CN105836152B - Synchronous acting catapult technique is concentrated in heavy spacecraft ejection system and its scattered accumulation of energy - Google Patents
Synchronous acting catapult technique is concentrated in heavy spacecraft ejection system and its scattered accumulation of energy Download PDFInfo
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- CN105836152B CN105836152B CN201610178828.5A CN201610178828A CN105836152B CN 105836152 B CN105836152 B CN 105836152B CN 201610178828 A CN201610178828 A CN 201610178828A CN 105836152 B CN105836152 B CN 105836152B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F1/00—Ground or aircraft-carrier-deck installations
- B64F1/04—Launching or towing gear
- B64F1/06—Launching or towing gear using catapults
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/80—Energy efficient operational measures, e.g. ground operations or mission management
Abstract
The present invention provides a kind of heavy spacecraft ejection system and its synchronous acting catapult technique is concentrated in scattered accumulation of energy,System includes positive ejection unit,Gravity reversal launches unit and recirculated water Storage Unit,Several gravity reversals launch the rear portion and both sides that unit is integrated in positive ejection unit,Each gravity reversal, which is launched in unit, is provided with gravity accelerator,All gravity accelerators are all connected in parallel by wirerope and ejection platform,When heavy spacecraft prepares ejection,Ejection platform is allowed to be positioned at the bottom of positive ejection unit,Gravity accelerator is positioned at the top that gravity reversal launches unit,By step pumping system, the water filling into gravity accelerator makes it increase high potential energy to recirculated water Storage Unit,When heavy spacecraft needs ejection,All gravity accelerators fall simultaneously at the top of forward direction ejection unit,Sync pulling ejection platform from forward direction ejection unit bottom to top in a manner of acceleration of gravity by heavy spacecraft bullet to high-altitude,Then heavy spacecraft igniting,Continue with itself motor power and load is sent into space.
Description
Technical field
The present invention relates to a kind of field of aerospace technology, specifically a kind of heavy spacecraft ejection system and its point
Dissipate accumulation of energy and concentrate synchronous acting catapult technique.
Background technology
With the fast development of aeronautical and space technology, eye is gradually invested the outer space by people, not only wants exoatmosphere to build
Large space station is made, people also is sent into other celestial bodies away from the earth goes to build the artificial space for adapting to human survival, also
The solar system that flies out looks for the livable celestial body of suitable human survival to the outer space, and above-mentioned all space scientific activities will use weight
Load is sent out atmosphere by type spacecraft, but the carrying capacity of heavy spacecraft is extremely limited used in the mankind at present,
The heavy spacecraft maximum load for knowing the former Soviet Union is 100 tons, and the heavy spacecraft maximum load in the U.S. is 127 tons, and various countries commonly use
Heavy spacecraft load all in tens tons, the carrying capacity of the heavy spacecraft of currently available technology does not reach much
The following mankind explore the needs of space, it is necessary to increase substantially the carrying capacity of heavy spacecraft using brand-new method.
The content of the invention
The technical assignment of the present invention is to provide a kind of synchronous mode weight that can increase substantially heavy spacecraft carrying capacity
Type spacecraft ejection system.
The technical scheme is that realize in the following manner：Unit is launched including forward direction ejection unit, gravity reversal
With recirculated water Storage Unit, several gravity reversals launch the rear portion and both sides that unit is integrated in positive ejection unit, positive bullet
Penetrate and ejection platform is provided with unit, heavy spacecraft is arranged in ejection platform, and each gravity reversal launches to be set in unit
There is gravity accelerator, all gravity accelerators are all connected in parallel by wirerope and ejection platform, and heavy spacecraft prepares ejection
When, allow ejection platform to be positioned at the bottom of positive ejection unit, gravity accelerator is positioned at the top that gravity reversal launches unit,
By step pumping system, the water filling into each gravity accelerator makes it store high potential energy to recirculated water Storage Unit, when heavy type is navigated
When its device needs ejection, all gravity accelerators are fallen at the top of reverse ejection unit simultaneously, and each gravity is stored in by scattered
Gravitional force in bucket puts together synchronous acting, and traction ejection platform is from forward direction ejection unit bottom to top with identical
Heavy spacecraft bullet to high-altitude, then heavy spacecraft igniting, is continued with the thrust of itself engine by load by acceleration
Space is sent into, is accelerated in advance for heavy spacecraft by forward direction ejection unit, the load of heavy spacecraft is greatly improved, no
It is only capable of reducing fuel consumption, moreover it is possible to improve emission security and launching success rate.
Described synchronous mode heavy type spacecraft ejection system, including transmitter unit be by positive launching cradle, ejection platform and
Hoistable platform, the anteriomedial of positive launching cradle is in open type, to facilitate the immigration of heavy spacecraft or assembling, positive launching cradle
Both sides inwall or rear side inwall be provided with rack guide rail and conductive plate, be arranged on positive launching cradle centre hoistable platform and
The periphery of ejection platform is provided with guide runner and brush and is slidably connected with rack guide rail and conductive plate.
Described synchronous mode heavy type spacecraft ejection system, is connected between hoistable platform and ejection platform by Program-controlled lock,
Brake is provided with the guide runner that hoistable platform and ejection platform periphery are set, the bottom of hoistable platform is provided with lifting and subtracted
Fast mechanism, lifting decelerator structure are connected by wheel and rack guide rail, and brake and lifting decelerator structure pass through conductive plate power taking
And be connected by wireless telecommunications with ground control system, control the positioning of hoistable platform and ejection platform and move up and down.
Described synchronous mode heavy type spacecraft ejection system, ejection platform top are provided with rail, and rail launches with positive
Railway rail before frame is relative, and heavy spacecraft is placed in track transfer trolley, and track transfer trolley is transferred to bullet by rail
Penetrate above the rail on platform or be transferred to by crane gear in ejection platform, ejection platform bottom is provided with wirerope interface.
Described synchronous mode heavy type spacecraft ejection system, gravity reversal, which launches unit, to be added by reverse launching cradle, gravity
Fast device, damping well and angle pulley group composition, the bottom of reverse launching cradle are provided with damping well, and centre is provided with gravity and added
Fast device, top are provided with angle pulley group, linkage wirerope are wound with angle pulley group, one end and the ejection platform bottom of the wirerope that links
Portion's wirerope interface connects, the wirerope interface connection at the top of the other end and gravity accelerator of the wirerope that links, below angle pulley group
Gravity accelerator lockable mechanism is provided with, lockable mechanism at the top of gravity accelerator together with hooking, the bottom of gravity accelerator
It is provided with buoyancy and valve opening, top is provided with water filling port.
Described synchronous mode heavy type spacecraft ejection system, circulation is by cistern, cascade pumping station and damping water
Water pump in cistern is sent at the top of reverse launching cradle by well construction, cascade pumping station, by water filling port inject gravity accelerator it
In, gravity accelerator bottom is provided with buoyancy from valve opening, and after gravity accelerator sinks to damping well, buoyancy is beaten automatically from valve opening
Open, treat that gravity accelerator leaves damping well, buoyancy automatically opens up from valve opening and empties the water in gravity accelerator and close again
Close.
Described synchronous mode heavy type spacecraft ejection system, gravity accelerator are the bucket or reverse boosting that bottom is taper
The complex of one or both of rocket.
Described synchronous mode heavy type spacecraft ejection system, cistern include underground conservation pool, surface storage pond or high mountain
Cistern.
Acting catapult technique is concentrated in the scattered accumulation of energy of synchronous mode heavy type spacecraft ejection system ejection, is comprised the following steps that：
1）Prepare before transmitting：The weight of ejection platform is set to be slightly larger than the weight of gravity accelerator, gravity accelerator is with weight
Exemplified by power bucket, ejection platform is connected by lock device with hoistable platform, and hoistable platform is consolidated ejection platform by elevating mechanism
Surely the position that positive launching cradle intermediate vertical opens door is arrived, hoistable platform passes through on brake and lock device and positive launching cradle inwall
Rack guide rail locking is positioned, and rail is provided with ejection platform and is connected with heavy spacecraft transport rail, heavy spacecraft passes through
Track transfer trolley is integrally transported into ejection platform, and track transfer trolley and ejection platform are fixed together with fixture, or passes through
Hydraulic mechanism replaces out track transfer trolley, allows heavy spacecraft to be rest directly upon in ejection platform, or directly by heavy space flight
Device is in ejection platform over-assemble, during heavy spacecraft transfer is installed in ejection platform, cascade pumping station classification constantly to
Water filling in gravity bucket, make to remain gravitational equilibrium between hoistable platform and gravity accelerator；
2）System debug：System installation and debugging are carried out to heavy spacecraft by the lifting and decline of hoistable platform, it is heavy
After all system debugs of spacecraft itself, hoistable platform traction ejection platform moves down into transmitting bottom, ground control
System continues to carry out heavy spacecraft remote testing, and gravity bucket is risen to below angle pulley group to be locked by lockable mechanism
Only, heavy spacecraft starts to fill propellant, while cascade pumping station continues the water filling into gravity bucket makes the gross weight of gravity bucket
Amount is in launch standby more than ejection platform and the summation of heavy spacecraft, heavy spacecraft；
3）Heavy Spacecraft Launch：Heavy all systems of spacecraft all by test after, hoistable platform and ejection platform
Between lock device and lockable mechanism at the top of gravity bucket open, gravity bucket is released with 98.8 meters per second of acceleration
Fall downwards, gravity bucket by wirerope draw ejection platform with identical acceleration under the guiding of rack guide rail to positive bullet
Penetrate frame top to launch, all connection members in ejection platform all separate with heavy spacecraft, and heavy spacecraft is risen by ejection
Sky, heavy spacecraft are lighted a fire simultaneously, continue to accelerate to promote the flight of load space-ward on the basis of the acceleration of ejection ejection platform；
4）Ejection platform ejection is located at angle pulley group to positive launching cradle top, in the reverse traction of wirerope and itself
Stop moving upwards under the braking of brakes, gravity bucket is fallen into damping well, gravity bucket with the speed of freely falling body
Stop falling under the damping of damping well, after gravity bucket crashes into damping well, the buoyancy of bottom is opened from valve opening, due to bullet
The weight for penetrating platform is slightly larger than the weight of gravity bucket empty barrel, and gravity bucket is slowly lifted off water under the traction of ejection platform
Face, the water filling in gravity bucket are slowly discharged from gravity bucket, and gravity bucket is drained after water leaves the water surface, the buoyancy of bottom from
Valve opening is re-closing off preparing water filling counterweight next time；
5）By the water that gravity bucket is discharged, pumped back cistern, damping well recover cascade pumping station again from damping well
To original water level, ejection platform slowly declines under the control of brake, and hoistable platform is flat by elevating mechanism driving lifting
Platform rises to positive launching cradle intermediate vertical and opens door position again together with ejection platform chain, prepares new heavy spacecraft
Immigration or assembling.
The excellent effect of the present invention is to reduce the consumption of heavy Spacecraft Launch fuel, increases the effective of heavy spacecraft
Load, it can be just set to obtain effective acceleration by ejection mode before heavy spacecraft engine ignition, because heavy type is navigated
Effective acceleration is obtained before the igniting of its device, is produced when rocket engine works when can greatly reduce conventional heavy-duty Spacecraft Launch
Huge vibrations injured to caused by heavy spacecraft, reduce failure improve launching success rate, due also to heavy spacecraft be by
High-altitude is arrived in orientation ejection, even if just in case heavy spacecraft breaks down, heavy spacecraft self-destruction is to complete in the air, also will not be right
Transmitting station and surface structures and personnel cause destructive injury, so with high security.
Brief description of the drawings：
Fig. 1 is the operation principle schematic diagram of ejector；
Fig. 2 is the structural representation of ejector；
Fig. 3 is the embodiment schematic diagram of heavy spacecraft transfer process；
Embodiment schematic diagram when Fig. 4 is heavy spacecraft ejection lift-off；
Fig. 5 is the cross-sectional configuration schematic diagram at ejector ejection platform position.
Description of reference numerals：Angle pulley group 1, lockable mechanism 2, water filling port 3, gravity accelerator 4, buoyancy from valve opening 5, just
To launching cradle 6, reverse launching cradle 7, linkage wirerope 8, cascade pumping station 9, cistern 10, heavy spacecraft 11, ejection platform 12, journey
Control lock 13, lifting decelerator structure 14, hoistable platform 15, damping well 16, wirerope interface 17, rack guide rail 18, conductive plate 19.
Embodiment
Following detailed description of is made to synchronous mode heavy type spacecraft ejection system referring to the drawings.
Operation principle is as follows：
As shown in figure 1, launching unit and recirculated water Storage Unit including forward direction ejection unit, gravity reversal, several are heavy
Power reversely launches the rear portion and both sides that unit is integrated in positive ejection unit, is provided with ejection platform in forward direction ejection unit, weight
Type spacecraft is arranged in ejection platform, and each gravity reversal launches and gravity accelerator is provided with unit, and all gravity accelerate
Device is all connected in parallel by wirerope and ejection platform, when heavy spacecraft prepares ejection, allows ejection platform to be positioned at positive bullet
The bottom of unit is penetrated, gravity accelerator is positioned at the top that gravity reversal launches unit, and recirculated water Storage Unit passes through step pump
Water system water filling into each gravity accelerator makes it increase high potential energy, when heavy spacecraft needs ejection, all gravity
Accelerator is fallen at the top of reverse ejection unit simultaneously, and the scattered gravitional force being stored in each gravity bucket is put together
Synchronous acting, sync pulling ejection platform from forward direction ejection unit bottom to top with identical acceleration of gravity by heavy space flight
Load is sent into space, passes through forward direction by device bullet to high-altitude, then heavy spacecraft igniting, the thrust for continuing with itself engine
Launch unit in advance for heavy spacecraft to accelerate, the load of heavy spacecraft be greatly improved, fuel consumption can not only be reduced,
Emission security and launching success rate can also be improved.
As in Figure 2-4, described synchronous mode heavy type spacecraft ejection system, including transmitter unit is by positive launching cradle
6th, ejection platform 12 and hoistable platform 15, the anteriomedial of positive launching cradle 6 is in open type, to facilitate the shifting of heavy spacecraft 11
Enter or assemble, the both sides inwall or rear side inwall of positive launching cradle 6 are provided with rack guide rail 18 and conductive plate 19, are arranged on forward direction
The periphery of hoistable platform 15 and ejection platform 12 among launching cradle 6 is provided with guide runner and brush and rack guide rail 18 and led
Electroplax 19 is slidably connected.
Described synchronous mode heavy type spacecraft ejection system, passes through Program-controlled lock 13 between hoistable platform 15 and ejection platform 12
Brake, the bottom of hoistable platform 15 are provided with the guide runner that connection, hoistable platform 15 and the periphery of ejection platform 12 are set
Lifting decelerator structure 14 is provided with, lifting decelerator structure 14 is connected by wheel and rack guide rail 18, and brake and lifting are slowed down
Mechanism 14 is connected by the power taking of conductive plate 19 and by wireless telecommunications with ground control system, and control hoistable platform 15 and ejection are flat
The positioning of platform 12 and move up and down.
As shown in figure 5, described synchronous mode heavy type spacecraft ejection system, the top of ejection platform 12 is provided with rail, steel
Rail is relative with the railway rail before positive launching cradle 6, and heavy spacecraft 11 is placed in track transfer trolley, and track transfer trolley is led to
Cross above the rail that rail is transferred in ejection platform 12 or be transferred to by crane gear in ejection platform 12, ejection platform 12
Bottom is provided with wirerope interface 17.
As Figure 1-5, described synchronous mode heavy type spacecraft ejection system, it is by reverse bullet that gravity reversal, which launches unit,
Penetrate frame 7, gravity accelerator 4, damping well 16 and angle pulley group 1 to form, the bottom of reverse launching cradle 7 is provided with damping well
16, centre is provided with gravity accelerator 4, and top is provided with angle pulley group 1, and linkage wirerope 8, connection are wound with angle pulley group 1
One end of dynamic wirerope 8 is connected with the bottom wirerope interface 17 of ejection platform 12, and the other end of linkage wirerope 8 pushes up with gravity accelerator 4
The wirerope interface 17 in portion connects；The lower section of angle pulley group 1 is provided with gravity accelerator lockable mechanism 2, and lockable mechanism 2 adds with gravity
The fast top of device 4 hooks together, and the bottom of gravity accelerator 4 is provided with buoyancy from valve opening 5, and top is provided with water filling port 3.
Described synchronous mode heavy type spacecraft ejection system, circulation are by cistern 10, cascade pumping station 9 and damping
Well 16 is formed, and the water pump in cistern 10 is sent to the reverse top of launching cradle 7 by cascade pumping station 9, injects gravity by water filling port 3
Among accelerator 4, the bottom of gravity accelerator 4 is provided with buoyancy from valve opening 5, after gravity accelerator 4 sinks to damping well 16, floats
Power automatically opens up from valve opening 4, when gravity accelerator 4 slowly be lifted off damp well 16 when, buoyancy from valve opening 5 automatically open up by
Water in gravity accelerator 4 is emptied and is re-closing off.
Described synchronous mode heavy type spacecraft ejection system, gravity accelerator 4 are the gravity buckets that bottom is taper or anti-
To the complex of one or both of booster rocket.
Described synchronous mode heavy type spacecraft ejection system, cistern 10 include underground conservation pool, surface storage pond or height
Mountain cistern.
Described heavy spacecraft 11 refers to carrier rocket, space shuttle, cargo ship etc..
Embodiment 1
Comprise the following steps that：
1）Prepare before transmitting：The weight of ejection platform is set to be slightly larger than the weight of gravity accelerator, gravity accelerator is with weight
Exemplified by power bucket, ejection platform is connected by lock device with hoistable platform, and hoistable platform is consolidated ejection platform by elevating mechanism
Surely the position that positive launching cradle intermediate vertical opens door is arrived, hoistable platform passes through on brake and lock device and positive launching cradle inwall
Rack guide rail locking is positioned, and rail is provided with ejection platform and is connected with heavy spacecraft transport rail, heavy spacecraft passes through
Track transfer trolley is integrally transported into ejection platform, and track transfer trolley and ejection platform are fixed together with fixture, or passes through
Hydraulic mechanism replaces out track transfer trolley, allows heavy spacecraft to be rest directly upon in ejection platform, or directly by heavy space flight
Device is in ejection platform over-assemble, during heavy spacecraft transfer is installed in ejection platform, cascade pumping station classification constantly to
Water filling in gravity bucket, make to remain gravitational equilibrium between hoistable platform and gravity accelerator；
2）System debug：System installation and debugging are carried out to heavy spacecraft by the lifting and decline of hoistable platform, it is heavy
After all system debugs of spacecraft itself, hoistable platform traction ejection platform moves down into transmitting bottom, ground control
System continues to carry out heavy spacecraft remote testing, and gravity bucket is risen to below angle pulley group to be locked by lockable mechanism
Only, heavy spacecraft starts to fill propellant, while cascade pumping station continues the water filling into gravity bucket makes the gross weight of gravity bucket
Amount is in launch standby more than ejection platform and the summation of heavy spacecraft, heavy spacecraft；
3）Heavy Spacecraft Launch：Heavy all systems of spacecraft all by test after, hoistable platform and ejection platform
Between lock device and lockable mechanism at the top of gravity bucket open, gravity bucket is released with 98.8 meters per second of acceleration
Fall downwards, gravity bucket by wirerope draw ejection platform with identical acceleration under the guiding of rack guide rail to positive bullet
Penetrate frame top to launch, all connection members in ejection platform all separate with heavy spacecraft, and heavy spacecraft is risen by ejection
Sky, heavy spacecraft are lighted a fire simultaneously, continue to accelerate to promote the flight of load space-ward on the basis of the acceleration of ejection ejection platform；
4）Ejection platform ejection is located at angle pulley group to positive launching cradle top, in the reverse traction of wirerope and itself
Stop moving upwards under the braking of brakes, gravity bucket is fallen into damping well, gravity bucket with the speed of freely falling body
Stop falling under the damping of damping well, after gravity bucket crashes into damping well, the buoyancy of bottom is opened from valve opening, due to bullet
The weight for penetrating platform is slightly larger than the weight of gravity bucket empty barrel, and gravity bucket is slowly lifted off water under the traction of ejection platform
Face, the water filling in gravity bucket are slowly discharged from gravity bucket, and gravity bucket is drained after water leaves the water surface, the buoyancy of bottom from
Valve opening is re-closing off preparing water filling counterweight next time；
5）By the water that gravity bucket is discharged, pumped back cistern, damping well recover cascade pumping station again from damping well
To original water level, ejection platform slowly declines under the control of brake, and hoistable platform is flat by elevating mechanism driving lifting
Platform rises to positive launching cradle intermediate vertical and opens door position again together with ejection platform chain, prepares new heavy spacecraft
Immigration or assembling.
Positive launching cradle and reverse launching cradle can use steel construction, concrete structure to build, in order to improve positive ejection
The stability of frame and reverse launching cradle, the high vertical overhanging cliff of drop can be selected to have within Chinese territory and much fall to rely on
Poor more than 2000 meters of overhanging cliff, plus the silo depth of underground, ejection acceleration distance is up to more than 2500 meters, because weight
The weight of power accelerator is more than the weight of heavy spacecraft and ejection platform, and the end speed that heavy spacecraft leaves ejection platform can
To be calculated by below equation, it is known that gravity accelerator height of drop and the matter beyond heavy spacecraft and flat pad
Amount, passes through formula（1）Freely falling body time t is calculated, recycles formula（2）It is flat that heavy spacecraft ejection transmitting can be calculated
End speed Vt during platform.Calculate end speed Vt, so that it may calculate the fuel that can be saved by ejection mode heavy type spacecraft.
h=gt2/2---（1）, Vt=gt---（2）.
Cistern includes underground conservation pool, surface storage pond or high mountain cistern, and the height above sea level that cistern is set is higher, attaches most importance to
The waterflood injection rate of power accelerator is more fast more convenient.
Gravity reversal launches unit and is set using depending on the overall weight of quantity apparent weight type spacecraft, different ejection quality
The gravity reversal of varying number can be selected to launch unit.
Moved up and down because hoistable platform can lift heavy spacecraft lifting with ejection platform so that heavy spacecraft peace
Dress test is more prone to convenient, eliminates the floor stair type being arranged on inside the crane and launcher of legacy transmission top of the trellis
Labyrinth.
The present invention is applied not only to the ejection launch of heavy spacecraft, improves the ability of the exploitation outer space and the outer space, equally
The ejection launch of heavy multiple warhead intercontinental ballistic missile is can also be used for, can be with due also to the ejector has huge ejectability
Cluster ejection launch is carried out to large, medium and small tactics and strategy guided missile, thus with important military strategy deterrence meaning.
Embodiment 2
It is assumed that the gross weight of gravity accelerator is more than ejection platform and heavy spacecraft gross weight, positive launching cradle height
2500 meters, according to formula h=gt2/2---（1）Calculate time t=√ 2h/g=22.58 second, end speed according to formula Vt=
gt---（2）Calculate the end speed Vt=gt=221.28 meter seconds.
Except the known technology for disclosed in the specification of the present invention in addition to technical characteristic being those skilled in the art.
The preferred embodiments of the present invention are the foregoing is only, are not intended to limit the invention, although with reference to foregoing reality
Apply example the present invention is described in detail, for those skilled in the art, it still can be to foregoing each implementation
Technical scheme described in example is modified, or carries out equivalent substitution to which part technical characteristic.All essences in the present invention
Any modification, equivalent substitution or improvement made within refreshing and principle etc., should be included in the scope of the protection.
Claims (9)
1. synchronous mode heavy type spacecraft ejection system, it is characterised in that including forward direction ejection unit, gravity reversal launch unit and
Recirculated water Storage Unit, several gravity reversals launch the rear portion and both sides that unit is integrated in positive ejection unit, forward direction ejection
Ejection platform is provided with unit, heavy spacecraft is arranged in ejection platform, and each gravity reversal launches to be provided with unit
Gravity accelerator, all gravity accelerators are all connected in parallel by wirerope and ejection platform, when heavy spacecraft prepares ejection,
Ejection platform is allowed to be positioned at the bottom of positive ejection unit, gravity accelerator is positioned at the top that gravity reversal launches unit, followed
By step pumping system, the water filling into each gravity accelerator makes it increase high potential energy to ring water Storage Unit, when heavy space flight
When device needs ejection, all gravity accelerators are fallen at the top of reverse ejection unit simultaneously, and each bulk water is stored in by scattered
Gravitional force in bucket is put together, and synchronous acting traction ejection platform is added from forward direction ejection unit bottom to top with identical
Speed is by heavy spacecraft bullet to high-altitude, and sync pulling ejection platform is from forward direction ejection unit bottom to top with acceleration of gravity
Mode by heavy spacecraft bullet to high-altitude, then heavy spacecraft igniting, continue with the thrust of itself engine by load
Space is sent into, is accelerated in advance for heavy spacecraft by forward direction ejection unit, the load of heavy spacecraft is greatly improved, no
It is only capable of reducing fuel consumption, moreover it is possible to improve emission security and launching success rate.
2. synchronous mode heavy type spacecraft ejection system according to claim 1, it is characterised in that forward direction ejection unit includes
Positive launching cradle, ejection platform and hoistable platform, the anteriomedial of positive launching cradle is in open type, to facilitate heavy spacecraft
Move into or assemble, the both sides inwall or rear side inwall of positive launching cradle are provided with rack guide rail and conductive plate, are arranged on positive bullet
Penetrate the hoistable platform of the centre of frame and the periphery of ejection platform is provided with guide runner and brush and slided with rack guide rail and conductive plate
Dynamic connection.
3. synchronous mode heavy type spacecraft ejection system according to claim 2, it is characterised in that hoistable platform is flat with ejection
Connected between platform by Program-controlled lock, be provided with brake on the guide runner of hoistable platform and the setting of ejection platform periphery, lift
The bottom of platform is provided with lifting decelerator structure, and lifting decelerator structure is connected by wheel and rack guide rail, brake and lifting
Reducing gear is connected by conductive plate power taking and by wireless telecommunications with ground control system, controls hoistable platform and ejection platform
Positioning and move up and down.
4. synchronous mode heavy type spacecraft ejection system according to claim 2, it is characterised in that ejection platform top is set
There is rail, rail is relative with the railway rail before positive launching cradle, and heavy spacecraft is placed in track transfer trolley, and track turns
It is transferred to above the rail that fortune car is transferred to by rail in ejection platform or by crane gear in ejection platform, ejection platform
Bottom is provided with wirerope interface.
5. synchronous mode heavy type spacecraft ejection system according to claim 1, it is characterised in that gravity reversal launches unit
It is made up of reverse launching cradle, gravity accelerator, damping well and angle pulley group, the bottom of reverse launching cradle is provided with damping
Well, centre are provided with gravity accelerator, and top is provided with angle pulley group, and linkage wirerope is wound with angle pulley group, linkage
One end of wirerope is connected with ejection platform bottom wirerope interface, and the wirerope at the top of the other end and gravity accelerator of the wirerope that links connects
Mouth connection；Gravity accelerator lockable mechanism is provided with below angle pulley group, lockable mechanism at the top of gravity accelerator with being hooked on
Together, the bottom of gravity accelerator is provided with buoyancy and valve opening, top is provided with water filling port.
6. synchronous mode heavy type spacecraft ejection system according to claim 1, it is characterised in that circulation is by storing
Water pump in cistern is sent at the top of reverse launching cradle by pond, cascade pumping station and damping water well construction, cascade pumping station, passes through note
Among mouth of a river injection gravity accelerator, gravity accelerator bottom is provided with buoyancy from valve opening, when gravity accelerator sinks to damping water
After well, buoyancy automatically opens up from valve opening, treats that gravity accelerator leaves damping well, buoyancy automatically opens up from valve opening accelerates gravity
Water in device is emptied and is re-closing off.
7. synchronous mode heavy type spacecraft ejection system according to claim 6, it is characterised in that cistern stores including underground
Pond, surface storage pond or high mountain cistern.
8. synchronous mode heavy type spacecraft ejection system according to claim 1, it is characterised in that gravity accelerator is bottom
The complex of gravity bucket or one or both of reverse booster rocket for taper.
9. the ejection launch method of synchronous mode heavy type spacecraft ejection system ejection, it is characterised in that comprise the following steps that：
1）Prepare before transmitting：Set ejection platform weight be slightly larger than gravity bucket weight, ejection platform by lock device with
Hoistable platform connects, and ejection platform is fixed to the position of the spacious door of positive launching cradle intermediate vertical by elevating mechanism by hoistable platform
Put, hoistable platform is positioned by brake and lock device with positive launching cradle inwall upper rack guide rail locking, is set in ejection platform
Rail is equipped with to be connected with heavy spacecraft transport rail, heavy spacecraft is integrally transported into ejection platform by track transfer trolley,
Track transfer trolley and ejection platform are fixed together with fixture, or replaced out track transfer trolley by hydraulic mechanism, is allowed
Heavy spacecraft is rest directly upon in ejection platform, or directly by heavy spacecraft in ejection platform over-assemble, heavy spacecraft
Transfer be installed in ejection platform during, cascade pumping station classification the constantly water filling into gravity bucket, make hoistable platform with again
Gravitational equilibrium is remained between power accelerator；
2）System debug：System installation and debugging, heavy space flight are carried out to heavy spacecraft by the lifting and decline of hoistable platform
After all system debugs of device itself, hoistable platform traction ejection platform moves down into transmitting bottom, ground control system
Continue to carry out heavy spacecraft remote testing, gravity bucket is risen to below angle pulley group by lockable mechanism locking, weight
Type spacecraft starts to fill propellant, while cascade pumping station continues the water filling into gravity bucket and is more than the gross weight of gravity bucket
The summation of ejection platform and heavy spacecraft, heavy spacecraft are in launch standby；
3）Heavy Spacecraft Launch：Heavy all systems of spacecraft all by test after, between hoistable platform and ejection platform
Lock device and gravity bucket at the top of lockable mechanism open, gravity bucket is released downward with 98.8 meters per second of acceleration
Fall, gravity bucket by wirerope draw ejection platform with identical acceleration under the guiding of rack guide rail to positive launching cradle
Top is launched, and all connection members in ejection platform all separate with heavy spacecraft, and heavy spacecraft is gone up to the air by ejection, weight
Type spacecraft is lighted a fire simultaneously, continues to accelerate to promote the flight of load space-ward on the basis of the acceleration of ejection ejection platform；
4）Ejection platform ejection is located at angle pulley group to positive launching cradle top, in the reverse traction of wirerope and itself braking
Stop moving upwards under the braking of system, gravity bucket is fallen with the speed of freely falling body and hindered into damping well, gravity bucket
Stop falling under the damping of Buddhist nun's well, after gravity bucket crashes into damping well, the buoyancy of bottom is opened from valve opening, flat due to launching
The weight of platform is slightly larger than the weight of gravity bucket empty barrel, and gravity bucket is slowly lifted off the water surface under the traction of ejection platform,
Water filling in gravity bucket is slowly discharged from gravity bucket, and gravity bucket is drained after water leaves the water surface, and the buoyancy of bottom is from opening
Valve is re-closing off preparing water filling counterweight next time；
5）By the water that gravity bucket is discharged, pumped back cistern, damping well return to original to cascade pumping station again from damping well
Some water levels, ejection platform slowly decline under the control of brake, and hoistable platform is driven on hoistable platform by elevating mechanism
It is raised to positive launching cradle intermediate vertical and opens door position again together with ejection platform chain, prepares the shifting of new heavy spacecraft
Enter or assemble.
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| CN106314816B (en) * | 2016-08-23 | 2018-08-14 | 济南环太机电技术有限公司 | The design application method of electromechanical integration dynamic energy storage type carrier-based aircraft ejector system |
| CN106477063B (en) * | 2016-08-23 | 2019-02-26 | 济南环太机电技术有限公司 | Multipurpose dynamic energy storage type carrier-based aircraft ejector system and its application method |
| CN106228863B (en) * | 2016-08-23 | 2018-08-17 | 济南环太机电技术有限公司 | Simulated training vehicle is blocked in aircraft carrier ejection |
| CN106169264B (en) * | 2016-08-23 | 2018-08-17 | 济南环太机电技术有限公司 | Simulated training system is blocked in aircraft carrier ejection |
| CN107804472A (en) * | 2017-10-06 | 2018-03-16 | 廖忠民 | Express locomotive assist system |
| CN112046775A (en) * | 2019-06-06 | 2020-12-08 | 宋延军 | Vertical soft landing auxiliary system and landing method for jet aircraft |
| CN112937900A (en) * | 2021-02-10 | 2021-06-11 | 张志刚 | Aircraft launching system, launching method and aircraft |
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| CN1299764A (en) * | 1999-12-13 | 2001-06-20 | 徐志军 | Booster rocket launching method for launching pad |
| CN203572321U (en) * | 2013-09-25 | 2014-04-30 | 西安工程大学 | Piston type multi-position boosting silo |
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| US20070234893A1 (en) * | 2006-04-07 | 2007-10-11 | Lockheed Martin Corporation | Augmented EM Propulsion System |
| WO2008010180A2 (en) * | 2006-07-17 | 2008-01-24 | Spacego Technologies (Proprietary) Limited | Launching a flight vehicle |
| US9074844B2 (en) * | 2013-07-25 | 2015-07-07 | Alexander Dankwart Essbaum | Rocket launch tower |
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| CN1299764A (en) * | 1999-12-13 | 2001-06-20 | 徐志军 | Booster rocket launching method for launching pad |
| CN203572321U (en) * | 2013-09-25 | 2014-04-30 | 西安工程大学 | Piston type multi-position boosting silo |
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