CN105015795A - Airplane design method and scheme - Google Patents
Airplane design method and scheme Download PDFInfo
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Abstract
The invention discloses a scheme of a fighter comprehensively exceeding F22 and T50 and leading F22 and T50 by half generation to one generation. The fighter has such advantages as ultrahigh maneuverability, excellent invisible aerodynamic configuration, hypersonic speed and short-distance taking-off and landing capacity. Such methods as a large longitudinal windward side design principle, a stable triangle, a rapidity problem research and a fuselage side slash layout provide new thoughts for the airplane design. The research of a hypersonic speed aircraft involved in the rapidity problem research influences the sixth generation of fighters, the anti-missile of the intercontinental missile and aerospace engineering. A new aerodynamic simulation model made through research and development via the quantum statistics physics and a method for breaking through thermal barriers by a front edge are two keys for opening the door of hypersonic flight.
Description
The present invention relates to Airplane design method and scheme.
One surmounts F22 and T50 comprehensively, and its half generation leading is to the fighter plane scheme of a generation.This fighter plane has the advantages such as ultrahigh maneuverability, outstanding stealthy aerodynamic configuration, hypersonic speed and short take-off and landing ability.The method such as " large longitudinal windward side principle of design ", " stable triangle ", " research of rapidity problem " and " fuselage skew back line layout " is that the design of aircraft provides new thinking.The development hypersonic vehicle related in " research of rapidity problem " have influence on the 6th generation fighter plane, intercontinental missile anti-ballistic and space engineering etc.And by the new aerodynamic force realistic model of quantum Statistical Physics research and development and the method with forward position edge strip breakthrough thermal boundary, be two crucial keys of the door opening hypersonic flight.
1. large longitudinal windward side
Longitudinal windward side refers to the entire area of fighter plane birds-eye view.Effective longitudinal windward side is after the different affecting factors considering tailplane and canard, through the longitudinal windward side area revised.
The sharply turning flight of 1.1 fighter planes
Sharply turning flight is an importance of fighter plane manoevreability.The sharply turning flight of fighter plane is that the velocity vector of turning when starting is transformed into the velocity vector finally turned to.
The sharply turning flight of fighter plane is broadly divided into first half term and the second half.First half term: fighter plane utilizes effective longitudinal windward side to carry out the conversion of brakeing during cornereing and velocity vector.Be less than or equal to after 45 ° or fuselage turn over the condition of 90 ° when meeting fuselage and the angle finally to turn to, driving engine starts progressively to participate in the work into sharply turning.Now sharply turning progresses into the second half by first half term.The second half: mainly participate in brakeing during cornereing with driving engine and accelerate at final steering direction.Comprised finally turning to and participated in sharply turning with driving engine.
The energy source that the behavior of structure of 1.2 fighter planes and sharply turning fly
Behavior of structure: the constructional feature of fighter plane determines its longitudinal anti-overload ability comparatively by force, and side direction is taken second place, and top and bottom are more weak.
Energy source one: the larger kinetic energy of inceptive direction when sharply turning starts.This kinetic energy changes along with the process of turning, and the initial stage is very large, and the speed along with inceptive direction reduces and declines fast.
Energy source two: the driving engine of fighter plane.Feature: thrust is lasting, controlled.
The new sharply turning method trilogy of 1.3 fighter planes
The first step: with rear flank vector spray manipulation fighter plane along fuselage datum rolling, fix the position after rolling with aileron; Windward side is increased with control rudder face etc.Large longitudinal windward side is utilized to carry out the conversion of brakeing during cornereing and velocity vector.
Second step: the moment of rotation reducing rear flank vector spray, controls revolution fuselage with rear flank vector spray and aileron and reduces windward side; At side direction position or nearside to position, utilize fighter plane itself to produce and the fuselage side rotary torque controlled by rear flank vector spray, realize the quick steering of fighter plane.This process has a protection mechanism, prevents from turning over side direction position.In addition, the angle of inclination of rear flank vector spray and jet amount can both adjust rapidly as required.
3rd step: participate in brakeing during cornereing with driving engine and accelerate at final steering direction.Comprise: fuselage turns over and finally turns to, do brakeing during cornereing with driving engine and accelerate at final steering direction.
The describing in detail of process above: i. rear flank vector spray rolling fuselage.Ii. the fuselage positions after rolling is stablized with aileron.Now, the opposite rotational square that aileron and rear flank vector spray produce cancels each other.Iii. control rudder face etc. by level and increase windward side, utilize effective longitudinal windward side to carry out the conversion of brakeing during cornereing and velocity vector.The first half term of sharply turning starts in the process.Iv reduces the moment of rotation of rear flank vector spray, and revolution fuselage reduces windward side; Control as required at lateral position or nearly lateral position.V. the side rotary torque of aircraft itself and the side direction moment of rear flank vector spray is utilized, with the quick steering of rear flank vector spray control realization fuselage.This process has a protection mechanism, prevents fuselage from turning over side direction position.Wherein, the angle of inclination of rear flank vector spray and jet amount are all constantly doing quick adjusting as required; Adjustment excessive gas out, is synchronously discharged by the vector spray in dead aft.Vi. the diverse location residing for aircraft, driving engine adds high thrust gradually.Being less than or equal to after 45 ° or fuselage turn over the condition of 90 ° when meeting fuselage and the angle finally to turn to, turning and entering the second half.Vii., after fuselage turns over final steering position, driving engine also participates in into brakeing during cornereing and accelerates at final steering direction.Viii. align course, complete sharply turning process.
The principle of design of 1.4 large longitudinal windward sides
Can reach a conclusion from analysis above: substantially do not reducing maximum operating overload, when not increasing housing construction weight, by rational deployment, selection material, optimizing structure design, increase effective longitudinal windward side area of unit weight as much as possible.
Fighter plane adopt the design of large longitudinal windward side mainly because: initial kinetic energy when the large longitudinal windward side of i. can utilize fighter plane sharply turning to start better.More effectively reduce the speed of inceptive direction.Ii. large longitudinal windward side and new sharply turning method presented hereinbefore all meet the behavior of structure of fighter plane.Iii. large longitudinal windward side can not also affect finally to turn to and participate in sharply turning with driving engine.
The new sharply turning method of these place's promotion, the top and bottom of having evaded with fighter plane is the weakest directly overturn, and reduce the requirement to materials and structures.Its side direction quick steering method, also extends for jet pipe participates in sharply turning the scope played a role.
During sharply turning, large longitudinal windward side also means the same braking of generation and velocity vector conversion effect, and the angle windward of fuselage is less.From then on angle also can be regarded as, reduces the requirement to materials and structures.
I thinks that the quality of fighter plane manoevreability determines primarily of two indexs: effective longitudinal windward side area of i. unit weight; Ii. thrust-weight ratio.Effective longitudinal windward side area of unit weight determines the efficiency of sharply turning first half term.The thrust-weight ratio of fighter plane determines efficiency and accelerating ability, the climb rate of sharply turning the second half.Evaluate the manoevreability of fighter plane, effective longitudinal windward side area and empty machine thrust-weight ratio two indexs of unit empty weight should be used.
In addition, if the demand that control system can not meet sharply turning and high maneuver also can affect the manoevreability of fighter plane.The performance of fighter plane in actual combat is also relevant with radar and avionics system.Aviator and air weapon are also affect one of factor that its battlefield shows.
2. stable triangle
2.1 triangle maximum coursekeeping angle computing formula
Or:
That is:
In formula: β is maximum coursekeeping angle, W is the leg-of-mutton rear length of side, and d is the distance of center of gravity to back.
2.2 stable triangle with without vertical tail aircraft
The center of gravity of fighter jet more rearward.After eliminating vertical tail, the lateral aerodynamics square front portion of fighter plane is greater than rear portion.For the ease of controlling, aerodynamic configuration is needed to have certain course stability.The stable triangle that triangle fuselage etc. are formed can for providing the course stability of needs without vertical tail aircraft.
3. the research of rapidity problem
3.1 hypersonic speed
Hypersonic speed refers to aircraft in atmospheric envelope by the speed of carrying out between the velocity of sound of more than 5 times to the first cosmic velocity flying.The realization of hypersonic vehicle has two significances:
I. the realization of hypersonic vehicle means the beginning in rear nuclear weapon epoch.Reason defends anti-ballistic platform with hypersonic vehicle as the face of strategic missile, is a kind of economic, efficient method.Because it can realize the defence cost of strategic missile lower than attack cost.And multiple goal, multiple batches of interception can be realized and have very high interception probability.Making the overall arrangement for of NMD will become possibility with this understanding.And the thought having a large amount of offensive strategies nuclear missile is also nonsensical by what become.Do not fight and the reason of the soldier of people in the wrong can make nuclear superpowers abandon having in a large number the practice of nuclear weapon.Therefore the world also will enter the rear nuclear weapon epoch.
Ii. the realization of hypersonic vehicle greatly can reduce the cost of space engineering.The basic reason of the space shuttle failure that the U.S. is old is that it does hypersonic flight institute extremely with subsonic flight device.Hypersonic vehicle is used for space engineering, and the single-stage or the one-level that are expected to realize spacecraft are partly entered the orbit; It can also realize horizontal take-off, level landing, becomes real space shuttle.
3.2 flexible gas and plasticity gas
The speed of aircraft there will be sound barrier close to during velocity of sound.In order to overcome sound barrier, Richard Whitcomb proposes famous area rule.The area rule reflection of Richard Whitcomb be the elastic behavior of air.The Applicable scope of this area rule is flexible gas.When the speed of aircraft is approximately 2.5 times of velocities of sound, there will be thermal boundary.Now, air is very large relative to the ratio of plasticity aircraft.For the aircraft carrying out hypersonic flight with more than 5 times velocities of sound, air almost presents plastic properties completely.The area rule of Richard Whitcomb is not suitable for plasticity gas.
The thinking of 3.3 flying saucer problems
Based on the understanding to air characteristics, I thinks that disc-shaped flying craft is the ideal flight device carrying out hypersonic flight.Reason is that flying saucer mainly flies in plasticity gas.The aircraft flown in plasticity gas, mainly flies in the mode of cutting, separation air.Be different from the aircraft flown in flexible gas, mainly fly in the mode extruding air.
Use disc-shaped flying craft flies, and must solve its dynamical problem.If electric field force exists, it is perhaps the most applicable power of disc-shaped flying craft.Outburst motivation of shaking also is that a kind of power of disc-shaped flying craft under prior art level and cognitive condition is selected.
Disc-shaped flying craft is the ideal flight device carrying out the flight of empty sky.Disc-shaped flying craft returns ground use better than space shuttle from the outer space, and cheap, simple, low to material requirements.Disc-shaped flying craft is sent to enter outer space inconvenience with rocket.
3.4 aerodynamic force realistic models
The aerodynamic force realistic model software generally used now is set up based on fluid mechanics.When simulating hypersonic flight, this model has larger error.According to the needs of in-depth study hypersonic flight rule and the needs of design hypersonic vehicle, suggestion: based on quantum statistics physics, new aerodynamic force realistic model is researched and developed in organizational strength.
With the new aerodynamic force realistic model of quantum Statistical Physics research and development be research hypersonic flight rule, design hypersonic vehicle, design punching press and aloof driving engine, design hypersonic speed cruise missile etc. in the urgent need to instrument.Researching and developing new aerodynamic force realistic model is also realize that above-mentioned target is saved most, effective, high-caliber convenient way.
3.5 forward position edge strips break through thermal boundary conception
For carrying out hypersonic flight, first need to solve thermal boundary problem.Suggestion: break through thermal boundary with forward position edge strip.When thermal boundary occurs, the front end first heat-dissipating of forward position edge strip.And there is the refrigeration mechanism be directly proportional to speed the side of this forward position edge strip.This refrigeration mechanism can reduce the temperature of forward position edge strip.The triangle fuselage etc. of fighter plane is also placed in its wake flow by forward position edge strip.Play protection body, reduce the effect that body heats up.In addition, when the little high-speed flight of angle windward, forward position edge strip has the effect reducing windage.During the large flight of angle windward, the eddy effect that forward position edge strip produces, in the upper surface of lifting body fuselage, also has the effect increasing lift.
Forward position edge strip is the best method of known breakthrough thermal boundary at present.
3.6 hypersonic 6th generation fighter plane
This programme fighter plane has taken into full account the characteristic of flexible gas and plasticity gas.Both with respect to its flight in flexible gas, have also contemplated that its flight in plasticity gas.This fighter plane has low windage aerodynamic configuration, and has reserved space for its hypersonic flight, also breaks through thermal boundary for its is cheap and prepares.Based on the understanding to sound barrier mechanism, the research to air characteristics, based on reasons such as the Drag reduction devices of forward position edge strip and the employings of other aggregate measures, this fighter plane is had outstanding low windage aerodynamic configuration and transonic, hyprsonic and hypersonic speed ability.This programme fighter plane be the 6th generation fighter plane.6th generation fighter plane maximum feature be hypersonic speed.
4. fuselage skew back line layout
4.1 fuselage skew back lines
Fuselage skew back line is a straight line low early and high after in fuselage side.Canard and host wing are arranged on this oblique line.Meanwhile, it is also the demarcation line of triangle lifting body fuselage top and the bottom.
The benefit of employing fuselage skew back line layout is: it can coordinate and take into account the demand of each side such as wing, stable triangle lifting body fuselage, the aviator visual field, top air inlet road and V-arrangement symmetrical inclined-plane wing well; Fuselage skew back line layout is conducive to the lift increasing lifting body fuselage; The host wing arranged under can making both sides is at grade in the plane vertical with aircraft front plan with canard respectively, has the host wing at the dihedral angle also to have transverse stabilization function; Fuselage skew back line layout is conducive to stabilizing increases centre of lift reach with speed and the head that produces raises up phenomenon.
If the angle of plane and horizontal surface that two bar fuselage skew back line is formed is ζ, be 2 η in the board a plane angle of head of the plane of two fuselage skew back lines formation, the dihedral angle of host wing is λ, then have:
ctgλ＝tgη·(1/sinζ)
When adopting fuselage skew back line layout, triangle lifting body fuselage is placed in its wake flow by forward position edge strip, canard and host wing, and thus the windage of body is less.Part host wing is also placed in its wake flow by canard, turn reduces some resistances.
During high-angle-of-attack flight, be in conplane forward position edge strip with the layout association of fuselage skew back line with canard and host wing, the eddy current to be produced at its edge imports the upper surface of triangle lifting body fuselage, thus can increase the lift of lift fuselage.
Fuselage skew back line is that design provides a kind of layout method being suitable for triangle fuselage.After wind tunnel experiment, if it is motor-driven to affect rolling because lateral stability spends greatly, ζ can be reduced.Otherwise, increase.
" large longitudinal windward side principle of design ", " stable triangle " and " research of rapidity problem " be three large core technologies herein." fuselage skew back line layout " is their a kind of implementing method of contact.And research and develop a hypersonic vehicle thing with national strategy aspect significance especially.In order to research and develop hypersonic vehicle author suggestion: i. researches and develops new aerodynamic force realistic model based on quantum statistics physics; Ii. thermal boundary is broken through with forward position edge strip.
5. fighter plane scheme
5.1 canard configuration
Intend adopting canard configuration.Canard configuration can increase effective longitudinal windward side area, improves manoevreability etc.
5.2 high speed canards
For adapting to the requirement of canard configuration and high-speed flight, need to adopt closely coupling high speed canard.
High speed canard divides movable and fixing two parts.Moving part is front, and fixed part is rear.Fixed part is less, is fixed on fuselage, plays a part fixing and supports.The feature of high speed canard is: i. it and host wing are arranged in same plane; Ii. closely coupling; Iii. sweepback angle is comparatively large, and this sweepback angle angle is more than or equal to the largest sweep of variable host wing; Iv. the connection mode that moving part presents large slot after opening with fixed part connects.
5.3 resistance rudders
Respectively establish in the outside of host wing one pair can the resistance rudder of opening and closing.
5.4 vertical tail
Adopt without vertical tail fighter plane scheme.
Cancelling the benefit of vertical tail is: expendable weight, improve stealth, reduce windage, be conducive to high-speed flight; Eliminate vertical tail and also mean the deuce to pay broken away from and brought to design effort because original lateral stability is machine-processed.
5.5 fuselage
Intend adopting stable triangle lifting body fuselage.
5.6 host wing
The fighter plane of this programme is intended adopting the variable host wing having the dihedral angle.The sweepforward taking off, when landing of this host wing, sweepback during high-speed flight.
5.7 inlet channel
The side inlet that employing is put.
5.8 driving engine
Employing can up and down controlling party to, have left and right controlling party to the vector engine of ability.
5.9 hypersonic speed driving engines
The driving engine of hypersonic plane can adopt liquid oxygen-kerosene Rocket Engines and punching press and aloof driving engine through integrated design and the combination engine researched and developed further.
5.10 forward position edge strip
Intend helping to break through thermal boundary with forward position edge strip.And realize the object of cooling, drag reduction, lift-rising.
5.11 the center of gravity of airplane
Known by the calculating of diabolo angle of stability: the center of gravity of aircraft is more forward, the stability of stable triangle is better.
5.12 short take-off and landing ability
Take off, variable host wing adopts sweepforward mode when landing.Short take-off and landing ability realizes primarily of following factors: the better lift of i. sweepforward host wing itself and lifting body fuselage etc.; Ii. sweepforward host wing and canard make centre of lift move forward, and therefore vector spray is had an opportunity directly to produce lift and helped to support rear body.
During short range landing, the air rudder of two rear flank vector sprays deflects down the jet-stream wind that about 45 ° form downward 90 °; The air rudder of two just rear vector sprays upward deflects the jet-stream wind that about 45 ° form upwards 90 °.Two " rear flank vector spray " forms aerial rear supported at three point with " centre of lift and two just rear vector sprays ".Two rear flank vector spray excessive gas that quick adjusting produces when controlling, are synchronously discharged by two just rear vector sprays.
Program fighter plane when low-speed operations, have enough lift, velocity of approach lower, relatively weak, the stability of effect also fine, therefore its landing distance is shorter.Take off and performance of landing all fine.This fighter plane has very-short-reach landing ability.
5.13 two dimensions, omnidirectional, the conception of low infrared signature vector spray
The conception of two fighter plane vector sprays.Each driving engine has two two-dimensional vector jet pipes: one towards dead aft, another is towards proceeds posterolateral.Two-dimensional vector jet pipe respectively has two pieces the baffle plate of opening and closing can adjust open area.In addition, it also has an outer cover to be responsible for the deflection up and down of tail gas stream, and mixing hot and cold air, minimizing infrared signature.The adjustment of this fighter plane left and right directions and control, can with two driving engines separately rear flank towards two-dimensional vector jet pipe participate in.
In actual enforcement, if the resistance of this air rudder scheme is comparatively large, also can consider to adopt universal-joint scheme.
The supercirculation that flat two-dimensional vector jet pipe causes can also increase the lift of lifting body fuselage, increases pitch control moment.This vector spray also helps the backward resistance reducing fuselage.
6. conclusion
6.1 manoevreability
This fighter plane employs the motor-driven method of aforesaid new sharply turning, adopts and expands the motor-driven method finally turned to.The empty machine thrust-weight ratio controlling this fighter plane during design is greater than F22, T50, and the empty machine effective longitudinal windward side area controlling unit weight is greater than F22, T50.Closely coupling high speed canard in low windage aerodynamic configuration, same plane, variable host wing, canard can both improve manoevreability effectively without vertical tail layout, resistance rudder, vector spray, control technology etc.This fighter plane has ultrahigh maneuverability, and manoevreability is more than F22, T50 etc.
6.2 stealth
Without the employing of the layout of vertical tail, natural blended wing-body, flat flap-type fuselage and top stealth inlet, the aerodynamic profile of program fighter plane is had good radar invisible performance.The use of low infrared signature vector spray, this fighter plane is had good infrared stealth performance.The stealth of this fighter plane aerodynamic configuration is more than F22, T50 etc.
6.3 rapidity
Based on the understanding to air characteristics, and the research to sound barrier, thermal boundary, program fighter plane is had good rapidity.This programme had both looked after its flight needs in flexible gas, again for space has been reserved in its flight in plasticity gas.
This fighter plane has outstanding subsonic, transonic, hyprsonic and hypersonic speed performance.The host wing of forward position edge strip Drag reduction devices, wide-angle sweepback, resistance when high speed canard and low windage aerodynamic configuration body etc. are reduced flight.Natural blended wing-body, flat fuselage etc. are also all favourable to high-speed flight.There is no vertical tail in addition.The aerodynamic configuration of this fighter plane has good rapidity.The rapidity of aerodynamic configuration is more than F22, T50 etc.
This programme both can use as superfighter scheme, also can be used as hypersonic speed fighter plane scheme.
6.4 short take-off and landings and vertical takeoff and landing performance
The landing distance of this programme fighter plane is shorter.There is short take-off and landing ability.Two
Only need do a little change, program fighter plane also can become vertical take off and landing fighter.
6.5 other favorable factors
Magazine and fuel tank in the machine that the convenient design of triangle fuselage is large.
Low windage aerodynamic configuration, large fuel tank space, make this fighter plane be provided with larger voyage and combat radius.
Advanced aerodynamic configuration ensure that this fighter plane has good stability when low speed high-angle-of-attack flight.The employing of the vector spray good low speed gesture stability ability that made again it have.This fighter plane of the large angle windward flight exceeding common fighter plane, can make various advanced flight maneuver, also not have the worry of tailspin simultaneously.
The high stability of this fighter plane and High-speed Control ability are also very outstanding.
Without vertical tail, triangle flat fuselage, shorter top air inlet road, less host wing and canard, make the structural weight of this fighter plane light compared with general fighter plane.
This pair sends out fighter plane certain modification, is well suited for doing aircraft carrier.
6.6 other
Method used in literary composition can be conveniently used in unmanned plane.The drag reduction of stable triangle, fuselage skew back line layout, forward position edge strip with overcome the technology such as sound barrier, thermal boundary and be also applicable to bomber, airliner and transport plane etc.
The design of space shuttle also can use for reference the principle described in literary composition and method.
6.7 conclusion
If use hypersonic speed driving engine this programme to produce to have hypersonic speed ability the 6th generation fighter plane.Use existing fanjet this programme can produce five generation half fighter plane.
Advanced aerodynamic configuration, advanced control technology the fighter plane in scheme is provided with superelevation is motor-driven, stealthy, hypersonic speed and short take-off and landing ability etc.This programme fighter plane is classic fighter plane scheme in the world today.In its leading F22, T50 half generation, is to a generation.
In addition, develop hypersonic vehicle have influence on the 6th generation fighter plane, intercontinental missile anti-ballistic and space engineering.And by the new aerodynamic force realistic model of quantum Statistical Physics exploitation and the method with forward position edge strip breakthrough thermal boundary, be two crucial keys of the door opening hypersonic flight.Had this two keys, hypersonic 6th generation fighter plane realization will point the day and await for it.
Accompanying drawing illustrates:
Fig. 1 is fighter plane schematic front view.
Fig. 2 is fighter plane schematic top plan view.
Fig. 3 is fighter plane schematic side view.
Fig. 4 is vector spray schematic diagram.
Claims (2)
1. forward position edge strip is characterized in that, forward position edge strip is a kind of banded heat-conducting plate, and this banded heat-conducting plate is arranged on the windward side of aircraft; When the windward side heat-dissipating of heat-conducting plate, heat-conducting plate can reduce the temperature of windward side.
2. fuselage skew back line is characterized in that, fuselage skew back line is that this straight line is low early and high after at the monosymmetric straight line of airframe, is in canard in same plane and host wing is arranged on this oblique line; Fuselage skew back line is characterized in that, the canard of both sides respectively can be vertical with the front plan of aircraft with the plane at host wing place.
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| CN105857575A (en) * | 2016-04-11 | 2016-08-17 | 中国空气动力研究与发展中心计算空气动力研究所 | Control surface suitable for course autostability and control of high-aspect-ratio flying wing arranging airplane |
| CN106741850A (en) * | 2016-11-17 | 2017-05-31 | 北京临近空间飞行器系统工程研究所 | A kind of deformable lateral stabilization suitable for high-speed aircraft |
| CN106741850B (en) * | 2016-11-17 | 2019-01-15 | 北京临近空间飞行器系统工程研究所 | A kind of deformable lateral stabilization suitable for high-speed aircraft |
| CN108190005A (en) * | 2016-12-08 | 2018-06-22 | 中国航空工业集团公司哈尔滨空气动力研究所 | A kind of aerofoil fusion type edge strip |
| CN109614644A (en) * | 2018-11-02 | 2019-04-12 | 中国航空工业集团公司西安飞机设计研究所 | A kind of Externally Blown Flap airplane power-boosting effect evaluation method |
| CN109614644B (en) * | 2018-11-02 | 2023-03-14 | 中国航空工业集团公司西安飞机设计研究所 | Method for evaluating power lift-increasing effect of external blowing type flap layout airplane |
| CN109625240A (en) * | 2018-11-23 | 2019-04-16 | 中国航空工业集团公司沈阳飞机设计研究所 | Weaken the apparatus and system of flying wing layout plane pitching angle moment nonlinearity |
| CN110348081A (en) * | 2019-06-26 | 2019-10-18 | 南京航空航天大学 | Based on the fighter plane HAOA characteristics analysis method up to balance collection |
| CN113335499A (en) * | 2021-06-01 | 2021-09-03 | 中国航空工业集团公司沈阳飞机设计研究所 | High-mobility unmanned aerial vehicle based on fixed fire alarm auxiliary power |
| CN113335499B (en) * | 2021-06-01 | 2024-05-24 | 中国航空工业集团公司沈阳飞机设计研究所 | High-mobility unmanned aerial vehicle based on solid rocket auxiliary power |
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