CN1167718A - Landing transportation shuttle for cosmonautic vehicle - Google Patents
Landing transportation shuttle for cosmonautic vehicle Download PDFInfo
- Publication number
- CN1167718A CN1167718A CN96107913.4A CN96107913A CN1167718A CN 1167718 A CN1167718 A CN 1167718A CN 96107913 A CN96107913 A CN 96107913A CN 1167718 A CN1167718 A CN 1167718A
- Authority
- CN
- China
- Prior art keywords
- landing
- wheel
- winding
- aircraft
- takeoff
- 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
- 238000004804 winding Methods 0.000 claims description 13
- 238000007747 plating Methods 0.000 claims description 4
- 239000000203 mixture Substances 0.000 claims description 2
- 230000001360 synchronised effect Effects 0.000 abstract description 2
- 230000008859 change Effects 0.000 description 3
- 230000008676 import Effects 0.000 description 3
- 230000009467 reduction Effects 0.000 description 3
- 230000009471 action Effects 0.000 description 2
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical group [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 description 1
- 244000062793 Sorghum vulgare Species 0.000 description 1
- 238000007599 discharging Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000036541 health Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 235000019713 millet Nutrition 0.000 description 1
- 239000003381 stabilizer Substances 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/14—Space shuttles
-
- 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
- B64G1/40—Arrangements or adaptations of propulsion systems
- B64G1/411—Electric propulsion
Landscapes
- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Electric Propulsion And Braking For Vehicles (AREA)
Abstract
A space shuttle has two sets of propulsion system instead of only a single rocket one, resulting in less expense. A kind of synchronous wheel is disclosed, which can synchronize with the take-off and landing.
Description
The present invention relates to a kind of transport plane of space system.
The space shuttle list of being taken aspect the space flight at present space shuttle of rocket propulsion system, because the effect that the earth's core attracts, the cost of space shuttle is very expensive.
The objective of the invention is to overcome the space shuttle of single use rocket propulsion system, a kind of later-model space shuttle is provided.
The present invention can reach by following means:
Radome, navigationsystem, chaufeur by aircraft are sat the storehouse, left and right, left and right sides wing flap, left and right sides aileron, left and right sides fixed fin, left and right directions rudder, left and right sides abdomeinal fin, front and back alighting gear, the synchronous tire of takeoff and landing, left and right sides power generator, left and right sides electric propulsion device, rocket engine, variable geometry inlet, compositions such as driving engine adjustable nozzle.The centre of two electric motors about rocket is mounted in can add a joint rocket where necessary.About two electric motors also can change existing propulsion system, being used for convective zone when navigation, can save rocket propulsion and make freight house into.
After aircraft utilized runway to take off at a high speed, when arriving the high-altitude about 2 myriametres, rocket started the millet cake fire to arrive 100 kilometers high-altitude, where discharges satellite or goods.In the time of maybe need arriving the high-altitude of more transporting as the aircraft heavy burden is excessive, can add a joint rocket in rocket spout back.After finishing using, put right second rocket stage again.Reentry again after discharging satellite or goods, utilize navigationsystem in runway landing, because aircraft speed of a ship or plane when landing is bigger, common existing aircraft tyre and ground produce huge friction force, cause the deadweight loss of aircraft tyre, so install the landing synchronizing wheel.
The takeoff and landing synchronizing wheel is made up of tire, wheel rim, spoke, the lost core of rotor, armature loop, stator core, stator winding, bearing, aircraft wheel shaft, wheel spoke.Wheel rim rotor core, winding be housed in interior week, on the outer bearing, stator core and winding are housed on the aircraft wheel shaft in inside and outside spoke is installed in, electric power is imported by the wheel spoke.Vehicle wheel rotational speed is identical with the speed of taking off when taking off, and when aircraft landing, input electric power makes the rotating speed of wheel and aircraft reduction of speed basic identical, reduces wheel and ground-surface friction, can import inverse current and play brake action when aircraft taxi.
The drawing of accompanying drawing is described as follows:
Fig. 1---the landing carrier structural representation of universe travelling airship
Fig. 2---aircraft takeoffs and landings synchronizing wheel structure intention
Fig. 3---Fig. 2 A-A section-drawing
Accompanying drawing is marked on a map as follows: (1) radome, (2) navigationsystem, (3) chaufeur is sat storehouse (4) freight house, (5) rocket engine, (6) right power generator, (7) adjustability admission port, (8) starboard wing, (9) right flank aileron, (10) right flank wing flap, (11) abdomeinal fin (right side), (12) right fixed fin, (13) right rudder, (14) right propelling unit spout, (15) rocket engine adjustability spout, (16) left fixed fin, (17) left yaw rudder, (18) left propelling unit spout, (19) full dynamic formula horizontal stabilizer (left side), (20) abdomeinal fin (left side), (21) left wing's wing flap, (22) left wing's aileron, (23) left wing, (24) back alighting gear Cang Gai, (25) back alighting gear, (26) nose-gear Cang Gai, (27) nose-gear, (28) left side energy device producer, (29) freight house lid, (30) electric plating propulsion, (31) tire, (32) wheel rim, (33) rotor core and winding, (34) stator core and winding, (35) interior outer bearing, (36) wheel axle, (37) wheel bar, (38) lead and drag-line, (39) brake system and brush installation place, (40) accessory whorl spoke, (41) spoke.
The present invention is described further below with reference to (accompanying drawing) embodiment:
The radar that keeps existing aircraft and navigationsystem, wing, full level is fixed and vertically decide face tail fin etc., power generator (29) and electric plating propulsion (30) are installed in the left side at fuselage, power generator (6) and electric plating propulsion (30) also are equipped with in the right, rocket engine (5) and rocket adjustability spout (16) are then installed in the centre, because the aircraft reduction of speed is too fast, then replace the landing wheel of existing aircraft with the takeoff and landing synchronizing wheel.
After aircraft utilizes runway to take off at a high speed, when arriving the high-altitude about 2 myriametres, rocket engine (5) igniting arrives 100 kilometers high-altitude, discharge health or goods there, when maybe needing to arrive farther high-altitude as the aircraft heavy burden is excessive, can go up at rocket spout (15) a joint rocket is installed, after finishing using, refire and reentry again after second rocket stage discharges satellite or goods, utilize navigationsystem in runway landing, because aircraft speed of a ship or plane when landing is bigger, common aircraft landing wheel is relative static with ground.During landing and ground produces huge friction, so install the takeoff and landing synchronizing wheel.
When flying in the convective zone, about two electric motors also can change existing aircraft propelling system.Also can save rocket propulsion system and change freight house into.Aircraft can be driven by chaufeur in addition, also can install computer system, navigates by water under unpiloted situation.
Takeoff and landing are by tire (31) synchronously, wheel rim (32), rotor core and winding (33), stator core and winding (34), interior outer bearing (35), wheel main shaft (36), wheel bar (37), lead (38), brush and emergency brake arrangement (39) accessory whorl spoke (40), interior outer spokes (41) is formed.The iron core of rotor and winding (34) are mounted in the interior week of wheel (32), and stator core and winding (34) then are installed on the arbor (35), and electric power is to go up brush and the lead installed by accessory whorl spoke (40) to import.When taking off, wheel is identical with the speed of a ship or plane of aircraft, and when aircraft landing, input electric power makes the rotating speed of wheel and aircraft reduction of speed basic identical, can import inverse current and play brake action when aircraft taxi.
Claims (3)
1, a kind of space transportation instrument is characterized in that: by radar navigator, control loop, wing, vertically decide face, tail fin, full level and decide face, three propulsion systems in left, center, right, front and back alighting gear and takeoff and landing synchronizing wheel composition.
2, according to three propulsion systems in the described left, center, right of claim, it is characterized in that: about two propulsion systems are the electric plating propulsions that drag fan blade by the power generator newspaper, middle propulsion system is made up of rocket engine.
3, takeoff and landing synchronizing wheel according to claim 1, it is by tire (31), wheel rim (32), rotor core and winding (33), stator core and winding (34), interior outer bearing (35), inside and outside spoke (41) lead (38) of wheel main shaft (36), electric power input and brake system (39) accessory whorl spoke (40) are formed, its characteristics are: be equipped with in week in the wheel rim on rotor core and winding, the wheel dead axle stator core and winding are housed, input electric power when takeoff and landing, it is identical with landing speed that aircraft wheel is rotated to.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN96107913.4A CN1167718A (en) | 1996-06-06 | 1996-06-06 | Landing transportation shuttle for cosmonautic vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN96107913.4A CN1167718A (en) | 1996-06-06 | 1996-06-06 | Landing transportation shuttle for cosmonautic vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN1167718A true CN1167718A (en) | 1997-12-17 |
Family
ID=5119826
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN96107913.4A Pending CN1167718A (en) | 1996-06-06 | 1996-06-06 | Landing transportation shuttle for cosmonautic vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN1167718A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105452106A (en) * | 2013-02-06 | 2016-03-30 | 空中客车防务及航天公司 | Space aircraft |
| CN105762489A (en) * | 2015-01-05 | 2016-07-13 | 德尔福技术有限公司 | Radar Antenna Assembly With Panoramic Detection |
-
1996
- 1996-06-06 CN CN96107913.4A patent/CN1167718A/en active Pending
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105452106A (en) * | 2013-02-06 | 2016-03-30 | 空中客车防务及航天公司 | Space aircraft |
| CN105762489A (en) * | 2015-01-05 | 2016-07-13 | 德尔福技术有限公司 | Radar Antenna Assembly With Panoramic Detection |
| CN105762489B (en) * | 2015-01-05 | 2020-11-17 | 安波福技术有限公司 | Radar antenna assembly with panoramic detection |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C57 | Notification of unclear or unknown address | ||
| DD01 | Delivery of document by public notice |
Addressee: He Ruihua Document name: Notice of first review |
|
| C12 | Rejection of a patent application after its publication | ||
| RJ01 | Rejection of invention patent application after publication |