CN106240850A - Spacecraft is transmitted back to be closed flat platform - Google Patents
Spacecraft is transmitted back to be closed flat platform Download PDFInfo
- Publication number
- CN106240850A CN106240850A CN201610679665.9A CN201610679665A CN106240850A CN 106240850 A CN106240850 A CN 106240850A CN 201610679665 A CN201610679665 A CN 201610679665A CN 106240850 A CN106240850 A CN 106240850A
- Authority
- CN
- China
- Prior art keywords
- elevator
- spacecraft
- transmitted back
- flat platform
- closed flat
- 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
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G5/00—Ground equipment for vehicles, e.g. starting towers, fuelling arrangements
Landscapes
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Astronomy & Astrophysics (AREA)
- General Physics & Mathematics (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Types And Forms Of Lifts (AREA)
Abstract
The invention discloses a kind of spacecraft to be transmitted back to be closed flat platform, it includes launching tower, on described launching tower, elevator is set, air elevator is set in described elevator, described air elevator is connected with described elevator slipper seal, the cavity that described air elevator bottom is formed with described elevator inwall is connected with regulation valve, and described regulation valve is connected with described air compressor.By the present invention the most substantially without terrestrial gravitation affect, without air drag in the case of emission space aircraft, have only to ground-launched 1/3rd power, just can be transmitted into the most suitable height, it is greatly saved fuel cost, and improve reliability and safety, volume and the quality of spacecraft are the most unrestricted.
Description
Technical field
The present invention relates to spacecraft technical field, be specifically related to a kind of spacecraft and be transmitted back to be closed flat platform.
Background technology
At present, the launcher of almost all of spacecraft (space shuttle, satellite, guided missile etc.) is all disposed within ground,
Its transmitting needs to overcome terrestrial gravitation and air drag, reaches to fly away from the astronautical speed of the earth, needs one or more levels powerful
Rocket engine, make every 1 kilogram of object of feeding space required for the expense such as fuel be up to nearly ten thousand dollars, and by electromotor
The restriction of the factors such as power limit, the monomer weight of spacecraft is also restrained.
The recovery of spacecraft needs through dense atmosphere, it is therefore desirable to the material of excellent anti-yaw damper and landing
Auxiliary equipment, its expensive expense reclaimed is far above the surplus value of spacecraft, so a lot of spacecraft does not enters
Row recycling, thus cause substantial amounts of space trash.
Summary of the invention
Instant invention overcomes the deficiencies in the prior art, it is provided that recovery launched by a kind of spacecraft being easy to launch or reclaim
Platform.
In view of the problems referred to above of prior art, according to an aspect disclosed by the invention, the present invention uses techniques below
Scheme:
A kind of spacecraft is transmitted back to be closed flat platform, and it includes launching tower, and described launching tower arranges elevator, described electricity
Arranging air elevator in stair shaft, described air elevator is connected with described elevator slipper seal, described air elevator bottom and institute
The cavity stating the formation of elevator inwall is connected with regulation valve, and described regulation valve is connected with described air compressor.
In order to the present invention is better achieved, further technical scheme is:
According to one embodiment of the invention, between described air elevator outer wall and described elevator inwall, sealing is set
Circle.
According to another embodiment of the invention, bottom described elevator, elastic device is set.
According to another embodiment of the invention, described elastic device is spring.
According to another embodiment of the invention, described elevator top arranges removable top cover.
According to another embodiment of the invention, described launching tower is connected with ground also by drag-line.
The present invention it may also is that
According to another embodiment of the invention, described elevator is 4.
According to another embodiment of the invention, the height of described launching tower is 200,000 kilometers.
Compared with prior art, one of beneficial effects of the present invention is:
A kind of spacecraft of the present invention is transmitted back to be closed flat platform, has:
1, the most substantially without terrestrial gravitation impact with without the emission space aircraft in the case of air drag, it is only necessary to ground
/ 3rd power of surface launching, it is possible to be transmitted into the most suitable height, are greatly saved fuel cost, and improve can
By property and safety；
2, volume and the quality of spacecraft are unrestricted, and as being used on platform the method using branch to assemble, it is empty
Between the quality of aircraft to reach tens thousand of ton be also possible；
3, this platform reaches for realizing transmitting or is possibly realized close to ultraspeed, it might even be possible to close to the light velocity, from forming
The visual plant in universe is furtherd investigate for the mankind；
4, present invention purposes militarily will be the most notable, and the most general medium or short range guided missile is launched also on this platform
The speed of available superelevation and super remote distance, and under ultraspeed, any anti-missile system is exactly useless.
Accompanying drawing explanation
For clearer explanation present specification embodiment or technical scheme of the prior art, below will be to embodiment
Or the required accompanying drawing used is briefly described in the description of prior art, it should be apparent that, the accompanying drawing in describing below is only
It is to the reference of some embodiments in present specification, for those skilled in the art, is not paying creative work
In the case of, it is also possible to other accompanying drawing is obtained according to these accompanying drawings.
Fig. 1 shows launching tower structural representation according to an embodiment of the invention.
Fig. 2 shows launching tower top structure schematic diagram according to an embodiment of the invention.
Fig. 3 shows air elevator structure schematic diagram according to an embodiment of the invention.
Wherein, entitled corresponding to the reference in accompanying drawing:
1-launching tower, 2-removable top cover, 3-drag-line, 4-elevator, 5-air elevator, 6-sealing ring, 7-regulates
Valve, 8-air compressor, 9-cavity, 10-elastic device.
Detailed description of the invention
Below in conjunction with embodiment, the present invention is described in further detail, but embodiments of the present invention are not limited to this.
As shown in Figure 1, Figure 2 and Figure 3, a kind of spacecraft is transmitted back to be closed flat platform, and it includes launching tower 1, described transmitting
Arranging elevator 4 on tower 1, elevator 4 can preferably employ 4, arranges air elevator 5, described air electricity in described elevator 4
Ladder 5 is connected with the slipper seal of described elevator 4, the cavity 9 of described air elevator 5 bottom and the formation of described elevator 4 inwall and
Regulation valve 7 connects, and described regulation valve 7 is connected with described air compressor 8.
Between described air elevator 5 outer wall and described elevator 4 inwall, sealing ring 6 is set, is achieved by this sealing ring 6
Air elevator 5 is tightly connected with described elevator 4.
Arranging elastic device 10 bottom described elevator 4, this elastic device 10 can preferred spring.
Described elevator 4 top arranges removable top cover 2, and this removable top cover 2 can be opened or close.
Described launching tower 1 is connected with ground also by drag-line 3, and drag-line 3 can be many groups, it is generally preferable to be 4 groups.
The spacecraft of the present embodiment is transmitted back to be closed flat the firing altitude of platform, is arranged on and does not substantially have terrestrial gravitation, nothing
The height of air, by evacuated, the tower of enough buoyancy can be provided, spacecraft can be lifted between ground and platform
The piping shaft being arranged on tower, and lifting spacecraft (compression) air elevator 5, be used for reclaim spacecraft
Removable top cover 2.
Tower may to be made up of steel honeycomb texture, the buoyancy provided after being evacuated, can meet or exceed all
The weight of platform, and the height of platform, then reach the perigean satellite orbital altitude of about 20 myriametres.
May be provided in the middle of platform when reclaiming spacecraft with removable top cover 2, removable top cover 2, removable top cover 2 is permissible
It is that transparent material is made, and includes actuator, when reclaiming spacecraft, open removable top cover 2, after recovery, close
Hold together removable top cover 2, spacecraft is safeguarded, re-emit after note fuel, or by air elevator 5, by spacecraft
Send floor treatment back to.
Can arrange multilamellar in launching tower 1 and use space, the height of launching tower 1 is arranged on and is not the most affected by terrestrial gravitation
Position, the total satellite altitude of the most airfree near-earth away from ground 20 myriametre, after the diameter of launching tower 1 is arranged on vacuum pumping
The produced enough construction and installation of buoyancy need and support total weight and load.
The feature of the present invention:
1, launching tower 1 is set to vacuum state, is positioned at perigee satellite orbital altitude, it is possible to use produced liter
Power, makes platform launch and reclaims not affected by terrestrial gravitation and air drag.
2, spacecraft is made to reach the height affected without terrestrial gravitation and air drag by the air elevator 5 in this transmitting
Launch again after degree, spacecraft can be made to reach speed and the height needed only with the energy than ground launch much less
Degree.
3, reclaim spacecraft at platform, can thoroughly solve to reclaim on ground some difficult problems of spacecraft.
4, the spacecraft launched at this platform launched, for reaching and close to the light velocity, creating the condition of necessity,
Make the mankind explore space universe to be possibly realized.
Spacecraft is launched and reclaims platform, and the diameter of launching tower 1 can be 120 meters, tower height 20 myriametre, air elevator 4
Individual, a diameter of 5 meters.
In this specification, each embodiment uses the mode gone forward one by one to describe, and what each embodiment stressed is and other
The difference of embodiment, identical similar portion cross-reference between each embodiment.
" embodiment ", " another embodiment ", " embodiment " spoken of in this manual, etc., refer to knot
Specific features, structure or the feature of closing the description of this embodiment are included at least one embodiment that the application generality describes
In.The most multiple local appearance statement of the same race is not necessarily to refer to same embodiment.Appoint furthermore, it is understood that combine
When one embodiment describes a specific features, structure or feature, to be advocated is, and to combine other embodiments this to realize
Feature, structure or feature also fall within the scope of the present invention.
Although reference be made herein to invention has been described for the multiple explanatory embodiment of the present invention, however, it is to be understood that
Those skilled in the art can be designed that a lot of other amendments and embodiment, and these amendments and embodiment will fall in this Shen
Within spirit disclosed in please and spirit.More specifically, in the range of disclosure and claim, can be to master
Building block and/or the layout of topic composite configuration carry out multiple modification and improvement.Except what building block and/or layout were carried out
Outside modification and improvement, to those skilled in the art, other purposes also will be apparent from.
Claims (8)
1. a spacecraft is transmitted back to be closed flat platform, it is characterised in that include launching tower (1), and described launching tower (1) is upper to be arranged
Elevator (4), arranges air elevator (5) in described elevator (4), described air elevator (5) is slided close with described elevator (4)
Envelope connects, and the cavity (9) that described air elevator (5) bottom is formed with described elevator (4) inwall is connected with regulation valve (7), institute
State regulation valve (7) to be connected with described air compressor (8).
Spacecraft the most according to claim 1 is transmitted back to be closed flat platform, it is characterised in that described air elevator (5) outer wall
And sealing ring (6) is set between described elevator (4) inwall.
Spacecraft the most according to claim 1 is transmitted back to be closed flat platform, it is characterised in that described elevator (4) bottom sets
Put elastic device (10).
Spacecraft the most according to claim 3 is transmitted back to be closed flat platform, it is characterised in that described elastic device (10) is
Spring.
Spacecraft the most according to claim 1 is transmitted back to be closed flat platform, it is characterised in that described elevator (4) top sets
Put removable top cover (2).
Spacecraft the most according to claim 1 is transmitted back to be closed flat platform, it is characterised in that described launching tower (1) also by
Drag-line (3) is connected with ground.
Spacecraft the most according to claim 1 is transmitted back to be closed flat platform, it is characterised in that described elevator (4) is 4.
Spacecraft the most according to claim 1 is transmitted back to be closed flat platform, it is characterised in that the height of described launching tower (1)
It it is 200,000 kilometers.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610679665.9A CN106240850A (en) | 2016-08-17 | 2016-08-17 | Spacecraft is transmitted back to be closed flat platform |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610679665.9A CN106240850A (en) | 2016-08-17 | 2016-08-17 | Spacecraft is transmitted back to be closed flat platform |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106240850A true CN106240850A (en) | 2016-12-21 |
Family
ID=57592252
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610679665.9A Pending CN106240850A (en) | 2016-08-17 | 2016-08-17 | Spacecraft is transmitted back to be closed flat platform |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106240850A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111994309A (en) * | 2019-04-19 | 2020-11-27 | 蓝箭航天空间科技股份有限公司 | Auxiliary recovery system for carrier rocket recovery |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1267616A (en) * | 1999-03-22 | 2000-09-27 | 麻红生 | Method of reducing power consumption of rocket for launching satellite during initial flying stage |
| CN1299764A (en) * | 1999-12-13 | 2001-06-20 | 徐志军 | Booster rocket launching method for launching pad |
| JP2008132957A (en) * | 2006-11-27 | 2008-06-12 | Masafumi Kuribayashi | Method for launching space rocket |
| CN103994691A (en) * | 2013-02-18 | 2014-08-20 | 刘祖学 | Novel launching device |
-
2016
- 2016-08-17 CN CN201610679665.9A patent/CN106240850A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1267616A (en) * | 1999-03-22 | 2000-09-27 | 麻红生 | Method of reducing power consumption of rocket for launching satellite during initial flying stage |
| CN1299764A (en) * | 1999-12-13 | 2001-06-20 | 徐志军 | Booster rocket launching method for launching pad |
| JP2008132957A (en) * | 2006-11-27 | 2008-06-12 | Masafumi Kuribayashi | Method for launching space rocket |
| CN103994691A (en) * | 2013-02-18 | 2014-08-20 | 刘祖学 | Novel launching device |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111994309A (en) * | 2019-04-19 | 2020-11-27 | 蓝箭航天空间科技股份有限公司 | Auxiliary recovery system for carrier rocket recovery |
| CN111994310A (en) * | 2019-04-19 | 2020-11-27 | 蓝箭航天空间科技股份有限公司 | Auxiliary recovery system for rocket recovery |
| CN111994309B (en) * | 2019-04-19 | 2022-03-04 | 蓝箭航天空间科技股份有限公司 | Auxiliary recovery system for carrier rocket recovery |
| CN111994310B (en) * | 2019-04-19 | 2022-03-04 | 蓝箭航天空间科技股份有限公司 | Auxiliary recovery system for rocket recovery |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US7131613B2 (en) | High-altitude launching of rockets lifted by helium devices and platforms with rotatable wings | |
| RU2735441C1 (en) | Space elevator for delivery of passengers and cargoes from surface of earth or other planet to low orbit and back and method of construction thereof | |
| CN109018444A (en) | Rocket-powered mars transporter power system | |
| US20110114792A1 (en) | Sky station | |
| CN104943864A (en) | Long-airborne-period combined stratosphere aircraft system scheme based on solar unmanned aerial vehicles | |
| CN106374995A (en) | Space application communication platform based on rail retaining last stage of carrier rocket | |
| JP2008539131A (en) | Supersonic light flight vehicle | |
| CN105129086B (en) | A kind of Combined flat fluid layer aerocraft system scheme | |
| CN214729792U (en) | End shield and one-level integral recovery low-cost second-level low-orbit carrier rocket | |
| CN105667835A (en) | Heavy lift launch vehicle catapult and ejection method thereof | |
| WO2011042065A1 (en) | "momoheli" lifting module and vehicles | |
| CN113443172A (en) | Rocket-mounted recyclable low-cost low-orbit carrier rocket | |
| CN101580133A (en) | Gas rocket space vehicle | |
| CN106240850A (en) | Spacecraft is transmitted back to be closed flat platform | |
| CN216332865U (en) | Rocket-mounted recyclable low-cost low-orbit carrier rocket | |
| CN113195362B (en) | Global transport system and method for placing payloads in circular orbit | |
| CN214690264U (en) | End shield and one-level integrally-recycled suborbital carrier rocket | |
| CN107792395A (en) | The deployable spacecraft of radome fairing primary integration heavy caliber | |
| US4939976A (en) | Electromagnetic ground to orbit propulsion method and operating system for high mass payloads | |
| CN218410904U (en) | Pneumatic separation recoverable carrier rocket for launching suborbital loads | |
| CN202300868U (en) | Wing ring, wing ring mechanism, vertical take off and landing aircraft, opposite-pull aircraft and wind power generation mechanism | |
| CN101898632B (en) | Captive balloon with turbojet engine or self-pressurized burner | |
| CN115158709B (en) | Carrier rocket with pneumatic separation and power recovery system | |
| CN111977029A (en) | Multipurpose transmission system and construction scheme thereof | |
| CN219056600U (en) | Inflatable filling type protective structure in moon environment |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20161221 |