CN104828260A - Three-stage space carrying system - Google Patents
Three-stage space carrying system Download PDFInfo
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- CN104828260A CN104828260A CN201510078060.XA CN201510078060A CN104828260A CN 104828260 A CN104828260 A CN 104828260A CN 201510078060 A CN201510078060 A CN 201510078060A CN 104828260 A CN104828260 A CN 104828260A
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Abstract
The invention relates to a three-stage space carrying system and belongs to the aerospace technology field. The three-stage space carrying system of the invention comprises a catapult, a carrier aircraft and a space aircraft. The three-stage space carrying system is characterized in that the carrier aircraft is driven by a ramjet engine; the catapult is used for supporting, propelling and accelerating the carrier aircraft so that the carrier aircraft can achieve a speed required by the startup of the ramjet engine; the carrier aircraft is used for carrying the space aircraft and drives and carries the space aircraft to achieve a predetermined flight speed, a predetermined position and a predetermined space height through the ramjet engine; and the space aircraft is used for achieving a space orbit. According to the three-stage space carrying system of the invention, a process is divided into three stages according to the speed and height of the space carrying system based on different characteristics of environments, and an optimal propulsion tool is adopted in each stage, and inherent contradiction of space carrying can be avoided or avoided partially, and space carrying capacity and economical efficiency can be improved.
Description
Technical field
The present invention relates to a kind of syllogic space vehicles system, belong to space technology field.
Background technology
In existing space technology, or near vertical vertical from ground launches a carrier rocket to transport material to space orbit usually.This space vehicles mode has much contradiction to be difficult to strike a balance, and result in the inefficiencies of rocket, very poor economy and be not suitable for some application scenario, also limit the limit of space vehicles ability.These contradictions show.
1) loss of thrust direction and drag losses, owing to being level or almost horizontal to final flight attitude that is circular, oval and other most mission requirements.Change relevant loss (loss of thrust direction) in order to reduce with thrust direction, desirable mode makes space vehicles instrument when relatively low speed is climbed with regard to pitching upwards, and flight path just shows as almost horizontal in early days and climbs and non-perpendicularly to climb.But the factors such as structural stress and aerodynamic force heating, hinder this desirable flight path in the application of space vehicles instrument under atmospheric conditions.Aerodynamic force be one with the parameter of atmospheric density and the velocity correlation of space vehicles instrument own, vertical launch can reduce aerodynamic force loss, but this is what to have paid the excessive propellant of the use that causes due to loss of thrust direction be cost.
2) gravity losses, carrier rocket does flight that is vertical or near vertical in the most of the time, and gravity has directly offseted the thrust of considerable part, result in significant gravity losses.
3) thrust of atmosphere pressure induction is reduced the loss, and the efficiency of rocket engine and the area of exhaust nozzle are positively related, but when the area of exhaust nozzle increases, the atmospheric environmental pressure acting on rocket engine spout too increases.So firing a rocket in dense atmosphere, it is compromise in these three parameters to have to, and finally, driving engine propulsion coefficient receives impact.
4) due to propellant and fly through densely populated area and may bring danger, the operation of rocket launching and address receive obvious restriction.
In order to solve or partly solve above-mentioned contradiction, improve space vehicles ability and economy, invent new space vehicles instrument, needed for when being.
Summary of the invention
The object of the invention is, for the needs of existing space delivery, to propose a kind of syllogic space vehicles system, to improve space vehicles ability and economy.
The present invention is achieved in that described a kind of syllogic space vehicles system comprises: ejector, mother aircraft, space vehicle, wherein, mother aircraft comprises more than one or one ramjet driving engine, it is characterized in that: mother aircraft is by ramjet engine drive; Mother aircraft is removably installed in ejector by adaptor union A; Space vehicle is removably installed in mother aircraft by adaptor union B; Ejector is used for supporting, promotes, accelerates mother aircraft, makes mother aircraft reach speed required for ramjet engine starting; Mother aircraft is used for bearing space aircraft, and reaches predetermined flying speed, preposition, predetermined spatial altitude by the driving carrying space aircraft of ramjet driving engine; Space vehicle is used for reaching space orbit.Space vehicle can be carrier rocket, spaceship, space shuttle etc.
Described ejector is Electromagnetical ejector.The benefit of Electromagnetical ejector be to ancillary system require low, efficiency is high, lightweight, operation and maintenance cost is cheap.
The ejection orbit of described ejector is level or almost horizontal.Level or the track handled easily of almost horizontal, applicable mother aircraft takes off.
Described ejector is installed on land fixed-site.Land fixed-site handled easily, maintenance.
Described ejector is installed on water surface movable platform, as aircraft carrier.Water surface movable platform has obvious manoevreability, for launch site and flight path provide obvious advantage.
In the flight path of mother aircraft, maximum climbing angle is less angle (being less than 45 degree), and this angle meets the pneumatic requirement of described mother aircraft.To utilize the aerodynamic configuration of mother aircraft, avoid destructive aerodynamic load and hot lotus.
Mother aircraft is in flight course, by maneuvering flight and the adjustment of mother aircraft self, make mother aircraft can fly on the desired trajectory direction of space vehicle, make contributions to space vehicle institute's energy requirement in predetermined rising trace with gross energy during meeting spatial vehicle launch.Space vehicle maneuvering flight is more much lower than mother aircraft maneuvering flight efficiency.
It is inner that space vehicle is removably installed in mother aircraft poplar body by adaptor union B.To obtain good aerodynamic configuration, reduce air resistance.
Space vehicle is removably installed under mother aircraft fuselage by adaptor union B.More convenient safety when both are separated like this.
The workflow of described a kind of syllogic space vehicles system is as follows.
1) space vehicle is removably installed under mother aircraft by adaptor union B; Mother aircraft is removably installed on ejector by adaptor union A.Enter first stage.
2) air ejector for starting; Mother aircraft, along ejection orbit to preacceleration, reaches the speed required for ramjet engine starting; Start ramjet driving engine, mother aircraft further to preacceleration, reaches mother aircraft takeoff speed along ejection orbit; Adaptor union A opens, and mother aircraft is separated with ejector, and mother aircraft takes off.Enter subordinate phase.
3) mother aircraft rises to preacceleration further under ramjet engine drive, and ascending angle is a less angle (being less than 45 degree), this angle meets the pneumatic requirement of mother aircraft.
4) mother aircraft does maneuvering flight and adjustment, makes mother aircraft can fly on the desired trajectory direction of space vehicle, makes contributions to space vehicle institute's energy requirement in predetermined rising trace with the gross energy of satisfied transmitting time space aircraft.
5) after mother aircraft reaches predetermined flying speed, preposition, predetermined spatial altitude, adaptor union B opens, and space vehicle is separated with mother aircraft, launch.Enter the phase III.
6) space vehicle starts, and space vehicle rises to preacceleration further, reaches space orbit according to desired trajectory.
In the present invention, because the feature of ramjet driving engine, it needs certain speed to start, so ejector is absolutely necessary.
The invention has the advantages that: based on environment different characteristics, whole process is divided into three sections with height by the speed according to space vehicles system, each section selects optimum driving tool, avoids or partly avoids space vehicles intrinsic contradictions, improve space vehicles ability and economy; At first paragraph, use ejector to make ramjet driving engine reach toggle speed fast, compensate for the feature of ramjet low engine speed cisco unity malfunction; At second segment, ramjet driving engine accelerates, ramjet engine construction is simple, lightweight, thrust-weight ratio is large, cost is low, with the oxygen in air for ignition promotor, add the aerodynamic configuration of mother aircraft, obviously will reduce total system mass, and more excellent track can be selected, also can fly to and need arbitrarily position and appropriate height; At the 3rd section, space vehicle accelerates and enters space orbit, because space vehicle is needing arbitrarily the high-altitude of position to launch, reduces loss of thrust direction and drag losses, gravity losses; The exhaust nozzle of rocket engine can do greatly, reduces the thrust loss of atmosphere pressure induction, optimizes launching track, gets around densely populated area, avoid unnecessary maneuvering flight.
Accompanying drawing explanation
A kind of syllogic space vehicles of Fig. 1 system schematic side view.
A kind of syllogic space vehicles of Fig. 2 system front elevational schematic.
A kind of syllogic space vehicles of Fig. 3 systems radiate process schematic.
In figure, 1 ejector, 1.1 adaptor union A, 2 mother aircrafts, 2.1 adaptor union B, 2.2 ramjet driving engines, 3 space vehicles, 10 flight tracks, 20 flight tracks.
Detailed description of the invention
Below in conjunction with the accompanying drawing 1 of specification sheets, accompanying drawing 2 and accompanying drawing 3, the invention will be further described.
Certain year, in such a month, and on such a day a kind of syllogic space vehicles system of the present invention prepared in certain launch site to launch.
Described a kind of syllogic space vehicles system comprises: ejector (1), mother aircraft (2), space vehicle (3), mother aircraft (2) is binary aircraft, left and right both wings respectively have a ramjet driving engine (2.2), it is characterized in that: mother aircraft (2) is driven by two ramjet driving engines (2.2); Mother aircraft (2) is by adaptor union A(1.1) be removably installed in ejector (1); Space vehicle (3) is by adaptor union B(2.1) be removably installed in mother aircraft (2), space vehicle (3) is positioned between two bodies of the mother aircraft (2) of binary; Ejector (1) for supporting, promote, accelerate mother aircraft (2), make mother aircraft (2) reach ramjet driving engine (2.2) start required for speed; Mother aircraft (2) for bearing space aircraft (3), and reaches predetermined flying speed, preposition, predetermined spatial altitude by the driving carrying space aircraft (3) of ramjet driving engine (2.2); Space vehicle (3) is for reaching space orbit.
Described ejector (1) is Electromagnetical ejector.
The ejection orbit of described ejector (1) is level.
Described ejector (1) is installed on land fixed-site.
Described a kind of syllogic space vehicles system prepares to launch, and emission process is as follows.
1) space vehicle (3) is by adaptor union B(2.1) be removably installed under mother aircraft (2); Mother aircraft (2) is by adaptor union A(1.1) be removably installed on ejector (1).Enter first stage.
2) air ejector for starting (1); Mother aircraft (2), along electromagnetic launch track to preacceleration, reaches the speed 0.6 Mach required for ramjet driving engine (2.2) startup; Start two ramjet driving engines (2.2), under ejector (1) and ramjet driving engine (2.2) drive jointly, mother aircraft (2) further to preacceleration, reaches mother aircraft (2) takeoff speed along ejection orbit; Adaptor union A(1.1) to open, mother aircraft (2) is separated with ejector (1), and mother aircraft (2) takes off.Enter subordinate phase.
3) mother aircraft (2) starts to fly according to predetermined flight track (10), mother aircraft (2) rises to preacceleration further under ramjet driving engine (2.2) drives, ascending angle is a less angle (40 degree), and this angle meets mother aircraft (2) pneumatic requirement.
4) mother aircraft (2) does maneuvering flight and adjustment, make mother aircraft (2) can fly on the desired trajectory direction of space vehicle (3), make contributions to space vehicle (3) institute's energy requirement in predetermined rising trace with the gross energy of described space vehicle (3) during satisfied transmitting, get around densely populated area simultaneously.
5) mother aircraft (2) reaches predetermined flying speed 3 Mach, preposition, predetermined spatial altitude, the advection layer that height above sea level is 30000 meters, exceed aerodynamic force peak value, adaptor union B(2.1) to open, space vehicle (3) is separated with mother aircraft (2), launches.Enter the phase III.
6) space vehicle (3) starts, and space vehicle (3) rises to preacceleration further, reaches space orbit according to predetermined flight track (20).
7) after mother aircraft (2) is separated with space vehicle (3), fly to desired location, then do unpowered glide landing, fall within certain airport, like this, use the primary space launch mission of a kind of syllogic space vehicles system of the present invention just to complete.During mother aircraft (2) landing, its speed is less than the speed of the normal need of work of ramjet driving engine (2.2), unpowered glide can only be used to land, and for once chance, this has certain risk, but really can accomplish, the space shuttle landing like this of the such as U.S., is only left mother aircraft (2) itself during mother aircraft of the present invention (2) landing, without any load, difficulty should be less than space shuttle.
The above, it is only preferred embodiment of the present invention, but be understandable that, the present invention is not limited to disclosed embodiment and component, on the contrary, the various remodeling within the purport being included in appending claims and scope, integrate features, the device of equivalence and the component of equivalence is intended to contain.In addition, occur that the size of the feature of each component is in the accompanying drawings not restrictive, wherein the size of each component can be different from the size of the component described in the accompanying drawings.Therefore, the present invention is used for covering remodeling of the present invention and distortion, as long as they are all within the scope of appending claims with their equivalents.
Claims (10)
1. syllogic space vehicles system comprises: ejector, mother aircraft, a space vehicle, and wherein, described mother aircraft comprises more than one or one ramjet driving engine, it is characterized in that: mother aircraft is by ramjet engine drive; Mother aircraft is removably installed in ejector by adaptor union A; Space vehicle is removably installed in mother aircraft by adaptor union B; Ejector is used for supporting, promotes, accelerates mother aircraft, makes mother aircraft reach speed required for ramjet engine starting; Mother aircraft is used for bearing space aircraft, and reaches predetermined flying speed, preposition, predetermined spatial altitude by the driving carrying space aircraft of ramjet driving engine; Space vehicle is used for reaching space orbit.
2. a kind of syllogic space vehicles system according to claim 1, is characterized in that: described ejector is Electromagnetical ejector.
3. a kind of syllogic space vehicles system according to claim 1, is characterized in that: the ejection orbit of described ejector is level or almost horizontal.
4. a kind of syllogic space vehicles system according to claim 1, is characterized in that: described ejector is installed on land fixed-site.
5. a kind of syllogic space vehicles system according to claim 1, is characterized in that: described ejector is installed on water surface movable platform.
6. a kind of syllogic space vehicles system according to claim 1, it is characterized in that: in the flight path of mother aircraft, maximum climbing angle is less angle, and this angle meets the pneumatic requirement of described mother aircraft.
7. a kind of syllogic space vehicles system according to claim 1, it is characterized in that: mother aircraft is in flight course, by maneuvering flight and the adjustment of mother aircraft self, make mother aircraft can fly on the planned orbit direction of space vehicle, make contributions to space vehicle institute's energy requirement in predetermined rising trace with gross energy during meeting spatial vehicle launch.
8. a kind of syllogic space vehicles system according to claim 1, is characterized in that: it is inner that space vehicle is removably installed in mother aircraft poplar body by adaptor union B.
9. a kind of syllogic space vehicles system according to claim 1, is characterized in that: space vehicle is removably installed under mother aircraft fuselage by adaptor union B.
10. a kind of syllogic space vehicles system according to claim 1, is characterized in that: the workflow of described a kind of syllogic space vehicles system is as follows:
1) space vehicle is removably installed under mother aircraft by adaptor union B; Mother aircraft is removably installed on ejector by adaptor union A; Enter first stage;
2) air ejector for starting; Mother aircraft, along ejection orbit to preacceleration, reaches the speed required for ramjet engine starting; Start ramjet driving engine, mother aircraft further to preacceleration, reaches mother aircraft takeoff speed along ejection orbit; Adaptor union A opens, and mother aircraft is separated with ejector, and mother aircraft takes off; Enter subordinate phase;
3) mother aircraft rises to preacceleration further under ramjet engine drive, and ascending angle is a less angle, this angle meets the pneumatic requirement of mother aircraft;
4) mother aircraft does maneuvering flight and adjustment, makes mother aircraft can fly on the desired trajectory direction of space vehicle, makes contributions to space vehicle institute's energy requirement in predetermined rising trace with the gross energy of satisfied transmitting time space aircraft;
5) after mother aircraft reaches predetermined flying speed, preposition, predetermined spatial altitude, adaptor union B opens, and space vehicle is separated with mother aircraft, launch; Enter the phase III;
6) space vehicle starts, and space vehicle rises to preacceleration further, reaches space orbit according to desired trajectory.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510078060.XA CN104828260A (en) | 2015-02-14 | 2015-02-14 | Three-stage space carrying system |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201510078060.XA CN104828260A (en) | 2015-02-14 | 2015-02-14 | Three-stage space carrying system |
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| CN104828260A true CN104828260A (en) | 2015-08-12 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2020140178A1 (en) * | 2018-12-30 | 2020-07-09 | 中国科学院沈阳自动化研究所 | On-orbit launching apparatus |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO1998030449A1 (en) * | 1997-01-13 | 1998-07-16 | Kelly Space & Technology, Inc. | Space launch vehicles configured as gliders and towed to launch altitude by conventional aircraft |
| CN1237934A (en) * | 1996-09-16 | 1999-12-08 | 太空通道有限公司 | Low earth orbit payload launch system |
| US20080087764A1 (en) * | 2003-10-20 | 2008-04-17 | Central Japan Railway Compay | Flying vehicle-launching apparatus and method |
-
2015
- 2015-02-14 CN CN201510078060.XA patent/CN104828260A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1237934A (en) * | 1996-09-16 | 1999-12-08 | 太空通道有限公司 | Low earth orbit payload launch system |
| WO1998030449A1 (en) * | 1997-01-13 | 1998-07-16 | Kelly Space & Technology, Inc. | Space launch vehicles configured as gliders and towed to launch altitude by conventional aircraft |
| US20080087764A1 (en) * | 2003-10-20 | 2008-04-17 | Central Japan Railway Compay | Flying vehicle-launching apparatus and method |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2020140178A1 (en) * | 2018-12-30 | 2020-07-09 | 中国科学院沈阳自动化研究所 | On-orbit launching apparatus |
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Application publication date: 20150812 |
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