CN102390547B - Laser propulsion aircraft with vector nozzle - Google Patents
Laser propulsion aircraft with vector nozzle Download PDFInfo
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- CN102390547B CN102390547B CN 201110293873 CN201110293873A CN102390547B CN 102390547 B CN102390547 B CN 102390547B CN 201110293873 CN201110293873 CN 201110293873 CN 201110293873 A CN201110293873 A CN 201110293873A CN 102390547 B CN102390547 B CN 102390547B
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- catadioptre
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- reflecting mirror
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Abstract
The invention discloses a laser propulsion aircraft with vector nozzle, comprising an effective load and control instrument bay (1), a propellant storage box (2), a plane reflecting mirror (3), a concave paraboloid reflecting mirror (4), a convex paraboloid reflecting mirror (5), a high transmittance plate glass (6) and a laser propulsion engine (7). The effective load and control instrument bay is set on the head of the aircraft; said propellant storage box is set in the middle part of the aircraft and is adjacent to the effective load and control instrument bay. The concave paraboloid reflecting mirror and the convex paraboloid reflecting mirror are set on the aircraft belly on the back position, wherein the two mirrors have the same axle line and focus. The high transmittance plate glass is set below the convex paraboloid reflecting mirror and is round plate glass, and diameter thereof is slightly bigger than that of the concave paraboloid reflecting mirror, and is embedded in the shell of the aircraft belly. The plane reflecting mirror is set on the top of the concave paraboloid reflecting mirror. The invention provides a laser propulsion aircraft, which has uncorrelated propulsion direction and laser beam direction, pollution free engine and lower requirement on performance of laser incoming window of the thrust chamber, for aerospace launch and proximity space flight.
Description
Technical field
The present invention relates to aerospace laser and advance the field, the incoherent laser of particularly a kind of beam direction and thrust direction advances aircraft.
Background technology
It is to utilize the antagonistic force of the High Temperature High Pressure plasma flow of superlaser and the generation of working medium mutual action to promote the new ideas Push Technology that aircraft advances that laser advances.Compare with traditional chemical propulsion system, laser propulsion system has three characteristics: at first aircraft need not self-contained energy supplyystem, and aircraft institute energy requirement can be provided by the superlaser that long-distance transmissions is come; Secondly, the energy that laser emission provided has been broken through the restriction of combustion temperature, and specific impulse is very high; At last, laser propulsion system requires low to working medium, can not adopt traditional chemical rocket propellant as working medium.
Only there is at present U.S. Myrabo to design complete laser and advances aircraft-bareboat, and it has been applied for patent (Myrabo L N, Laser propelled vehicle, US Patent 6488233B1,2002).Bareboat can mainly comprise parts such as front portion, rear portion and ring jacket with air-breathing mode and the work of rocket pattern.The front portion is dome-shaped, and its edge can be used as engine inlet port.The rear portion parabola that to be a parabola form around the straight line rotation that is parallel to axis of symmetry, but both reflector laser of parabola laser is focused on the loop wire, can be used as the gas expansion surface again, become the part of plug nozzle.The ring jacket and the rear portion paraboloid of revolution are formed plug nozzle jointly.Plug nozzle is the keystone configuration that produces thrust.The focus lamp and the jet pipe of bareboat are shared, have following shortcoming: (1) laser beam must overlap with the bareboat axis of symmetry, focuses on otherwise can influence laser; (2) high-velocity particles in the jet pipe fails to be convened for lack of a quorum and washes away jet pipe, destroys to focus on minute surface; (3) jet pipe and focus lamp are difficult to accomplish optimization in design, can attend to one thing and lose sight of another; (4) thrust is parallel with the bareboat axis of symmetry, does not possess the thrust vectoring control ability.
It is " clock " shape aircraft that another kind of simple laser advances aircraft.Aircraft propulsion mainly is made up of the bell jet pipe, and the jet pipe inside face is the face that a parabola forms along its axis of symmetry rotation.The jet pipe inside face is done polishing, with reflector laser.The jet pipe inside face will be parallel to the laser that nozzle axis injects and focus on the parabolic focus place, and working medium produces detonation wave to produce thrust in the jet pipe by puncturing.The shortcoming of this aircraft and the shortcoming of bareboat are similar.
People such as Russia Ageichik have proposed the notion of " empty day laser propelling motor " (ASLPE, Airspace Laser Propulsion Engine).The aircraft that constitutes by ASLPE make with function on the optical unit of propulsion system is separated with driving engine.Laser beam is injected rotational paraboloid mirror after by the light beam corrective system of being made up of two sheets of mirrors, and laser beam becomes the ring focused beam after reflection.Before light beam focuses on, there is an annular arrangement light deflector that light beam is focused on by ring and changes into point focusing, its focus is in engine nozzle.Aircraft thrust direction and beam direction are irrelevant, have the thrust vectoring control ability.But, opening being arranged to introduce laser on the jet pipe of ASLPE, this can bring two problems to aircraft: (1) working medium is overflowed from the jet pipe opening part, brings pollution for the aircraft miscellaneous part; (2) raising of jet pipe opening restriction aircraft thrust.
2006, Tang Zhiping proposed the separation type omnibearing take-over laser booster and has applied for patent (China national patent of invention, publication number CN 1970389A).The separation type omnibearing take-over laser booster comprises optical system, propellant tank, combustion chamber and jet pipe.One side of combustion chamber has transparent circular window, and laser beam converges and enters the combustion chamber center by window through optical system.Propellant in the combustion chamber is lighted the back from jet pipe ejection generation thrust forward by laser.The major defect of this thruster is that the transparent circular window environment of living in of combustion chamber is abominable, should bear the calorific effect that light laser produces, and stand washing away and heat transfer of high-temperature fuel gas again, so window material damages easily.
Summary of the invention
The technical problem to be solved in the present invention is, defective at the prior art existence, for the flight of space launch and proximity space provides a kind of thrust direction uncorrelated with beam direction, driving engine is pollution-free, the laser propelling aircraft low to the laser incidence window performance requriements of thrust chamber.
Technical scheme of the present invention is: described laser advances aircraft to comprise capacity weight and control instrument cabin 1, propellant tank 2, plane mirror 3, concave paraboloid catadioptre 4, convex paraboloid catadioptre 5, high-transmission rate plate glass 6, laser propelling motor 7.Capacity weight and control instrument cabin 1 are positioned at the head of aircraft, and propellant tank 2 is positioned at the aircraft middle part, and is adjacent with capacity weight and control instrument cabin 1.Concave paraboloid catadioptre 4 and convex paraboloid catadioptre 5 are positioned at the position after the aircraft belly leans on, both coaxial lines and focus.Be high-transmission rate flat glass 6 below convex paraboloid catadioptre 5, be circular flat glass, diameter is more bigger than concave paraboloid catadioptre, is embedded in aircraft belly housing.At the top of concave paraboloid catadioptre 4 are plane mirrors 3.
High-transmission rate flat glass 6 can allow superlaser by and prevent extraneous airflow influence concave paraboloid catadioptre 4 and convex paraboloid catadioptre 5.The laser propelling motor 7 that is positioned at the aircraft afterbody introduced laser by plane mirror 3.
Wherein, concave paraboloid catadioptre 4 is positioned at the aircraft belly with convex paraboloid catadioptre 5, and both coaxial lines and focus can be dwindled the hot spot along the straight beam of axis incident, but do not changed beam direction.The diameter of concave paraboloid catadioptre 4 is a bit larger tham the laser beam diameter of incident, and the diameter of convex paraboloid catadioptre 5 then can determine the beam diameter after narrow the contracting.In aircraft, concave paraboloid catadioptre 4 and convex paraboloid catadioptre 5 are movable part, and certain interval is arranged between the miscellaneous part.Concave paraboloid catadioptre 4 and convex paraboloid catadioptre 5 keep relative position constant (coaxial confocal point) when rotating, the angle between its axis and high-transmission rate flat glass 6 normals can reach about 30 degree.In the aircraft flight process, concave paraboloid catadioptre 4 can constantly rotate to point to beam direction with convex paraboloid catadioptre 5.In order to allow aircraft keep good aerodynamic configuration to shield the influence of outer gas stream simultaneously, high-transmission rate flat glass 6 is housed at the aircraft belly to the aircraft interior optics.
After the laser beam that sends from ground based laser converges through large diameter concave paraboloid catadioptre 4 and convex paraboloid catadioptre 5, be tens of centimetres light beam with the narrow spot diameter that shortens into of laser.Plane mirror 3 can change the direction of the narrow light beam that contracts, and makes light beam enter laser propelling motor 7.Light beam enters the engine thrust chamber by the planar lens 8 at driving engine top, has taper parabolic reflector 9 and convex surface light deflector 10 that laser is focused in the thrust chamber.Propellant is formed plasma by laser breakdown near engine nozzle throat.Propellant through LASER HEATING advances along jet pipe ejection generation thrust promotion aircraft.
The propulsion system of aircraft can adopt monomotor propulsion system or twin-engined propulsion system.In twin-engined propulsion systems, the narrow laser beam that contracts at first is divided into two bundle laser by wedge spectroscope 11, introduces laser propelling motor 7 through plane mirror 3 respectively then.
The advantage of this aircraft is: the big I of (1) minute surface is decided according to the size and the power of laser beam, to the laser incidence window performance requriements low (2) of thrust chamber with thrust vectoring direction and beam direction decoupling zero, eliminated the restriction of beam direction, realized thrust vectoring control thrust vectoring; (3) aircraft has good aerodynamic configuration; (4) comformability is strong, and the also available pulse laser of both available continuous wave laser provides energy for aircraft.
Description of drawings
Fig. 1 is that laser advances the aircraft scheme drawing;
Fig. 2 is a monomotor propulsion system scheme drawing;
Fig. 3 is twin-engined propulsion system scheme drawings.
The specific embodiment
Referring to accompanying drawing 1～3, in this embodiment, the laser of band vector spray advances aircraft to provide energy by the ground based laser of 100MW level, can enter the near-earth orbit of 200km height from the ground surface launching.Aircraft is about 7m, wide about 3m, and high about 2m, its profile is similar to the space shuttle orbiter of the U.S., but fuselage is flat a little.The housing of aircraft is made by high-intensity aluminum copper alloy.Fill liquid hydrogen as propellant in propellant tank 2, the liquid hydrogen quality accounts for 60～70% of aircraft total mass.
The about 1m of the diameter of concave paraboloid catadioptre 4, it is made by lightweight, material that deflection is little, scribbles high reflectivity film at concave surface.Convex paraboloid catadioptre 5 and plane mirror 3 are made by the material of reflectivity height, rapid heat dissipation, and initiatively cooling mechanism of water-cooled also is housed on mirror.After 5 reflections of convex paraboloid catadioptre, beam diameter is about 20cm.Concave paraboloid catadioptre 4 and convex paraboloid catadioptre 5 can turn an angle, and are subjected to the restriction of aircraft casing, and the maximum rotation angle of both forward and reverse directions is about 27 °.
The size of laser propelling motor 7 is by planar lens 8 decisions.The diameter of planar lens 8 is 20cm, and the damage threshold of its eyeglass is 293kW/cm
2, can allow the laser of 90MW pass through.
The aircraft total mass is 1000kg, and engine/motor specific impulse is 700s.During emission, the near-earth orbit of aircraft through entering 200km after the flight of about 1300km, its capacity weight is 100kg.
Claims (1)
1. the laser of band vector spray advances aircraft, comprise capacity weight and control instrument cabin (1), propellant tank (2), plane mirror (3), concave paraboloid catadioptre (4), convex paraboloid catadioptre (5), high-transmission rate plate glass (6) and laser propelling motor (7), capacity weight and control instrument cabin (1) are positioned at the head of aircraft, and propellant tank (2) is positioned at the aircraft middle part, and is adjacent with capacity weight and control instrument cabin (1); It is characterized in that: concave paraboloid catadioptre (4) and convex paraboloid catadioptre (5) are positioned at the position after the aircraft belly leans on, both coaxial lines and focus; In the below of convex paraboloid catadioptre (5) is high-transmission rate flat glass (6), is circular flat glass, and diameter is more bigger than concave paraboloid catadioptre, is embedded in aircraft belly housing; At the top of concave paraboloid catadioptre (4) is plane mirror (3);
The diameter of described concave paraboloid catadioptre (4) is a bit larger tham the laser beam diameter of incident, beam diameter after narrow the contracting of diameter decision of convex paraboloid catadioptre (5), concave paraboloid catadioptre (4) and convex paraboloid catadioptre (5) are movable part, and certain interval is arranged between the miscellaneous part, concave paraboloid catadioptre (4) and convex paraboloid catadioptre (5) keep relative position constant when rotating, and the angle between its axis and high-transmission rate flat glass (6) normal reaches about 30 degree;
When thrust direction need change with the control of realization thrust vectoring, can realize by rotational plane catadioptre (3) and laser propelling motor (7), during rotation, the axis of laser propelling motor (7) and plane mirror (3) are positioned at straight line all the time, the axis of laser propelling motor (7) and the angle between the aircraft longitudinal axis reach 10 to 15 degree, the slightly larger in diameter of plane mirror (3) and planar lens (8) is in laser facula, and the power density of laser is less than the damage threshold of planar lens (8).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201110293873 CN102390547B (en) | 2011-10-08 | 2011-10-08 | Laser propulsion aircraft with vector nozzle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201110293873 CN102390547B (en) | 2011-10-08 | 2011-10-08 | Laser propulsion aircraft with vector nozzle |
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| Publication Number | Publication Date |
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| CN102390547A CN102390547A (en) | 2012-03-28 |
| CN102390547B true CN102390547B (en) | 2013-07-24 |
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| CN 201110293873 Expired - Fee Related CN102390547B (en) | 2011-10-08 | 2011-10-08 | Laser propulsion aircraft with vector nozzle |
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Families Citing this family (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2559030C2 (en) * | 2012-07-18 | 2015-08-10 | Федеральное государственное бюджетное учреждение "Научно-исследовательский испытательный центр подготовки космонавтов имени Ю.А. Гагарина" (ФГБУ "НИИ ЦПК имени Ю.А. Гагарина) | Laser rocket engine (versions) |
| CN103233872A (en) * | 2013-02-05 | 2013-08-07 | 空军工程大学 | Glass laser thruster |
| CN105197258B (en) * | 2015-09-02 | 2017-03-22 | 覃政 | Light pressure power system |
| RU2618558C1 (en) * | 2016-01-25 | 2017-05-04 | Асхат Абрарович Гарафутдинов | Missile launcher with laser-driven rocket engine |
| WO2018112723A1 (en) * | 2016-12-20 | 2018-06-28 | 覃政 | Light source energy boosting system |
| CN107401489A (en) * | 2017-08-18 | 2017-11-28 | 张雄志 | A kind of engine that thrust is produced using laser |
| CN108974395B (en) * | 2018-06-21 | 2019-11-15 | 中国人民解放军战略支援部队航天工程大学 | Extraterrestrial target based on the driving of sky-based laser platform becomes rail calculation method and its device |
| CN112555114B (en) * | 2020-12-01 | 2022-06-17 | 中国人民解放军战略支援部队航天工程大学 | Electromagnetic combined vector acceleration spray pipe for laser ablation propulsion |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4036012A (en) * | 1976-02-18 | 1977-07-19 | The United States Of America As Represented By The Secretary Of The Army | Laser powered rocket engine using a gasdynamic window |
| US6488233B1 (en) * | 2001-04-30 | 2002-12-03 | The United States Of America As Represented By The Secretary Of The Air Force | Laser propelled vehicle |
| RU2266420C2 (en) * | 2003-10-08 | 2005-12-20 | Федеральное государственное унитарное предприятие Научно-исследовательский институт комплексных испытаний оптико-электронных приборов и систем (ФГУП НИИКИ ОЭП) | Aerospace laser jet engine |
| CN100519343C (en) * | 2006-12-06 | 2009-07-29 | 中国科学技术大学 | Split type omnibearing take-over laser booster |
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| CN102390547A (en) | 2012-03-28 |
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Effective date of registration: 20170803 Address after: 518107 01C-1 building, B5 building, Guangming Science Park, 3009 Guangming Road, Guangming Street, Guangming District, Guangming District, Guangdong, Shenzhen Patentee after: SHENZHEN XUNTIAN SPACE TECHNOLOGY CO.,LTD. Address before: Zheng Jie in Hunan province 410073 Changsha City Yan w pool No. 47 Patentee before: NATIONAL University OF DEFENSE TECHNOLOGY |
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Granted publication date: 20130724 |