CN109264036A - Spacecraft leaves the right or normal track electric power rope system - Google Patents
Spacecraft leaves the right or normal track electric power rope system Download PDFInfo
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- CN109264036A CN109264036A CN201811308255.9A CN201811308255A CN109264036A CN 109264036 A CN109264036 A CN 109264036A CN 201811308255 A CN201811308255 A CN 201811308255A CN 109264036 A CN109264036 A CN 109264036A
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- electric power
- power rope
- elastic layer
- normal track
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- 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
- B64G1/66—Arrangements or adaptations of apparatus or instruments, not otherwise provided for
Abstract
It leaves the right or normal track technical field the present invention relates to spacecraft, it discloses a kind of spacecraft to leave the right or normal track electric power rope system, including electric power rope and aerating and exhaust device, electric power rope includes conductor wire and the elastic layer that is set in outside conductor wire, aerating and exhaust device is connect with electric power rope, for carrying out inflation/deflation into elastic layer.Spacecraft provided by the invention leaves the right or normal track electric power rope system, it is inflated by aerating and exhaust device to being set in the elastic layer outside conductor wire, become elastic layer with air pressure inside and with the air column of certain stretched tension, making electric power rope in space in turn becomes the bar with certain bending and torsion stiffness, improve the stability of electric power rope system in space, it avoids the occurrence of and is folded back the problem of causing tether effective length to reduce, there is the disturbance of axis direction without the concern for tether, makes to become relatively easy to the state control of electric power rope system entirety.In addition, facilitate modeling so that electric power rope tie up to it is all more convenient, succinct on theory analysis and model calculation.
Description
Technical field
It leaves the right or normal track technical field the present invention relates to spacecraft, leaves the right or normal track electric power rope system more particularly to a kind of spacecraft.
Background technique
With being continuously increased for mankind's space operation, earth overhead is just becoming more and more crowded, satellite and space trash day
Benefit increases.According to statistics, the artificial satellite at present around Earth's orbit operating shares more than 4,300, wherein only 1,200
Remaining is operating normally.A large amount of space trashes including discarding satellite have seriously affected the movable development of mankind's space, no
But valuable track resources are tied up, greatly uncertain and safe prestige can be also brought to the normal operation of in-orbit spacecraft
The side of body.The size of space junk all largely exists from grade to tens centimetres, and the collision and existing rubbish between them are broken
Piece and the satellite of operation collide, and can generate more new fragments, and lead to the increase of space trash quantity geometric progression.2009 2
Space collision accident occurs for " according to the star 33 " in the moon 10, Russian discarded satellite " universe 2251 " and the U.S., this is that the mankind go through
Satellite accidents for the first time in history.For the sustainable use of terrestrial space track resources, it is necessary to effectively control space trash
It generates.The spacecraft that oneself is completed mission actively leave the right or normal track to reduce its hang time, is to control and reduce space rubbish
The important method of rubbish.
It is relatively new and convenient and energy-saving the method for leaving the right or normal track risen in recent years using the electric power rope system method of leaving the right or normal track.This
Kind method only needs to install a leave the right or normal track device lighter relative to sole mass to spacecraft, utilizes controlling electric energy rope later
It is work, can integrally brings control force to spacecraft under conditions of not consuming fuel.Spacecraft complete space tasks it
Afterwards, electric power rope system starts to release tether, and tether both ends respectively connected spacecraft and payload, by tether both ends
The plasma exchanger that installation acquires and emits for charge respectively makes the charge in tether and space form closed circuit.By
The magnetic field line in earth's magnetic field is quickly cut with the movement of spacecraft in tether, it will generate huge electricity at tether both ends
Kinetic potential causes the displacement of charge to generate induced current on tether.At this moment it is equivalent to a live wire cutting
The Lorentz force in earth's magnetic field, generation can make spacecraft rapidly leave the right or normal track as the power of control spacecraft movement.Into
One step, the current direction in electric power rope system can also be controlled and then control the direction of Lorentz force.When Lorentz force and boat
When the angle in its device speed of service direction is less than 90 degree, so that it may provide acceleration for spacecraft, allow spacecraft orbit height
Degree increases；Spacecraft orbit height can be allowed to reduce conversely, changing current direction.
Although actually carrying out complete spacecraft using electric power rope system not yet at present to leave the right or normal track space test,
Many relevant space tests have done in many countries, demonstrate the feasibility of this method.Research about theoretical side
It is the hot issue of current various countries' research, mainly includes mechanical model building, dynamics Controlling and ground simulation test etc..
Due to being all the thinner electric power rope system used in in-orbit experimental and theoretical study, the length of rope system in space is several hundred
Change in the range of rice to hundred kilometers and be all possible to, the shape and state of tether can change, tether with the change of external force
It is the cutting earth magnetic field line in space environment, gravity gradient power and Lorentz force act on the electric power of certain length
Therefore rope is fastened, and the spatiality of electric power rope system can be made to become unstable, also can be for the kinematics analysis of spacecraft entirety
And become inaccurate.
On the other hand, it when carrying out theoretical research and leaving the right or normal track and emulating, involves the need for establishing electric power rope system
Theoretical model, at present existing rope be model include rigid rod model, it is model of elastic rod, chain rod model, bead model, continuous
Body Model etc., model are chosen closer to actual conditions, and calculating process is also more complicated, but existing model can not be simultaneous at present
Care for the convenience of good validity and analytic operation.
Summary of the invention
(1) technical problems to be solved
It is convenient that rope system entirety is controlled the object of the present invention is to provide a kind of spatial stability that can be improved tether
System, and leave the right or normal track electric power rope system convenient for the spacecraft of modeling analysis.
(2) technical solution
It leaves the right or normal track electric power rope system, including electric power rope in order to solve the above technical problem, the present invention provides a kind of spacecraft
And aerating and exhaust device, the electric power rope include conductor wire and the elastic layer that is set in outside the conductor wire, the inflation/deflation dress
It sets and is connect with the electric power rope, for carrying out inflation/deflation into the elastic layer.
Wherein, the electric power rope further includes protective layer, and the protective layer is located at outside the elastic layer.
It wherein, further include roll, the roll is equipped in the roll by rotating electric power rope described in folding and unfolding
The first port of air flue, the air flue is set to the roll side, and the starting point of the elastic layer is socketed in the first end
Mouthful, the second port of the air flue is set to the coiling axial end rotation center, connect with the aerating and exhaust device, the conduction
Line passes through the air flue and connect with plasma exchanger.
Wherein, the aerating and exhaust device includes air accumulator, solenoid valve and rotary joint, the solenoid valve include air inlet,
Gas outlet and leakage port, the rotary joint include fixing end and round end, and the air inlet connects the air accumulator, it is described go out
Port is connect with the fixing end, and the leakage port is for gas in the elastic layer of releasing, the round end and described second
Port connection.
Wherein, the rotary joint further includes swingle and sealing bearing, and the swingle is hollow structure, the rotation
Bar one end is fixedly connected with the second port, and the other end is rotatably connected by the sealing bearing with the round end.
Wherein, the gas stored in the air accumulator is high-pressure helium.
Wherein, the tank body of the air accumulator is equipped with the first stomata, the second stomata and third stomata；First stomata connects
The air inlet is connect, for inflating to the elastic layer；Second stomata connects pressure gauge, for measuring in the air accumulator
Pressure；The third stomata is spare hole.
Wherein, the elastic layer is graphene film, and with a thickness of 0.18-0.22mm, outer diameter is 4.5- when inside and outside no pressure difference
5.5mm。
Wherein, the protective layer includes the superposition of aramid fiber strength member and nomex mesh grid
Layer, the protective layer with a thickness of 0.45-0.55mm, outer diameter 9-11mm.
Wherein, the conductor wire is aluminum steel, and the diameter of the aluminum steel is 0.8-1.2mm.
(3) beneficial effect
Compared with prior art, the invention has the following advantages that
Spacecraft provided by the invention leaves the right or normal track electric power rope system, by aerating and exhaust device to the elasticity being set in outside conductor wire
Inflation in layer becomes elastic layer with air pressure inside and with the air column of certain stretched tension, and then makes the embodiment of the present invention
Electric power rope become the bar with certain bending and torsion stiffness in space, improve the stabilization of electric power rope system in space
Property, it avoids the occurrence of and is folded back the problem of causing tether effective length to reduce.Also, it is not necessary to consider that axis direction occurs in tether
Disturbance, make to become relatively easy to the control of the state of electric power rope system entirety.In addition, the electric power rope of the embodiment of the present invention is close
It is seemingly equivalent to the bar with bending stiffness, facilitates modeling, so that electric power rope ties up on theory analysis and model calculation all more
It is convenient, succinct.
Detailed description of the invention
Fig. 1 is electric power of embodiment of the present invention rope structure schematic diagram；
Fig. 2 is that spacecraft of the embodiment of the present invention leaves the right or normal track electric power rope architecture schematic diagram；
In figure: 1, conductor wire；2, elastic layer；3, protective layer；4, roll；5, baffle disk；6, air accumulator；7, solenoid valve；
8, rotary joint；9, leakage port；10, steam hose；11, the first stomata；12, the second stomata；13, third stomata；14, air pressure transmission
Sensor interface.
Specific embodiment
With reference to the accompanying drawings and examples, specific embodiments of the present invention will be described in further detail.Implement below
Example is not intended to limit the scope of the invention for illustrating the present invention.
In the description of the present invention, it should be noted that term " center ", " longitudinal direction ", " transverse direction ", "upper", "lower",
The orientation or positional relationship of the instructions such as "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom" "inner", "outside" is
It is based on the orientation or positional relationship shown in the drawings, is merely for convenience of description of the present invention and simplification of the description, rather than instruction or dark
Show that signified device or element must have a particular orientation, be constructed and operated in a specific orientation, therefore should not be understood as pair
Limitation of the invention.In addition, term " first ", " second ", " third " etc. are used for description purposes only, and should not be understood as instruction or
Imply relative importance.
In the description of the present invention, it should be noted that unless otherwise clearly defined and limited, term " installation ", " phase
Even ", " connection " shall be understood in a broad sense, for example, it may be being fixedly connected, may be a detachable connection, or be integrally connected；It can
To be mechanical connection, it is also possible to be electrically connected；It can be directly connected, can also can be indirectly connected through an intermediary
Connection inside two elements.For the ordinary skill in the art, concrete condition can be regarded and understand that above-mentioned term exists
Concrete meaning in the present invention.
In addition, in the description of the present invention, unless otherwise indicated, " multiple ", " more ", " multiple groups " be meant that two or
It is more than two.
As shown in Figure 1 and Figure 2, the spacecraft of the embodiment of the present invention leaves the right or normal track electric power rope system, including electric power rope and inflation/deflation
Device, electric power rope include conductor wire 1 and the elastic layer 2 that is set in outside conductor wire, and aerating and exhaust device is connect with electric power rope, use
In carrying out inflation/deflation into elastic layer 2.Spacecraft provided in an embodiment of the present invention leaves the right or normal track electric power rope system, passes through aerating and exhaust device
It is inflated into the elastic layer 2 being set in outside conductor wire, becomes elastic layer 2 with air pressure inside and with certain stretched tension
Air column, and then the electric power rope of the embodiment of the present invention is made to become the bar with certain bending and torsion stiffness in space, it improves
The stability of electric power rope system in space avoids the occurrence of and is folded back the problem of causing tether effective length to reduce.Moreover, not
It needs to consider that the disturbance of axis direction occurs in tether, makes to become relatively easy to the state control of electric power rope system entirety.In addition,
The electric power rope Approximate Equivalent of the embodiment of the present invention facilitates modeling in the bar with bending stiffness, so that electric power rope ties up to reason
By all more convenient, succinct in analysis and model calculation.
The spacecraft of the embodiment of the present invention leaves the right or normal track electric power rope system, and protective layer 3 can be arranged outside elastic layer 2.Elastic layer 2
High strength elastic material can be used, can expand after inflation and form the air column with certain internal pressure.Protective layer 3 can
Certain guarantor can be provided elastic layer 2 in severe space environment using the high molecular polymer with some strength
Shield, and certain constraint can be formed to the expansion of elastic layer 2.Further, the conductor wire of the embodiment of the present invention can be using conventional
Aluminum steel, diameter can be 0.8-1.2mm；Elastic layer 2 can be using the graphene film with certain elasticity and toughness, thickness
For 0.18-0.22mm, outer diameter is 4.5-5.5mm when non-aerating or inside and outside no pressure difference；Protective layer 3 can be aramid fiber intensity structure
The superimposed layer of part and nomex mesh grid, with a thickness of 0.45-0.55mm, outer diameter is 9- under non-aerating state
11mm.Can be vacuum in elastic layer 2 in the state that electric power rope does not use, with the state of minimum volume retract storage with
Save valuable spacecraft space.It can be vacuum state between elastic layer 2 and protective layer 3, when elastic layer 2 is in inflated condition
When, elastic layer 2 can be expanded and be fitted closely with protective layer, protective layer 3 to elastic layer 2 expansion its arrive certain effect of contraction,
To increase the inflation pressure in elastic layer 2 to a certain extent, and then enhance the stretched tension of electric power rope air column.
Further, the spacecraft of the embodiment of the present invention leaves the right or normal track electric power rope system, can also include for winding electric power
The roll 4 of rope, roll 4 pass through rotation folding and unfolding electric power rope.Baffle disk 5 can be set in 4 both ends of roll, forms electric power
The placing room of rope.Electric power rope when not in use, is wound in roll 4；When need to use, it rotates roll 4 and discharges
Electric power rope；It can be reversed rotation roll after use and withdraw electric power rope.Air flue, charge and discharge are equipped in roll 4
Device of air passes through 2 air circuit connection of elastic layer of air flue and electric power rope and the inflation/deflation into elastic layer 2.Air flue can be set two
Port, first port are set to 4 side of roll, and the starting point of elastic layer 2 is socketed in first port, the conductor wire 1 of electric power rope
Air flue can be passed through to connect with plasma exchanger, second port is set to coiling axial end rotation center, connects with aerating and exhaust device
It connects.One nut can be installed as electric power rope inflation/deflation port in the starting point of electric power rope elastic layer 2, elastic layer 2 is tight
It is close to be socketed in nut outer surfaces, and it is connected through a screw thread the first port that electric power rope is fixedly attached to 4 air flue of roll.
The aerating and exhaust device of the embodiment of the present invention may include air accumulator 6, solenoid valve 7 and rotary joint 8.Air accumulator 6 is used
In the helium that storage high pressure gas, high pressure gas can use light specific gravity, chemical property stable.Solenoid valve 7 vacuum, negative pressure,
It can be worked normally when zero-pressure, the parameters such as flow, the speed that regulating gas passes through can control by electric signal, electricity can be selected
Magnet valve 7 controls the inflation/deflation of electric power rope system.Solenoid valve 7 may include air inlet, gas outlet and leakage port 9, rotary joint
It may include fixing end and round end.The air inlet of solenoid valve 7 can connect air accumulator 6 by steam hose 10.Steam hose
10 can use common PVC plastic hose, and the fixed upper nipple in both ends is convenient to be connected with each aeration equipment.Electromagnetism
The gas outlet of valve 7 is connected with the fixing end of rotary joint 8, the gas that the leakage port 9 of solenoid valve 7 is used to release in elastic layer 2,
The round end of rotary joint 8 is connect with the second port of 4 air flue of roll.Further, rotary joint 8 can also include rotation
Bar and sealing bearing.Swingle is hollow structure, and one end is fixedly connected with the second port of 4 air flue of roll, and the other end is logical
Sealing bearing is crossed to be rotatably connected with round end formation.In this way, the high pressure gas stored in air accumulator 6, passes through steam hose 10
The air inlet for connecting solenoid valve 7, when control solenoid valve 7 is inflated, high pressure gas enters rotation from 7 gas outlet of solenoid valve and connects
First 8, and further enter the air flue of roll 4 by hollow swingle, it is finally filled in the elastic layer 2 of electric power rope.When
Need to release gas in elastic layer 2 when, control solenoid valve 7 opens leakage port 9 and simultaneously closes air inlet, make in elastic layer 2 space with
Exterior space connection completes gas and releases.Furthermore it is possible to add baroceptor interface 14 in rotary joint 8 or air flue, use
Gas pressure intensity in elastic layer 2 is measured, pressure signal is sent to control system can be formed and control to adjust pressure in elastic layer 2
Feedback signal, and by solenoid valve 7 complete in elastic layer 2 pressure adjusting control.
The tank body of air accumulator of the embodiment of the present invention 6 is equipped with multiple holes, such as, the air inlet with solenoid valve 7 can be set
The first stomata 11 that mouth is connected, for being inflated to elastic layer 2；The second stomata 12 that connection pressure gauge can be set, for surveying
Measure the pressure in air accumulator 6；It is spare hole that third stomata 13, which can also be arranged, provides redundancy backup and facilitates gas for space flight
Device other parts.
The spacecraft of the embodiment of the present invention leaves the right or normal track that electric power rope ties up in spacecraft can be there are four types of working condition:
1) dormant state.Spacecraft does not need leave the right or normal track when operate, leave the right or normal track during completing space tasks
System is in the state of suspend mode, and all components are among the state of power-off.
2) tether state is discharged.When spacecraft needs to leave the right or normal track, spacecraft leave the right or normal track electric power rope system energization, tether is first
Specified length is discharged under certain rule, the solenoid valve 7 of control system control later opens and closes, in tether
Elastic layer 2 is filled with suitable gas, and electric power rope is made to become the stock state of the rigidity and torsional strength that have certain.
3) holding and the state that leaves the right or normal track.The spacecraft plasma exchanger in system that leaves the right or normal track is started to work, and electric power rope is led
Start to generate electric current in electric wire 1, spacecraft will quickly be left the right or normal track under the action of Lorentz force.It is controlled by control system
Size of current in tether can control the physical quantitys such as the attitude angle of tether in space.
4) recycling tether fills state.After spacecraft leaves the right or normal track successfully, 7 leakage port 9 of solenoid valve is opened, and empties the gas in tether
It turns off later, carries out the removal process of tether later.
Further, the spacecraft of the embodiment of the present invention leaves the right or normal track electric power rope system, conductor wire 1 using diameter 1mm aluminum steel；
Elastic layer 2 is using the graphene film with a thickness of 0.2mm, and outer diameter is 5mm under non-aerating state；Protective layer 3 is that aramid fiber is strong
The superimposed layer of component and nomex mesh grid is spent, thickness 0.5mm, outer diameter is 10mm under non-aerating state.?
On the basis of this, 5km is set by the length of electric power rope, is carried out spacecraft of the embodiment of the present invention and is left the right or normal track the quality of electric power rope system
With space budget.6 mass of air accumulator is estimated as 2000g, volume estimate for 300mm (length) * 160mm (width) * 190mm it is (high
Degree)；7 mass of solenoid valve is estimated as 200g, and volume is estimated as 60mm (length) * 40mm (width) * 110mm (height), while can
To carry out overall calculating according to two solenoid valves 7.Elastic layer 2 and the increased quality of protective layer 3 outside electric power rope conductor wire 1 are
500g, then all in all, using spacecraft of the embodiment of the present invention leave the right or normal track electric power rope system spacecraft compared to traditional rope system,
It is about 3000g that quality, which increases, and dilatation is about 400mm (length) * 200mm (width) * 200mm (height).
As can be seen from the above embodiments, spacecraft provided in an embodiment of the present invention leaves the right or normal track electric power rope system, passes through charge and discharge
Device of air is inflated into the elastic layer 2 being wrapped in outside conductor wire 1, becomes elastic layer 2 with air pressure inside and with centainly stretching
The air column of tension is opened up, and then becomes the electric power rope of the embodiment of the present invention in space with certain bending and torsion stiffness
Bar improves the stability of electric power rope system in space, avoids the occurrence of and be folded back the problem of causing tether effective length to reduce.
Also, it is not necessary to consider that the disturbance of axis direction occurs in tether, make to become relatively simple to the state control of electric power rope system entirety
It is single.In addition, the electric power rope Approximate Equivalent of the embodiment of the present invention facilitates modeling in the bar with bending stiffness, so that electric power
Rope ties up to all more convenient, succinct on theory analysis and model calculation.It is possible to further which guarantor can be set outside elastic layer 2
Sheath 3 can provide certain protection to elastic layer 2 in severe space environment and form one to the expansion of elastic layer 2
Conclude a contract or treaty beam.
The foregoing is merely illustrative of the preferred embodiments of the present invention, is not intended to limit the invention, all in essence of the invention
Within mind and principle, any modification, equivalent replacement, improvement and so on be should all be included in the protection scope of the present invention.
Claims (10)
- The electric power rope system 1. a kind of spacecraft leaves the right or normal track, which is characterized in that including electric power rope and aerating and exhaust device, the electric power Rope includes conductor wire and the elastic layer being set in outside the conductor wire, and the aerating and exhaust device is connect with the electric power rope, uses In carrying out inflation/deflation into the elastic layer.
- The electric power rope system 2. spacecraft according to claim 1 leaves the right or normal track, which is characterized in that the electric power rope further includes protecting Sheath, the protective layer are located at outside the elastic layer.
- The electric power rope system 3. spacecraft according to claim 1 leaves the right or normal track, which is characterized in that further include for winding the electricity The roll of dynamic ropes, the roll is interior to be equipped with air flue, and the first port of the air flue is set to the roll side, described The starting point of elastic layer is socketed in the first port, and the conductor wire passes through the air flue and connect with plasma exchanger, institute The second port for stating air flue is set to the coiling axial end rotation center, connect with the aerating and exhaust device.
- The electric power rope system 4. spacecraft according to claim 3 leaves the right or normal track, which is characterized in that the aerating and exhaust device includes storage Gas tank, solenoid valve and rotary joint, the solenoid valve include air inlet, gas outlet and leakage port, and the rotary joint includes solid Fixed end and round end, the air inlet connect the air accumulator, and the gas outlet is connect with the fixing end, and the leakage port is used It is connect in gas, the round end in the elastic layer of releasing with the second port.
- The electric power rope system 5. spacecraft according to claim 4 leaves the right or normal track, which is characterized in that the rotary joint further includes rotation Bull stick and sealing bearing, the swingle are hollow structure, and described swingle one end is fixedly connected with the second port, another End is rotatably connected by the sealing bearing with the round end.
- The electric power rope system 6. spacecraft according to claim 4 leaves the right or normal track, which is characterized in that the gas stored in the air accumulator Body is high-pressure helium.
- The electric power rope system 7. spacecraft according to claim 4 leaves the right or normal track, which is characterized in that set on the tank body of the air accumulator There are the first stomata, the second stomata and third stomata；First stomata connects the air inlet, for filling to the elastic layer Gas；Second stomata connects pressure gauge, for measuring the gas storage pressure inside the tank；The third stomata is spare hole.
- The electric power rope system 8. spacecraft according to claim 1 leaves the right or normal track, which is characterized in that the elastic layer is that graphene is thin Film, with a thickness of 0.18-0.22mm, outer diameter is 4.5-5.5mm when inside and outside no pressure difference.
- The electric power rope system 9. spacecraft according to claim 2 leaves the right or normal track, which is characterized in that the protective layer includes aramid fiber fibre Tie up strength member and nomex mesh grid superimposed layer, the protective layer with a thickness of 0.45-0.55mm, outside Diameter is 9-11mm.
- The electric power rope system 10. spacecraft according to claim 1 leaves the right or normal track, which is characterized in that the conductor wire is aluminum steel, institute The diameter for stating aluminum steel is 0.8-1.2mm.
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| CN201811308255.9A CN109264036B (en) | 2018-11-05 | 2018-11-05 | Off-orbit electric power rope system of spacecraft |
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| CN201811308255.9A CN109264036B (en) | 2018-11-05 | 2018-11-05 | Off-orbit electric power rope system of spacecraft |
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| CN110510152A (en) * | 2019-08-21 | 2019-11-29 | 中国科学院力学研究所 | A kind of low orbit earth magnetism accumulation of energy-release delivery system |
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| CN110510152B (en) * | 2019-08-21 | 2021-01-01 | 中国科学院力学研究所 | Low-orbit geomagnetic energy storage-release delivery system |
| CN115959308A (en) * | 2023-01-31 | 2023-04-14 | 北京理工大学 | Low-cost electrically-driven electrodynamic force rope releasing device and off-track experimental device |
| CN115959308B (en) * | 2023-01-31 | 2024-03-22 | 北京理工大学 | Low-cost electrically-driven electrodynamic force rope release device and off-track experimental device |
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