CN202624648U - Track acceleration plane using two stages of motion platforms to finish levitation of two-stage rocket spacecraft - Google Patents
Track acceleration plane using two stages of motion platforms to finish levitation of two-stage rocket spacecraft Download PDFInfo
- Publication number
- CN202624648U CN202624648U CN2012200352755U CN201220035275U CN202624648U CN 202624648 U CN202624648 U CN 202624648U CN 2012200352755 U CN2012200352755 U CN 2012200352755U CN 201220035275 U CN201220035275 U CN 201220035275U CN 202624648 U CN202624648 U CN 202624648U
- Authority
- CN
- China
- Prior art keywords
- platform
- track
- aircraft
- spacecraft
- stage rocket
- 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.)
- Expired - Lifetime
Links
Images
Classifications
-
- 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
Landscapes
- Automatic Assembly (AREA)
Abstract
The utility model relates to a track acceleration plane using two stages of motion platforms to finish levitation of a two-stage rocket spacecraft. The track acceleration plane comprises a track, a track motion platform, a plane platform and the two-stage rocket spacecraft and is characterized in that the track motion platform and the plane platform use different self power sources to finish startup, acceleration and levitation, penetrates through the convection zone into the upper stratosphere, and sends the rocket spacecraft into space in a relay launch method. Compared with the prior art, the track acceleration plane has the obvious advantages of being capable of saving jet engine fuel, small in size of rockets, low in cost, small in limit of launching site positions, weather and climate, selective in lunching windows, capable of carrying various spacecrafts through the track motion platform and the plane platform, repeated to use, good in using value and the like.
Description
One, technical field:
The utility model relates to space technology, particularly relates to the track acceleration aircraft that a kind of two-stage motion platform is accomplished the lift-off of two-stage rocket spacecraft.
Two, background technology:
The three-stage rocket relay boosting spacecraft that father's Tsiolkovsky of space flight is founded gets into the theory of space; Become design, the design of existing space technology, the basic model of practice; But; Extension and expansion along with the mankind explore and utilize the cosmic space to transmitting frequency, scale, the distance of going deep into space and return etc., are all producing the comprehensive demand that matter, amount, technical risk and cost reduce.Prior art is faced with the rocket volume and the boosting power limit, launch site addressing, weather, meteorological follow, the restriction of numerous aspects such as accurate assurance of launch window.
Three, summary of the invention:
The purpose of the utility model is the limitation to above demand and prior art, provides a kind of cost track that two-stage motion platform low, reusable, that can select and chase launch window is accomplished the lift-off of two-stage rocket spacecraft to quicken aircraft.
The purpose of the utility model realizes through following technical scheme:
The track that a kind of two-stage motion platform is accomplished the lift-off of two-stage rocket spacecraft quickens aircraft; It comprises track, orbiting motion platform, aircraft platform and two-stage rocket spacecraft; It is characterized in that transmitting operation through the interim relay mode of orbiting motion platform, aircraft platform and two-stage rocket sends spacecraft into planned orbit, its track is the double rail type of ray property; Its orbiting motion platform has autonomous active power system, and is Orbiting, carries and let fly away the stream line pattern express locomotive of aircraft platform through fastening automatic disconnecting gear; Its aircraft platform is that top is open, cockpit is arranged at the fuselage head below, rudder fin is outer Zhang Shuanyi, is the special-shaped aircraft of power with the jet engine; Aircraft platform carries and lets fly away the two-stage rocket spacecraft through fastening automatic disconnecting gear in open cabin position.
Above-described track is ray shape, double rail type, the acceleration of confession orbiting motion platform, is decelerated to dedicated track out of service.
Described orbiting motion platform is to have autonomous active power system, through 3 orbiting motion platforms of preceding triangle negative pressure disconnecting gear, fastening and carry aircraft platform, acceleration and discharge aircraft platform, Orbiting streamline contour, high-performance express locomotive.
The cabin Position Design of described aircraft platform is that top is open; Circular arc flute profile rocket dress fastening through aircraft platform negative pressure disconnecting gear and carrying two-stage rocket spacecraft is taken the storehouse; The aircraft platform cockpit is arranged at the fuselage head below; Rudder fin is set to outer Zhang Shuanyi, is the special-shaped aircraft of power with the jet engine.
The alighting gear of described aircraft platform is promptly packed up after aircraft platform is anchored on the orbiting motion platform, to the aerial mission overall process of accomplishing aircraft platform, before landing, opens and puts, in conventional airfield runway landing.
Described aircraft platform can be used as aerospace master, carries and let fly away three grades, one-stage rocket spacecraft, other forms and spacecrafts function, different orbits.
The track that the two-stage motion platform of the utility model is accomplished the lift-off of two-stage rocket spacecraft quickens aircraft compared with prior art, has following outstanding advantage:
1, the dual dynamic source with the aircraft platform of orbiting motion platform with powerful autonomous dynamic and jet engine power promotes to take off and accomplish and pass through convective zone and part advection layer; Let the booster-missile combination spacecraft fly away in the advection layer that minimum and terrestrial gravitation reduces at air resistance; The first order that replaces traditional three-stage rocket that power consumption is maximum, volume is maximum, risk is maximum makes that the spacecraft emission is safer, environmental protection, cost be lower.
2, carry emission two-stage rocket spacecraft by the two-stage motion platform, start balance, speed-raising is slow, process is long, spacecraft receives the acceleration/accel impulsive force little.
3, track takes off, and system is prone to control, and the place builds that cost is low, emission process less infringement orbiting motion platform and aircraft platform, but all repeated multiple times is used, and polytypic is general.
4, aircraft platform carries the lift-off of two-stage rocket spacecraft, traverse at a distance, and launch window selected and chased to the transmitting site restriction can less, receives effects limit such as weather, meteorology and influence less.
Four, description of drawings:
Accompanying drawing 1 is accomplished the front part plan scheme drawing of the track acceleration aircraft of two-stage rocket spacecraft lift-off for the two-stage motion platform.
Accompanying drawing 2 is accomplished the lateral plane scheme drawing of the track acceleration aircraft of two-stage rocket spacecraft lift-off for the two-stage motion platform.
Reference numeral: 1, the base of the rail; 2, track; 3, orbiting motion platform; 4, aircraft platform; 5, two-stage rocket spacecraft.
Five, the specific embodiment:
Like Fig. 1, shown in Figure 2, the track that the two-stage motion platform of the utility model is accomplished the lift-off of two-stage rocket spacecraft quickens aircraft, its track 2 is to originate in the reliable base of the rail 1 of having of composing room, the outward extending double track of ray shape.Its orbiting motion platform 3 be have autonomous active power system, through orbiting motion platform negative pressure disconnecting gear, fastening and carry aircraft platform 4, quicken and discharge aircraft platform 4, along streamline contour, the high-performance express locomotive of track 2 operations.Its aircraft platform 4 is that top circular arc flute profile rocket dress open, fastening through aircraft platform negative pressure disconnecting gear and carrying two-stage rocket spacecraft is taken the storehouse in conventional cabin Position Design, and the cockpit of aircraft platform 4 is arranged at the fuselage head below, rudder fin is set to outer Zhang Shuanyi.
Except that the described technical characterictic of specification sheets, be the known technology of those skilled in the art.
Claims (1)
1. a two-stage motion platform is accomplished the track acceleration aircraft that the two-stage rocket spacecraft goes up to the air; It comprises track, orbiting motion platform, aircraft platform and two-stage rocket spacecraft; It is characterized in that transmitting operation through the interim relay mode of orbiting motion platform, aircraft platform and two-stage rocket sends spacecraft into planned orbit, its track is the double rail type of ray property; Its orbiting motion platform has autonomous active power system, and is Orbiting, carries and let fly away the stream line pattern express locomotive of aircraft platform through fastening automatic disconnecting gear; Its aircraft platform is that top is open, cockpit is arranged at the fuselage head below, rudder fin is outer Zhang Shuanyi, is the special-shaped aircraft of power with the jet engine; Aircraft platform carries and lets fly away the two-stage rocket spacecraft through fastening automatic disconnecting gear in open cabin position.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012200352755U CN202624648U (en) | 2012-02-06 | 2012-02-06 | Track acceleration plane using two stages of motion platforms to finish levitation of two-stage rocket spacecraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012200352755U CN202624648U (en) | 2012-02-06 | 2012-02-06 | Track acceleration plane using two stages of motion platforms to finish levitation of two-stage rocket spacecraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202624648U true CN202624648U (en) | 2012-12-26 |
Family
ID=47377872
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2012200352755U Expired - Lifetime CN202624648U (en) | 2012-02-06 | 2012-02-06 | Track acceleration plane using two stages of motion platforms to finish levitation of two-stage rocket spacecraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202624648U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102556360A (en) * | 2012-02-06 | 2012-07-11 | 董兰田 | Orbit accelerating airplane capable of completing lift-off of two-stage rocket spacecraft with two-stage moving platforms |
-
2012
- 2012-02-06 CN CN2012200352755U patent/CN202624648U/en not_active Expired - Lifetime
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102556360A (en) * | 2012-02-06 | 2012-07-11 | 董兰田 | Orbit accelerating airplane capable of completing lift-off of two-stage rocket spacecraft with two-stage moving platforms |
| CN102556360B (en) * | 2012-02-06 | 2014-04-02 | 董兰田 | Orbit accelerating airplane capable of completing lift-off of two-stage rocket spacecraft with two-stage moving platforms |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| Torenbeek et al. | Flight physics: essentials of aeronautical disciplines and technology, with historical notes | |
| AU2007312198B2 (en) | Aircraft with hybrid aerodynamic and space flight, and associated flight control method | |
| CN102822054A (en) | Ultra-rapid air vehicle and related method for aerial locomotion | |
| CA2870808C (en) | An aerospace plane system | |
| CN205221105U (en) | Solar energy VTOL fixed wing uavs | |
| CN100519336C (en) | Method and device for improving maneuverability of an aircraft | |
| CN102556360B (en) | Orbit accelerating airplane capable of completing lift-off of two-stage rocket spacecraft with two-stage moving platforms | |
| CN104787306A (en) | Low-speed safety aircraft capable of controlling flight attitude by aerodynamic force | |
| CN111959824B (en) | Heavy reusable aerospace vehicle system with space-based emission | |
| CN202624648U (en) | Track acceleration plane using two stages of motion platforms to finish levitation of two-stage rocket spacecraft | |
| CN205293058U (en) | Conveniently carry on fixed wing uavs of jumbo size loading device | |
| CN203032936U (en) | Passenger helicopter | |
| CN101121441A (en) | Aircraft with multi-wing and multi-thruster | |
| CN203497168U (en) | Front camera bin of unmanned plane | |
| CN113335526A (en) | Intercontinental rapid arrival transportation system based on rocket power | |
| RU178017U1 (en) | VERTICAL TAKEOFF AND LANDING PLANE | |
| Marino et al. | Benefits of the blended wing body aircraft compared to current airliners | |
| CN109532889A (en) | Angle of attack bottom wing punching press gas suspension train | |
| Torenbeek et al. | History of aviation | |
| RU2693356C1 (en) | Supersonic aircraft with tunnel fuselage | |
| US20160009415A1 (en) | Expanded airliner configured symmetrically rear to front or rear to rear | |
| RU2661005C2 (en) | Method of regulating the lifting force of the aircraft and aircraft itself | |
| RU143505U1 (en) | VERTICAL TAKEOFF AND LANDING FLIGHT | |
| CN205150256U (en) | Novel an unmanned aerial vehicle platform for air -drop | |
| Grose | CLOSE ENOUGH |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20121226 Effective date of abandoning: 20140402 |
|
| RGAV | Abandon patent right to avoid regrant |