CN1970389A - Split type omnibearing take-over laser booster - Google Patents
Split type omnibearing take-over laser booster Download PDFInfo
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- CN1970389A CN1970389A CN 200610164810 CN200610164810A CN1970389A CN 1970389 A CN1970389 A CN 1970389A CN 200610164810 CN200610164810 CN 200610164810 CN 200610164810 A CN200610164810 A CN 200610164810A CN 1970389 A CN1970389 A CN 1970389A
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Abstract
The separate omnibearing laser receiving thruster comprises one or two optical systems, thrusting agent storage boxes, one or two burning chambers and spraying tubes, with the optical system at one side of the burning chamber, whose one side opens a transparent laser entrance portal, based on which, the optical system rotating and receiving all the laser beam of XY surfaces, accumulating to the center of the burning chamber through the optical system, with the trusting agent sprayed from the spray tube to generate forward thrusting. Complete separation of the optical system and the thrust system, free from the influence of high temperature and pressure thrust air flow, omnibearingly receiving laser beams from every direction, to adapt to all kinds of track conditions.
Description
Technical field
The present invention relates to space flight Push Technology field laser Push Technology, particularly a kind of separation type omnibearing take-over laser booster.
Background technology
In space flight Push Technology field, how to reduce launch cost, improve the focus that capacity weight is research and development always.Traditional satellite launching needs large-scale chemical carrier rocket, and fuel has accounted for very big ratio in the throw-weight, and the capacity weight proportion of entering the orbit only is about 1.5%, launch cost up to, and pollute big.First artificial satellite with China is example, " Dongfanghong " number heavy 173kg, if 1.5% to be capacity weight, actual transmission weight is: 11533kg, the visible most energy is used for advancing propellant itself, causes the waste of the energy.So scientists is all being explored all the time, seek to replace the legacy transmission mode with new principle of propeller.
Laser advances (Laser Propulsion) 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.
This imagination is that American scholar Kantrowitz at first proposed in 1972.Laser advances and can reach than high thrust (104N magnitude), can obtain again to be expected to be used for the Single Stage To Orbit of microminiature space vehicle than high specific impulse (more than the 103S), and the space propultion of aircraft or attitude adjustment.Because than leaping high, energy can be from remote ground or the input of space base laser, and self need not carry energy resource system, can improve the load of effectively entering the orbit (reaching more than 15%) of aircraft greatly, cost-cutting (it is estimated and can reduce by 1 more than the order of magnitude), pollution abatement simultaneously.Therefore, laser advances research to obtain the general attention in various countries and develops rapidly.
Typical case's representative of laser thruster is " bareboat (lightcraft) " model that Myrabo proposes, as shown in Figure 1, the bareboat model vertical launch of using the 10kW CO 2 pulse laser device will weigh 50g in 2000 has arrived the height of 71m, and applied for patent (Myrabo L N in 2002, Laser propelled vehicle, US Patent6488233B1,2002), the parabolical tail cone plays reflect focalization and expanding nozzle simultaneously in this model.This class design focus lamp and thrust chamber jet pipe all are shared, but have following shortcoming: (1) laser beam and propelling unit are coaxial, are difficult to change the laser incident direction, are unfavorable for receiving the laser beam and the change of flight direction of different azimuth incident; (2) because of taking into account 2 points, be difficult to accomplish optimum, need paraboloidal, but as thrust chamber and jet pipe, the parabolic type expansion is not necessarily best as focusing; (3) with temperature rise of jet pipe inside face or pollution, will influence reflecting properties, optical mirror plane was lost efficacy;
People such as Russia Ageichik have proposed a kind of " empty day laser propelling motor " (ASLPE, Airspace LaserPropulsion Engine) imagination, as shown in Figure 2, it is by twice rotational symmetry reflect focalization independently, has realized the unify separation of push system of focus optical.In order to regulate the laser pick-off direction, increased the external optical receiving system in focusing system the place ahead, but so, laser beam has passed through 4 secondary reflections, not only the light path complexity has also caused the loss of energy.Though this class driving engine can be regulated the direction that receives laser beam, the scope of its adjusting is limited.
Summary of the invention
Technology of the present invention is dealt with problems: overcome the deficiencies in the prior art, a kind of separation type omnibearing take-over laser booster is provided, the optical system of this thruster is thoroughly separated with push system, optical system is not subjected to High Temperature High Pressure to advance the influence of air-flow, the laser beam of any direction in comprehensive reception space is to adapt to various track conditions; And the tool optical system only focuses on through 2 secondary reflections, and simple in structure, light loss is less
One of technical solution of the present invention: for adopting the separation type omnibearing take-over laser booster of single beam engine structure, it comprises: optical system, propellant tank, combustion chamber and jet pipe, described optical system is positioned at the outer side of combustion chamber, on combustion chamber one side, have the laser incidence window of transparent circle, optical system serves as the axle rotation with the laser incidence window, realize receiving all laser beams in the xz plane, when the laser beam remittance is focused to the combustion chamber center, the propellant that ignition combustion is indoor, from jet pipe, spray, produce thrust forward, reach the purpose of propelling.
Two of technical solution of the present invention: the separation type omnibearing take-over laser booster that adopts dual-beam monomotor structure, it comprises: two optical systems, propellant tank, combustion chamber and jet pipe, described two optical systems symmetry respectively are positioned at the outer both sides of combustion chamber, on the both sides of combustion chamber, have the laser incidence window of transparent circle, two optical systems serve as the axle rotation with the laser incidence window, realize receiving all laser beams in the xz plane, when two laser beams converge in the center of same combustion chamber, the propellant that ignition combustion is indoor, from jet pipe, spray, produce thrust forward, reach the purpose of propelling.
Three of technical solution of the present invention: the separation type omnibearing take-over laser booster that adopts the twin-engined structures of dual-beam, comprise: two optical systems, propellant tank, two combustion chambers and two jet pipes, described two optical systems symmetry respectively are positioned at the outer both sides of two combustion chambers side by side, on a side of two combustion chambers, have the laser incidence window of transparent circle, two optical systems serve as the axle rotation with the laser incidence window, to realize receiving all laser beams in the xz plane, when two laser beams converge in two combustion chambers respectively separately during the center, light the propellant in two combustion chambers respectively, produce plasma, and from jet pipe separately, spray, produce thrust forward, reach the purpose of propelling.
The optical system of above-mentioned three schemes constitutes by the parabolic mirror and the plane mirror that are fixed on the support, plane mirror is placed on the center of parabolic mirror and parabolic reflector mirror foci, at the center of plane mirror is turning cylinder, rotating machine drives turning cylinder and rotates around the y axle, laser beam is assembled back reflection to plane mirror through parabolic mirror, and the center of passing S. A. again after plane mirror is assembled enters combustion chamber.
The position vertical with S. A. at an end of support is provided with bob-weight so that optical system barycenter is constant when rotated.
The present invention's advantage compared with prior art is:
(1) optical system is thoroughly separated with push system, and optical system is not subjected to High Temperature High Pressure to advance the influence of air-flow, and the structure of two systems and selection can be distinguished optimal design.
(2) laser beam that can any direction in comprehensive reception space is to adapt to various track conditions.When receiving dual-beam simultaneously, two bundle laser are as long as coplane needn't be parallel to each other.For laser cloth position, relay etc. are provided convenience.During vertical launch, laser beam needn't upwards shine from the aircraft bottom, can be from side direction incident, shown in Fig. 4,5.
(3) optical system only focuses on through 2 secondary reflections, and simple in structure, light loss is less.
(4) adopt dual-beam list/twin-engined configurations, the one, the needs of Flight Vehicle Structure symmetry, the 2nd, can reduce the power of separate unit laser.At present, high power laser is the technical bottleneck that realizes the maximum of laser propelling, and the emission micro-satellite is entered the orbit and needed the laser of 1MW at least, if adopt the dual-beam design, can use the laser of 2 500KW, reduce the development cost of laser and laser transmitting system greatly.Dual-beam list/twin-engined configurations can be realized laser relay (as close a laser, switch to another laser) than pulsation-free, and function such as heading etc. is regulated in the transition of the of short duration fault of laser.
(5) the present invention is applicable to solid, gas and liquid propellant.
Description of drawings
" bareboat " model that Fig. 1 proposes for Myrabo;
Fig. 2 is empty day laser propelling motor model;
Fig. 3 adopts the separation type omnibearing take-over laser booster figure of single beam engine structure for the present invention;
Fig. 4 is the separation type omnibearing take-over laser booster constructional drawing of dual-beam monomotor structure of the present invention;
Fig. 5 is the separation type omnibearing take-over laser booster constructional drawing of the twin-engined structures of dual-beam of the present invention;
Fig. 6 is an optical system configuration composition of the present invention;
Fig. 7 be in the xz of the present invention plane 360 ° regulate laser beam and thrust angle;
Fig. 8 is the layout of emission incident laser of the present invention and follows the tracks of scheme drawing.
The specific embodiment
The present invention has three kinds of versions, adopts structure, the employing single-engined structure of dual-beam of single beam driving engine and adopts dual-beam two-engined structure, describes in detail respectively below.
As shown in Figure 3, adopt the thruster of single beam engine structure for the present invention, it is by optical system 1, propellant tank 2, combustion chamber 3 and jet pipe 4 are formed, optical system 1 is positioned at an outer side of combustion chamber 3, and be connected with the rocket body solid, on combustion chamber 3, have the laser incidence window 5 of transparent circle, optical system 1 serves as the axle rotation with the laser incidence window, realize receiving all laser beams in the xz plane, when laser beam vertically is aggregated on the center 6 that is incident upon combustion chamber 3 by laser incidence window 5, the propellant that ignition combustion is indoor sprays from jet pipe, produces thrust forward.
As shown in Figure 4, be dual-beam monomotor thruster of the present invention, it is by two optical systems 1 and 1 ' that are positioned at combustion chamber 3 both sides, combustion chamber 3, jet pipe 4 is formed, two optical systems 1 and 1 ' symmetry respectively are positioned at the outer both sides of combustion chamber 3, and be connected with the both sides solid of rocket body, on the both sides of combustion chamber 3, have the laser incidence window 5 and 5 ' of transparent circle, two optical systems 1 and 1 ' serve as the axle rotation with separately laser incidence window 5 and 5 ', two laser incidence windows 5 and 5 ' are coaxial, and with rocket body axis RR ' vertical, realize to receive all laser beams in the xz plane, when two laser beams vertically converge in the center 6 of same combustion chamber 3 by laser incidence window 5 and 5 ', propellant in the ignition combustion chamber 3, the plasma that produces, ejection from jet pipe 4 produces thrust forward.
As shown in Figure 5, be the twin-engined thrusters of dual-beam of the present invention, it comprises: two optical systems 1 and 1 ', propellant tank 2, two combustion chambers 3 and 3 ' and two jet pipe 4 and 4 ', two optical systems 1 and 1 ' symmetry respectively are positioned at two combustion chambers that are arranged side by side 3 and 3 ' outer both sides, on two outsides of two combustion chambers 3 and 3 ', have the laser incidence window 5 and 5 ' of transparent circle, two optical systems 1 and 1 ' serve as the axle rotation with two laser incidence windows 5 and 5 ', realize receiving all laser beams in the xz plane, when two laser beams respectively vertically by laser incidence window 5 and 5 ' converge in two combustion chambers 3 and 3 ' separately center 6 and 6 ' time, light the propellant in two combustion chambers 3 and 3 ' respectively, ejection from two jet pipes 4 and 4 ' produces thrust forward.
As shown in Figure 6, optical system 1 of the present invention or 1 ' is made of the parabolic mirror 12 and the plane mirror 13 that are fixed on the support 11, plane mirror 13 is placed on the center of parabolic mirror 12 and parabolic reflector mirror foci, in the lower end of plane mirror 12 is turning cylinder 14, rotating machine 15 drives turning cylinder 14 and rotates around the y axle, laser beam is assembled back reflection to plane mirror 13 through parabolic mirror 12, after plane mirror 13 is assembled, pass the center of S. A. 14 again, enter combustion chamber 3 or 3 ' through transparent circular window or 5 '.Be provided with bob-weight 16 in an end of support 11 and S. A. 14 vertical positions, the effect of bob-weight 16 is to make optical system 1 or 1 ' barycenter is constant when rotated.
As shown in Figure 7, fixed optical system 1 and 1 ', promptly the orientation in the xz plane of laser is fixed, and the axis direction (being that aircraft is around the rotation of y axle) around y axle adjusting aircraft changes the direction of thrust in the xz plane, realizes the bending of track.
Principle of the present invention: as shown in Figure 8, in the xy plane, regulate and enter the orbit, wherein LS1 and LS2 are the Laser emission base, can know no matter aircraft is in any position, two of the laser that laser can track on the thruster receive catadioptre, be on parabolic mirror and the plane mirror, realize entering the orbit.Principles of Regulation are: optical system 1 and 1 ' can be driven by rotating machine 15 respectively rotates around the y axle, like this, optical system 1 or 1 ' can receive the laser beam from any direction incident in the xz plane, and keeps the aircraft thrust axis constant, all the time along the x direction.Because optical system 1 and 1 ' can independent regulation, so they can receive laser beam LB1 and LB2 from different directions in the xz plane respectively, and promptly laser needn't be placed in same direction or same place.Also can be as shown in Figure 7, fixed optical system 1 and 1 ', promptly the orientation in the xz plane of laser is fixed, and around the direction of y axle 360 ° of adjusting aircraft axis RR ' and thrust in the xz plane, thereby realizes the bending of track.The change in aircraft orientation can pass through to regulate method realizations such as spout direction, and the adjusting in optical system 1 and 1 ' orientation can rotate the relative y axle of optical system by Fu and realize, and adopts bob-weight 16 to make that centroid position is constant when rotating.
If aircraft is made lateral rotation (this point can be accomplished by methods such as lateral thrust spouts) around the x axle together with optical system, corner is , so in new coordinate, repeat the control process in the above-mentioned xz plane, but the omnibearing adjusting in implementation space, no matter promptly where laser to (but requiring two bundle laser in same plane), can receive laser energy by the lateral rotation and the rotatablely moving of optical system of aircraft, do not influence the flight path of aircraft.Because the angle between laser beam and the thrust can be regulated arbitrarily, therefore, can realize the design of various flight tracks according to mission requirements.
Claims (11)
1, separation type omnibearing take-over laser booster, it is characterized in that comprising: optical system, propellant tank, combustion chamber and jet pipe, described optical system is positioned at the outer side of combustion chamber, on combustion chamber one side, have the laser incidence window of transparent circle, optical system serves as the axle rotation with this laser incidence window, realize receiving all laser beams in the xz plane, laser beam is focused to the center of combustion chamber through the optical system remittance, the propellant that ignition combustion is indoor, from jet pipe, spray, produce thrust forward.
2, separation type omnibearing take-over laser booster according to claim 1, it is characterized in that: described optical system is made of the parabolic mirror and the plane mirror that are fixed on the support, plane mirror is placed on the midway location of parabolic mirror and parabolic reflector mirror foci, at the center of plane mirror is turning cylinder, rotating machine drives turning cylinder and rotates around the y axle, laser beam is assembled back reflection to plane mirror through parabolic mirror, and the center of passing S. A. again after plane mirror is assembled enters combustion chamber.
3, separation type omnibearing take-over laser booster according to claim 2 is characterized in that: the end position vertical with S. A. of described support is provided with bob-weight so that optical system barycenter is constant when rotated.
4, the separation type omnibearing take-over laser booster, it is characterized in that comprising: two optical systems, propellant tank, combustion chamber and jet pipe, described two optical systems symmetry respectively are positioned at the outer both sides of combustion chamber, on the both sides of combustion chamber, have the laser incidence window of transparent circle, two optical systems serve as the axle rotation with the laser incidence window, realize receiving all laser beams in the xz plane, when two laser beams converge in the center of same combustion chamber, the propellant that ignition combustion is indoor, from jet pipe, spray, produce thrust forward, reach the purpose of propelling.
5, separation type omnibearing take-over laser booster according to claim 4, it is characterized in that: described optical system is made of the parabolic mirror and the plane mirror that are fixed on the support, plane mirror is placed on the midway location of parabolic mirror and parabolic reflector mirror foci, at the center of plane mirror is turning cylinder, rotating machine drives turning cylinder and rotates around the y axle, laser beam is assembled back reflection to plane mirror through parabolic mirror, and the center of passing S. A. again after plane mirror is assembled enters combustion chamber.
6, separation type omnibearing take-over laser booster according to claim 5 is characterized in that: the end position vertical with S. A. of described support is provided with bob-weight so that optical system barycenter is constant when rotated.
7, separation type omnibearing take-over laser booster according to claim 4 is characterized in that: described two laser beam coplanes.
8, the separation type omnibearing take-over laser booster, it is characterized in that comprising: two optical systems, propellant tank, two combustion chambers and two jet pipes, described two optical systems symmetry respectively are positioned at the outer both sides of two combustion chambers that are arranged side by side, on two outsides of two combustion chambers, have the laser incidence window, two optical systems serve as the axle rotation with the laser incidence window, to realize receiving all laser beams in the xz plane, when two laser beams converge in two combustion chambers respectively separately during the center, light the propellant in two combustion chambers respectively, from jet pipe separately, spray, produce thrust forward.
9, separation type omnibearing take-over laser booster according to claim 8, it is characterized in that: described optical system is made of the parabolic mirror and the plane mirror that are fixed on the support, plane mirror is placed on the midway location of parabolic mirror and parabolic reflector mirror foci, at the center of plane mirror is turning cylinder, rotating machine drives turning cylinder and rotates around the y axle, laser beam is assembled back reflection to plane mirror through parabolic mirror, and the center of passing S. A. again after plane mirror is assembled enters combustion chamber.
10, separation type omnibearing take-over laser booster according to claim 9 is characterized in that: the end position vertical with S. A. of described support is provided with bob-weight so that optical system barycenter is constant when rotated.
11, separation type omnibearing take-over laser booster according to claim 8 is characterized in that: described two laser beam coplanes.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2006101648106A CN100519343C (en) | 2006-12-06 | 2006-12-06 | Split type omnibearing take-over laser booster |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2006101648106A CN100519343C (en) | 2006-12-06 | 2006-12-06 | Split type omnibearing take-over laser booster |
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| Publication Number | Publication Date |
|---|---|
| CN1970389A true CN1970389A (en) | 2007-05-30 |
| CN100519343C CN100519343C (en) | 2009-07-29 |
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| Application Number | Title | Priority Date | Filing Date |
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| CNB2006101648106A Expired - Fee Related CN100519343C (en) | 2006-12-06 | 2006-12-06 | Split type omnibearing take-over laser booster |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102390547A (en) * | 2011-10-08 | 2012-03-28 | 中国人民解放军国防科学技术大学 | Laser propulsion aircraft with vector nozzle |
| CN105197258A (en) * | 2015-09-02 | 2015-12-30 | 覃政 | Light pressure power system |
| CN107401489A (en) * | 2017-08-18 | 2017-11-28 | 张雄志 | A kind of engine that thrust is produced using laser |
| CN107672824A (en) * | 2017-09-30 | 2018-02-09 | 北华航天工业学院 | Optical-fiber laser self-propelled universe bareboat control system |
| CN108843461A (en) * | 2018-05-31 | 2018-11-20 | 上海新力动力设备研究所 | A kind of air flue middle solid micro-thruster |
| CN109131943A (en) * | 2018-08-08 | 2019-01-04 | 上海新力动力设备研究所 | Piston for laser chemistry joint propeller drives charge constitution |
Family Cites Families (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3818700A (en) * | 1972-10-20 | 1974-06-25 | Avco Corp | Ram jet powered by a laser beam |
| US4426843A (en) * | 1980-11-12 | 1984-01-24 | United Technologies Corporation | CO2 Coupling material |
| DE4222677A1 (en) * | 1992-05-11 | 1993-11-18 | Klaus Rasbach | Rocket propulsion by annular and revolving conc. laser beams - involves generation of thrust by reaction of beams radiated with unequal energy density due to magnetic rotation |
| JP2002195151A (en) * | 2000-12-26 | 2002-07-10 | Ishikawajima Harima Heavy Ind Co Ltd | Plasma gas propulsion device |
| 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 |
| ITNA20030044A1 (en) * | 2003-07-10 | 2005-01-11 | Biagio Ancarola | AERO / SPACIAL VEHICLE WITH RESERVE OF PROPELLENT, OR OUTDOOR SOURCE OF ENERGY. |
| US7080504B2 (en) * | 2004-07-23 | 2006-07-25 | Northrop Grumman Corporation | Laser augmented turbojet propulsion system |
-
2006
- 2006-12-06 CN CNB2006101648106A patent/CN100519343C/en not_active Expired - Fee Related
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102390547A (en) * | 2011-10-08 | 2012-03-28 | 中国人民解放军国防科学技术大学 | Laser propulsion aircraft with vector nozzle |
| CN105197258A (en) * | 2015-09-02 | 2015-12-30 | 覃政 | Light pressure power system |
| CN107401489A (en) * | 2017-08-18 | 2017-11-28 | 张雄志 | A kind of engine that thrust is produced using laser |
| CN107672824A (en) * | 2017-09-30 | 2018-02-09 | 北华航天工业学院 | Optical-fiber laser self-propelled universe bareboat control system |
| CN108843461A (en) * | 2018-05-31 | 2018-11-20 | 上海新力动力设备研究所 | A kind of air flue middle solid micro-thruster |
| CN109131943A (en) * | 2018-08-08 | 2019-01-04 | 上海新力动力设备研究所 | Piston for laser chemistry joint propeller drives charge constitution |
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| Publication number | Publication date |
|---|---|
| CN100519343C (en) | 2009-07-29 |
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Granted publication date: 20090729 Termination date: 20101206 |