CN106081050A - Integration High Altitude UAV is beaten in detecing of a kind of variable flying state - Google Patents
Integration High Altitude UAV is beaten in detecing of a kind of variable flying state Download PDFInfo
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- CN106081050A CN106081050A CN201610530935.XA CN201610530935A CN106081050A CN 106081050 A CN106081050 A CN 106081050A CN 201610530935 A CN201610530935 A CN 201610530935A CN 106081050 A CN106081050 A CN 106081050A
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- 230000010354 integration Effects 0.000 title claims abstract description 19
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/0009—Aerodynamic aspects
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/38—Constructions adapted to reduce effects of aerodynamic or other external heating
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C17/00—Aircraft stabilisation not otherwise provided for
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/10—Shape of wings
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/40—Arrangements for mounting power plants in aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/25—Fixed-wing aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U20/00—Constructional aspects of UAVs
- B64U20/10—Constructional aspects of UAVs for stealth, e.g. reduction of cross-section detectable by radars
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/20—Rotors; Rotor supports
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C2001/0045—Fuselages characterised by special shapes
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U2101/00—UAVs specially adapted for particular uses or applications
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- Aviation & Aerospace Engineering (AREA)
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Abstract
The invention discloses detecing of a kind of variable flying state and beat integration High Altitude UAV, including body and dynamical system；Body uses blended wing-body layout, and body is mutually spliced to form a rhomboid aerodynamic configuration of class by two two-way dalta wings；Block upper surface is in protruding streamlined, and body lower surface is smooth flat.Two isosceles triangles equal sized by two two-way dalta wings, the base of two two-way dalta wings is mutually spliced；Dynamical system is arranged on the stitching portion of body, and dynamical system includes power set and lift unit；Power set, for realizing the conversion between supersonic flight state and subsonic flight state；Lift unit, the lift needed for providing body to rise.The present invention can realize the conversion of subsonic and sapersonic velocities state of flight, there is high maneuverability, advantage that ceiling altitude is high, it is possible to come into operation as a unmanned plane with lasting deterrent force and operational potential.
Description
Technical field
The present invention relates to spacecraft technical field, a kind of variable flying state detect beat integration high-altitude without
Man-machine.
Background technology
Unmanned plane is that one can carry and throw in fatal and nonlethal weapon, implements attack and had information to enemy
The unmanned battle platform of the tasks such as collection, reconnaissance and surveillance and electronic interferences.Man-machine compared to having, its fuselage is more easily done hidden
Body, is also easier to use advanced aerodynamic shape, is easier to use the tactics such as evasive maneuvering and surprise attack, existence in operation
Ability is high, is not limited by physiological limit and the psychology of people due to it again, and its flight envelope can greatly extend, thus have have people without
The lasting deterrent force of method realization and operational potential.
Since " unmanned plane " that the seventies in last century proposes for fighting, various countries competitively develop.Development at unmanned plane
On, the U.S. is walked in foremost, has developed the UCAV(UCAV of air and naval force), Boeing has signed compacting ground
The first stage of the UCAV advanced technology demonstration plan of side's antiaircraft weapon, and put on display unmanned fight with in JIUYUE, 2000
Machine demonstration and verification machine X-45A, Mei Nuoge company endorsed an operation with advanced research projects agency of US Department of Defense (DAR-PA)
Evaluation item contract, continues as U.S. army's associating unmanned combat system (J-UCAS) demonstration plan development X-47B UCAV.English
State uses UCAV by considering in the future attacks aircraft system (FOAS) being on active service at 2018-2020 or has people/nothing
The probability of people's aircraft shuffling system.France is considering control machine that fitful wind aircraft conversion is UCAV.India also exists
Development unmanned plane.
From Vietnam War to the Gulf War, from Kosovo War to Afghan War, unmanned plane is pre-with its outstanding performance
Show its important function in operation and following irreplaceability.But, constantly update and contention at current air defense means
The aspects such as control of the air, unmanned plane baffles the most repeatedly, 1999, and in Balkan " lofty anvil action ", the U.S. is at least
Two frame unmanned planes are had to be destroyed by antiaircraft gun and guided missile；In the war in Iraq in 2003, frame Predator's unmanned plane is in no-fly zone
Overhead and frame Iraq meter Ge-25 jet plane are crashed after fighting.U.S. Predator UCAV speed per hour is 240 public affairs
In, ceiling altitude is 7.62 kms.Analyzing and understand, the UCAV ceiling altitude that main cause is current has
Limit, flight Mach number is relatively low, and mobility needs to be improved further.At present, the U.S. developing two UCAV design refer to
Being designated as, X-45A cruise Mach number is 0.8, and X-45B cruise Mach number is 0.85, and X-45A ceiling altitude is 12.2 kms.
X-47B design speed per hour is 800 kilometers, and ceiling altitude is 12 kms, it is seen that at maximum flying speed and ceiling altitude
Aspect improves a lot, but is still designed as subsonic flight state.
Even if it addition, the unmanned plane of certain model breaches the velocity of sound, even achieving hypersonic, but simply at design shape
Higher flying quality could be obtained under state, at off design point, all there is certain limitation, it is impossible in subsonic speed and ultrasonic
Good flying quality is all obtained under speed state of flight.Such as, subsonic aircraft cannot realize supersonic flight, and exceed and set
Along with the increase by force of flight speed after meter state, resistance will be greatly increased, and aeroperformance will be substantially reduced, and bring huge therewith
Fuel oil consumption, the damage of Flight Vehicle Structure, even cause the huge disaster that aircraft disintegrates.And the big sweepback of supersonic aircraft
The feature of angle, the aerodynamic arrangement of low aspect ratio and steerable system layout usually affects its subacoustic flight characteristics, flies away from as risen
Ground speed, landing speed, landing glide speed, glide ration and gliding angle all bigger than subsonic aircraft, thus take off and
The distance alightinged run greatly increases, thus needs longer runway.And when low-speed operations, need the big angle of attack to provide
Enough lift, aeroperformance is substantially reduced.When high subsonic flight, aircraft is the sensitiveest to the reaction of fore-and-aft control, holds
Pitching unintentionally is easily caused to wave.The Lateral static stability of landing state is excessive so that aircraft is to outside little disturbance and longitudinal direction
Control response strengthens, and the reaction to crosswind is the sensitiveest.
As can be seen from the above analysis, current unmanned plane exists that maximum flying speed is relatively low, ceiling altitude not
High, maneuverability not enough, cannot take into account subsonic speed and supersonic flight state, be substantially reduced etc. at Off-design performance and ask
Topic.
Summary of the invention
The technical problem to be solved in the present invention is for above-mentioned the deficiencies in the prior art, and provides a kind of variable flying state
Detect and beat integration High Altitude UAV, the detecing of this variable flying state is beaten integration High Altitude UAV and can be solved existing unmanned plane
It is big that flight speed is relatively low, ceiling altitude is the highest, maneuverability is not enough, subsonic speed cannot be taken into account and supersonic flight state,
In the problem that Off-design performance is substantially reduced.
For solving above-mentioned technical problem, the technical solution used in the present invention is:
Detecing of a kind of variable flying state beats integration High Altitude UAV, including body and dynamical system；
Body uses blended wing-body layout, and it is rhomboid pneumatic that body is mutually spliced to form a class by two two-way dalta wings
Profile；Two isosceles triangles equal sized by two two-way dalta wings, the base of two two-way dalta wings is mutually spliced；
Dynamical system is arranged on the stitching portion of body, and dynamical system includes power set and lift unit；
Power set, for realizing the conversion between supersonic flight state and subsonic flight state；
Lift unit, the lift needed for providing body to rise.
The drift angle of two two-way dalta wings is the acute angle less than 60 °.
Under subsonic flight state, full captain 11.5m, span 25m, machine height 3.65m, angle of sweep is 22.4 °, aspect ratio
It is 5.192；Under supersonic flight state, full captain 25m, span 11.5m, machine height 3.65m, angle of sweep is 67.56 °, aspect ratio
It is 1.099.
Also including 8 ailerons, 8 ailerons are symmetricly set on the outer ledge of body.
Each aileron all includes pendulum and lower pendulum；Upper pendulum and lower pendulum all can carry out the most inclined independently
Turn.
Power set include turntable, turntable rotary drive mechanism and two the first electromotors；Turntable is arranged on the spelling of body
Connecing in the middle part of place, turntable can carry out 360 ° of rotations under the effect of turntable rotary drive mechanism；Two the first electromotors are solid side by side
Surely turntable top it is arranged on.
Described lift unit includes the second electromotor and lift fan；Lift fan is arranged in the middle part of turntable, by being arranged on
Described second electromotor of internal body is driven.
Described lift unit also includes that several stability controls jet pipe.
Described lift unit also includes that can regulate stability controls the electric valve of jet pipe flow.
Block upper surface is in protruding streamlined, and body lower surface is smooth flat.
After the present invention uses said structure, have the advantages that
1. body uses blended wing-body layout, can reduce the resistance brought due to wing-body interference；In addition without the all-wing aircraft cloth of vertical fin
Office, is conducive to reducing Radar Cross Section, improves Stealth Fighter.It addition, the design of two-way dalta wing makes it have center
Symmetrical profile, to realize the change of state of flight and heading.
2. body has the aerodynamic configuration of rhombus, can realize two-way flight, additionally have sharp-pointed leading edge, can reduce ultrasonic
Drag due to shock wave under speed state of flight, improves aeroperformance.
3. body lower surface is flat, and unconventional moulding so that when carrying out supersonic cruising under Low Angle Of Attack, will
Downward shock wave can be reduced produce and propagate, thus also can effectively suppress the adverse effect of noise.
4. the unique design of eight ailerons and stability control the design of jet pipe and improve the stability of the present invention and controlled
Property.
The design of the most above-mentioned power set, it is possible to realize turning to of electromotor, under the cooperation of lift unit, Ke Yigeng
Hurry up, more directly change motor-driven direction, the rapid switching in 90 ° and 180 ° directions, significantly enhance the existence energy of unmanned plane
Power and fight capability.
6., under subsonic speed and supersonic flight environment, different state of flights can be used respectively, can realize as required
Conversion between different flight state.
7. under subsonic flight state, captain of the present invention is 11.5m, and the span is 25m, and angle of sweep is 22.4 °, and aspect ratio is
5.192, compared with existing aircraft, there is bigger aspect ratio and less angle of sweep, the relative thickness of aerofoil profile is local string
Long 0.08, keeps constant along spanwise, and it is relatively large that these designs make unmanned plane of the present invention can produce when low speed
Lift, beneficially the taking off/land of aircraft.Lower surface that subsonic speed aerofoil profile is flat and about circular arc point-symmetric in chord length
Upper surface, the two-way flight being advantageously implemented under subsonic flight state.
8. under supersonic flight state, captain of the present invention is 25m, and the span is 11.5m, and angle of sweep is 67.56 °, airfoil
Amassing is 120.3775 m, and aspect ratio is 1.099.Compared with existing aircraft, there are less aspect ratio and bigger sweepback
Angle, the relative thickness of aerofoil profile is the 0.03 of local chord.This ratio keeps constant along length direction so that the present invention has
Sharp-pointed leading edge, can effectively reduce the generation of detached shock wave, and compared with some traditional supersonic profiles, drag due to shock wave will
Greatly reduce, and improve the aeroperformance under supersonic flight environment.Effectively overcome conventional airplane profile cannot hold concurrently simultaneously
Turn round and look at subsonic speed and the contradiction of supersonic flight, improve the aerodynamic characteristic under two states.Application prospect is considerable feasible, is suitable for not
Carry out the strategic development trend of unmanned plane.
Accompanying drawing explanation
Fig. 1 shows the overall structure signal detecing dozen integration High Altitude UAV of the present invention a kind of variable flying state
Figure.
Fig. 2 shows the close-up schematic view of aileron.
Fig. 3 shows that stability controls the layout of jet pipe.
Fig. 4 shows the partial enlarged drawing of engine mounting positions.
Fig. 5 shows subsonic flight view.
Fig. 6 shows the aerofoil profile illustraton of model under subsonic flight state.
Fig. 7 shows supersonic flight view.
Fig. 8 shows the aerofoil profile illustraton of model under supersonic flight state.
Fig. 9 shows the transformation process schematic diagram from subsonic flight state to supersonic flight state.
Wherein have: 1. body；The most two-way dalta wing；3. aileron；4. turntable；5. the first electromotor；6. the second electromotor；7.
Lift fan；8. stability controls jet pipe；9. rotating vane；10. hatchcover；11. power transmission shafts；12. pipelines.
Detailed description of the invention
The present invention is further detailed explanation with concrete better embodiment below in conjunction with the accompanying drawings.
As it is shown in figure 1, a kind of variable flying state detect beat integration High Altitude UAV, including body 1, dynamical system and
8 ailerons 3.
Body uses blended wing-body, Flying-wing, greatly reduces the resistance that wing-body interference brings, increases in body
Free space, can carry the payload such as synthetic aperture radar, semi-active laser guidance air-to-ground guided missile；In addition without the all-wing aircraft of vertical fin
Layout, is conducive to reducing Radar Cross Section, improves Stealth Fighter.
Body is mutually spliced to form a rhomboid aerodynamic configuration of class by two two-way dalta wings；Two two-way dalta wings
Sized by equal two isosceles triangles, the base of two two-way dalta wings is mutually spliced.The drift angle of two two-way dalta wings
It is both preferably the acute angle less than 60 °.
The design of two-way dalta wing makes it have centrosymmetric profile, to realize changing of state of flight and heading
Become.It addition, body has the aerodynamic configuration of rhombus, two-way flight can be realized, additionally there is sharp-pointed leading edge, supersonic speed can be reduced
Drag due to shock wave under state of flight, improves aeroperformance.
Block upper surface is in protruding streamlined, and body lower surface is smooth flat.Improve lift and also can reduce air resistance
Power, improves stealth, agility etc..During further, it enables carry out supersonic cruising under Low Angle Of Attack, it will reduce downward shock wave
Produce and propagate, thus also can effectively suppress the adverse effect of noise.
Dynamical system is arranged on the stitching portion of body, and dynamical system includes power set and lift unit.Wherein, power dress
Put, for realizing the conversion between supersonic flight state and subsonic flight state.Lift unit, is used for providing body to rise
Required lift.
As in figure 2 it is shown, 8 ailerons are symmetricly set on the outer ledge of body, each aileron all includes pendulum and the bottom
Sheet；Upper pendulum and lower pendulum are performed by electrical and pneumatic servo actuator, it is possible to deflect the most up or down, with
Compensate and lack the impact that fixed fin brings.
Power set include turntable 4, turntable rotary drive mechanism and two the first electromotors 5.
Turntable is arranged in the middle part of the stitching portion of body, namely at fuselage back symmetrical centre, it is thus possible to realize two kinds of flights
The balance of moment under state.Turntable can carry out 360 ° of rotations under the effect of turntable rotary drive mechanism, and turntable is preferably by electricity
Air Valve Control servo control mechanism has driven its direction to change, and changes electromotor direction.
As shown in Figure 4, two the first electromotors are fixedly installed on turntable top side by side, and can carry out along with the rotation of turntable
Rotate.Two the first electromotors all preferably employ the fanjet of medium thrust.
Lift unit includes that the second electromotor 6, lift fan 7, several stability control jet pipe 8 and can regulate stability
Control the electric valve of jet pipe flow.
As shown in Figure 1 and Figure 4, lift fan is arranged in the middle part of turntable, by the second electromotor institute being arranged on internal body
Drive.
Lift fan includes rotating vane 9 and hatchcover 10, and the second electromotor is connected with rotating vane by power transmission shaft, drives
Dynamic rotating vane rotates.
When starting the second electromotor, the power transmission shaft transmission power being attached thereto drives lift fan to rotate, and hatchcover is certainly simultaneously
Move and open.
Stability controls the quantity of jet pipe and is preferably 4, as it is shown on figure 3, be arranged symmetrically in supersonic wing and subsonic speed
At the wing root of wing, the high-pressure gas that the second electromotor produces by the road 12 and Jet with downward flow direction, by electric valve regulation stability control
Jet pipe flow processed and then control balance, can produce a small amount of lift simultaneously.
Above-mentioned turntable diameter is preferably 2000mm, and the diameter of lift fan is preferably 1500mm, and fuselage is highly preferred is
2000mm, and lift fan is highly preferred for 1600mm, can reach design requirement.
As it is shown in figure 5, the arrow in Fig. 5 represents heading, under subsonic flight state, full captain 11.5m, the span
25m, machine height 3.65m, angle of sweep is 22.4 °, and aspect ratio is 5.192, and cruising speed is more than 800km/h.
Under subsonic flight state, compared with existing aircraft, there is bigger aspect ratio and less angle of sweep, the wing
The relative thickness of type is the 0.08 of local chord, keeps constant along spanwise, and these designs make unmanned plane of the present invention exist
Taking off/landing of relatively large lift, beneficially aircraft can be produced during low speed.Lower surface that subsonic speed aerofoil profile is flat and pass
Point-symmetric circular arc upper surface in chord length, the two-way flight being advantageously implemented under subsonic flight state.
As shown in Figure 6, the aileron of the leading edge of a wing is locked for aerofoil profile under subsonic flight state, two ailerons of trailing edge
Playing a role, during opposite direction flight, the aileron of leading edge is opened, and the aileron of trailing edge is locked.
As it is shown in fig. 7, the arrow in Fig. 7 represents heading, under supersonic flight state, full captain 25m, the span
11.5m, machine height 3.65m, angle of sweep is 67.56 °, and wing area is 120.3775m, and aspect ratio is 1.099, and cruising speed is big
In 2000km/h.Normally take off quality 15436kg, mission payload 1000kg, cruising altitude 18000m～20000m, combat radius
2100km, takeoff distance 420m, distance of landing run 530m.
Aerofoil profile under supersonic flight state is as shown in Figure 8.
Under supersonic flight state, compared with existing aircraft, there are less aspect ratio and bigger angle of sweep, the wing
The relative thickness of type is the 0.03 of local chord.This ratio keeps constant along length direction so that the present invention has sharply
Leading edge, can effectively reduce the generation of detached shock wave, compared with some traditional supersonic profiles, drag due to shock wave will greatly
Reduce, and improve the aeroperformance under supersonic flight environment.Effectively overcome conventional airplane profile and cannot take into account Asia simultaneously
The velocity of sound and the contradiction of supersonic flight, improve the aerodynamic characteristic under two states.Application prospect is considerable feasible, is suitable for following nothing
Man-machine strategic development trend.
When subsonic flight state dress is changed to supersonic flight state, it is gradually reduced the thrust of two the first electromotors,
It is adjusted to holding state, increases the power of the second electromotor, supplement lift when subsonic and sapersonic velocities state of flight is changed
Deficiency, the first engine rotation 90 ° realizes supersonic flight state direction and changes.Then, it is gradually increased throttle, the first electromotor
Thrust increases, and flight speed increases, and air lift continues to increase, and the lift of lift fan constantly reduces until shutting down, and makes flight
Stress balance in device vertical direction.Ramp up breakthrough sound barrier again, finally accelerate to the supersonic cruising state of Ma=2.From infrasound
Speed state of flight is to the transformation process of supersonic flight state, the most as shown in Figure 9.
The preferred embodiment of the present invention described in detail above, but, the present invention is not limited in above-mentioned embodiment
Detail, in the technology concept of the present invention, technical scheme can be carried out multiple equivalents, this
A little equivalents belong to protection scope of the present invention.
Claims (10)
1. detecing of a variable flying state beats integration High Altitude UAV, it is characterised in that: include body and dynamical system；
Body uses blended wing-body layout, and it is rhomboid pneumatic that body is mutually spliced to form a class by two two-way dalta wings
Profile；Two isosceles triangles equal sized by two two-way dalta wings, the base of two two-way dalta wings is mutually spliced；
Dynamical system is arranged on the stitching portion of body, and dynamical system includes power set and lift unit；
Power set, for realizing the conversion between supersonic flight state and subsonic flight state；
Lift unit, the lift needed for providing body to rise.
Integration High Altitude UAV is beaten in detecing of variable flying state the most according to claim 1, it is characterised in that: two are double
It is the acute angle less than 60 ° to the drift angle of dalta wing.
Integration High Altitude UAV is beaten in detecing of variable flying state the most according to claim 2, it is characterised in that: at infrasound
Under speed state of flight, full captain 11.5m, span 25m, machine height 3.65m, angle of sweep is 22.4 °, and aspect ratio is 5.192；Supersonic speed
Under state of flight, full captain 25m, span 11.5m, machine height 3.65m, angle of sweep is 67.56 °, and aspect ratio is 1.099.
Integration High Altitude UAV is beaten in detecing of variable flying state the most according to claim 1, it is characterised in that: also include
8 ailerons, 8 ailerons are symmetricly set on the outer ledge of body.
Integration High Altitude UAV is beaten in detecing of variable flying state the most according to claim 4, it is characterised in that: each pair
The wing all includes pendulum and lower pendulum；Upper pendulum and lower pendulum all can deflect the most up or down.
Integration High Altitude UAV is beaten in detecing of variable flying state the most according to claim 1, it is characterised in that: power fills
Put and include turntable, turntable rotary drive mechanism and two the first electromotors；Turntable is arranged in the middle part of the stitching portion of body, turntable energy
Enough under the effect of turntable rotary drive mechanism, carry out 360 ° of rotations；Two the first electromotors are fixedly installed on turntable top side by side
Portion.
Integration High Altitude UAV is beaten in detecing of variable flying state the most according to claim 6, it is characterised in that: described liter
Power apparatus includes the second electromotor and lift fan；Lift fan is arranged in the middle part of turntable, by being arranged on described in internal body
Second electromotor is driven.
Integration High Altitude UAV is beaten in detecing of variable flying state the most according to claim 7, it is characterised in that: described liter
Power apparatus also includes that several stability controls jet pipe.
Integration High Altitude UAV is beaten in detecing of variable flying state the most according to claim 8, it is characterised in that: described liter
Power apparatus also includes that can regulate stability controls the electric valve of jet pipe flow.
Integration High Altitude UAV is beaten in detecing of variable flying state the most according to claim 1, it is characterised in that: body
Upper surface is in protruding streamlined, and body lower surface is smooth flat.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201610530935.XA CN106081050A (en) | 2016-07-07 | 2016-07-07 | Integration High Altitude UAV is beaten in detecing of a kind of variable flying state |
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| CN (1) | CN106081050A (en) |
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| CN110763090A (en) * | 2019-10-11 | 2020-02-07 | 南京理工大学 | Combinable and deformable primary-secondary type patrol and play integrated flying bomb and working method thereof |
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| JP2008149735A (en) * | 2006-12-14 | 2008-07-03 | Morio Okatsu | Aeroplane |
| US20100140389A1 (en) * | 2008-12-04 | 2010-06-10 | Thales Holdings Uk Plc | Air vehicle |
| CN101795939A (en) * | 2007-08-29 | 2010-08-04 | 高级产品开发有限责任公司 | Oblique blended wing body aircraft |
| CN104015922A (en) * | 2014-04-11 | 2014-09-03 | 南京航空航天大学 | Unmanned aerial vehicle with rotary wing body and variable aspect ratio |
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| JP2008149735A (en) * | 2006-12-14 | 2008-07-03 | Morio Okatsu | Aeroplane |
| CN101795939A (en) * | 2007-08-29 | 2010-08-04 | 高级产品开发有限责任公司 | Oblique blended wing body aircraft |
| US20100140389A1 (en) * | 2008-12-04 | 2010-06-10 | Thales Holdings Uk Plc | Air vehicle |
| CN104015922A (en) * | 2014-04-11 | 2014-09-03 | 南京航空航天大学 | Unmanned aerial vehicle with rotary wing body and variable aspect ratio |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN110763090A (en) * | 2019-10-11 | 2020-02-07 | 南京理工大学 | Combinable and deformable primary-secondary type patrol and play integrated flying bomb and working method thereof |
| CN110763090B (en) * | 2019-10-11 | 2022-04-08 | 南京理工大学 | Combinable and deformable primary-secondary type patrol and play integrated flying bomb and working method thereof |
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