CN108750101A - A kind of super maneuver high speed compound unmanned rotary wing aircraft, assembly, assembly and disassembly methods - Google Patents
A kind of super maneuver high speed compound unmanned rotary wing aircraft, assembly, assembly and disassembly methods Download PDFInfo
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- CN108750101A CN108750101A CN201810684601.7A CN201810684601A CN108750101A CN 108750101 A CN108750101 A CN 108750101A CN 201810684601 A CN201810684601 A CN 201810684601A CN 108750101 A CN108750101 A CN 108750101A
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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
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/10—Manufacturing or assembling aircraft, e.g. jigs therefor
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
Abstract
The present invention relates to a kind of super maneuver high speed compound unmanned rotary wing aircraft, assembly, assembly and disassembly methods, by installing main rotor system on housing construction, tail-rotor system, promoting oar system, aerofoil system and empennage system so that aircraft is operated in different modalities according to control instruction free switching.The aircraft can be worked with four kinds of operation modes, to adapt to different aerial mission demands.The advantages of having both helicopter, autogyro and fixed-wing so that the excellent properties such as compound unmanned rotary wing system has both high motor-driven, high speed and high safety is reliable.
Description
Technical field
The present invention relates to a kind of super maneuver high speed compound unmanned rotary wing aircrafts, belong to rotor class unmanned vehicle field.
Background technology
The sharpest edges of fixed-wing are that safe, technology maturation, speed are fast, mobility is high, safety and comfort.
The sharpest edges of autogyro are in low cost, high reliability, short take-off and landing ability and rapid deployment, recycling, machine
It is dynamic neatly to execute various tactical missions, it can perform tactical mission.
The sharpest edges of helicopter are there is good low latitude, low-speed performance and unique VTOL and hovering
Performance, thus there is the adaptability outstanding to different task, it is easy to combine compared with existing weapons system, improves its task effect
Can, there is extensive military application prospect.
With the development of artificial intelligence technology, piloted vehicle is replaced by unmanned vehicle, can whole day
Wait on duty, reply dangerous greatly work or repetitive operation dry as dust.
In summary, it is proposed that a motor-driven height of height for having both helicopter, autogyro, fixed-wing and unmanned plane advantage
Conjunction unmanned rotary wing aircraft is replied immediately, has both high motor-driven, high speed and the excellent properties such as high safety is reliable.
Invention content
The purpose of the present invention is：Overcome the deficiencies in the prior art (mainly can vertically rise to adapt to different landing conditions
Drop) and the high motor-driven demand of high speed is taken into account, the present invention provides a kind of super maneuver high speed compound unmanned rotary wing aircraft, can be with four kinds
Operational modal is run, to realize that high motor-driven, high speed, high safety be reliable and the excellent properties such as VTOL.
The object of the invention is achieved by following technical solution：
A kind of super maneuver high speed compound unmanned rotary wing aircraft, by installing main rotor system, tail-rotor on housing construction
System promotes oar system, aerofoil system and empennage system so that aircraft is operated in difference according to control instruction free switching
Mode.
Preferably, the housing construction includes forebody, middle fuselage and rear body；During wherein main rotor system is mounted on
The top of fuselage, tail-rotor system and empennage system are installed in the tail portion of rear body；Oar system is promoted to be mounted on tail-rotor system
Rear portion；Aerofoil system is mounted on the both sides of middle fuselage.
Preferably, Plasma Stealth system is installed on housing construction, by discharging plasma on the body whole body, with
Improve the stealth capabilities of helicopter.
Preferably, the mode includes that helicopter mode, autogyro mode, autogyro are combined with fixed-wing
Mode, helicopter and fixed-wing combined modality.
Preferably, the propulsion oar system includes propelling screws；Propelling screws are variable-distance constant speed paddle, for carrying
For thrust needed for helicopter mode and autogyro mode flight.
Preferably, the aerofoil system includes fixed short limb and aileron；Short limb is for supplementing helicopter mode to rotation
The lift lacked in gyroplane mode conversion process；Rolling of the aileron with main rotor system cooperation for aircraft controls.
Preferably, the empennage system includes band wingtip tailplane and elevator, vertical tail and rudder；Winged
Tip tailplane is controlled for longitudinal stability, and the elevator on tailplane is used for pitching and roll guidance；Tailplane
Wingtip be used for the pneumatic efficiency of empennage of improving the standard；Vertical tail is controlled for lateral stability, the direction on vertical tail
Rudder is used for yaw control.
Preferably, the tail-rotor system includes duct, ducted tail rotor drive motor and ducted tail rotor；Ducted tail rotor drives
Motor and ducted tail rotor are installed in the supporting beam of duct, and ducted tail rotor drive motor drives ducted tail rotor, straight for balancing
The main rotor system torque of machine mode is risen, or yaws and controls for the body of autogyro state with the cooperation of empennage system.
Preferably, duct is located at tailplane top and parallel with vertical tail.
Preferably, the hanging point of payload is set on the short limb, for weapon needed for carry.
Preferably, the weapon that aircraft carries includes aircraft gun, air-to-ground guided missile, air-to-air missile, cruise missile, guides and fry
Bullet；Wherein, aircraft gun is placed in inside forebody, by stretching out outside forebody, attack over the ground and to sky；Air-to-ground guided missile,
Air-to-air missile, cruise missile, guided bomb can carry on short limb, or the rotary force by being arranged inside middle fuselage
Weapon to be launched is rotated to launch window position to execute strike mission by device emitter.
Preferably, the load that aircraft carries includes the O-E Payload and radar for target search.
Preferably, it is communicated by line of sight link and Wei Tong links between aircraft and field war.
Preferably, the aircraft is used suitable for the fistfight with enemy's armed helicopter or subsonic speed fixed-wing.
Preferably, the dynamical system of aircraft includes engine, air intake duct and radome fairing, exhaust system；
Air intake duct and radome fairing are located at forebody top, are used for the air inlet of the importing engine of outer gas stream stable and uniform
Mouthful；It is main rotor system by engine, tail-rotor system and propulsion oar system provide power；Exhaust system is located at middle fuselage two
Side, it is external for the exhaust gas of engine to be discharged.
Preferably, the air intake duct uses backpack S type air intake ducts, for external air flow to be imported engine charge
Mouthful, reduce radar scattering area.
Preferably, the exhaust gas of engine carries out cooling processing before exhaust outlet discharge, is visited to it with reducing infrared equipment
The ability of survey.
Preferably, aircraft realizes torque distribution and Mode-switch by transmission system；The transmission system includes master
Transmission system and propulsion paddle transmission system；
In helicopter mode or helicopter and fixed-wing combined modality, main transmission by the torque of dynamical system in proportion
Distribution is to main rotor system and promotes paddle transmission system；In autogyro mode or autogyro and fixed-wing combination die
State, main transmission, which delivers torque to, promotes paddle transmission system；
Dynamical system and main rotor system are connected by universal hinge in main transmission and clutch, passes through clutch
Break-make realizes the switching of different modalities.
A kind of assembly method of super maneuver high speed compound unmanned rotary wing aircraft, includes the following steps：
1), radar (28) and O-E Payload (29) are mounted on forebody (2), and by radome (1) and forebody (2)
Connection；
2) main transmission (19) and propelling screws transmission system (18), are separately mounted to middle fuselage (3) and rear machine
It is connect in body (4) and by main transmission (19) with propelling screws transmission system (18)；
3) engine (24), is installed to middle fuselage (3) inside, and is connected with main transmission (19) by installing interface
It connects；
4), main rotor system and main transmission are attached：By main rotor propeller hub (21) and main transmission (19)
Connection；High speed main rotor (20) is connect with main rotor propeller hub (21)；By main rotor steerable system (23) and main rotor propeller hub
(21) it connects, is controlled with completing total square and period square；
It 5), will be from the control stick that rotor control system (36) is mounted on main transmission (19)；
6), radome fairing (22) is installed to main rotor propeller hub (21) upper end；
7), air intake duct and radome fairing (25) are connect with middle fuselage (3) and engine (24) air inlet respectively；
8), exhaust system (32) is mounted in middle fuselage (3), and is connect with the exhaust outlet of engine (24)；
9), the equipment of satellite and navigation subsystem (27) is installed in forebody inside the equipment compartment of (2)；
10), fuel tank (35) is installed internal to middle fuselage (3)；
It 11), will be in rotary internal magazine and guided missile (33) installation to middle fuselage (3) ventral；
12), APU (37) is installed into the cabins APU of middle fuselage (3)；
13), ducted tail rotor drive motor (5) is connect with duct (7), and by ducted tail rotor (6) installation and ducted tail rotor
Drive motor (5) and duct (7) connection；
14) propelling screws (17), are mounted on rear body tail portion, and are connect with propelling screws transmission system (18)；
15) include, that short limb aileron (15) is mounted on middle fuselage (3) both sides by short limb (16)；
16), rear body tail portion will be mounted on wingtip tailplane (11), elevator (8)；By vertical tail (10), side
It is mounted on rear body tail portion to rudder (9)；
17), external hair frame (39) of leading is mounted on short limb (16), and external guided missile (40) is installed to external and leads hair frame
(39) on；
18), by counterweight, either extra load is installed to spare load cabin or counterweight cabin (30)；
19), nose-gear (41) and rear undercarriage (42) are separately mounted on forebody (3) and vertical tail (10)；
20), installation radar altimeter (31), marine satellite antenna (13) and Beidou navigation antenna (12).
21, a kind of method for dismounting of super maneuver high speed compound unmanned rotary wing aircraft, which is characterized in that including walking as follows
Suddenly：
1), radar altimeter (31), marine satellite antenna (13) and Beidou navigation antenna (12) and housing construction are disconnected
Connection；
2) external lead, is removed from short limb (16) sends out frame (39) and external guided missile (40)；
3) vertical tail (10) and rudder (9), are removed from tail portion；
4) band wingtip tailplane (11), the elevator (8) of body tail portion, are removed；
5), the short limb (16) for removing middle fuselage (3) both sides includes short limb aileron (15)；
6) propelling screws (17), are disconnected to connect with propelling screws transmission system (18), and are removed；
7) connection of ducted tail rotor drive motor (5) and ducted tail rotor (6), is disconnected, and duct 7 is removed；
8), APU (37) is removed from the cabins APU of middle fuselage (3)；
9), rotary internal magazine and guided missile (33) are removed out of middle fuselage (3) ventral；
10), fuel tank (35) is removed from middle fuselage (3)；
11), the equipment of satellite and navigation subsystem (27) is removed from the inside of the equipment compartment of forebody (2)；
12) connection of exhaust system (32) and middle fuselage (3) and engine (24), is disconnected, and is removed；
13) connection of air intake duct and radome fairing (25) and middle fuselage (3) and engine (24) air inlet, is disconnected, and is removed；
14) connection from rotor control system (36) and the control stick of main transmission (19), is disconnected, and is removed；
15) connection of high-speed rotor (20) and main rotor propeller hub (21), is disconnected, and is removed；
16) connection of main rotor steerable system (23) and main rotor propeller hub (21), is disconnected；
17) connection of main rotor propeller hub (21) and main transmission (19), is disconnected；
18) connection of engine (24) and main transmission (19), is disconnected, and is removed inside middle fuselage (3)；
19) connection of main transmission (19) and propelling screws transmission system (18), is disconnected；
20), main transmission (19) and propelling screws transmission system (18) are removed from body；
21), nose-gear (41) and rear undercarriage (42) are disconnected with forebody (2) and vertical tail (10)；
22) radome (1), is removed；
23) connection of phased-array radar (28) and O-E Payload (29) and forebody (2), is disconnected；
24) counterweight and load in spare load cabin or counterweight cabin (30), are removed；
A kind of operational exertion method of super maneuver high speed compound unmanned rotary wing aircraft, steps are as follows：
According to combat duty, super maneuver high speed compound unmanned rotary wing aircraft takes off mould according to battlefield situation unrestricted choice
State, acquiescence operation mode are helicopter mode；
Before reaching preplanned mission point, super maneuver high speed compound unmanned rotary wing aircraft carries out high-speed flight, into cruise
The acquiescence operation mode in stage, the stage is autogyro+fixed-wing combined modality；
After reaching the predetermined theater of war, target search is carried out, acquiescence operation mode is helicopter+fixed-wing combined modality；
After having executed task, during making a return voyage, acquiescence operation mode is autogyro+fixed-wing combined modality；
After reaching level point, acquiescence operation mode is helicopter mode.
The present invention has the following advantages that compared with prior art：
(1) environmental suitability is strong：Due to can be suitable in helicopter mode or autogyro mode landing
Different field landing conditions；
(2) reliability is high：The system is the peculiar fusion of existing mature technology, and reliability is inevitable very high, and due to being
Unmanned operation, therefore the not life security of entail dangers to people；
(3) round-the-clock：Since the equipment is Unmanned operation, rises and have 24 hours round-the-clock functions on duty；
(4) speed is high；Since cruising condition uses autogyro+fixed-wing combined modality up to 800km/h, more than existing
Some VTOL rotor class aircraft are fast；
(5) mobility is high：Since when executing combat duty, operation mode switches to helicopter+fixed-wing combined modality,
The rotor class aircraft of the far super active service of its mobility；
(6) good economy performance：Due to adding autorotating rotor and fixed-wing mode, the VTOL rotor of active service is compared
The high oil consumption of aircraft, oil consumption is very low, has saved operation cost.
(7) present invention can make to fly by adjust automatically rotor, short limb aileron, empennage, ducted tail rotor and propelling screws
Machine easily realizes the motor-driven rolling of 360 ° of superelevation, high motor-driven yaw and high motor-driven pitching.
Description of the drawings
A kind of super maneuver high speed compound unmanned rotary wing aircraft normal axomometric drawings (gear up) of Fig. 1；
A kind of super maneuver high speed compound unmanned rotary wing aircraft perspective side elevation views (gear up) of Fig. 2；
A kind of super maneuver high speed compound unmanned rotary wing aircraft perspective side elevation views of Fig. 3 (undercarriage opening)；
A kind of super maneuver high speed compound unmanned rotary wing aircraft operation diagrammatic sectional views of Fig. 4；
A kind of super maneuver high speed compound unmanned rotary wing aircraft electrical principles of Fig. 5
Specific implementation mode
The present invention is directed to design a kind of high speed of invention, high motor-driven, safe and reliable and unmanned rotary wing strong environmental suitability flies
Row device.
(1) super maneuver high speed compound unmanned rotary wing aircraft includes：
Housing construction, dynamical system, fuel system, main rotor system, tail-rotor system, aerofoil system, empennage system, transmission
System promotes oar system, steerable system, Landing Gear System, flight control and navigation subsystem, scouting and load subsystem, electricity
Gas subsystem and weapon system composition.
Housing construction includes mainly：Radome 1, forebody 2, middle fuselage 3 and rear body 4.Forebody 2, middle fuselage 3 and after
Fuselage 4 is the agent structure of unmanned plane, the alternating load for bearing inside and outside complexity.
Main rotor system includes mainly：High speed main rotor 20, radome fairing 22 and main rotor propeller hub 21.High speed main rotor 20 is pacified
At the top of middle fuselage, excellent aerodynamic configuration can take into account low speed and high-speed flight；Radome fairing 22 is covered in main rotor propeller hub
On 21, for the flow field around rectification propeller hub to reduce resistance；Main rotor propeller hub 21 is connect with high speed main rotor 20, for bearing
Alternating load from high speed main rotor 20.
Empennage system includes band wingtip tailplane 11 and elevator 8, vertical tail 10 and rudder 9；Band wingtip is horizontal
Empennage 11 is controlled for longitudinal stability, and the elevator 8 on tailplane is used for pitching and roll guidance；The wing of tailplane
Pneumatic efficiency of the tip for empennage of improving the standard；Vertical tail 10 is controlled for lateral stability, the direction on vertical tail 10
Rudder 9 is used for yaw control.
Tail-rotor system includes mainly：Ducted tail rotor drive motor 5, ducted tail rotor 6 and duct 7.Ducted tail rotor drive motor 5
In the supporting beam of duct 7, for driving ducted tail rotor 6 to rotate；Ducted tail rotor 6 is mounted in the supporting beam of duct 7, quilt
Ducted tail rotor drive motor 5 drives, with the torque of the main rotor system of balancing helicopter mode；It is horizontal that duct 7 is located at band wingtip
11 top of empennage and parallel with vertical tail 10, compares non-ducted tail rotor, and vertical duct 7 improves the pneumatic effect of ducted tail rotor 6
Rate.
It includes propelling screws 17 to promote oar system mainly, is mounted on tail-rotor system rear portion；Propelling screws are variable-distance
Constant speed paddle, for providing thrust needed for helicopter mode and autogyro mode flight.
Aerofoil system includes the fixation short limb 16 and aileron 15 for being distributed in 3 both sides of middle fuselage；Short limb 16 is produced in fast state
Raw lift, for supplementing the lift lacked in helicopter mode and autorotating rotor mode mode conversion process, short limb 16 is gone back in addition
If the hanging point of payload, for weapon needed for carry；Rolling of the aileron 15 with main rotor cooperation for aircraft controls.
The present invention can also install Plasma Stealth system on housing construction, by body whole body release plasma
Body, to improve the stealth capabilities of helicopter.
Dynamical system includes mainly：Engine 24, air intake duct and radome fairing 25, exhaust system 32.Engine 24 is mainly used
In for main rotor, tail-rotor and promote paddle power is provided；Air intake duct and radome fairing 25 are located at 2 top of forebody, are used for external gas
Flow the air inlet of the importing engine 24 of stable and uniform；Exhaust system 32 is located at 3 both sides of middle fuselage, for giving up engine 24
Engine body exterior is discharged in gas, and reduces delivery temperature by built-in cooling system, to improve infrared stealth ability；
Fuel system includes mainly：Fuel tank 35.Fuel tank 35 is located inside rear body, is mainly used for carrying fuel oil, with
The fuel oil for meeting certain flow and certain pressure is provided for engine 24, to maintain engine normal operation.
Transmission system includes mainly：Main transmission 19 and propelling screws transmission system 18.Main transmission 19 is located at
Engine torque is distributed to high speed main rotor 20 and propelling screws transmission system 18 by main rotor lower part essentially according to ratio；
Propelling screws transmission system 18 is located inside rear body 4, is mainly connect with main transmission 19, and torque is transferred to propulsion
Propeller 17.Specifically：
In helicopter mode or helicopter and fixed-wing combined modality, main transmission by the torque of dynamical system in proportion
Distribution is to main rotor system and promotes paddle transmission system；In autogyro mode or autogyro and fixed-wing combination die
State, main transmission, which delivers torque to, promotes paddle transmission system.
Steerable system includes mainly：Main rotor manipulates 23, accelerator operating system, tail-rotor steerable system, Aileron control system
With from rotor control system 36.Main rotor manipulates 23 and is mainly used for completing the manipulations such as total square, the period square of main rotor system, with control
The working condition of main rotor processed；Accelerator operating system is used to control engine 24 and the engine power control of APU37；Tail-rotor is grasped
Vertical system is used to manipulate total square of tail-rotor；Aileron control system is used for pitching, yaw and roll guidance under fixed-wing state.From
Rotor control system 36 is used to operate the pitching, rolling and yaw of autogyro mode.
Fly control with navigation subsystem 27 by flight-control computer, sensor (such as radar altimeter 31, Beidou navigation day
Line 12, marine satellite antenna 13, defend it is logical 26), servo start equipment three parts composition, the redundance for being equipped with autonomous flight flies automatically
Row control system can ensure aircraft in helicopter mode, helicopter+fixed-wing mode (high speed mode), autogyro
Mode and autogyro+fixation are flown with mode (high speed mode), and can be safely smoothly between this several mode
Switch over control.
It scouts with load subsystem and includes mainly：Phased-array radar 28, O-E Payload 29, spare load cabin or counterweight
Cabin is mainly used for battle reconnaissance and Situation Awareness, to help aircraft to carry out mission planning.
Weapon system includes mainly：It is external to lead hair frame 39, external guided missile 40, built-in magazine missile launcher 34 and rotary
Built-in magazine and guided missile 33 mainly hang over attack of the different guided missile completions to specific objective according to task.It is external to lead hair frame 39
It is mounted on short limb 16 with external guided missile 40, built-in magazine missile launcher 34 and rotary internal magazine and guided missile 33 are mounted on
In ventral, the transmitting of guided missile is controlled by fire control system.From aircraft carry weapon type description, can carrying arms include boat
Big gun, air-to-ground guided missile, air-to-air missile, cruise missile, guided bomb；Wherein, aircraft gun is placed in inside forebody, before stretching
External fuselage attacked over the ground and to sky；Air-to-ground guided missile, air-to-air missile, cruise missile, guided bomb can carry short
On the wing, or the rotary arm discharge device by being arranged inside middle fuselage, weapon to be launched is rotated into launch window
Position is to execute strike mission.
Electrical system includes mainly：APU (power generation) 37, cable and related electric equipment.Be mainly used for full function source into
Row management, and distributed management and monitoring are carried out to equipment by way of CAN bus.
It is communicated by line of sight link and Wei Tong links between aircraft and field war.Flying instrument is for the motor-driven of superelevation
Performance can easily win in the fistfight with enemy's armed helicopter and subsonic speed fixed-wing, and easily hide ground firepower
Attack.
(2) main assemble flow according to the present invention is：
1), phased-array radar 28 and O-E Payload 29 are mounted on forebody 2, and radome 1 and forebody 2 are connected
It connects；
2) it is ranked among in, being mounted on main transmission 19 and propelling screws transmission system 18 in 3 and rear body 4；
3), main transmission 19 is connect with propelling screws transmission system 18；
4) it is ranked among in, being installed to engine 24 inside 3, and connect with main transmission 19 by installing interface；
5), main rotor propeller hub 21 is connect with main transmission 19；
6), high speed main rotor 20 is connect with main rotor propeller hub 21；
7) main rotor steerable system 23 is connect with main rotor propeller hub 21, is controlled with completing total square and period square；
It 8), will be from the control stick that rotor control system 36 is mounted on main transmission 19；
9), radome fairing 22 is installed to 21 upper end of main rotor propeller hub；
10), air intake duct and radome fairing 25 are connect with middle fuselage 3 and 24 air inlet of engine respectively；
11), exhaust system 32 is mounted in middle fuselage 3, and is connected respectively with the exhaust outlet of engine 24 and middle fuselage 3
It connects；
12), the equipment of satellite and navigation subsystem 27 is installed to inside the equipment compartment of forebody 2；
13), fuel tank 35 is installed to middle fuselage 3；
It 14), will be in rotary internal magazine and the installation to 3 ventral of middle fuselage of guided missile 33；
15), APU (power generation) 37 is installed into the cabins APU of middle fuselage 3；
16) ducted tail rotor drive motor 5 is connect with vertical duct 7, and the installation of ducted tail rotor 6 is driven with ducted tail rotor
Dynamic motor 5 and vertical duct 7 connect；
17) propelling screws 17, are mounted on body tail portion, and are connect with propelling screws transmission system 18；
18) short limb 16 (including short limb aileron 15), is mounted on 3 both sides of middle fuselage；
19), afterbody will be mounted on wingtip tailplane 11 (including band wingtip tailplane elevator 8)；
20) vertical tail 10 (including vertical tail rudder 9), is mounted on afterbody；
21), external hair frame 39 of leading is mounted on short limb 16, and the installation of external guided missile 40 is led to external on hair frame 39；
22), by counterweight, either extra load is installed to spare load cabin or counterweight cabin 30；
23), nose-gear 41 and rear undercarriage 42 are separately mounted on forebody 3 and vertical tail 10；
24) radar altimeter 31, marine satellite antenna 13 and Beidou navigation antenna 12, are installed to body corresponding position,
Part Fig. 2.
Involved dismounting flow：
1), radar altimeter 31, marine satellite antenna 13 and Beidou navigation antenna 12 are disconnected with body；
2) external lead, is removed from short limb 16 sends out frame 39 and external guided missile 40；
3), vertical tail 10 (including vertical tail rudder 9) is removed from tail portion；
4) the band wingtip tailplane 11 (including band wingtip tailplane elevator 8) of body tail portion, is removed；
5) short limb 16 (including short limb aileron 15) of 3 both sides of middle fuselage, is removed；
6) propelling screws 17, are disconnected to connect with propelling screws transmission system 18, and are removed；
7) connection of ducted tail rotor drive motor 5 and tail-rotor 6, is disconnected, and vertical duct 7 is removed；
8), APU (power generation) 37 is removed from the cabins APU of middle fuselage 3；
9), rotary internal magazine and guided missile 33 are removed out of middle fuselage 3 ventral；
10), fuel tank 35 is removed from middle fuselage 3；
11), the equipment of satellite and navigation subsystem 27 is removed from the inside of the equipment compartment of forebody 2；
12) connection of exhaust system 32 and middle fuselage 3 and engine 24, is disconnected, and is removed；
13) connection of air intake duct and radome fairing 25 and 24 air inlet of middle fuselage 3 and engine, is disconnected, and is removed；
14) connection from rotor control system 36 and the control stick of main transmission 19, is disconnected, and is removed；
15) connection of high-speed rotor 20 and main rotor propeller hub 21, is disconnected, and is removed；
16) connection of main rotor steerable system 23 and main rotor propeller hub 21, is disconnected；
17) connection of main rotor propeller hub 21 and main transmission 19, is disconnected；
18) connection of engine 24 and main transmission 19, is disconnected, and is removed from 3 inside of middle fuselage；
19) connection of main transmission 19 and propelling screws transmission system 18, is disconnected；
20), main transmission 19 and propelling screws transmission system 18 are removed from body；
21), nose-gear 41 and rear undercarriage 42 are disconnected on forebody 2 and vertical tail 10；
22) radome 1, is removed；
23) connection of phased-array radar 28 and O-E Payload 29 and forebody 2, is disconnected；
24) spare load cabin or the counterweight in counterweight cabin 30 and load, are removed；
(3) functional mode explanation
The operating mode of super maneuver high speed compound unmanned rotary wing aircraft includes：
Helicopter mode
Helicopter+fixed-wing mode (high-speed helicopter mode)
Autogyro mode
Autogyro+fixation is with mode (high speed autogyro mode)
1), helicopter mode → autogyro mode
The transmission break-make between free switching rotor and engine is realized by clutch, to realize helicopter and rotate certainly
The free switching of the wing, and the motor-driven and stable state to full machine is realized by propelling screws, empennage system, aileron and main rotor system
Control.
The state is suitable for cruising condition and maneuvering flight state, realizes supermaneuver flight.
2), autorotating rotor mode → helicopter mode
Slow down the torque load pressure of transmission system using the lift of short limb in flat winged state, and restores helicopter mode
Transmission system position, connect clutch, and utilize tail-rotor system balancing rotor torque, finally realize mode conversion.
The state is suitable for cruising condition.
3) ground lands and takes off
Super maneuver high speed compound unmanned rotary wing aircraft both can land and take off in helicopter mode, can also rotate certainly
Land and take off under wing machine state, runway is not strict with, adaptability is high.
(4) Universal electric system forms explanation
Universal electric system includes mainly：APU, airborne power supply, power-supply management system, airborne equipment and motor etc..Substantially
Theory of constitution is as shown in Figure 5.
Following function may be implemented：
1) APU power generations are startup power supply, emergency power supply and airborne power supply charging；
2) APU is matched by center supplies electricity to airborne equipment and motor power supply；
3) emergency cell can power directly to airborne equipment under the state of emergency；
4) on-board batteries can power directly to airborne equipment；
5) power-supply management system is according to the state of the art free switching power supply mode of aircraft, and monitors entire power-supply system
Health status.
The present invention realizes following function：
A) aircraft subsystem has remote control, program-controlled flight performance；
B) flying instrument is provided simultaneously with artificial intelligence ability for sighting distance and over the horizon Situation Awareness System, can be according to state
Urine scent unfriendly target, and complete high evasive tactics during being battled with enemy plane and act, has ability of self-teaching, can be
The tactical operation of enemy plane is constantly accumulated during being battled with enemy plane and makes assessment, to identify the tactics loophole of enemy plane, is caught
Chance is attacked；
C) super maneuver high speed compound unmanned rotary wing aircraft carries Plasma Stealth system, can be discharged on the body whole body
Plasma, to improve the stealth capabilities of helicopter；
D) cooling processing is carried out before engine exhaust port discharge, to have reduced the ability that infrared equipment detects it；
E) engine inlets use backpack S type air intake ducts, to reduce radar scattering area；
F) there is command and control subsystem ground control to control and aerial mission is planned and management function, take into account information processing
Function has and receives vision signal, real-time processing/storage image, data investigation and information and the abilities such as report, distribute, and can be with
Higher level commanding agency, information handling center are connected；
G) observing and controlling and information transmission subsystem system have by line of sight link and satellite communications link remote control, telemetering, with
The functions such as track, positioning, information transmission, have multimachine, multistation compatible operations and certain anti-intercepting and capturing, anti-interference ability；
H) task device subsystem has the function of that round-the-clock obtains target image information in real time round the clock, can find rapidly,
Capture, identification, positioning and tracking target；The ability for implementing to attack in real time with over the ground/waterborne target；
I) comprehensive coverage subsystem has Measuring error, communication and the ability of simulated training.
Basic performance：
The operation section of super maneuver high speed compound unmanned rotary wing aircraft is shown in that Fig. 4 is：According to combat duty, super maneuver high speed
Compound unmanned rotary wing aircraft takes off mode according to battlefield situation unrestricted choice, and the mode of taking off of recommendation is helicopter mode；It arrives
Up to before preplanned mission point, super maneuver high speed compound unmanned rotary wing aircraft carries out high-speed flight, and the cruise mode of recommendation is certainly
Switch rotor machine+fixed-wing combined modality；After reaching the predetermined theater of war, target search is carried out, the model of flight of recommendation is to go straight up to
Machine+fixed-wing combined modality；After having executed task, during making a return voyage, model of flight is recommended as autogyro+fixed-wing combination
Mode；After reaching level point, the landing mode of recommendation is helicopter mode.
The above, best specific implementation mode only of the invention, but scope of protection of the present invention is not limited thereto,
Any one skilled in the art in the technical scope disclosed by the present invention, the change or replacement that can be readily occurred in,
It should be covered by the protection scope of the present invention.
The content that description in the present invention is not described in detail belongs to the known technology of professional and technical personnel in the field.
Claims (21)
1. a kind of super maneuver high speed compound unmanned rotary wing aircraft, it is characterised in that:By installing main rotor on housing construction
System, promotes oar system, aerofoil system and empennage system at tail-rotor system so that aircraft is according to control instruction free switching
It is operated in different modalities.
2. aircraft according to claim 1, it is characterised in that：The housing construction include forebody, middle fuselage and
Rear body；Wherein main rotor system is mounted on the top of middle fuselage, and tail-rotor system and empennage system are installed in rear body
Tail portion；Oar system is promoted to be mounted on tail-rotor system rear portion；Aerofoil system is mounted on the both sides of middle fuselage.
3. aircraft according to claim 1, it is characterised in that：Plasma Stealth system is installed on housing construction,
By discharging plasma on the body whole body, to improve the stealth capabilities of helicopter.
4. aircraft according to claim 1 or 2 or 3, it is characterised in that：The mode include helicopter mode, from
Switch rotor machine mode, autogyro and fixed-wing combined modality, helicopter and fixed-wing combined modality.
5. aircraft according to claim 4, it is characterised in that：The propulsion oar system includes propelling screws；It pushes away
It is variable-distance constant speed paddle into propeller, for providing thrust needed for helicopter mode and autogyro mode flight.
6. aircraft according to claim 5, it is characterised in that：The aerofoil system includes fixed short limb and aileron；
Short limb is for supplementing the lift that helicopter mode is lacked into autogyro mode conversion process；Aileron is matched with main rotor system
Share the rolling control in aircraft.
7. aircraft according to claim 6, it is characterised in that：The empennage system include band wingtip tailplane and
Elevator, vertical tail and rudder；Band wingtip tailplane is controlled for longitudinal stability, and the elevator on tailplane
For pitching and roll guidance；Pneumatic efficiency of the wingtip of tailplane for empennage of improving the standard；Vertical tail is for laterally
Stability control, the rudder on vertical tail are used for yaw control.
8. the aircraft according to claim 4 or 7, it is characterised in that：The tail-rotor system includes duct, ducted tail rotor
Drive motor and ducted tail rotor；Ducted tail rotor drive motor and ducted tail rotor are installed in the supporting beam of duct, ducted tail rotor
Drive motor drives ducted tail rotor, is used for the main rotor system torque of balancing helicopter mode, or match with empennage system and share
Control is yawed in the body of autogyro state.
9. aircraft according to claim 8, it is characterised in that：Duct is located at tailplane top and is put down with vertical tail
Row.
10. aircraft according to claim 6, it is characterised in that：The hanging point that payload is set on the short limb, is used for
Weapon needed for carry.
11. according to the aircraft described in claims 1 or 2 or 6, it is characterised in that：The weapon that aircraft carries includes aircraft gun, sky
Surface-to-surface missile (SSM), air-to-air missile, cruise missile, guided bomb；Wherein, aircraft gun is placed in inside forebody, by stretching out forebody
Outside attacked over the ground and to sky；Air-to-ground guided missile, air-to-air missile, cruise missile, guided bomb can carry in short limb
On, or the rotary arm discharge device by being arranged inside middle fuselage, weapon to be launched is rotated into launch window position
It sets to execute strike mission.
12. aircraft according to claim 1 or 2 or 3, it is characterised in that：The load that aircraft carries includes being used for mesh
Mark the O-E Payload and radar of search.
13. aircraft according to claim 1 or 2 or 3, it is characterised in that：Pass through sighting distance between aircraft and field war
Link and Wei Tong links are communicated.
14. aircraft according to claim 1 or 2 or 3, it is characterised in that：The aircraft is suitable for and enemy's force
It is used in the fistfight of dress helicopter or subsonic speed fixed-wing.
15. aircraft according to claim 8, it is characterised in that：The dynamical system of aircraft includes engine, air intake duct
And radome fairing, exhaust system；
Air intake duct and radome fairing are located at forebody top, are used for the air inlet of the importing engine of outer gas stream stable and uniform；
It is main rotor system by engine, tail-rotor system and propulsion oar system provide power；Exhaust system is located at middle fuselage both sides, uses
It is external in the exhaust gas of engine to be discharged.
16. aircraft according to claim 15, it is characterised in that：The air intake duct uses backpack S type air intake ducts,
For external air flow to be imported engine intake, radar scattering area is reduced.
17. aircraft according to claim 15, it is characterised in that：The exhaust gas of engine carries out before exhaust outlet discharge
Cooling is handled, to reduce the ability that infrared equipment detects it.
18. aircraft according to claim 1 or 2 or 3, it is characterised in that：Aircraft realizes torque by transmission system
Distribution and Mode-switch；The transmission system includes main transmission and propulsion paddle transmission system；
In helicopter mode or helicopter and fixed-wing combined modality, the torque of dynamical system is divided in portion by main transmission
To main rotor system and promote paddle transmission system；It is main in autogyro mode or autogyro and fixed-wing combined modality
Transmission system, which delivers torque to, promotes paddle transmission system；
Dynamical system and main rotor system are connected by universal hinge in main transmission and clutch, passes through the break-make of clutch
Realize the switching of different modalities.
19. a kind of assembly method of the super maneuver high speed compound unmanned rotary wing aircraft described in claim 15, which is characterized in that
Include the following steps：
1), radar (28) and O-E Payload (29) are mounted on forebody (2), and even by radome (1) and forebody (2)
It connects；
2) main transmission (19) and propelling screws transmission system (18), are separately mounted to middle fuselage (3) and rear body (4)
In and main transmission (19) connect with propelling screws transmission system (18)；
3) engine (24), is installed to middle fuselage (3) inside, and is connect with main transmission (19) by installing interface；
4), main rotor system and main transmission are attached：Main rotor propeller hub (21) is connect with main transmission (19)；
High speed main rotor (20) is connect with main rotor propeller hub (21)；Even by main rotor steerable system (23) and main rotor propeller hub (21)
It connects, is controlled with completing total square and period square；
It 5), will be from the control stick that rotor control system (36) is mounted on main transmission (19)；
6), radome fairing (22) is installed to main rotor propeller hub (21) upper end；
7), air intake duct and radome fairing (25) are connect with middle fuselage (3) and engine (24) air inlet respectively；
8), exhaust system (32) is mounted in middle fuselage (3), and is connect with the exhaust outlet of engine (24)；
9), the equipment of satellite and navigation subsystem (27) is installed in forebody inside the equipment compartment of (2)；
10), fuel tank (35) is installed internal to middle fuselage (3)；
It 11), will be in rotary internal magazine and guided missile (33) installation to middle fuselage (3) ventral；
12), APU (37) is installed into the cabins APU of middle fuselage (3)；
13) ducted tail rotor drive motor (5) is connect with duct (7), and ducted tail rotor (6) installation is driven with ducted tail rotor
Motor (5) and duct (7) connection；
14) propelling screws (17), are mounted on rear body tail portion, and are connect with propelling screws transmission system (18)；
15) include, that short limb aileron (15) is mounted on middle fuselage (3) both sides by short limb (16)；
16), rear body tail portion will be mounted on wingtip tailplane (11), elevator (8)；By vertical tail (10), rudder
(9) it is mounted on rear body tail portion；
17), external hair frame (39) of leading is mounted on short limb (16), and external guided missile (40) installation is led into hair frame (39) to external
On；
18), by counterweight, either extra load is installed to spare load cabin or counterweight cabin (30)；
19), nose-gear (41) and rear undercarriage (42) are separately mounted on forebody (3) and vertical tail (10)；
20), installation radar altimeter (31), marine satellite antenna (13) and Beidou navigation antenna (12).
20. a kind of method for dismounting of the super maneuver high speed compound unmanned rotary wing aircraft described in claim 15, which is characterized in that
Include the following steps：
1), radar altimeter (31), marine satellite antenna (13) and Beidou navigation antenna (12) are disconnected with housing construction；
2) external lead, is removed from short limb (16) sends out frame (39) and external guided missile (40)；
3) vertical tail (10) and rudder (9), are removed from tail portion；
4) band wingtip tailplane (11), the elevator (8) of body tail portion, are removed；
5), the short limb (16) for removing middle fuselage (3) both sides includes short limb aileron (15)；
6) propelling screws (17), are disconnected to connect with propelling screws transmission system (18), and are removed；
7) connection of ducted tail rotor drive motor (5) and ducted tail rotor (6), is disconnected, and duct 7 is removed；
8), APU (37) is removed from the cabins APU of middle fuselage (3)；
9), rotary internal magazine and guided missile (33) are removed out of middle fuselage (3) ventral；
10), fuel tank (35) is removed from middle fuselage (3)；
11), the equipment of satellite and navigation subsystem (27) is removed from the inside of the equipment compartment of forebody (2)；
12) connection of exhaust system (32) and middle fuselage (3) and engine (24), is disconnected, and is removed；
13) connection of air intake duct and radome fairing (25) and middle fuselage (3) and engine (24) air inlet, is disconnected, and is removed；
14) connection from rotor control system (36) and the control stick of main transmission (19), is disconnected, and is removed；
15) connection of high-speed rotor (20) and main rotor propeller hub (21), is disconnected, and is removed；
16) connection of main rotor steerable system (23) and main rotor propeller hub (21), is disconnected；
17) connection of main rotor propeller hub (21) and main transmission (19), is disconnected；
18) connection of engine (24) and main transmission (19), is disconnected, and is removed inside middle fuselage (3)；
19) connection of main transmission (19) and propelling screws transmission system (18), is disconnected；
20), main transmission (19) and propelling screws transmission system (18) are removed from body；
21), nose-gear (41) and rear undercarriage (42) are disconnected with forebody (2) and vertical tail (10)；
22) radome (1), is removed；
23) connection of phased-array radar (28) and O-E Payload (29) and forebody (2), is disconnected；
24) counterweight and load in spare load cabin or counterweight cabin (30), are removed；
21. a kind of operational exertion method of super maneuver high speed compound unmanned rotary wing aircraft described in claim 1, feature exist
In：
According to combat duty, super maneuver high speed compound unmanned rotary wing aircraft takes off mode according to battlefield situation unrestricted choice, writes from memory
It is helicopter mode to recognize operation mode；
Before reaching preplanned mission point, super maneuver high speed compound unmanned rotary wing aircraft carries out high-speed flight, into cruising phase,
The acquiescence operation mode in the stage is autogyro+fixed-wing combined modality；
After reaching the predetermined theater of war, target search is carried out, acquiescence operation mode is helicopter+fixed-wing combined modality；
After having executed task, during making a return voyage, acquiescence operation mode is autogyro+fixed-wing combined modality；
After reaching level point, acquiescence operation mode is helicopter mode.
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| CN201810684601.7A CN108750101A (en) | 2018-06-28 | 2018-06-28 | A kind of super maneuver high speed compound unmanned rotary wing aircraft, assembly, assembly and disassembly methods |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110510115A (en) * | 2019-08-19 | 2019-11-29 | 北京遥感设备研究所 | A kind of multi-purpose unmanned aerial vehicle |
| CN111498104A (en) * | 2020-04-20 | 2020-08-07 | 飞的科技有限公司 | Aircraft with a flight control device |
| CN111619800A (en) * | 2020-06-05 | 2020-09-04 | 中国科学院长春光学精密机械与物理研究所 | Tail sitting type vertical take-off and landing unmanned aerial vehicle |
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Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2439400Y (en) * | 2000-09-08 | 2001-07-18 | 韩秀文 | Helicopter with wings |
| CN1458030A (en) * | 2003-05-26 | 2003-11-26 | 韩培洲 | Horizontal and vertical take-off and landing plane with tilted front rotary wing |
| CN101010235A (en) * | 2004-07-02 | 2007-08-01 | 塞米肯公司 | Hybrid aircraft |
| CN101423117A (en) * | 2008-12-05 | 2009-05-06 | 北京航空航天大学 | Tilt-rotor plane operated and propelled by thrust scull and slipstream rudder |
| CN101607594A (en) * | 2008-01-30 | 2009-12-23 | 尤洛考普特公司 | The letter road reactive torque blade of optimizing autogiro is with method that minimizes noise jamming and the letter road reactive torque blade that obtains thus |
| CN101618763A (en) * | 2008-07-02 | 2010-01-06 | 孙为红 | Miniature high-speed vertical-lifting self rotor aircraft |
| CN202226057U (en) * | 2011-07-28 | 2012-05-23 | 西北工业大学 | Rotatable aerofoil airplane with variable flight mode |
| US20140061367A1 (en) * | 2012-07-27 | 2014-03-06 | Eurocopter Deutschland Gmbh | Compound helicopter |
| CN103661929A (en) * | 2013-12-19 | 2014-03-26 | 南京航空航天大学 | Plasma unmanned aerial vehicle |
| CN203946273U (en) * | 2014-05-16 | 2014-11-19 | 华东理工大学 | The little minute vehicle of a kind of coaxial double-rotary wing formula |
| US9056674B2 (en) * | 2010-09-09 | 2015-06-16 | Groen Brothers Aviation, Inc. | Detachable rotor blade fairing apparatus and method |
| CN206141828U (en) * | 2016-10-12 | 2017-05-03 | 张梓宸 | Unmanned rotation rotor helicopter |
-
2018
- 2018-06-28 CN CN201810684601.7A patent/CN108750101A/en active Pending
Patent Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2439400Y (en) * | 2000-09-08 | 2001-07-18 | 韩秀文 | Helicopter with wings |
| CN1458030A (en) * | 2003-05-26 | 2003-11-26 | 韩培洲 | Horizontal and vertical take-off and landing plane with tilted front rotary wing |
| CN101010235A (en) * | 2004-07-02 | 2007-08-01 | 塞米肯公司 | Hybrid aircraft |
| CN101607594A (en) * | 2008-01-30 | 2009-12-23 | 尤洛考普特公司 | The letter road reactive torque blade of optimizing autogiro is with method that minimizes noise jamming and the letter road reactive torque blade that obtains thus |
| CN101618763A (en) * | 2008-07-02 | 2010-01-06 | 孙为红 | Miniature high-speed vertical-lifting self rotor aircraft |
| CN101423117A (en) * | 2008-12-05 | 2009-05-06 | 北京航空航天大学 | Tilt-rotor plane operated and propelled by thrust scull and slipstream rudder |
| US9056674B2 (en) * | 2010-09-09 | 2015-06-16 | Groen Brothers Aviation, Inc. | Detachable rotor blade fairing apparatus and method |
| CN202226057U (en) * | 2011-07-28 | 2012-05-23 | 西北工业大学 | Rotatable aerofoil airplane with variable flight mode |
| US20140061367A1 (en) * | 2012-07-27 | 2014-03-06 | Eurocopter Deutschland Gmbh | Compound helicopter |
| CN103661929A (en) * | 2013-12-19 | 2014-03-26 | 南京航空航天大学 | Plasma unmanned aerial vehicle |
| CN203946273U (en) * | 2014-05-16 | 2014-11-19 | 华东理工大学 | The little minute vehicle of a kind of coaxial double-rotary wing formula |
| CN206141828U (en) * | 2016-10-12 | 2017-05-03 | 张梓宸 | Unmanned rotation rotor helicopter |
Non-Patent Citations (2)
| Title |
|---|
| 姚卫星: "《飞机结构设计》", 30 April 2016 * |
| 曹美龙: "《航空与战争》", 31 January 2014 * |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2020250010A1 (en) | 2019-06-12 | 2020-12-17 | Chong Qing Liang Jiang Aircraft Design Institute Ltd. | Operating method for a convertible uav |
| WO2020250029A1 (en) | 2019-06-12 | 2020-12-17 | Chong Qing Liang Jiang Aircrraft Design Institute Ltd. | Method and convertible vtol or evtol aircraft for transition from helicopter mode to gyroplane mode and vice versa |
| CN110510115A (en) * | 2019-08-19 | 2019-11-29 | 北京遥感设备研究所 | A kind of multi-purpose unmanned aerial vehicle |
| CN111498104A (en) * | 2020-04-20 | 2020-08-07 | 飞的科技有限公司 | Aircraft with a flight control device |
| CN111619800A (en) * | 2020-06-05 | 2020-09-04 | 中国科学院长春光学精密机械与物理研究所 | Tail sitting type vertical take-off and landing unmanned aerial vehicle |
| CN111964538A (en) * | 2020-08-19 | 2020-11-20 | 航天科工通信技术研究院有限责任公司 | Guided missile attack system of autorotation rotor mechanism |
| CN113120244A (en) * | 2021-04-27 | 2021-07-16 | 成都飞机工业（集团）有限责任公司 | Design method for improving performance of backpack parallel double-engine double-S-bend air inlet passage |
| CN113985926A (en) * | 2021-10-22 | 2022-01-28 | 航天科工通信技术研究院有限责任公司 | Unmanned aerial vehicle guidance missile attack system |
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| CN116124407A (en) * | 2023-04-10 | 2023-05-16 | 中国空气动力研究与发展中心低速空气动力研究所 | Test method for obtaining influence of radar wake on aerodynamic characteristics of helicopter tail piece |
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Application publication date: 20181106 |