radial magnetic bearing, and the motor is switched reluctance machines.
- 9. the multi-functional manned spacecraft according to claim 3 that can be flown for a long time, it is characterised in that the magnetic bearing is Permanent magnet offset radial magnetic bearing, the motor are switched reluctance machines.
- 10. the multi-functional manned spacecraft that can be flown for a long time according to any one of claim 1,2,5,6,7,9, it is special Sign is that the maximum gauge in the main cabin is 4.5m, and the axial overall length in the main cabin is 12m；First and second rotatable cabin External diameter is 10m, and the axial length of first and second rotatable cabin is 3m.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710721913.6A CN107585328A (en) | 2017-08-22 | 2017-08-22 | The multi-functional manned spacecraft that can be flown for a long time |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710721913.6A CN107585328A (en) | 2017-08-22 | 2017-08-22 | The multi-functional manned spacecraft that can be flown for a long time |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107585328A true CN107585328A (en) | 2018-01-16 |
Family
ID=61042571
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710721913.6A Pending CN107585328A (en) | 2017-08-22 | 2017-08-22 | The multi-functional manned spacecraft that can be flown for a long time |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107585328A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108414071A (en) * | 2018-03-02 | 2018-08-17 | 北京空间技术研制试验中心 | Manned spacecraft interior noise measurement method |
| CN110254754A (en) * | 2019-06-24 | 2019-09-20 | 北京机械设备研究所 | A kind of Space Rotating release device and rotation method for releasing |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH01220342A (en) * | 1988-02-26 | 1989-09-04 | Hitachi Ltd | Electron gun for color cathode-ray tube |
| CN101708778A (en) * | 2009-11-27 | 2010-05-19 | 北京航空航天大学 | Magnetically suspended gyroscope flywheel |
| CN101786505A (en) * | 2010-02-26 | 2010-07-28 | 哈尔滨工业大学 | Low-orbit aircraft based on aerodynamic attitude control and attitude control method thereof |
| CN104753273A (en) * | 2015-04-23 | 2015-07-01 | 清华大学 | Magnetic suspension momentum sphere |
| CN105947240A (en) * | 2016-05-26 | 2016-09-21 | 中国人民解放军第四军医大学 | Gravity cabin |
-
2017
- 2017-08-22 CN CN201710721913.6A patent/CN107585328A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH01220342A (en) * | 1988-02-26 | 1989-09-04 | Hitachi Ltd | Electron gun for color cathode-ray tube |
| CN101708778A (en) * | 2009-11-27 | 2010-05-19 | 北京航空航天大学 | Magnetically suspended gyroscope flywheel |
| CN101786505A (en) * | 2010-02-26 | 2010-07-28 | 哈尔滨工业大学 | Low-orbit aircraft based on aerodynamic attitude control and attitude control method thereof |
| CN104753273A (en) * | 2015-04-23 | 2015-07-01 | 清华大学 | Magnetic suspension momentum sphere |
| CN105947240A (en) * | 2016-05-26 | 2016-09-21 | 中国人民解放军第四军医大学 | Gravity cabin |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108414071A (en) * | 2018-03-02 | 2018-08-17 | 北京空间技术研制试验中心 | Manned spacecraft interior noise measurement method |
| CN110254754A (en) * | 2019-06-24 | 2019-09-20 | 北京机械设备研究所 | A kind of Space Rotating release device and rotation method for releasing |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| Bolam et al. | Review of electrically powered propulsion for aircraft | |
| WO2015152376A1 (en) | Debris removal device and debris removal system | |
| KR101820420B1 (en) | Hybrid system of drone | |
| US20220144441A1 (en) | Electromagnetic gyroscopic stabilizing propulsion system method and apparatus | |
| Pipenberg et al. | Design and fabrication of the mars helicopter rotor, airframe, and landing gear systems | |
| WO2006006311A1 (en) | Rapid air quantity generating and wind direction changing device and aircraft having the device mounted on side face of airframe | |
| US20220270802A1 (en) | Transfer type contra-rotating geomagnetic energy storage-release delivery system and method | |
| WO2015053063A1 (en) | Rotation suppressing device | |
| ATE532707T1 (en) | GYROSCOPE BASED ON PULSE CONTROL SYSTEMS IN SMALL SATELLITES | |
| CN105799956A (en) | Cubesat brake sail de-orbit device | |
| US20150108280A1 (en) | Mechanism for stabilizing and creating a variable gravitational field in a toroidal space station | |
| CN107585328A (en) | The multi-functional manned spacecraft that can be flown for a long time | |
| JP2014091413A (en) | Launching azimuth control device of air-launching system | |
| US5012170A (en) | Mechanical stabilization system with counter-rotating nested rotors | |
| CN205589529U (en) | Cube satellite braking sail device that leaves right or normal track | |
| JP6919514B2 (en) | Aircraft for power generation | |
| EP1912312A2 (en) | Fully redundant spacecraft power and attitude control system | |
| US5063336A (en) | Mechanical stabilization system using counter-rotation and a single motor | |
| CN109774986B (en) | Magnetic suspension cubic floating aircraft | |
| US10954004B2 (en) | Energy extraction and storage, and propulsion systems for space vehicles | |
| CN111516910A (en) | Flight method on moon and moon flight device | |
| US5042753A (en) | Mechanical stabilization system having counter-rotating rotors which are separate | |
| CN111516906A (en) | Flight method and flight device | |
| CN213735621U (en) | High-efficient safe spacecraft attitude adjustment ware | |
| US3582019A (en) | Rotor for satellite stabilization |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20180116 |
|
| WD01 | Invention patent application deemed withdrawn after publication |