CN107672824A - Optical-fiber laser self-propelled universe bareboat control system - Google Patents
Optical-fiber laser self-propelled universe bareboat control system Download PDFInfo
- Publication number
- CN107672824A CN107672824A CN201710928031.7A CN201710928031A CN107672824A CN 107672824 A CN107672824 A CN 107672824A CN 201710928031 A CN201710928031 A CN 201710928031A CN 107672824 A CN107672824 A CN 107672824A
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- Prior art keywords
- laser
- control system
- optical
- bareboat
- fiber laser
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- 239000013307 optical fiber Substances 0.000 title claims abstract description 45
- 238000005507 spraying Methods 0.000 claims abstract description 9
- 238000012544 monitoring process Methods 0.000 claims abstract description 7
- 239000013078 crystal Substances 0.000 claims 1
- 239000007921 spray Substances 0.000 claims 1
- 238000005516 engineering process Methods 0.000 abstract description 13
- 239000000126 substance Substances 0.000 abstract description 5
- 239000000835 fiber Substances 0.000 description 16
- 238000013461 design Methods 0.000 description 14
- 238000002679 ablation Methods 0.000 description 7
- 238000011160 research Methods 0.000 description 6
- 238000005094 computer simulation Methods 0.000 description 4
- 239000003574 free electron Substances 0.000 description 4
- 238000011835 investigation Methods 0.000 description 4
- 239000003380 propellant Substances 0.000 description 4
- 239000007787 solid Substances 0.000 description 4
- 241000196324 Embryophyta Species 0.000 description 3
- 238000010168 coupling process Methods 0.000 description 3
- 238000005859 coupling reaction Methods 0.000 description 3
- 238000002474 experimental method Methods 0.000 description 3
- 238000004364 calculation method Methods 0.000 description 2
- 238000006243 chemical reaction Methods 0.000 description 2
- 238000002485 combustion reaction Methods 0.000 description 2
- 238000001816 cooling Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 239000000446 fuel Substances 0.000 description 2
- 230000029058 respiratory gaseous exchange Effects 0.000 description 2
- 241000931526 Acer campestre Species 0.000 description 1
- 238000013459 approach Methods 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 239000003795 chemical substances by application Substances 0.000 description 1
- 230000000052 comparative effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000000428 dust Substances 0.000 description 1
- 238000005265 energy consumption Methods 0.000 description 1
- 230000003631 expected effect Effects 0.000 description 1
- 230000010354 integration Effects 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 239000004449 solid propellant Substances 0.000 description 1
Classifications
-
- 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
- B64G1/24—Guiding or controlling apparatus, e.g. for attitude control
- B64G1/242—Orbits and trajectories
-
- 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
- B64G1/24—Guiding or controlling apparatus, e.g. for attitude control
- B64G1/244—Spacecraft control systems
- B64G1/245—Attitude control algorithms for spacecraft attitude control
-
- 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
- B64G1/409—Unconventional spacecraft propulsion systems
Abstract
Optical-fiber laser self-propelled universe bareboat control system belongs to new ideas space technology field, and the present invention relates to optical-fiber laser self-advancing device system and control system.In order to solve, conventional airships propulsion control system is extremely difficult to quick accurate control track and flight attitude, the present invention are applied in the control system of airship using the exact controllability of optical-fiber laser.Optical-fiber laser is applied in laser propulsion device, so as to substitute traditional chemical propulsion plant, in space electric energy is provided using solar energy sailboard, the watt level of laser is controlled by Laser emission control device, reacted in propulsion plant with special working medium, produce high temperature and high pressure gas to erupt away to produce power, the spraying device of diverse location is selected to realize quick adjustment by the track and posture of the airship of monitoring system Real-time Feedback.Principle is exactly to control the thrust size of each propulsion plant by controlling the size of laser power, so as to the flight path and posture of quick accurate control airship.
Description
Technical field
The invention belongs to new ideas space technology field, and the present invention relates to optical-fiber laser self-advancing device system and control to be
System.
Background technology
Spacecraft control is the important component of aerospace engineering, and its longevity of service, required precision is high, and environment is special
Very, and by conditions such as weight and energy expenditures limited, the control system with carrier rocket in system architecture has bigger difference.
Spacecraft Control includes gesture stability and orbits controlling, it is necessary to which airship has very high control in deep space exploration
Precision, space flight track initial velocity and direction slightly error, very large deviation will be produced when reaching home.Such as：To Mars
The spacecraft of landing is at the end of initial guidance, if velocity error is 0.3m/s, deflection error is 1 ', then to the range deviation of Mars
Will be up to 20,000 kms, equivalent to three times of Mars diameter., can be by various and airship is departing from after carrier rocket does inertia motion
The effect of celestial body gravitation, these gravitation can make the flight path of spacecraft bend.This just needs airship to carry out track and fly
The accurate adjustment of row posture, therefore spaceborne each small-sized thrust propeller is by spraying the reaction force of gas come the side of adjustment
To and posture.These propellers support combustion reaction generally by using two distinct types of chemical substance, produce heat
Exhaust, so as to produce thrust.Both chemical substances just constitute the thing that expert is referred to as propellant.Regardless of whether it is that liquid pushes away
Enter agent or solid propellant, be all very difficult to accomplish accurately to control when the combustion chamber of propeller chemically reacts, so production
Raw thrust may not just reach expected effect, be difficult to posture and the track of accurate control airship yet.
1969, the R.L.Geisler in USAF rocket propulsion laboratory (AFRPL), which is proposed, utilized laser assisted fire
The concept that arrow promotes, its general principle are that remote laser energy is imported into propeller, steeply rise propellant Temperature of Working, shape
Ejected into high temperature and high pressure gas or plasma from jet pipe, so as to produce thrust.
In present laser Push Technology research, generally use YAG solid state lasers (1.06 μm), free electron laser and
TEA pulses CO2(10.6 μm) of laser promotes light source to be tested as light.
YAG solid state lasers repetition rate and peak power can be very high, but for laser threat warner, its single pulse energy
Amount and mean power are relatively low.Although free electron laser possesses the advantages that Wavelength tunable, power and efficiency high, but pulse
Energy is small (J or mJ magnitudes), and mean power is low, and repetition rate is relatively low, it is impossible to reaches the requirement of remote laser propulsion.
TEA pulses CO2Laser shortcoming is also quite obvious
(1)CO2Laser output laser-quality is poor, and Beam waist radius and far-field divergence angle are larger, causes to flying
The difficult increase of row device tracking aiming, the laser power density in fuel cavity can only be increased by improving power output.
(2) electro-optical efficiency is low, and only 15% or so, energy consumption is huge.
(3)CO2Optical Maser System caloric value is larger, it is necessary to corresponding cooling device, due to the presence of fuel factor so that be
The stability of system is bad.
(4)CO2Laser volume is relatively bulky, is only used for continental rise, is more suitable for Trend of Laser Propulsion Technology thus, it is desirable to find
It is required that LASER Light Source substitute CO2 lasers.
The content of the invention
1st, patent purpose
It is difficult to be rapidly achieved accurate control track and flight attitude, the present invention to solve conventional airships propulsion control system
Applied to using the exact controllability of optical-fiber laser in the control system of airship.
2nd, technical solution
The present invention replaces CO2 laser using optical-fiber laser, because optical-fiber laser beam quality is high, has very high work(
Rate and power density, laboratory have reached 100kW output level；High conversion efficiency and easily cool down, optical fiber laser one
As 70%~80% pump energy into optical fiber can be converted to output laser.Elongated optical fiber has very high surface
Product/volume ratio, caused heat are distributed along fiber lengths, and so quickly, loss is small, even if the optical-fiber laser of multikilowatt for radiating
Device also only needs simple and reliable air-cooled；Optical fiber laser has splendid stability, reliability, can be in dust, HI high impact, Gao Zhen
Worked under the various rugged environments such as dynamic, high-temperature, it is easy to maintenance；Pump diode long lifespan, can continuously or pulse operating, energy
Obtain broad tuning scope, good monochromaticjty and high stability.Can continuously or pulse output, output waveform can be pre- with program
If output frequency 0-5kHz continuously adjustabes；Because optical fiber has fabulous soft around property, laser can be designed to quite compact spirit
Living, compact appearance small volume, is easy to the system integration, and the ratio of performance to price is high.
Therefore optical-fiber laser is applied in laser propulsion device, so as to substitute traditional chemical propulsion plant, in space
Electric energy is provided using solar energy sailboard, the watt level of laser is controlled by Laser emission control device, in propulsion plant
In with special working medium react, produce high temperature and high pressure gas erupt away generation power, pass through the bareboat of monitoring system Real-time Feedback
Track and posture select the spraying device of diverse location to realize quick adjustment.Principle is exactly by controlling laser power
Size controls the thrust size of each propulsion plant, so as to quick accurate control bareboat (airship is defined as into bareboat herein)
Flight path and posture.
3rd, technique effect and advantage
YAG solid state lasers (1.06 μm), free-electron laser can solve the problem that using optical-fiber laser self-propelled control system
Device and TEA pulses CO2Various problems of the laser (10.6 μm) as laser threat warner light source, such as the list of YAG solid state lasers
Pulse energy and mean power are relatively low；Free electron single pulse energy is small (J or mJ magnitudes), and mean power is low, repetition rate
It is relatively low, it is impossible to reach the requirement of remote laser propulsion；CO2The weak point of laser is even more a lot.Swash first with optical fiber
Light propulsion controlling system can obtain a very big thrust, because laser threat warner can produce 10000~20000K high temperature,
Propellant molecular mass is small, specific thrust up to 20000N.s/Kg, this far beyond thrust caused by traditional chemical propulsion system,
It is enough to make universe bareboat reach a very high speed.Bareboat has responsible adjustment track and the posture of many again on this basis
Secondary propulsion system, because the power of optical-fiber laser has fabulous controllability, the thrust of a linear ratio can be produced,
The track and posture of bareboat will be accurately adjusted very much, such bareboat does not deviate by track again while high-speed flight is kept,
Explore and have great significance for deep space.
Brief description of the drawings
Fig. 1 is optical-fiber laser self-propelled universe bareboat control system frame diagram
Shown in figure：1st, solar energy sailboard；2nd, generating laser control device；3rd, special working medium；4th, master control system；5th, supervise
Examining system；6th, spraying device.
Embodiment
(1) round-based fiber optics laser device laser Push Technology
1. theoretical research and the transmitting of software emulation round-based fiber optics laser beam and control system, realize that large-power optical fiber swashs
The control of light device power, output waveform, output pulse frequency；
2. design round-based fiber optics laser air conduction light path and tracking control system；
3. design round-based fiber optics laser fiber guiding control system；
4. design round-based fiber optics laser air conduction air-breathing mode Laser Thruster；
5. design round-based fiber optics laser fiber guiding air-breathing mode Laser Thruster；
6. design round-based fiber optics laser air conduction rocket ablative laser propulsion device；
7. design round-based fiber optics laser fiber guiding rocket ablative laser propulsion device；
8. theoretical calculation air conducts and Laser Thruster under air-breathing mode during fiber guides and rocket Investigation of Ablation Mode
Specific impulse, the parameter such as momentum-coupling coefficient；
9. Computer Simulation air conducts and laser threat warner under air-breathing mode during fiber guides and rocket Investigation of Ablation Mode
Experiment；
10. round-based fiber optics laser device laser Push Technology application study.
(2) space-based optical fiber laser Trend of Laser Propulsion Technology
1. theoretical research space-based optical fiber laser platform and Laser emission and control system；
2. design space-based optical fiber laser light path and tracking control system；
3. design space-based optical fiber laser fiber guides control system；
4. design space-based optical fiber laser laser threat warner rocket ablation propeller；
5. the specific impulse of theoretical calculation space-based optical fiber laser laser threat warner rocket ablation propeller, momentum-coupling coefficient etc. are joined
Number；
6. Computer Simulation space-based optical fiber laser laser threat warner rocket ablation propulsion trial；
7. space-based optical fiber laser Trend of Laser Propulsion Technology application study.
(3) bareboat optical fiber laser self-propelled technology
1. optical fiber laser laser self-propelled bareboat designs；
2. optical fiber laser rocket ablative laser self-propelled impeller design；
3. optical fiber laser rocket ablative laser self-propelled laser energy demand prediction is studied；
4. optical fiber laser rocket ablative laser self-propelled propeller operation material is studied；
5. optical fiber laser rocket ablative laser self-propelled propeller control system research；
6. bareboat optical fiber laser rocket ablative laser self-propelled computer simulation experiment；
7. bareboat optical fiber laser self-propelled technology application study.
(4) optical fiber laser Laser Thruster comparison of design is studied
The characteristics of optical fiber laser Laser Thruster designs under various patterns and application environment are studied, by contrasting its propulsion
Performance, further optimize the design of optical fiber laser Laser Thruster, make aircraft in the presence of same power laser beam, produce
Specific impulse as high as possible and momentum-coupling coefficient.Aircraft cooling and propeller high temperature resistant problem-solving approach are explored, research is big
The outer energy of lasers of gas-bearing formation and Propellant Supply problem.
(5) air breathing mode and rocket Investigation of Ablation Mode Push Technology comparative study during optical fiber laser laser threat warner
By Computer Simulation and experiment, during research and contrast optical fiber laser laser threat warner air breathing mode and
The characteristics of rocket Investigation of Ablation Mode Push Technology, inquire into specific engineer applied.
Claims (2)
1. optical-fiber laser self-propelled universe bareboat control system, by master control system, monitoring system, solar energy sailboard, Laser emission
Control device, special working medium, spraying device are formed.It is characterized in that solar energy sailboard energizes, master control system controls with Laser emission
Device, monitoring system two-way communication, monitoring system again with spraying device two-way communication.
2. optical-fiber laser self-propelled universe bareboat control system according to claim 1, it is characterised in that：Described master control system
System is responsible for the operating of the whole bareboat of control, can control solar energy sailboard, Laser emission control device and monitoring system.Solar energy
Windsurfing provides energy, and Laser emission control device controls the watt level of laser, then heats special working medium and produces HTHP
Gas sprays from spraying device, produces thrust, the track of bareboat and posture are controlled by selecting the spraying device of diverse location.
Monitoring system can monitor space environment, the track of bareboat and posture and multichannel spraying device, real with master control system two-way communication
Now quick regulation and control.Special working medium is a kind of pollution-free crystal met high temperature and can gasify and expand rapidly.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710928031.7A CN107672824A (en) | 2017-09-30 | 2017-09-30 | Optical-fiber laser self-propelled universe bareboat control system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710928031.7A CN107672824A (en) | 2017-09-30 | 2017-09-30 | Optical-fiber laser self-propelled universe bareboat control system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107672824A true CN107672824A (en) | 2018-02-09 |
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| CN201710928031.7A Pending CN107672824A (en) | 2017-09-30 | 2017-09-30 | Optical-fiber laser self-propelled universe bareboat control system |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111120233A (en) * | 2019-12-10 | 2020-05-08 | 南京理工大学 | Optical fiber self-consumption type laser micro-propulsion system |
| CN112632709A (en) * | 2020-12-31 | 2021-04-09 | 北华航天工业学院 | Continuous laser thruster working medium analysis method based on FLUENT simulation |
| CN112651083A (en) * | 2020-12-31 | 2021-04-13 | 北华航天工业学院 | Detonation laser thruster analysis method based on FLUENT simulation |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2004270552A (en) * | 2003-03-07 | 2004-09-30 | National Aerospace Laboratory Of Japan | Solar heat propulsion system and used satellite self-disposal method using the same |
| CN1970389A (en) * | 2006-12-06 | 2007-05-30 | 中国科学技术大学 | Split type omnibearing take-over laser booster |
| CN101055215A (en) * | 2006-04-14 | 2007-10-17 | 中国科学院力学研究所 | Method and device for measuring jet thrust |
| CN101737201A (en) * | 2008-11-04 | 2010-06-16 | 中国科学院物理研究所 | Laser propulsion device |
| CN106545478A (en) * | 2016-11-02 | 2017-03-29 | 中国运载火箭技术研究院 | A kind of space junk energy conversion device and method based on laser threat warner |
| CN106800097A (en) * | 2016-12-12 | 2017-06-06 | 扬州大学 | A kind of space flight self start type propeller |
-
2017
- 2017-09-30 CN CN201710928031.7A patent/CN107672824A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2004270552A (en) * | 2003-03-07 | 2004-09-30 | National Aerospace Laboratory Of Japan | Solar heat propulsion system and used satellite self-disposal method using the same |
| CN101055215A (en) * | 2006-04-14 | 2007-10-17 | 中国科学院力学研究所 | Method and device for measuring jet thrust |
| CN1970389A (en) * | 2006-12-06 | 2007-05-30 | 中国科学技术大学 | Split type omnibearing take-over laser booster |
| CN101737201A (en) * | 2008-11-04 | 2010-06-16 | 中国科学院物理研究所 | Laser propulsion device |
| CN106545478A (en) * | 2016-11-02 | 2017-03-29 | 中国运载火箭技术研究院 | A kind of space junk energy conversion device and method based on laser threat warner |
| CN106800097A (en) * | 2016-12-12 | 2017-06-06 | 扬州大学 | A kind of space flight self start type propeller |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111120233A (en) * | 2019-12-10 | 2020-05-08 | 南京理工大学 | Optical fiber self-consumption type laser micro-propulsion system |
| CN112632709A (en) * | 2020-12-31 | 2021-04-09 | 北华航天工业学院 | Continuous laser thruster working medium analysis method based on FLUENT simulation |
| CN112651083A (en) * | 2020-12-31 | 2021-04-13 | 北华航天工业学院 | Detonation laser thruster analysis method based on FLUENT simulation |
| CN112632709B (en) * | 2020-12-31 | 2023-08-04 | 北华航天工业学院 | Continuous laser thruster working medium analysis method based on FLUENT simulation |
| CN112651083B (en) * | 2020-12-31 | 2023-08-11 | 北华航天工业学院 | Knock laser thruster analysis method based on FLUENT simulation |
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Application publication date: 20180209 |