CN106628163A - Supersonic unmanned combat air vehicle capable of achieving large-resistance deceleration and vertical take-off and landing - Google Patents
Supersonic unmanned combat air vehicle capable of achieving large-resistance deceleration and vertical take-off and landing Download PDFInfo
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- CN106628163A CN106628163A CN201710025513.1A CN201710025513A CN106628163A CN 106628163 A CN106628163 A CN 106628163A CN 201710025513 A CN201710025513 A CN 201710025513A CN 106628163 A CN106628163 A CN 106628163A
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- electromagnetic valve
- cabin
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- air vehicle
- vehicle
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
-
- 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
- B64C1/14—Windows; Doors; Hatch covers or access panels; Surrounding frame structures; Canopies; Windscreens accessories therefor, e.g. pressure sensors, water deflectors, hinges, seals, handles, latches, windscreen wipers
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby
- B64D27/02—Aircraft characterised by the type or position of power plant
Abstract
A supersonic unmanned combat air vehicle capable of achieving large-resistance deceleration and vertical take-off and landing comprises a structural system, power systems and a flying control system; the structural system comprises all constituent parts, namely a vehicle head, vehicle cabins, vehicle wings, a fuselage, a undercarriage and tail wings, of a vehicle body of the air vehicle; the power systems are energy source devices which supply power and manipulation to the air vehicle under different flying speeds, and the power systems comprise the vertical take-off and landing power system, the tail portion ducted turbine power system and the ram-air power systems on the two sides of the tail portion; and the power systems are composed of coaxial type dual rotor wing airscrews, the vehicle cabins and arc-shaped rotating type cabin doors. The supersonic unmanned combat air vehicle capable of achieving large-resistance deceleration and vertical take-off and landing is designed with two technologies serving as a breakthrough, and according to the repellent and complementary principles of relevant characteristics, the supersonic unmanned combat air vehicle has the characteristics of large-resistance deceleration, supersonic flying and vertical take-off and landing; and the maneuvering property of the air vehicle is better, and the air vehicle can fly in a wide velocity field and has a fighting capability in a complex environment.
Description
Technical field
The present invention relates to aircraft, more particularly, to a kind of supersonic speed for being capable of achieving big drag braking and VTOL nobody
Fighter plane.
Background technology
It is well known that the VTOL technology and supersonic flight technology of aircraft are the emphasis and heat of domestic and international research
Point.In recent years, although the performance of aircraft has respectively new breakthrough in terms of the two, can send out from current research
Existing, still not possessing can be while realizes the aircraft of VTOL and supersonic flight ability.
Chinese patent CN203740127U discloses a kind of variant UCAV, is changed using the variant manner of folded wing
Wing is plunderred to, aspect ratio and aerofoil profile, improves adaptability of the aerodynamic configuration in wide flight envelope；The ingenious combination whirlpool spray of engine
Engine and punching engine, solve the problems such as such engine runner is shared less, deadweight is more, supersonic combustion difficulty is realized；
Aerodynamic configuration aspect, Waverider head is mutual in combination with sweepforward folds outer wing with edge strip, leading edge of a wing breach with fuselage, canard
Mend, it is ensured that high-performance of the UCAV under wide speed interval, many flight attitudes.In context engine, by fan propeller
It is arranged between low-pressure compressor and high-pressure compressor and the design such as deceleration transmission, combustion gas precooling is combined with, is substantially improved and sends out
The overall performance of motivation；The utility model is superimposed with dual vector jet pipe by flow field Thrust Vectoring Technology, obtains ± 40 °
Jet deflexion angle, greatly improves the maneuverability and controllability of UCAV.
The content of the invention
It is an object of the invention to provide a kind of supersonic speed UCAV for being capable of achieving big drag braking and VTOL.
The present invention includes structural system, dynamical system and flight control system；
The structural system includes all constituents of aircraft body；Structural system include head, cabin, wing,
Fuselage, undercarriage and empennage, the cabin is located at fuselage interior, and cabin is provided with arcuate rotation formula hatch door and coaxial rotor
Screw, cabin provides folding and unfolding space for coaxial rotor screw, and arcuate rotation formula hatch door profile is fitted with cabin, coaxial
Formula DCB Specimen is made up of two pairs of blades, and laser aid is arranged on wing, as laser sensor or laser weapon, gas channel
The both sides being arranged in behind fuselage and biased downward, fuselage is respectively provided on two sides with exhaust duct, exhaust duct connection gas channel, row
Electromagnetic valve, left back electromagnetic valve and left front electromagnetic valve behind electromagnetic valve before the right side, the right side is installed, exhaust duct two ends are opened in air flue
Mouth is provided with porting and exhaust outlet.Wide speed domain turbogenerator is arranged on aircraft afterbody, and intake port layout is in front fuselage
Bottom.Turbogenerator is arranged on aircraft interior and before the turbogenerator of wide speed domain, and punching engine is arranged on the right side
The rear side of electromagnetic valve and left back electromagnetic valve afterwards；
The dynamical system is the energy source device that aircraft provides power and manipulation under different flying speeds；The power
System is using three kinds of power such as VTOL dynamical system, afterbody duct turbine power system and two sides of tail punching press dynamical systems
System；Dynamical system is made up of coaxial rotor screw, cabin, arcuate rotation formula hatch door；Afterbody duct turbo-power system
System is made up of air intake duct, wide speed domain turbogenerator, and two sides of tail punching press dynamical system is by magnetic valve behind electromagnetic valve, the right side before the right side
Door, left back electromagnetic valve, left front electromagnetic valve and punching engine composition；
The flight control system is the avionics device of real-time control state of flight, flight control is installed in cabin and is calculated
Machine, energy resource system and sensing system, the energy resource system includes power supply and fuel tank, and the sensing system is provided with GPS navigation
Instrument, gyroscope, radar, barometertic altimeter, transmission of wireless signals instrument, laser aid etc..
The present invention designs the nothing of a kind of achievable VTOL and supersonic flight with aforementioned two kinds of technologies as breach
People's fighter plane, the repulsion and complementarity principle according to correlation properties, the present invention design UCAV possess big drag braking with
And the characteristic of supersonic flight and VTOL, the mobility of aircraft more preferably, and being capable of the flight of wide speed domain.Meanwhile, this
It is bright to possess complex environment fight capability.
The present invention has advantage following prominent：
1st, on the basis of the flight for realizing VTOL, supersonic flight is realized, it is to avoid conventional jet formula aircraft needs
The high shortcoming of fixed runway, control difficulty, while hovering, fixed point that traditional fixed-wing unmanned plane cannot be completed can be realized
The highly difficult flare maneuvers such as steering；
2nd, the present invention possesses special power arrangement and aerodynamic characteristic to the supersonic aircraft of VTOL and all kinds of
Model plane make and research and development have reference significance.
Description of the drawings
Fig. 1 stretches out state isometric drawing for aircraft propeller.
Fig. 2 stretches out state right view for aircraft propeller.
Fig. 3 stretches out state front view for aircraft propeller.
Fig. 4 stretches out top view for aircraft propeller.
Fig. 5 is that aircraft propeller enters state isometric drawing in cabin.
Specific embodiment
Following examples are further described accompanying drawing is combined to the concrete structure and operation principle of the present invention.
Referring to Fig. 1～5, the present invention is made up of structural system, dynamical system, flight control system three digest journals.
First, structural system：Structural system is mainly with head 1, wing 4, fuselage 8, undercarriage 10 and empennage 6 as agent structure
Basis, cabin 2 is designed inside fuselage 8, and its effect is to provide folding and unfolding space for screw, and cabin 2 is provided with arcuate rotation formula
Hatch door 21 and coaxial rotor screw 3, the profile of arcuate rotation formula hatch door 21 fit with cabin 2 it is similar, can by motor turn
It is dynamic to be turned on and off cabin 2；Coaxial rotor 3 is made up of two pairs of blades, in cabin 2, coaxial rotor spiral
Oar 3 can be by its location status of motor control, and folding and unfolding when not working is risen from outside cabin in cabin during work.Laser aid 5
On wing 4, as laser sensor or laser weapon (warhead of aircraft).Gas channel 9 is arranged in after fuselage
The both sides in face and biased downward, exhaust duct 7 (fuselage both sides are each) connection gas channel 9, are provided with before the right side in exhaust duct 7
Electromagnetic valve 14, the right side after electromagnetic valve 15, left back electromagnetic valve 19 and left front electromagnetic valve 20, the both ends open of exhaust duct 7 have into
Exhaust outlet 13 and exhaust outlet 16.Wide fast domain turbogenerator 11 is arranged on aircraft afterbody, and air intake duct 12 is arranged in front fuselage
Bottom.Turbogenerator 17 is arranged on aircraft interior and before wide fast domain turbogenerator 11, and punching engine is installed
The rear side of electromagnetic valve 15 and left back electromagnetic valve 19 behind the right side, as shown in Figure 4.The aircraft vertical landing stage is by wide speed domain whirlpool
Turbine 11 provides lift；Power is provided by turbogenerator 17 in low cruise flight, (aircraft is low for reducing energy consumption
Under fast state of flight, jet flight energy loss is big)；In supersonic mode, by punching engine 18 power is provided.
2nd, dynamical system, the dynamical system adopts VTOL dynamical system, afterbody duct turbine power system and tail
Three kinds of dynamical systems such as portion both sides punching press dynamical system；Dynamical system is by coaxial rotor screw 3, cabin 2, arcuate rotation
Formula hatch door 21 is constituted；Afterbody duct turbine power system is made up of air intake duct 12, wide fast domain turbogenerator 11, for Asia transonic speed
Flight；Two sides of tail punching press dynamical system is by electromagnetic valve 15 behind electromagnetic valve before the right side 14, the right side, left back electromagnetic valve 19, left front
Electromagnetic valve 20 and punching engine 18 are constituted, and mainly realize aircraft supersonic flight.
1st, VTOL dynamical system is opened from servo-controlled motor control arcuate rotation formula hatch door 21, close coupled type bispin
The lifting of wing screw 3, turbogenerator can also be designed to the control of coaxial rotor screw 3 and drive power, fly
During row device VTOL, aircraft door 21 is first turned on, and servo-controlled motor control screw rises, and turbogenerator 17 leads to
The power of the rotation of gear-box and the blade of clutch offer coaxial rotor screw 3 is provided.
2nd, afterbody duct turbine power system adopts turbogenerator 17, main to provide aircraft sub- transonic speed mission phase
Power.
3rd, punching press dynamical system in both sides provides supersonic flight using punching engine 18 as power source for aircraft
Power.
3rd, flight control system：The present invention is using neutral net adaptive flight control system and intelligent computer programed flight
Control integrated system.Flight-control computer, energy resource system (including power supply and fuel tank) and sensor system are installed in cabin
System, sensing system is mainly by GPS navigator, gyroscope, radar, barometertic altimeter, transmission of wireless signals instrument, laser aid
(as laser sensor or laser weapon) etc. is constituted.
The operation principle of the present invention is as follows：
1. when aircraft vertical takes off, due to installing coaxial rotor screw 3, arcuate rotation in aircraft nacelle
Formula hatch door 21 is opened, and coaxial rotor screw 3 is risen from cabin 2, using two pairs of propeller blades of coaxial rotor
Piece is rotated both clockwise and counterclockwise respectively, makes aircraft reach power and balance, and finally realizing aircraft vertical taking off, (its structure is former
Reason is rotated the lift for producing using coaxial rotor screw 3 and keeps balance, course in the air referring to Fig. 1～4), aircraft
Manipulate top lower two rotors it is differential always away from adjusting.
2. when aircraft low-speed operations, as shown in figure 4, electromagnetic valve 15, left back electromagnetism behind right front electromagnetic valve 14, the right side
Valve 19 and left front electromagnetic valve 20 are closed, and air flow is A → B → C → D → H path, and aircraft afterbody width speed domain turbine is sent out
Motivation 17 provides initial driving force rotates wide fast domain turbogenerator 11, and aircraft low-speed operations and accelerates up to can to lift forward
During relying on turbogenerator to provide completely, coaxial rotor screw adjusting position to fuselage parastate, then under
It is down in hatch door 21.
3. aircraft supersonic mode (state of aircraft high-speed flight is shown in Fig. 5) has two gears, gear 1：Punching
Hydraulic motor 18 starts to start work, and electromagnetic valve 15 and left back electromagnetic valve 19 are opened behind the right side, electromagnetic valve 14 and a left side before the right side
Front electromagnetic valve 20 is closed, and due to airflow injection effect, air flow is A → B → C → D → E → F, and A → B → C → D → I →
J, wide fast domain turbogenerator 17 will be progressively closed off；Gear 2：Punching engine 18 fully opens work, it is right before electromagnetic valve 14,
Electromagnetic valve 15, left back electromagnetic valve 19 and left front electromagnetic valve 20 are opened behind the right side, due to airflow injection effect, punching engine
The main air inlet runner of 18 work is G → E → F, K → I → J, runner A → B → C → D → E → F and A → B → C → D → I → J
The air-flow of afterbunring or cooling can be provided according to punching engine operating mode and task.When aircraft is needed in supersonic mode
When turning to, can also be using electromagnetic valve 15, left back electromagnetic valve behind right front electromagnetic valve 14, the right side in addition to changing aileron
19 and the folding threshold degree of left front electromagnetic valve 20 adjust left and right punching engine and produce that asymmetric implementation of inference is more motor-driven to be turned
To flight.
4. the big drag braking state of flight of aircraft, electromagnetic valve 15, left back electromagnetic valve 19 are closed behind the right side, it is right before electromagnetism
Valve 14 and left front electromagnetic valve 20 are opened, and close turbogenerator 17, and punching engine 18 also quits work, this Airflow
To the gas momentum for A → B → C → D → E → G, A → B → C → D → I → K, inlet channel and exhaust passage conversely, air-flow phase
Mutually offset, resistance is increased, therefore flying instrument is for big drag braking function.
5. when aircraft vertical lands, turbogenerator 17 and punching engine 18 are closed, and aircraft coastdown is extremely
Lower-speed state can be stretched out safely outside hatch door 21 until speed is reduced to coaxial rotor 3, and coaxial rotor screw 3 leads to
Cross rotation and vertical lift is provided so that aircraft can slow down vertical landing.
6. the flight characteristicses such as steering are pinpointed.Aircraft controls electromagnetic valve 15, left back magnetic valve behind the right side by coordinating combination
Door 19 is closed, and right front electromagnetic valve 14, left front electromagnetic valve 20 and turbogenerator 17, punching engine 18 and close coupled type are double
The different working condition of the grade of propeller aircraft 3 can flexibly realize the flight attitudes, such as VTOL process such as aircraft fixed point steering,
By change coaxial rotor screw 3 it is differential always away from；Low speed, sub- transonic speed steering can be in the work shapes of turbogenerator 17
State changes empennage rudder and reaches；Not only can adjust steering moment by empennage rudder during supersonic and hypersonic flight can also be by the right side
Afterwards electromagnetic valve 15, left back electromagnetic valve 19 are closed, the folding threshold degree control of right front electromagnetic valve 14 and left front electromagnetic valve 20
Punching engine flow is realized turning to producing big steering moment.These various steering characteristics can be used for the fistfight of empty day with
And other complicated flight environment of vehicle, it is also an obvious supplement to VTOL flight, big drag braking flight performance.
7. the flight of saving oneself under unsafe condition.When aircraft runs into turbogenerator 17 in pressure during supersonic flight
When stopping or do not work with punching engine 18, (aileron can to provide lift by the spinning of coaxial rotor screw 3
Cooperating) slowing down slides.
Claims (1)
1. a kind of supersonic speed UCAV for being capable of achieving big drag braking and VTOL, it is characterised in that including structure system
System, dynamical system and flight control system；
The structural system includes head, cabin, wing, fuselage, undercarriage and empennage, and the cabin is located at fuselage interior, machine
Cabin is provided with arcuate rotation formula hatch door and coaxial rotor screw, and it is empty that cabin provides folding and unfolding for coaxial rotor screw
Between, arcuate rotation formula hatch door profile is fitted with cabin, and coaxial rotor is made up of two pairs of blades, and laser aid is arranged on wing
On, used as laser sensor or laser weapon, gas channel is arranged in the both sides behind fuselage and biased downward, fuselage both sides
Exhaust duct is respectively equipped with, exhaust duct connection gas channel is provided with electromagnetic valve, a left side behind electromagnetic valve before the right side, the right side in exhaust duct
Electromagnetic valve and left front electromagnetic valve afterwards, exhaust duct both ends open is provided with porting and exhaust outlet；Wide speed domain turbogenerator
Installed in aircraft afterbody, in front fuselage bottom, turbogenerator is arranged on aircraft interior and in wide speed to intake port layout
Before the turbogenerator of domain, punching engine is arranged on the rear side of electromagnetic valve and left back electromagnetic valve behind the right side；
The dynamical system is the energy source device that aircraft provides power and manipulation under different flying speeds；The dynamical system
Using VTOL dynamical system, afterbody duct turbine power system and two sides of tail punching press dynamical system；Dynamical system is by altogether
Shaft type DCB Specimen screw, cabin, arcuate rotation formula hatch door composition；Afterbody duct turbine power system is by air intake duct, wide speed domain
Turbogenerator is constituted, two sides of tail punching press dynamical system by electromagnetic valve behind electromagnetic valve before the right side, the right side, left back electromagnetic valve,
Left front electromagnetic valve and punching engine are constituted；
The flight control system for real-time control state of flight avionics device, in cabin install flight-control computer,
Energy resource system and sensing system, the energy resource system includes power supply and fuel tank, the sensing system be provided with GPS navigator,
Gyroscope, radar, barometertic altimeter, transmission of wireless signals instrument, laser aid.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710025513.1A CN106628163B (en) | 2017-01-13 | 2017-01-13 | A kind of supersonic speed unmanned fighter that big drag braking and VTOL can be achieved |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710025513.1A CN106628163B (en) | 2017-01-13 | 2017-01-13 | A kind of supersonic speed unmanned fighter that big drag braking and VTOL can be achieved |
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| Publication Number | Publication Date |
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| CN106628163A true CN106628163A (en) | 2017-05-10 |
| CN106628163B CN106628163B (en) | 2018-12-28 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710025513.1A Expired - Fee Related CN106628163B (en) | 2017-01-13 | 2017-01-13 | A kind of supersonic speed unmanned fighter that big drag braking and VTOL can be achieved |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108563218A (en) * | 2018-06-11 | 2018-09-21 | 中国科学院工程热物理研究所 | Supersonic speed unmanned plane ultra-viewing distance communicates and safety control system |
| CN109720562A (en) * | 2018-12-04 | 2019-05-07 | 北京空天技术研究所 | Double dynamical reuse high-speed aircraft and its application method |
| CN110398977A (en) * | 2018-04-25 | 2019-11-01 | 成都飞机工业（集团）有限责任公司 | A kind of unmanned plane aileron deceleration system and method |
| CN110816846A (en) * | 2019-11-29 | 2020-02-21 | 集美大学 | Can realize fixed wing unmanned aerial vehicle of vertical take-off |
| CN112078789A (en) * | 2019-06-14 | 2020-12-15 | 陶德泉 | Hypersonic aircraft |
| CN112648981A (en) * | 2020-12-04 | 2021-04-13 | 中国航空工业集团公司成都飞机设计研究所 | Method for measuring swing quantity of rotating mechanism in motion process based on laser positioning |
| CN113320693A (en) * | 2021-08-04 | 2021-08-31 | 中国空气动力研究与发展中心空天技术研究所 | Novel retractable tandem rotor wing composite wing aircraft layout |
| WO2023060678A1 (en) * | 2021-10-11 | 2023-04-20 | 广东汇天航空航天科技有限公司 | Aircraft and coaxial dual-rotor assembly |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN110398977A (en) * | 2018-04-25 | 2019-11-01 | 成都飞机工业（集团）有限责任公司 | A kind of unmanned plane aileron deceleration system and method |
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| CN109720562A (en) * | 2018-12-04 | 2019-05-07 | 北京空天技术研究所 | Double dynamical reuse high-speed aircraft and its application method |
| CN112078789A (en) * | 2019-06-14 | 2020-12-15 | 陶德泉 | Hypersonic aircraft |
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| CN110816846A (en) * | 2019-11-29 | 2020-02-21 | 集美大学 | Can realize fixed wing unmanned aerial vehicle of vertical take-off |
| CN110816846B (en) * | 2019-11-29 | 2021-05-04 | 集美大学 | Can realize fixed wing unmanned aerial vehicle of vertical take-off |
| CN112648981A (en) * | 2020-12-04 | 2021-04-13 | 中国航空工业集团公司成都飞机设计研究所 | Method for measuring swing quantity of rotating mechanism in motion process based on laser positioning |
| CN113320693A (en) * | 2021-08-04 | 2021-08-31 | 中国空气动力研究与发展中心空天技术研究所 | Novel retractable tandem rotor wing composite wing aircraft layout |
| WO2023060678A1 (en) * | 2021-10-11 | 2023-04-20 | 广东汇天航空航天科技有限公司 | Aircraft and coaxial dual-rotor assembly |
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| CN106628163B (en) | 2018-12-28 |
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