CN106628163B - A kind of supersonic speed unmanned fighter that big drag braking and VTOL can be achieved - Google Patents
A kind of supersonic speed unmanned fighter that big drag braking and VTOL can be achieved Download PDFInfo
- Publication number
- CN106628163B CN106628163B CN201710025513.1A CN201710025513A CN106628163B CN 106628163 B CN106628163 B CN 106628163B CN 201710025513 A CN201710025513 A CN 201710025513A CN 106628163 B CN106628163 B CN 106628163B
- Authority
- CN
- China
- Prior art keywords
- electromagnetic valve
- cabin
- aircraft
- vtol
- flight
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
Links
- 238000005183 dynamical system Methods 0.000 claims abstract description 30
- 238000004080 punching Methods 0.000 claims abstract description 27
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 claims abstract description 12
- 239000000203 mixture Substances 0.000 claims description 5
- 239000002828 fuel tank Substances 0.000 claims description 3
- 230000008054 signal transmission Effects 0.000 claims description 3
- 230000008450 motivation Effects 0.000 claims description 2
- 238000005516 engineering process Methods 0.000 abstract description 5
- 239000000470 constituent Substances 0.000 abstract description 2
- 108010066114 cabin-2 Proteins 0.000 description 7
- 230000000694 effects Effects 0.000 description 3
- 238000001816 cooling Methods 0.000 description 2
- 238000002347 injection Methods 0.000 description 2
- 239000007924 injection Substances 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 241000272517 Anseriformes Species 0.000 description 1
- 230000003044 adaptive effect Effects 0.000 description 1
- 238000013528 artificial neural network Methods 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 239000000567 combustion gas Substances 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 230000009977 dual effect Effects 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 238000005265 energy consumption Methods 0.000 description 1
- 230000006870 function Effects 0.000 description 1
- 239000007789 gas Substances 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000003825 pressing Methods 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 238000012827 research and development Methods 0.000 description 1
- 238000009987 spinning Methods 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
- 239000013589 supplement Substances 0.000 description 1
Classifications
-
- 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; 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
- B64D27/02—Aircraft characterised by the type or position of power plants
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Toys (AREA)
Abstract
A kind of supersonic speed unmanned fighter that big drag braking and VTOL can be achieved, including structural system, dynamical system and flight control system；Structural system includes all constituents of aircraft body；Structural system includes head, cabin, wing, fuselage, undercarriage and empennage；The dynamical system is that aircraft provides the energy source device of power and manipulation under different flying speeds；Dynamical system is using three kinds of dynamical systems such as VTOL dynamical system, tail portion duct turbine power system and two sides of tail punching press dynamical systems；Dynamical system is made of coaxial rotor propeller, cabin, arcuate rotation formula hatch door.The unmanned fighter of a kind of achievable VTOL and supersonic flight is designed using aforementioned two kinds of technologies as breach, according to the repulsion and complementarity principle of correlation properties, the characteristic for having big drag braking and supersonic flight and VTOL, the mobility of aircraft is more preferable, and can wide fast domain flight, have complex environment fight capability.
Description
Technical field
The present invention relates to aircraft, more particularly, to a kind of supersonic speed that big drag braking and VTOL can be achieved nobody
Fighter plane.
Background technique
It is well known that the VTOL technology and supersonic flight technology of aircraft are the emphasis studied both at home and abroad and heat
Point.In recent years, it although the performance of aircraft has new breakthrough respectively in terms of the two, can be sent out from current research
It is existing, do not have the aircraft that can realize VTOL and supersonic flight ability simultaneously still.
Chinese patent CN203740127U discloses a kind of variant unmanned fighter, is changed using the variant manner of folded wing
Wing is plunderred to, aspect ratio and aerofoil profile, and adaptability of the aerodynamic configuration in wide flight envelope is improved；The ingenious combination whirlpool spray of engine
Engine and punching engine solve the problems such as such engine runner shares less, deadweight is more, supersonic combustion difficulty is realized；?
In terms of aerodynamic configuration, Waverider head is folded outer wing with sweepforward and combined mutually with fuselage, canard with edge strip, leading edge of a wing notch
It mends, ensure that high-performance of the unmanned fighter under wide speed interval, more flight attitudes.In context engine, by fan propeller
It is arranged between low-pressure compressor and high-pressure compressor and the designs such as deceleration transmission, combustion gas pre-cooling is combined, hair is substantially improved
The overall performance of motivation；The utility model is superimposed by flow field Thrust Vectoring Technology and dual vector jet pipe, obtains ± 40 °
Jet deflexion angle greatly improves the maneuverability and controllability of unmanned fighter.
Summary of the invention
The purpose of the present invention is to provide a kind of supersonic speed unmanned fighter that big drag braking and VTOL can be achieved.
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 are located at fuselage interior, and cabin is equipped with arcuate rotation formula hatch door and coaxial rotor
Propeller, cabin provide folding and unfolding space for coaxial rotor propeller, and arcuate rotation formula hatch door shape is bonded with cabin, coaxial
Formula DCB Specimen is made of two pairs of blades, and laser aid is mounted on wing, as laser sensor or laser weapon, airflow channel
It is arranged in the subsequent two sides of fuselage and biased downward, fuselage two sides are respectively equipped with exhaust duct, and exhaust duct connects airflow channel, row
Be equipped in air flue electromagnetic valve before the right side, it is right after electromagnetic valve, left back electromagnetic valve and left front electromagnetic valve, exhaust duct both ends are opened
Mouth is equipped with porting and exhaust outlet.Wide speed domain turbogenerator is mounted on aircraft tail portion, and intake port layout is in front fuselage
Bottom.Turbogenerator is mounted on aircraft interior and before wide fast domain turbogenerator, and punching engine is mounted on the right side
The rear side of electromagnetic valve and left back electromagnetic valve afterwards；
The dynamical system is that aircraft provides the energy source device of power and manipulation under different flying speeds；The power
System is using three kinds of power such as VTOL dynamical system, tail portion duct turbine power system and two sides of tail punching press dynamical systems
System；Dynamical system is made of coaxial rotor propeller, cabin, arcuate rotation formula hatch door；Tail portion duct turbo-power system
System is made of air intake duct, wide fast domain turbogenerator, and two sides of tail punching press dynamical system is by solenoid 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, and installation flight control calculates in cabin
Machine, energy resource system and sensing system, the energy resource system include power supply and fuel tank, and the sensing system is equipped with GPS navigation
Instrument, gyroscope, radar, barometertic altimeter, wireless signal transmission instrument, laser aid etc..
The present invention designs the nothing of a kind of achievable VTOL and supersonic flight using aforementioned two kinds of technologies as breach
People's fighter plane, according to the repulsion and complementarity principle of correlation properties, the unmanned fighter that the present invention designs have big drag braking with
And the characteristic of supersonic flight and VTOL, the mobility of aircraft is more preferable, and being capable of wide fast domain flight.Meanwhile this hair
It is bright to have complex environment fight capability.
The invention has the following outstanding advantages:
1, it on the basis of realizing the flight of VTOL, realizes supersonic flight, avoids conventional jet formula aircraft needs
The high disadvantage of fixed runway, control difficulty, while the impossible hovering of traditional fixed-wing unmanned plane, fixed point may be implemented
The highly difficult flare maneuvers such as steering；
2, the present invention has special power arrangement and aerodynamic characteristic to the supersonic aircraft of VTOL and all kinds of
Model plane production and research and development have reference significance.
Detailed description of the invention
Fig. 1 is that aircraft propeller stretches out state isometric drawing.
Fig. 2 is that aircraft propeller stretches out state right view.
Fig. 3 is that aircraft propeller stretches out state main view.
Fig. 4 is that aircraft propeller stretches out top view.
Fig. 5 is that aircraft propeller enters state isometric drawing in cabin.
Specific embodiment
Following embodiment will be further described specific structure and working principle of the invention in conjunction with attached drawing.
Referring to Fig. 1~5, the present invention is made of structural system, dynamical system, flight control system three digest journals.
One, structural system: the main structure based on head 1, wing 4, fuselage 8, undercarriage 10 and empennage 6 of structural system
Basis, cabin 2 design inside fuselage 8, and effect is that folding and unfolding space is provided for propeller, and cabin 2 is equipped with arcuate rotation formula
Hatch door 21 and coaxial rotor propeller 3,21 shape of arcuate rotation formula hatch door be bonded with cabin 2 it is similar, can pass through motor turn
It is dynamic to open or close cabin 2；Coaxial rotor 3 is made of two pairs of blades, is mounted in cabin 2, coaxial rotor spiral
Paddle 3 can be by its location status of motor control, and folding and unfolding is in cabin when not working, when work outside emersion cabin.Laser aid 5
It is mounted on wing 4, as laser sensor or laser weapon (warhead of aircraft).After airflow channel 9 is arranged in fuselage
The two sides in face and biased downward, exhaust duct 7 (each one of fuselage two sides) connects airflow channel 9, before being equipped with the right side in exhaust duct 7
Electromagnetic valve 14, it is right after electromagnetic valve 15, left back electromagnetic valve 19 and left front electromagnetic valve 20,7 both ends open of exhaust duct have into
Exhaust outlet 13 and exhaust outlet 16.Wide speed domain turbogenerator 11 is mounted on aircraft tail portion, and air intake duct 12 is arranged in front fuselage
Bottom.Turbogenerator 17 is mounted on aircraft interior and before wide fast domain turbogenerator 11, punching engine installation
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 fast domain whirlpool
Turbine 11 provides lift；Power is provided by turbogenerator 17 in low cruise flight, reducing energy consumption, (aircraft is low
Under fast state of flight, jet flight energy loss is big)；In supersonic mode, power is provided by punching engine 18.
Two, dynamical system, the dynamical system use VTOL dynamical system, tail portion duct turbine power system and tail
Three kinds of dynamical systems such as portion two sides punching press dynamical system；Dynamical system is by coaxial rotor propeller 3, cabin 2, arcuate rotation
Formula hatch door 21 forms；Tail portion duct turbine power system is made of air intake duct 12, wide fast domain turbogenerator 11, transonic speed for Asia
Flight；Two sides of tail punching press dynamical system by electromagnetic valve 14 before the right side, it is right after electromagnetic valve 15, left back electromagnetic valve 19, left front
Electromagnetic valve 20 and punching engine 18 form, main to realize aircraft supersonic flight.
1, VTOL dynamical system selects servo-controlled motor control arcuate rotation formula hatch door 21 to open, close coupled type bispin
The lifting of wing propeller 3, turbogenerator can also be designed to control and the driving power of coaxial rotor propeller 3, fly
When row device VTOL, aircraft door 21 is first turned on, and servo-controlled motor controls propeller and rises, and turbogenerator 17 is logical
The power of the rotation of gear-box and clutch offer 3 blade of coaxial rotor propeller is provided.
2, duct turbine power system in tail portion uses turbogenerator 17, main to provide aircraft Asia transonic speed mission phase
Power.
3, punching press dynamical system in two sides is used as power source using punching engine 18, provides supersonic flight for aircraft
Power.
Three, flight control system: the present invention uses neural network 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, wireless signal transmission instrument, laser aid
The composition such as (as laser sensor or laser weapon).
Working principle of the present invention is as follows:
1. when aircraft vertical takes off, due to installing coaxial rotor propeller 3, arcuate rotation in aircraft nacelle
Formula hatch door 21 is opened, and coaxial rotor propeller 3 is risen out of cabin 2, utilizes two pairs of screw blades of coaxial rotor
Piece is rotated both clockwise and counterclockwise respectively, and aircraft is made to reach power and balance, and final realization aircraft vertical takes off, and (its structure is former
Reason is referring to Fig. 1~4), aircraft keeps balancing in the sky using the lift that the rotation of coaxial rotor propeller 3 generates, course
Manipulation by upper and lower two rotor it is differential always away from adjusting.
2. when aircraft low-speed operations, as shown in figure 4, electromagnetic valve 14 before the right side, it is right after electromagnetic valve 15, left back electromagnetism
Valve 19 and left front electromagnetic valve 20 are closed, and air flow direction is A → B → C → D → H path, aircraft tail portion turbogenerator 17
There is provided initial driving force rotates wide fast domain turbogenerator 11, and aircraft flies at low speed forward and accelerates until can be complete to lift
Rely on turbogenerator provide when, coaxial rotor propeller adjusting position to fuselage parastate, then drop to cabin
In door 21.
3. there are two gear, gears 1: punching for aircraft supersonic mode (state of aircraft high-speed flight is shown in Fig. 5)
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
Preceding electromagnetic valve 20 is closed, and due to airflow injection effect, air flow direction is A → B → C → D → E → F, and A → B → C → D → I →
J, turbogenerator 17 will progressively close off；Gear 2: punching engine 18 fully opens work, electricity behind electromagnetic valve 14, the right side before the right side
Magnet valve door 15, left back electromagnetic valve 19 and left front electromagnetic valve 20 are opened, and due to airflow injection effect, punching engine 18 works
Main air inlet runner be G → E → F, K → I → J, runner A → B → C → D → E → F and A → B → C → D → I → J can basis
Punching engine operating condition and task provide the air-flow of afterbunring or cooling.When aircraft needs to turn in supersonic mode
When, electromagnetic valve 15, left back electromagnetic valve 19 and a left side behind electromagnetic valve 14, the right side before the right side can also be utilized other than changing aileron
The folding threshold degree of preceding electromagnetic valve 20 adjusts left and right punching engine and generates the more motor-driven steering flight of asymmetric implementation of inference.
4. the big drag braking state of flight of aircraft, it is right after electromagnetic valve 15, left back electromagnetic valve 19 close, it is right before electromagnetism
Valve 14 and left front electromagnetic valve 20 are opened, and turbogenerator 17 is closed, and punching engine 18 also stops working, this Airflow
To for A → B → C → D → E → G, A → B → C → D → I → K, the gas momentum of inlet channel and exhaust passage is on the contrary, air-flow phase
It mutually offsets, resistance increases, therefore flying instrument is for big drag braking function.
5. turbogenerator 17 and punching engine 18 are closed, and aircraft coastdown is extremely when aircraft vertical landing
Lower-speed state can stretch out safely outside hatch door 21 until speed is reduced to coaxial rotor 3, and coaxial rotor propeller 3 is logical
It crosses rotation and vertical lift, the vertical landing so that aircraft can slow down is provided.
6. flight characteristicses such as fixed point steerings.Aircraft passes through electromagnetic valve 15, left back solenoid valve behind the coordination combination control right side
Door 19 is closed, and electromagnetic valve 14, left front electromagnetic valve 20 and turbogenerator 17, punching engine 18 and close coupled type are double before the right side
The different working condition of propeller aircraft 3 etc. can flexibly realize that aircraft fixed point such as turns at the flight attitudes, such as VTOL process,
By change coaxial rotor propeller 3 it is differential always away from；Low speed, sub- transonic speed turn to can be in the work shapes of turbogenerator 17
State changes empennage rudder and reaches；Not only steering moment, which can be adjusted, by empennage rudder when supersonic and hypersonic flight can also pass through the right side
Electromagnetic valve 15, left back electromagnetic valve 19 are closed afterwards, and the folding threshold degree of electromagnetic valve 14 and left front electromagnetic valve 20 controls before the right side
Punching engine flow realizes steering to generate big steering moment.Steering characteristics of these multiplicity can be used for the fistfight of empty day with
And other complicated flight environment of vehicle, and an obvious supplement to VTOL flight, big drag braking flight performance.
7. the flight of saving oneself under unsafe condition.When aircraft encounters turbogenerator 17 during pressing across supersonic flight
When stopping or do not work with punching engine 18, can providing lift by 3 spinning of coaxial rotor propeller, (aileron can
Cooperating) slowing down slides.
Claims (1)
1. a kind of supersonic speed unmanned fighter that big drag braking and VTOL can be achieved, 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 equipped with arcuate rotation formula hatch door and coaxial rotor propeller, and cabin provides folding and unfolding sky for coaxial rotor propeller
Between, arcuate rotation formula hatch door shape is bonded with cabin, and coaxial rotor is made of two pairs of blades, and first laser device is mounted on
On wing, as laser sensor or laser weapon, airflow channel is arranged in the subsequent two sides of fuselage and biased downward, fuselage
Two sides are respectively equipped with exhaust duct, and exhaust duct connects airflow channel, be equipped in exhaust duct electromagnetic valve before the right side, it is right after solenoid valve
Door, left back electromagnetic valve and left front electromagnetic valve, exhaust duct both ends open are equipped with porting and exhaust outlet；Wide speed domain turbine hair
Motivation is mounted on aircraft tail portion, intake port layout in front fuselage bottom, turbogenerator be mounted on aircraft interior and
Before the turbogenerator of wide speed domain, punching engine is mounted on the rear side of electromagnetic valve and left back electromagnetic valve behind the right side；
The dynamical system is that aircraft provides the energy source device of power and manipulation under different flying speeds；The dynamical system
Using VTOL dynamical system, tail portion duct turbine power system and two sides of tail punching press dynamical system；Dynamical system is by altogether
Shaft type DCB Specimen propeller, cabin, arcuate rotation formula hatch door composition；Tail portion duct turbine power system is by air intake duct, wide fast domain
Turbogenerator composition, two sides of tail punching press dynamical system by electromagnetic valve before the right side, it is right after electromagnetic valve, left back electromagnetic valve,
Left front electromagnetic valve and punching engine composition；
The flight control system be real-time control state of flight avionics device, in cabin install flight-control computer,
Energy resource system and sensing system, the energy resource system include power supply and fuel tank, the sensing system be equipped with GPS navigator,
Gyroscope, radar, barometertic altimeter, wireless signal transmission instrument, second laser device.
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 |
Applications Claiming Priority (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 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106628163A CN106628163A (en) | 2017-05-10 |
| CN106628163B true CN106628163B (en) | 2018-12-28 |
Family
ID=58843271
Family Applications (1)
| 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 |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106628163B (en) |
Families Citing this family (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| 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 |
| CN112078789B (en) * | 2019-06-14 | 2024-04-09 | 陶德泉 | Hypersonic aircraft |
| CN110816846B (en) * | 2019-11-29 | 2021-05-04 | 集美大学 | Can realize fixed wing unmanned aerial vehicle of vertical take-off |
| CN112648981B (en) * | 2020-12-04 | 2023-01-13 | 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 |
| CN113753231A (en) * | 2021-10-11 | 2021-12-07 | 广东汇天航空航天科技有限公司 | Aircraft and coaxial dual-rotor assembly |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1435355B (en) * | 2002-12-04 | 2011-01-12 | 韩国庆 | Light buzzard-type wing jet plane and its use |
| US8720814B2 (en) * | 2005-10-18 | 2014-05-13 | Frick A. Smith | Aircraft with freewheeling engine |
| US8708273B2 (en) * | 2009-10-09 | 2014-04-29 | Oliver Vtol, Llc | Three-wing, six tilt-propulsion unit, VTOL aircraft |
| CN203740127U (en) * | 2014-03-31 | 2014-07-30 | 冯加伟 | Variant unmanned combat aerial vehicle (UCAV) |
| CN203906120U (en) * | 2014-03-31 | 2014-10-29 | 冯加伟 | Combined engine for unmanned combat aircraft |
| CN103993982A (en) * | 2014-04-25 | 2014-08-20 | 西北工业大学 | Double-S-bend infrared stealth spray pipe structure capable of achieving multi-direction thrust vector control |
-
2017
- 2017-01-13 CN CN201710025513.1A patent/CN106628163B/en not_active Expired - Fee Related
Also Published As
| Publication number | Publication date |
|---|---|
| CN106628163A (en) | 2017-05-10 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106628163B (en) | A kind of supersonic speed unmanned fighter that big drag braking and VTOL can be achieved | |
| US11987352B2 (en) | Fluid systems that include a co-flow jet | |
| JP6191039B2 (en) | VTOL machine | |
| CN106988926B (en) | Whirlpool axis turbofan combined cycle engine | |
| EP3016859B1 (en) | Propulsion system for an aerial vehicle | |
| CN103879556B (en) | Wide flight envelope morphing aircraft | |
| US20210171209A1 (en) | Efficient low-noise aircraft propulsion system | |
| US20140223884A1 (en) | Ultra-efficient propulsor with an augmentor fan circumscribing a turbofan | |
| CN104816824A (en) | Fixed structure type vertical takeoff and landing aircraft based on dual-flight control system and control method for fixed structure type vertical takeoff and landing aircraft | |
| CN109878704A (en) | It is a kind of based on circulation control principle without rudder face aircraft | |
| CN103910060A (en) | Combined-type push/lift airplane | |
| KR101828924B1 (en) | An aircraft including an internal combustion engine and electric motors | |
| EP2871131B1 (en) | Variable geometry helicopter engine inlet | |
| CN109677608A (en) | Tailless flying wing coupling power aircraft | |
| CN206694149U (en) | Whirlpool axle turbofan combined cycle engine | |
| CN103754360A (en) | Similar flying saucer type rotaplane | |
| CN102935891A (en) | Airplane design method and scheme | |
| CN103797229A (en) | Method for adjusting a supersonic air inlet | |
| CN103171758A (en) | Lift-rising method of flying wing type airplane | |
| CN112173065A (en) | Be applied to wing of wing aircraft that verts | |
| CN101804861B (en) | Wing plate for post-stall manipulation control of airplane | |
| CN204701764U (en) | Based on the fixed sturcture formula vertical take-off and landing aircraft (VTOL aircraft) of round trip flight Ore-controlling Role | |
| RU2457151C1 (en) | Manoeuvrable aircraft with gas-dynamic control system | |
| EP2032433A2 (en) | Airfoil having a movable control surface | |
| CN102745332B (en) | Pneumatic type power augmenting device |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20181228 Termination date: 20200113 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |