CN104973234A - Aircraft using distributed electric ducted fan flap lift-rising system - Google Patents
Aircraft using distributed electric ducted fan flap lift-rising system Download PDFInfo
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- CN104973234A CN104973234A CN201510297892.0A CN201510297892A CN104973234A CN 104973234 A CN104973234 A CN 104973234A CN 201510297892 A CN201510297892 A CN 201510297892A CN 104973234 A CN104973234 A CN 104973234A
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Abstract
The present invention discloses an aircraft using a distributed electric ducted fan flap lift-rising system. The aircraft symmetrically arranges two distributed electric ducted fan flap lift-rising systems on both sides of the front middle part of the fuselage; the distributed electric ducted fan wing flap lift system has relatively large wingspan and aspect ratio; the number of electric ducted fans arranged on the leading edge is relatively large; the rear middle part of the fuselage is provided with a lift fan; rear wings are symmetrically disposed both sides of the rear middle part of the fuselage; the center of gravity of the aircraft is located in the middle of the fuselage; and the aircraft has a tandem wing layout. The aircraft of the present invention has the advantages of small friction, and no pollution and low noise of the electric ducted fan.
Description
Technical field
The present invention relates to a kind of aircraft, particularly a kind of aircraft using distributed electric ducted fan wing flap high-lift system.
Background technology
Patent 201510232718.8 discloses a kind of distributed electric ducted fan wing flap high-lift system and hovercar thereof, this distributed electric ducted fan wing flap high-lift system is provided with some electric ducted fans in wing top airfoil leading edge, the slip-stream of ducted fan can flow to wing top airfoil trailing edge after outflow duct exhausr port, power-boosting is carried out to wing, because electric ducted fan has several, and with the leading edge linear rank of suitable spacing distance at wing, ducted fan slip-stream simultaneously can pull more air flowing around, so wing top airfoil has a large amount of air from the leading edge tangential flowing of edge high speed backward, wing is made to produce large lift coefficient, the trailing edge that position, electric ducted fan place is corresponding, be provided with trailing edge flap, during electric ducted fan work, by inclined under trailing edge flap, like this by generation two power, one is produced the thrust of forward upward by the fan slip that trailing edge flap local derviation flows to the back lower place, two is the lift that wing inclined under trailing edge flap produces rearwardly and upwardly, by arranging the suitable aforesaid downward angle degree of trailing edge flap, makes in above-mentioned two power, offset before and after component forward and backward, the lift that remaining is exactly upwards is made a concerted effort, this design is very ingenious, and distributed electric ducted fan wing flap high-lift system uses electric energy work, pollute and noise little, very environmental protection, but this system just applies to hovercar in this patent, do not apply to special VTOL craft, and hovercar is due to various constraint, wing span and the aspect ratio of distributed electric ducted fan wing flap high-lift system are relatively little, the electric ducted fan number that the leading edge of a wing is arranged is relatively less, make the 1ift-drag ratio of distributed electric ducted fan wing flap high-lift system low, lift is little, less economical, load-carrying is little.
Patent 201410173022.8 discloses a kind of duct aerofoil system and uses the aircraft of this system, this duct aerofoil system is made a concerted effort by the lift arranging the suitable angle of attack and trailing edge flap aforesaid downward angle degree and enable this system produce upwards, this aircraft is arranged at aircraft fuselage front part sides duct aerofoil system, wing and lift fan are arranged at aircraft fuselage postmedian, enable aircraft vertical takeoff and landing (VTOL), and vertical takeoff and landing (VTOL) state is smooth-going to level flight condition conversion, and deadweight is little simultaneously; But aircraft adopts two duct aerofoil system, there is huge facade each duct aerofoil system left and right sides, two duct aerofoil system have 4 pieces of huge facades, cause friction drag large, this design is simultaneously relatively preferably uses the driving engine adopting fossil fuel, the not too electronic mode of suitable utilization, makes pollution and noise greatly, not environmentally.
Summary of the invention
Object of the present invention is just to provide a kind of aircraft using distributed electric ducted fan wing flap high-lift system, and this aircraft increases 1ift-drag ratio and the lift of distributed electric ducted fan wing flap high-lift system, improves economy and load-carrying ability; This uses, and the aircraft friction drag of distributed electric ducted fan wing flap high-lift system is little, not pollution, and noise is little, and the feature of environmental protection is good.
The present invention uses the aircraft of distributed electric ducted fan wing flap high-lift system, comprise distributed electric ducted fan wing flap high-lift system, fuselage, rear wing, lift fan, it is characterized in that: described distributed electric ducted fan wing flap high-lift system is two and is arranged at fuselage middle front part both sides symmetrically, wing span and the aspect ratio of distributed electric ducted fan wing flap high-lift system are relatively large, the electric ducted fan number that the leading edge of a wing is arranged is relatively many, fuselage postmedian is provided with lift fan, be provided with rear wing to fuselage postmedian bilateral symmetry, aircraft center of gravity is positioned at waist, aircraft is tandem wing layout.
The present invention uses wing span and the aspect ratio of the distributed electric ducted fan wing flap high-lift system of the aircraft enlarged relative of distributed electric ducted fan wing flap high-lift system, relatively increase the number of the electric ducted fan being arranged at the leading edge of a wing, also 1ift-drag ratio and the lift of distributed electric ducted fan wing flap high-lift system is just increased, improve economy and load-carrying ability, in the present invention, the number of electric ducted fan that distributed electric ducted fan wing flap high-lift system comprises is 4; Two distributed electric ducted fan wing flap high-lift systems are arranged at fuselage middle front part both sides symmetrically, at fuselage postmedian, lift fan is set, fuselage postmedian bilateral symmetry rear wing is set simultaneously, because aircraft center of gravity is positioned at waist, distributed like this electric ducted fan wing flap high-lift system, can most of weight of load aircraft when flying just closer to aircraft center of gravity; Lift fan and rear wing more farther from aircraft center of gravity, only need load aircraft fraction weight during flight; Although the duct of each electric ducted fan has two facades in left and right in distributed electric ducted fan wing flap high-lift system, have certain friction drag, facade area is relatively little, and cumulative resistance is still relatively little; Distributed electric ducted fan wing flap high-lift system adopts electric ducted fan simultaneously, and does not use driving engine and fossil fuel, and thus do not pollute, noise is little.
Beneficial effect of the present invention: the present invention uses the aircraft of distributed electric ducted fan wing flap high-lift system to increase 1ift-drag ratio and the lift of distributed electric ducted fan wing flap high-lift system, improves economy and load-carrying ability; This uses the aircraft friction drag of distributed electric ducted fan wing flap high-lift system little, does not use driving engine and fossil fuel, and do not pollute, noise is little, and the feature of environmental protection is good.
Accompanying drawing explanation
Fig. 1 is the front perspective view of the first embodiment of aircraft in level flight condition that the present invention uses distributed electric ducted fan wing flap high-lift system;
Fig. 2 is the rear perspective view of the first embodiment of aircraft in vertical takeoff and landing (VTOL) state that the present invention uses distributed electric ducted fan wing flap high-lift system;
Fig. 3 is the front perspective view of aircraft the second embodiment in level flight condition that the present invention uses distributed electric ducted fan wing flap high-lift system;
In figure; 1. wing; 2. duct; 3. fan; 4. electrical motor; 5. the sub-wing; 6. wing flap; 7. propulsion source cabin; 8. inlet channel; 9. thermovent; 10. rear wing; 11. trailing edge flaps; 12. elevons; 13. fixed fins; 14. yaw rudders; 15. cover plates; 16. driving compartments; 17. parachute hatchcovers; 18. luggage-boot lids; 19. plate baffles; 20. lift fans; 21. hatch doors; 22. main landing gears; Alighting gear after 23.; 24. passenger compartments.
Detailed description of the invention
Below in conjunction with drawings and Examples, the present invention is described in further detail.
As Fig. 1, 2, shown in 3, the present invention uses the aircraft of distributed electric ducted fan wing flap high-lift system, comprise distributed electric ducted fan wing flap high-lift system, fuselage, rear wing 10, lift fan 20, it is characterized in that: described distributed electric ducted fan wing flap high-lift system is two and is arranged at fuselage middle front part both sides symmetrically, wing 1 span and the aspect ratio of distributed electric ducted fan wing flap high-lift system are relatively large, the electric ducted fan number that wing 1 leading edge is arranged is relatively many, fuselage postmedian is provided with lift fan 20, be provided with rear wing 10 to fuselage postmedian bilateral symmetry, aircraft center of gravity is positioned at waist, aircraft is tandem wing layout.
The present invention uses wing 1 span and the aspect ratio of the distributed electric ducted fan wing flap high-lift system of the aircraft enlarged relative of distributed electric ducted fan wing flap high-lift system, relatively increase the number of the electric ducted fan being arranged at wing 1 leading edge, also 1ift-drag ratio and the lift of distributed electric ducted fan wing flap high-lift system is just increased, improve economy and load-carrying ability, in the present invention, the number of electric ducted fan that distributed electric ducted fan wing flap high-lift system comprises is 4; Two distributed electric ducted fan wing flap high-lift systems are arranged at fuselage middle front part both sides symmetrically, at fuselage postmedian, lift fan 20 is set, fuselage postmedian bilateral symmetry rear wing 10 is set simultaneously, because aircraft center of gravity is positioned at waist, distributed like this electric ducted fan wing flap high-lift system, can most of weight of load aircraft when flying just closer to aircraft center of gravity; Lift fan 20 and rear wing 10 more farther from aircraft center of gravity, only need load aircraft fraction weight during flight; Although the duct 2 of each electric ducted fan has two facades in left and right in distributed electric ducted fan wing flap high-lift system, have certain friction drag, facade area is relatively little, and cumulative resistance is still relatively little; Distributed electric ducted fan wing flap high-lift system adopts electric ducted fan simultaneously, and does not use driving engine and fossil fuel, and thus do not pollute, noise is little.
The first embodiment of the array mode of fuselage and fuselage and distributed electric ducted fan wing flap high-lift system: as Fig. 1, shown in 2, described fuselage relatively tubbiness, propulsion source cabin 7 is positioned at forebody, driving compartment 16 to be positioned at after propulsion source cabin 7 i.e. waist, and two distributed electric ducted fan wing flap high-lift systems are arranged at the belly both sides between propulsion source cabin 7 and driving compartment 16 symmetrically.
The fuselage relatively tubbiness of aircraft, propulsion source cabin 7 is positioned at forebody, and the propulsion source in propulsion source cabin 7 is battery, can be such as lithium cell, there is inlet channel 8 front portion, propulsion source cabin 7, and there is thermovent 9 both sides, rear portion, is used for the heat radiation of battery with ventilating air, driving compartment 16 is waist after being positioned at propulsion source cabin 7, and driving compartment 16 is relatively little, can only take several people, and aircraft should be domestic type aircraft mutually, because the battery in forebody propulsion source cabin 7 is heavier, position in the middle part of driving compartment 16 is dropped on making the center of gravity of aircraft after other part counterweights of aircraft, because two distributed electric ducted fan wing flap high-lift systems are arranged at the belly both sides between propulsion source cabin 7 and driving compartment 16 symmetrically, close to center of gravity, make two distributed electric ducted fan wing flap high-lift systems can most of weight of load aircraft, make the plane of revolution of the fan 3 of electric ducted fan correspond to position before the pin of first row driver and crew in driving compartment 16 simultaneously, avoid the health of described driver and crew, like this, aircraft be no matter vertical takeoff and landing (VTOL) or horizontal flight time, even if the impaired injection of fan 3 blade, also can not the driver and crew riding in first row seat in driving compartment 16 be damaged.
The second embodiment of the array mode of fuselage and fuselage and distributed electric ducted fan wing flap high-lift system: as shown in Figure 3, described fuselage is relatively elongated, propulsion source cabin 7 is positioned at forebody, after driving compartment 16 is positioned at propulsion source cabin, passenger compartment 24 to be positioned at after driving compartment 16 i.e. waist, and two distributed electric ducted fan wing flap high-lift systems are arranged at the belly both sides between driving compartment 16 and passenger compartment 24 symmetrically.
The fuselage of aircraft is relatively elongated, and propulsion source cabin 7 is positioned at forebody, and the propulsion source in propulsion source cabin 7 is battery, can be such as lithium cell, there is inlet channel 8 front portion, propulsion source cabin 7, and there is thermovent 9 both sides, rear portion, is used for the heat radiation of battery with ventilating air, after driving compartment 16 is positioned at propulsion source cabin 7, can take two chaufeurs in driving compartment 16, passenger compartment 24 is waist after being positioned at driving compartment 16, and passenger compartment 24 can be taken several to tens of passengers, and aircraft should be business airplane mutually, because the battery in forebody propulsion source cabin 7 is heavier, the center of gravity of aircraft is made to drop on the position of passenger compartment 24 middle front part with after other part counterweights of aircraft, because two distributed electric ducted fan wing flap high-lift systems are arranged at the belly both sides between driving compartment 16 and passenger compartment 24 symmetrically, close to center of gravity, make two distributed electric ducted fan wing flap high-lift systems can most of weight of load aircraft, make the plane of revolution of the fan 3 of electric ducted fan correspond to position in driving compartment 16 in chaufeur and passenger compartment 24 between first row passenger simultaneously, avoid the health of described driver and crew, like this, aircraft be no matter vertical takeoff and landing (VTOL) or horizontal flight time, even if the impaired injection of fan 3 blade, also can not damage the passenger of first row seat in the chaufeur rided in driving compartment 16 and passenger compartment 24.
The aircraft that the array mode of the fuselage described in embodiment one and fuselage and distributed electric ducted fan wing flap high-lift system can be formed, with the fuselage described in embodiment two and fuselage identical with other part-structures of the aircraft that the array mode of distributed electric ducted fan wing flap high-lift system can be formed, the aircraft that can be formed for the array mode of the fuselage described in embodiment one and fuselage and distributed electric ducted fan wing flap high-lift system below continues the structure describing other parts of aircraft.
As Fig. 1, shown in 2, described lift fan 20 is one, lift fan 20 admission port is provided with the cover plate 15 that can open and close to fuselage head direction as required, exhausr port is provided with as required can the louver that arranges of the longitudinal direction of deflection, and lift fan 20 is for coaxial to turning motor fan, and lift fan 20 low-angle leans forward setting, to make aircraft when the state vertical takeoff and landing (VTOL) of low-angle new line, the axis vertical of the rotating shaft of lift fan 20 is downward.
Lift fan 20 is for trim before and after the vertical takeoff and landing (VTOL) state of aircraft and the lift of distributed electric ducted fan wing flap high-lift system; The cover plate 15 of lift fan 20 admission port opens and closes to fuselage head flight, is conducive to the air inlet when front flying; Lift fan 20 exhausr port is provided with as required can the louver that arranges of the longitudinal direction of deflection, in vertical takeoff and landing (VTOL), carries out driftage control when hovering and ease ahead to aircraft; Lift fan 20 due to for coaxial to rotary fan, fan rotate produce anti-twisted power will cancel out each other; Lift fan 20 adopts direct motor drive, and electric power is from the battery in propulsion source cabin 7; Lift fan 20 exhausr port has hatch door 21, and when aircraft vertical rises and falls, hatch door 21 is opened, and lift fan 20 can be worked, and closes hatch door 21, to reduce flight resistance when the horizontal high-speed flight lift fan 20 of aircraft quits work.
As Fig. 1, shown in 2, the wing root of described rear wing 10 is connected to the back of fuselage postmedian, be positioned at before lift fan 20, rear wing 10 has on low-angle anti-, and has low-angle sweepback, in rear wing 10, wing panel is provided with trailing edge flap 11, outer panel is provided with elevon 12, and rear wing 10 wingtip is provided with the vertical tail of similar winglet, and vertical tail is made up of the fixed fin 13 of front portion and the yaw rudder 14 at rear portion.
The wing root of rear wing 10 is connected by the reinforcing frame of central wing box with fuselage postmedian, the back of the fuselage of wing body junction is more smooth, be beneficial to lift fan 20 air inlet at rear, rear wing 10 to have on low-angle anti-, to avoid the wake flow of front distributed electric ducted fan wing flap high-lift system when horizontal flight; Rear wing 10 has low-angle sweepback, to reduce resistance, makes the elevon 12 of outer panel simultaneously, and the fixed fin 13 of wingtip and yaw rudder 14 farther from aircraft center of gravity, the arm of force is longer, and operating torque is larger.
As Fig. 1, shown in 2, described main landing gear 22 is two, the wing body connecting portion both sides that the wing root being arranged at the wing 1 of two distributed electric ducted fan wing flap high-lift systems is symmetrically connected with fuselage; Rear alighting gear 23 is one, is arranged at the belly of fuselage postmedian, before lift fan 20.
Alighting gear is tail wheel landing gear, and when aircraft is parked in ground, be low-angle cocked-up attitude, like this, rear alighting gear 23 can be relatively shorter, correspondingly alleviates weight.
The working process of aircraft described in detail by the aircraft that can be formed for the array mode of the fuselage described in embodiment one and fuselage and distributed electric ducted fan wing flap high-lift system below.
When aircraft needs to take off vertically, in rear wing 10, the trailing edge flap 11 times of wing panel partially, wing 1 time inclined rear wing double slotted flaps be made up of the sub-wing 5 and wing flap 6 of distributed electric ducted fan wing flap high-lift system, two plate baffles 19 arranged by each electric ducted fan exhausr port are symmetrically towards outer angular deflection, battery conduct electrical power in propulsion source cabin 7 makes electrical motor 4 rotate, drive fan 3 high speed rotating, distributed electric ducted fan wing flap high-lift system is started working, and the lift produced upward is made a concerted effort, open the cover plate 15 of lift fan 20 admission port simultaneously, open the hatch door 21 of lift fan 20 exhausr port, High Rotation Speed lift fan 20, lift fan 20 is made to produce the corresponding generation of downward slip-stream lift upwards, the lift of this power and distributed electric ducted fan wing flap high-lift system is made a concerted effort anterior-posterior balance, and exceed the weight of aircraft, aircraft is taken off vertically gradually, aircraft balance in roll is now responsible for by the distributed electric ducted fan wing flap high-lift system of both sides, after aircraft vertical rises to certain altitude, pack up main landing gear 22 and rear alighting gear 23, due to the sub-wing 5 of wing 1 trailing edge of distributed electric ducted fan wing flap high-lift system and wing flap 6 times to the rear, the lift point of resultant force of distributed electric ducted fan wing flap high-lift system is positioned at wing 1 trailing edge, here from aircraft center of gravity more close to, enable most of weight of distributed electric ducted fan wing flap high-lift system load aircraft, accordingly, lift fan 20 is due to relatively farther from aircraft center of gravity, only need load aircraft fraction weight that aircraft pitching just can be kept to balance, this reduces the volume and weight of lift fan 20, it also reduce the deadweight of aircraft when horizontal flight, improve economy, due to wing panel in now rear wing 10 trailing edge flap 11 times partially, the injection of the surrounding air that the slip-stream blowing to below when the lift fan 20 on side works causes, will wing panel top airfoil be from leading edge edge flowing backward in rear wing 10, and this will produce certain lift.
When aircraft rises to certain altitude gradually, when needing to enter floating state, suitable reduction fan 3 rotating speed, distributed electric ducted fan wing flap high-lift system lift is upwards reduced with joint efforts slightly, corresponding reduction lift fan 20 rotating speed, makes the also corresponding reduction of lift fan 20 lift upwards, trim before and after the two simultaneously, and just can load aircraft weight, aircraft enters floating state.
Aircraft enters floating state when needing ease ahead, lift fan 20 rotating speed of suitable increase fuselage postmedian, the lift of lift fan 20 is increased slightly, this power makes aircraft reduce the new line angle of attack, the lift of distributed electric ducted fan wing flap high-lift system is made a concerted effort slightly toward the front, make the thrust direction of lift fan 20 also slightly toward the front, power slightly toward the front both this makes aircraft ease ahead simultaneously, aircraft is when floating state wants ease astern, fan 3 rotating speed of suitable increase distributed electric ducted fan wing flap high-lift system, distributed electric ducted fan wing flap high-lift system lift is upwards made to make a concerted effort suitably to increase, the corresponding aircraft that makes of this power increases the new line angle of attack slightly, make the thrust direction of lift fan 20 slightly towards rear, make the lift of distributed electric ducted fan wing flap high-lift system make a concerted effort also slightly towards rear simultaneously, both this, slightly make aircraft ease astern towards rearward power, aircraft is when floating state wants low speed transverse shifting, such as will transverse shifting to the left, now suitably increase fan 3 rotating speed of the distributed electric ducted fan wing flap high-lift system in right side, make a concerted effort with the lift suitably increasing the distributed electric ducted fan wing flap high-lift system on right side, make aircraft towards left side low-angle roll, then fan 3 rotating speed of the distributed electric ducted fan wing flap high-lift system in right side is suitably reduced, make a concerted effort with the lift suitably reducing the distributed electric ducted fan wing flap high-lift system on right side, now the distributed electric ducted fan wing flap in both sides high-lift system will produce towards the component in left side, this power makes aircraft towards left side low speed transverse shifting, aircraft is when floating state needs turning in hover, suitable increasing lift fan 20 rotating speed, deflect the louver that lift fan 20 exhausr port is arranged round about simultaneously, the oblique ejection of slip-stream of lift fan 20, this will produce conicity force, because lift fan 20 is arranged on aircraft fuselage postmedian, away from aircraft center of gravity, the conicity force of generation will make aircraft towards respective direction turning in hover, when aircraft needs ease ahead and goes off course, increase lift fan 20 rotating speed, the Combination of Methods simultaneously deflecting the louver that lift fan 20 exhausr port is arranged uses.
When aircraft needs to transfer horizontal flight to from floating state, suitable increase lift fan 20 thrust makes aircraft eliminate the new line angle of attack, suitably increase fan 3 rotating speed of distributed electric ducted fan wing flap high-lift system simultaneously, the aforesaid downward angle degree of the sub-wing 5 of suitable reduction and wing flap 6, the lift resultant direction making distributed electric ducted fan wing flap high-lift system more toward the front, makes aircraft flight forward gradually when there being enough lift not reduce height, now, the outer panel of rear wing 10 produces lift by starting, and the interior wing panel of rear wing 10 will produce greater lift, continue fan 3 rotating speed increasing distributed electric ducted fan wing flap high-lift system, continue the aforesaid downward angle degree reducing the sub-wing 5 and wing flap 6, aircraft flies before continuation being accelerated, rear wing 10 will produce greater lift, simultaneously the outer panel of rear wing 10 and elevon 12 produce lateral stability and pitching stability by starting, and fixed fin 13 and yaw rudder 14 produce course stability by starting, continue to keep this trend, rear wing 10 will produce enough lift, with with distributed electric ducted fan wing flap high-lift system before and after trim, aircraft is made to keep pitching balance, now, by two plate baffles 19 of each electric ducted fan exhausr port symmetrically towards interior angular deflection, make fan 3 slip-stream promote aircraft to greatest extent to advance, the sub-wing 5 and wing flap 6 are all packed up, the trailing edge flap 11 of wing panel in trailing edge 10 is packed up, to reduce aerodynamic drag, lift fan 20 is stopped to rotate, close cover plate 15, close hatch door 21, aircraft enters level flight condition, now, rear wing 10 outer panel and elevon 12 will make aircraft produce enough lateral stabilitys, fixed fin 13 and yaw rudder 14 will make aircraft keep enough course stabilities, aircraft becomes tandem wing airplane, suitable reduction electrical motor 4 rotating speed, with cruising flight economically, the pitch control of aircraft when tandem wing airplane and lateral control are responsible for by elevon 12, and directional control is responsible for by yaw rudder 14.
When aircraft needs to transfer floating state to from level flight condition, the partially sub-wing 5 and wing flap 6 suitably, by the plate baffle 19 of each ducted fan exhausr port symmetrically towards outer angular deflection, distributed electric ducted fan wing flap high-lift system reduces propelling forward, aircraft reduces speed now, the partially sub-wing 5 and wing flap 6 under continuation, aircraft continues to slow down, because speed reduces, distributed electric ducted fan wing flap high-lift system can not produce enough lift, suitable increasing electrical motor 4 rotating speed, to increase the lift of distributed electric ducted fan wing flap high-lift system, now, rear wing 10 also can not produce enough lift, lower inclined trailing edge flap 11, rear wing 10 is made to increase lift, to keep aircraft pitching balance with front distributed electric ducted fan wing flap high-lift system, along with aircraft continues to slow down, rear wing 10 can not produce enough lift again, now, open the cover plate 15 of lift fan 20 admission port, open the hatch door 21 of lift fan 20 exhausr port, make lift fan 20 start rotation work, produce thrust upwards, with distributed electric ducted fan wing flap high-lift system before and after trim, continue to keep this trend, aircraft will be decelerated to gradually and halt, and aircraft enters floating state.
When aircraft needs from floating state vertical landing, put down main landing gear 22 and rear alighting gear 23, suitable reduction lift fan 20 rotating speed, with the thrust of corresponding reduction lift fan 20, suitably reduce fan 3 rotating speed simultaneously, make a concerted effort with the lift of corresponding reduction distributed electric ducted fan wing flap high-lift system, aircraft slowly can decline because lift is less than gravity, along with main landing gear 22 and rear alighting gear 23 kiss the earth, pack up the sub-wing 5 and wing flap 6, fan 3 is stopped to rotate, close cover plate 15, close hatch door 21, lift fan 20 is stopped to rotate, pack up trailing edge flap 11, pack up the sub-wing 5 and wing flap 6, the aircraft vertical process of rising and falling terminates,
The present embodiment aircraft, when vertical takeoff and landing (VTOL) state and level flight condition flight, all needs to adopt control augmentation stability system to carry out artificial increasing surely.
The present embodiment aircraft is arranged on fuselage middle front part due to two distributed electric ducted fan wing flap high-lift systems, and the duct 2 of each electric ducted fan has two facades in left and right, these facades are as the vertical tail be arranged on before aircraft center of gravity, the course stability of aircraft can be reduced, stablize so aircraft needs to adopt control augmentation stability system to coordinate fixed fin 13 and yaw rudder 14 to maintain aircraft course.
The present embodiment is the aircraft of family expenses form, and in the driving compartment 16 of waist, seat is front two rows, can take 4 people altogether; After driving compartment 16, before lift fan 20, there is parachute compartment, have parachute hatchcover 17 outward, in parachute compartment, have parachute, can be used for forced landing during aircraft fault; Because parachute compartment is after the center of gravity of aircraft, when force-landing with parachute, the head of aircraft can be spent towards front lower place, and the propulsion source cabin 7 of forebody has certain length, like this when aircraft lands, the form that the propulsion source cabin 7 of forebody and battery thereof can destroy with structural distortion, absorbing impact energy, thus the passenger in protection driving compartment 16; Below parachute compartment, before rear alighting gear 23, there is boot compartment, have luggage compartment door 18 outward; In present stage, battery technology is not very perfect, can not ensure that aircraft has enough cruise duration, therefore also can adopt by driving engine, the hybrid power system of electrical generator and battery composition, can ensure that aircraft has enough cruise duration, reduces the power of driving engine so simultaneously, it also reduce pollution and the noise of driving engine; Hybrid power system is also arranged in propulsion source cabin 7, engine air is entered by inlet channel 8, the hot gas produced is discharged by thermovent 9, the waste gas exhaust pipe of driving engine stretches out at belly, and the fuel storage needed for driving engine is in the wing 1 of distributed electric ducted fan wing flap high-lift system and in rear wing 10; The present embodiment aircraft can suitably reduce or increase profile and power in proportion, make it should be able to take mutually less or more personnel, such as aircraft can be reduced, make aircraft can only take a people, make aircraft become individual lift device, the aircraft Ride Style of single form can be traditional Chinese chair formula, also can be the saddle ride type of motor cycle type, when saddle ride type for motor cycle type, the volume of aircraft can be reduced.
The aircraft of the business airplane form that the array mode of the fuselage described in embodiment two and fuselage and distributed electric ducted fan wing flap high-lift system can be formed, identical with the working process of the aircraft of the family expenses form that the array mode of the fuselage described in embodiment one and fuselage and distributed electric ducted fan wing flap high-lift system can be formed, repeat no more.
The present embodiment aircraft, when vertical takeoff and landing (VTOL) state and level flight condition flight, all needs to adopt control augmentation stability system to carry out artificial increasing surely.
The present embodiment aircraft is arranged on fuselage middle front part due to two distributed electric ducted fan wing flap high-lift systems, and the duct 2 of each electric ducted fan has two facades in left and right, these facades are as the vertical tail be arranged on before aircraft center of gravity, the course stability of aircraft can be reduced, stablize so aircraft needs to adopt control augmentation stability system to coordinate fixed fin 13 and yaw rudder 14 to maintain aircraft course.
The present embodiment aircraft is the aircraft of business airplane form, can carry several to tens of passengers in the passenger compartment of waist, in present stage, battery technology is not very perfect, can not ensure that aircraft has enough cruise duration, therefore also can adopt by driving engine, the hybrid power system of electrical generator and battery composition, can ensure that aircraft has enough cruise duration like this, reduce the power of driving engine simultaneously, it also reduce pollution and the noise of driving engine, hybrid power system is also arranged in propulsion source cabin 7, engine air is entered by inlet channel 8, the hot gas produced is discharged by thermovent 9, the waste gas exhaust pipe of driving engine stretches out at belly, fuel storage needed for driving engine is in the wing 1 of distributed electric ducted fan wing flap high-lift system and in rear wing 10, the present embodiment aircraft can suitably reduce or increase profile and power in proportion, makes it should be able to take mutually less or more personnel, such as can increase aircraft, make aircraft become feeder liner.
The aircraft of the aircraft of the family expenses form described in embodiment one and the business airplane form described in embodiment two, lift fan is arranged on fuselage postmedian, By Using Active Lift is produced by vent, this set can change cancellation exhausr port into, drainage pipe is set in addition, the slip-stream of lift fan 20 is sprayed by the gap of pipeline from the trailing edge flap 11 of wing panel in rear wing 10, with the form of jet flap, power-boosting is carried out to rear wing 10, such efficiency is higher, and doing disadvantageous one side is like this complexity and the weight that can increase pipeline; Under this configuration, the maneuverability pattern of aircraft and original maneuverability pattern similar.
Embodiment one aircraft and embodiment two aircraft, can from civilian change into military.Also unmanned plane or model plane can be changed into.
What finally illustrate is, above embodiment is only in order to illustrate technical scheme of the present invention and unrestricted, although be described in detail with reference to preferred embodiment, those of ordinary skill in the art is to be understood that, can modify to technical scheme of the present invention or equivalent replacement and do not depart from aim and the scope of technical solution of the present invention, it all should be encompassed in the middle of right of the present invention.
Claims (6)
1. one kind is used the aircraft of distributed electric ducted fan wing flap high-lift system, comprise distributed electric ducted fan wing flap high-lift system, fuselage, rear wing (10), lift fan (20), it is characterized in that: described distributed electric ducted fan wing flap high-lift system is two and is arranged at fuselage middle front part both sides symmetrically, wing (1) span and the aspect ratio of distributed electric ducted fan wing flap high-lift system are relatively large, the electric ducted fan number that wing (1) leading edge is arranged is relatively many, fuselage postmedian is provided with lift fan (20), be provided with rear wing (10) to fuselage postmedian bilateral symmetry, aircraft center of gravity is positioned at waist, aircraft is tandem wing layout.
2. the aircraft of utilization according to claim 1 distributed electric ducted fan wing flap high-lift system, it is characterized in that: described fuselage relatively tubbiness, propulsion source cabin (7) is positioned at forebody, driving compartment (16) to be positioned at after propulsion source cabin (7) i.e. waist, and two distributed electric ducted fan wing flap high-lift systems are arranged at the belly both sides between propulsion source cabin (7) and driving compartment (16) symmetrically.
3. the aircraft of utilization according to claim 1 distributed electric ducted fan wing flap high-lift system, it is characterized in that: described fuselage is relatively elongated, propulsion source cabin (7) is positioned at forebody, after driving compartment (16) is positioned at propulsion source cabin, passenger compartment (24) to be positioned at after driving compartment (16) i.e. waist, and two distributed electric ducted fan wing flap high-lift systems are arranged at the belly both sides between driving compartment (16) and passenger compartment (24) symmetrically.
4. according to claim 2, the aircraft of the distributed electric ducted fan wing flap of the utilization described in 3 high-lift system, it is characterized in that: described lift fan (20) is one, lift fan (20) admission port is provided with the cover plate (15) that can open and close to fuselage head direction as required, exhausr port be provided with as required can deflection longitudinal direction arrange louver, lift fan (20) for coaxial to turning motor fan, lift fan (20) low-angle leans forward setting, to make aircraft when the state vertical takeoff and landing (VTOL) of low-angle new line, the axis vertical of the rotating shaft of lift fan (20) is downward.
5. according to claim 2, the aircraft of the distributed electric ducted fan wing flap of the utilization described in 3 high-lift system, it is characterized in that: the wing root of described rear wing (10) is connected to the back of fuselage postmedian, be positioned at before lift fan (20), rear wing (10) has on low-angle anti-, and have low-angle sweepback, rear wing (10) interior wing panel is provided with trailing edge flap (11), outer panel is provided with elevon (12), rear wing (10) wingtip is provided with the vertical tail of similar winglet, vertical tail is made up of the fixed fin (13) of front portion and the yaw rudder (14) at rear portion.
6. according to claim 4, the aircraft of the distributed electric ducted fan wing flap of the utilization described in 5 high-lift system, it is characterized in that: described main landing gear (22) is two, the wing body connecting portion both sides that the wing root being arranged at the wing (1) of two distributed electric ducted fan wing flap high-lift systems is symmetrically connected with fuselage; Rear alighting gear (23) is one, is arranged at the belly of fuselage postmedian, before lift fan (20).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510297892.0A CN104973234A (en) | 2015-06-02 | 2015-06-02 | Aircraft using distributed electric ducted fan flap lift-rising system |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510297892.0A CN104973234A (en) | 2015-06-02 | 2015-06-02 | Aircraft using distributed electric ducted fan flap lift-rising system |
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| CN104973234A true CN104973234A (en) | 2015-10-14 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201510297892.0A Pending CN104973234A (en) | 2015-06-02 | 2015-06-02 | Aircraft using distributed electric ducted fan flap lift-rising system |
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| CN (1) | CN104973234A (en) |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105857579A (en) * | 2016-05-12 | 2016-08-17 | 中国航空工业集团公司西安飞机设计研究所 | Propeller airplane |
| CN107010196A (en) * | 2015-12-23 | 2017-08-04 | 空中客车运营简化股份公司 | It is a kind of to be used for all-wing aircraft leading edge and the door at the lateral margin parallel to symmetrical plane |
| CN107539472A (en) * | 2017-09-29 | 2018-01-05 | 清华大学 | A kind of single lift culvert vertical take-off and landing aircraft based on tilting duct |
| WO2018103762A1 (en) | 2017-01-06 | 2018-06-14 | 西北工业大学 | Distributed propulsion system |
| CN109665088A (en) * | 2017-10-17 | 2019-04-23 | 空中客车运营公司 | The landing gear compartment top for aircraft including inclined rear bulkhead |
| CN109665094A (en) * | 2017-10-13 | 2019-04-23 | 空客直升机德国有限公司 | Multi-rotor aerocraft with fuselage He at least one wing |
| CN113291459A (en) * | 2021-07-27 | 2021-08-24 | 中国空气动力研究与发展中心高速空气动力研究所 | Distributed ducted fan high-lift system and application method thereof |
| CN115892439A (en) * | 2023-03-10 | 2023-04-04 | 中国空气动力研究与发展中心高速空气动力研究所 | High-wind-resistance distributed propulsion aircraft |
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2015
- 2015-06-02 CN CN201510297892.0A patent/CN104973234A/en active Pending
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107010196A (en) * | 2015-12-23 | 2017-08-04 | 空中客车运营简化股份公司 | It is a kind of to be used for all-wing aircraft leading edge and the door at the lateral margin parallel to symmetrical plane |
| CN105857579A (en) * | 2016-05-12 | 2016-08-17 | 中国航空工业集团公司西安飞机设计研究所 | Propeller airplane |
| WO2018103762A1 (en) | 2017-01-06 | 2018-06-14 | 西北工业大学 | Distributed propulsion system |
| CN107539472A (en) * | 2017-09-29 | 2018-01-05 | 清华大学 | A kind of single lift culvert vertical take-off and landing aircraft based on tilting duct |
| CN109665094A (en) * | 2017-10-13 | 2019-04-23 | 空客直升机德国有限公司 | Multi-rotor aerocraft with fuselage He at least one wing |
| CN109665094B (en) * | 2017-10-13 | 2022-05-31 | 空客直升机德国有限公司 | Multi-rotor aircraft with fuselage and at least one wing |
| CN109665088A (en) * | 2017-10-17 | 2019-04-23 | 空中客车运营公司 | The landing gear compartment top for aircraft including inclined rear bulkhead |
| CN113291459A (en) * | 2021-07-27 | 2021-08-24 | 中国空气动力研究与发展中心高速空气动力研究所 | Distributed ducted fan high-lift system and application method thereof |
| CN115892439A (en) * | 2023-03-10 | 2023-04-04 | 中国空气动力研究与发展中心高速空气动力研究所 | High-wind-resistance distributed propulsion aircraft |
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Application publication date: 20151014 |