CN205602117U - Novel high lift VTOL aircraft - Google Patents
Novel high lift VTOL aircraft Download PDFInfo
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- CN205602117U CN205602117U CN201620406354.0U CN201620406354U CN205602117U CN 205602117 U CN205602117 U CN 205602117U CN 201620406354 U CN201620406354 U CN 201620406354U CN 205602117 U CN205602117 U CN 205602117U
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Abstract
The utility model discloses a novel high lift VTOL aircraft, this aircraft includes: the fuselage, set up the main wing in the tail both sides of fuselage, the main wing is by inboard main wing and outside main wing is conformal constitutes, inboard main wing is the buzzard -type wing, and the sweepforward angle is 10~75, the tail top of fuselage is provided with two vertical fins, the aircraft nose both sides of fuselage are provided with the duck wing, the top of fuselage is provided with the rotor, be provided with power device between inboard main wing and the outside main wing, the lower part of fuselage is provided with the undercarriage. The utility model discloses the flight performance of VTOL with high speed, long flight time, big voyage has been compromise to the ware, has the characteristic of great task load for lift -to -drag characteristic and driving system's propulsive efficiency will be higher than the helicopter and vert the gyroplane during high -speed flight, have wideer flight envelope, and lift and horizontal thrust control decoupling zero simultaneously makes the aircraft carry out the transition to the high -speed state of cruising by the low -speed state of flight smoothly.
Description
Technical field
This utility model belongs to field of flight vehicle design, is specifically related to a kind of novel high-lift vertically taking off and landing flyer.
Background technology
Vertically taking off and landing flyer, is originating primarily from VTOL aeronautical technology, and VTOL aeronautical technology, as the term suggests referring to aircraft to need not the sliding aeronautical technology run and can complete take-off and landing.VTOL aeronautical technology originates from the fifties in last century, and Britain, the U.S., Russia successively just have employed this technology on the carrier-borne aircraft of its aircraft carrier in the world.
The aircraft with VTOL ability need not special airport and runway, have only to the least level land and be to ensure that safe take-off and the landing of aircraft, reduce the aircraft degree of dependence to facilities such as airfield runways, substantially increase availability and the comfort level of aircraft.
Along with automatically controlling, the progress of the technology such as aviation power, composite, electronic technology and machining so that VTOL aeronautical technology is developed rapidly, and various forms of vertically taking off and landing flyer continue to bring out.The development of VTOL aeronautical technology, directly affects military, civil aircraft developing direction.The vertically taking off and landing flyer that can adapt to complicated terrain environment has been classified as the first term of U.S. army ten big future key equipment by the U.S..In terms of civilian angle, VTOL aircraft is alleviating urban ground traffic, ground mapping, agricultural plant protection, power-line patrolling, mineral exploration aviation etc., and performing task under complicated terrain environment, the aspect such as such as earthquake relief work, forest fire protection, outlying district first aid has great application prospect and application space.
Pure helicopter possesses VTOL ability, but does not possess the efficient, the most flat of fixed wing airplane and fly ability, and common fixed wing airplane possesses efficiently, high speed is flat flies ability, but does not possess VTOL ability.Therefore, allow aircraft be provided simultaneously with the VTOL ability of helicopter and fly ability with the efficient, the most flat of fixed wing airplane, be to be engaged in the thing that aeronautical technology researcher is dreamed of the present age, there is the biggest economy and military value.
Utility model content
For solving the technical problem of existing existence, this utility model provides a kind of novel high-lift vertically taking off and landing flyer.
For reaching above-mentioned purpose, the technical scheme of this utility model embodiment is achieved in that
This utility model embodiment provides a kind of novel high-lift vertically taking off and landing flyer, this aircraft includes: fuselage, be arranged on the main wing of the tail both sides of fuselage, described main wing is by inner side main wing and outside main wing is conformal constitutes, described inner side main wing is buzzard-type wing, sweepforward angle is 10 ° ~ 75 °, the tail of described fuselage is provided above two vertical fins, the head both sides of described fuselage are provided with canard, described fuselage be provided above rotor, being provided with power set between described inner side main wing and outside main wing, the bottom of described fuselage is provided with undercarriage.
In such scheme, described head is flat lifting body head, head both sides and be positioned at the position in canard front and be provided with the fusant strake wing for lift-rising.
In such scheme, two outside main wings are provided with aileron, said two vertical fin is provided with rudder.
In such scheme, described tail is provided with elevator.
In such scheme, between described fuselage and rotor, it is provided with trousers.
In such scheme, described rotor is single rotor or DCB Specimen, and blade is two panels blade, three blades, four blades, five blades or six blades.
In such scheme, described outside main wing is buzzard-type wing, tapered airfoil, RECTANGULAR WINGS, dalta wing or swept-back wing.
In such scheme, described canard is tapered airfoil, RECTANGULAR WINGS, buzzard-type wing, dalta wing, swept-back wing or the S-shaped leading edge wing.
In such scheme, described undercarriage uses first three point type, bicycle type, rear bikini or cunning to stick up formula.
In such scheme, described power set use airscrew engine or turboprop or genemotor or turbojet or turbofan.
Compared with prior art, the beneficial effects of the utility model:
This utility model provides a kind of novel high-lift vertically taking off and landing flyer, a kind of novel high-lift vertically taking off and landing flyer, it is characterized in that, this aircraft includes fuselage, it is arranged on the main wing of the tail both sides of fuselage, described main wing is by inner side main wing and outside main wing is conformal constitutes, described inner side main wing is buzzard-type wing, sweepforward angle is 10 ° ~ 75 °, the tail of described fuselage is provided above two vertical fins, the head both sides of described fuselage are provided with canard, described fuselage be provided above rotor, it is provided with power set between described inner side main wing and outside main wing, the bottom of described fuselage is provided with undercarriage；This utility model device taken into account VTOL and at a high speed, long boat time, the flying quality of big voyage, there is the characteristic of bigger mission payload, inside this utility model, the rearmounted and sweepforward setting of main wing avoids main wing and is in the purling district of rotor, reduce the rotor unfavorable interference to main wing, the aerodynamic advantages of fixed-wing can be given full play to, it also avoid the main wing impact on rotor, improve rotor efficiency.The sweepforward of main wing so that lifting surface, near center of gravity, reduces the nose-down pitching moment that main wing produces to a certain extent；Canard uses active control technology, makes canard can produce certain lift component, not only balances the nose-down pitching moment that main wing produces, and also solves the problem that the longitudinal controllability of full machine in prior art is not enough, also significantly reduces the bending moment acting on main wing root；Lifting body head and the setting of fusant strake wing, the longitudinal moment trim to aircraft is played good effect, is improve maneuverability and the mobility of aircraft.When such configuration feature makes high-speed flight, the propulsive efficiency of lifting resistance characteristic and dynamical system will be above helicopter and tiltrotor, there is broader flight envelope, lift and horizontal thrust control decoupling simultaneously, make aircraft be smoothly transitioned into high speed cruise conditions by low-speed condition.
Accompanying drawing explanation
Fig. 1 is the structural representation of a kind of novel high-lift vertically taking off and landing flyer that this utility model embodiment 1 provides；
Fig. 2 is the top view of a kind of novel high-lift vertically taking off and landing flyer that this utility model embodiment 1 provides；
Fig. 3 is the front view of a kind of novel high-lift vertically taking off and landing flyer that this utility model embodiment 1 provides；
Fig. 4 is the side view of a kind of novel high-lift vertically taking off and landing flyer that this utility model embodiment 1 provides；
Fig. 5 is the structural representation of a kind of novel high-lift vertically taking off and landing flyer that this utility model embodiment 2 provides；
Fig. 6 is the structural representation of a kind of novel high-lift vertically taking off and landing flyer that this utility model embodiment 3 provides；
Fig. 7 is the structural representation of a kind of novel high-lift vertically taking off and landing flyer that this utility model embodiment 4 provides；
Fig. 8 is the structural representation of a kind of novel high-lift vertically taking off and landing flyer that this utility model embodiment 5 provides；
In figure: 1-fuselage；Main wing inside 2-；Main wing outside 3-；4-tail；5-vertical fin；6-head；7-canard；8-aileron；9-rudder；10-elevator；11-rotor；12-power set；13-fusant strake wing；14-trousers；15-undercarriage.
Detailed description of the invention
With detailed description of the invention, this utility model is described in detail below in conjunction with the accompanying drawings.
Embodiment 1:
This utility model embodiment provides a kind of novel high-lift vertically taking off and landing flyer, as shown in Fig. 1 ~ 4, this aircraft includes: fuselage 1, it is arranged on the main wing of tail 4 both sides of fuselage 1, described main wing is by inner side main wing 2 and outside main wing 3 is conformal constitutes, described inner side main wing 2 is buzzard-type wing, sweepforward angle is 10 ° ~ 75 °, the tail 4 of described fuselage 1 is provided above two vertical fins 5, head 6 both sides of described fuselage 1 are provided with canard 7, described fuselage 1 be provided above rotor 11, it is provided with power set 12 between described inner side main wing 2 and outside main wing 3, the bottom of described fuselage 1 is provided with undercarriage 15.Inside this utility model, the rearmounted and sweepforward setting of main wing avoids wing and is in the purling district of rotor 11, thus avoid the purling unfavorable interference to wing of rotor 11, the aerodynamic advantages of fixed-wing can be given full play to, it also avoid the wing impact on rotor 11 lift-rising, thus improve rotor 11 lift efficiency.The sweepforward of inner side main wing 2 so that lifting surface, near center of gravity, reduces the nose-down pitching moment that main wing produces to a great extent.When such configuration feature makes high-speed flight, the propulsive efficiency of lifting resistance characteristic and dynamical system will be above helicopter and tiltrotor, aircraft is made to have broader flight envelope, lift and horizontal thrust control decoupling simultaneously, can realize aircraft stable transition and conversion flight between VTOL and horizontal flight.When this utility model has taken into account VTOL and long boat, the performance of big voyage, has the characteristic of bigger mission payload.When making high-speed flight, the propulsive efficiency of lifting resistance characteristic and dynamical system will be above helicopter and tiltrotor.
Described canard 7 is trapezoidal or sweepback or straight or sweepforward design regards wing specific design parameter determination.
Described canard 7 is lower anti-or upper anti-or flat design regards wing specific design parameter determination, canard 7 is used to increase full machine useful lift, increase the nose-up pitching moment of full machine, the nose-down pitching moment that balance is produced by main wing, and use active control technology, solve the problem that the longitudinal controllability of full machine in prior art is not enough.
Embodiment 2:
This utility model embodiment provides a kind of novel high-lift vertically taking off and landing flyer, as shown in Figure 5, this aircraft includes: fuselage 1, it is arranged on the main wing of tail 4 both sides of fuselage 1, described main wing is by inner side main wing 2 and outside main wing 3 is conformal constitutes, described inner side main wing 2 is buzzard-type wing, sweepforward angle is 10 ° ~ 75 °, the tail 4 of described fuselage 1 is provided above two vertical fins 5, head 6 both sides of described fuselage 1 are provided with canard 7, described fuselage 1 be provided above rotor 11, it is provided with power set 12 between described inner side main wing 2 and outside main wing 3, the bottom of described fuselage 1 is provided with undercarriage 15.Inside this utility model, the rearmounted and sweepforward setting of main wing avoids wing and is in the purling district of rotor 11, thus avoid the purling unfavorable interference to wing of rotor 11, the aerodynamic advantages of fixed-wing can be given full play to, it also avoid the wing impact on rotor 11 lift-rising, thus improve rotor 11 lift efficiency.The sweepforward of inner side main wing 2 so that lifting surface, near center of gravity, reduces the nose-down pitching moment that main wing produces to a great extent.When such configuration feature makes high-speed flight, the propulsive efficiency of lifting resistance characteristic and dynamical system will be above helicopter and tiltrotor, aircraft is made to have broader flight envelope, lift and horizontal thrust control decoupling simultaneously, can realize aircraft stable transition and conversion flight between VTOL and horizontal flight.When this utility model has taken into account VTOL and long boat, the performance of big voyage, has the characteristic of bigger mission payload.When making high-speed flight, the propulsive efficiency of lifting resistance characteristic and dynamical system will be above helicopter and tiltrotor.
Described canard 7 determines depending on wing specific design number for trapezoidal or sweepback or straight or sweepforward design.
Described canard 7 is lower anti-or upper anti-or flat design regards wing specific design parameter determination, canard 7 is used to increase full machine useful lift, increase the nose-up pitching moment of full machine, the nose-down pitching moment that balance is produced by main wing, and use active control technology, solve the problem that the longitudinal controllability of full machine in prior art is not enough.
Described head 6 is flat lifting body, and the both sides of head 6 are provided with the fusant strake wing 13 for lift-rising, and good effect is played in the longitudinal moment trim to aircraft that arranges of described fusant strake wing 13, improves maneuverability and the mobility of aircraft.
Embodiment 3:
This utility model embodiment provides a kind of novel high-lift vertically taking off and landing flyer, as shown in Figure 6, this aircraft includes: fuselage 1, it is arranged on the main wing of tail 4 both sides of fuselage 1, described main wing is by inner side main wing 2 and outside main wing 3 is conformal constitutes, described inner side main wing 2 is buzzard-type wing, sweepforward angle is 10 ° ~ 75 °, the tail 4 of described fuselage 1 is provided above two vertical fins 5, head 6 both sides of described fuselage 1 are provided with canard 7, described fuselage 1 be provided above rotor 11, it is provided with power set 12 between described inner side main wing 2 and outside main wing 3, the bottom of described fuselage 1 is provided with undercarriage 15.Inside this utility model, the rearmounted and sweepforward setting of main wing avoids wing and is in the purling district of rotor 11, thus avoid the purling unfavorable interference to wing of rotor 11, the aerodynamic advantages of fixed-wing can be given full play to, it also avoid the wing impact on rotor 11 lift-rising, thus improve rotor 11 lift efficiency.The sweepforward of inner side main wing 2 so that lifting surface, near center of gravity, reduces the nose-down pitching moment that main wing produces to a great extent.When such configuration feature makes high-speed flight, the propulsive efficiency of lifting resistance characteristic and dynamical system will be above helicopter and tiltrotor, aircraft is made to have broader flight envelope, lift and horizontal thrust control decoupling simultaneously, can realize aircraft stable transition and conversion flight between VTOL and horizontal flight.When this utility model has taken into account VTOL and long boat, the performance of big voyage, has the characteristic of bigger mission payload.When making high-speed flight, the propulsive efficiency of lifting resistance characteristic and dynamical system will be above helicopter and tiltrotor.
Described canard 7 is trapezoidal or sweepback or straight or sweepforward design regards wing specific design parameter determination.
Described canard 7 is lower anti-or upper anti-or flat design regards wing specific design parameter determination, canard 7 is used to increase full machine useful lift, increase the nose-up pitching moment of full machine, the nose-down pitching moment that balance is produced by main wing, and use active control technology, solve the problem that the longitudinal controllability of full machine in prior art is not enough.
Described head 6 is flat lifting body, and the both sides of head 6 are provided with the fusant strake wing 13 for lift-rising, and good effect is played in the longitudinal moment trim to aircraft that arranges of described fusant strake wing 13, improves maneuverability and the mobility of aircraft.
It is provided with aileron 8 on described outside main wing 3, described vertical fin 5 is provided with rudder 9.Increase course stability and the rudder face driving efficiency of aircraft, improve the anti-side wind performance of aircraft.
Embodiment 4:
This utility model embodiment provides a kind of novel high-lift vertically taking off and landing flyer, as shown in Figure 7, this aircraft includes: fuselage 1, it is arranged on the main wing of tail 4 both sides of fuselage 1, described main wing is by inner side main wing 2 and outside main wing 3 is conformal constitutes, described inner side main wing 2 is buzzard-type wing, sweepforward angle is 10 ° ~ 75 °, the tail 4 of described fuselage 1 is provided above two vertical fins 5, head 6 both sides of described fuselage 1 are provided with canard 7, described fuselage 1 be provided above rotor 11, it is provided with power set 12 between described inner side main wing 2 and outside main wing 3, the bottom of described fuselage 1 is provided with undercarriage 15.Inside this utility model, the rearmounted and sweepforward setting of main wing avoids wing and is in the purling district of rotor 11, thus avoid the purling unfavorable interference to wing of rotor 11, the aerodynamic advantages of fixed-wing can be given full play to, it also avoid the wing impact on rotor 11 lift-rising, thus improve rotor 11 lift efficiency.The sweepforward of inner side main wing 2 so that lifting surface, near center of gravity, reduces the nose-down pitching moment that main wing produces to a great extent.When such configuration feature makes high-speed flight, the propulsive efficiency of lifting resistance characteristic and dynamical system will be above helicopter and tiltrotor, aircraft is made to have broader flight envelope, lift and horizontal thrust control decoupling simultaneously, can realize aircraft stable transition and conversion flight between VTOL and horizontal flight.When this utility model has taken into account VTOL and long boat, the performance of big voyage, has the characteristic of bigger mission payload.When making high-speed flight, the propulsive efficiency of lifting resistance characteristic and dynamical system will be above helicopter and tiltrotor.
Described canard 7 is trapezoidal or sweepback or straight or sweepforward design regards wing specific design parameter determination.
Described canard 7 is lower anti-or upper anti-or flat design regards wing specific design parameter determination, canard 7 is used to increase full machine useful lift, increase the nose-up pitching moment of full machine, the nose-down pitching moment that balance is produced by main wing, and use active control technology, solve the problem that the longitudinal controllability of full machine in prior art is not enough.
Described head 6 is flat lifting body, and the both sides of head 6 are provided with the fusant strake wing 13 for lift-rising, and good effect is played in the longitudinal moment trim to aircraft that arranges of described fusant strake wing 13, improves maneuverability and the mobility of aircraft.
It is provided with aileron 8 on described outside main wing 3, described vertical fin 5 is provided with rudder 9.Increase course stability and the rudder face driving efficiency of aircraft, improve the anti-side wind performance of aircraft.
It is provided with elevator 10 on described tail 4, is controlled by the combination of elevator 4, canard 7, be conducive to obtaining the direct lift force control of full machine；By two rudders 9 and aileron 8 combination control, be conducive to the Direct Side Force producing full machine to control, so that the unconventional mode of motion of aircraft controls to be possibly realized, and improve the control response quality of aircraft.
Embodiment 5:
This utility model embodiment provides a kind of novel high-lift vertically taking off and landing flyer, as shown in Figure 8, this aircraft includes: fuselage 1, it is arranged on the main wing of tail 4 both sides of fuselage 1, described main wing is by inner side main wing 2 and outside main wing 3 is conformal constitutes, described inner side main wing 2 is buzzard-type wing, sweepforward angle is 10 ° ~ 75 °, the tail 4 of described fuselage 1 is provided above two vertical fins 5, head 6 both sides of described fuselage 1 are provided with canard 7, described fuselage 1 be provided above rotor 11, it is provided with power set 12 between described inner side main wing 2 and outside main wing 3, the bottom of described fuselage 1 is provided with undercarriage 15.Inside this utility model, the rearmounted and sweepforward setting of main wing avoids wing and is in the purling district of rotor 11, thus avoid the purling unfavorable interference to wing of rotor 11, the aerodynamic advantages of fixed-wing can be given full play to, it also avoid the wing impact on rotor 11 lift-rising, thus improve rotor 11 lift efficiency.The sweepforward of inner side main wing 2 so that lifting surface, near center of gravity, reduces the nose-down pitching moment that main wing produces to a great extent.When such configuration feature makes high-speed flight, the propulsive efficiency of lifting resistance characteristic and dynamical system will be above helicopter and tiltrotor, aircraft is made to have broader flight envelope, lift and horizontal thrust control decoupling simultaneously, can realize aircraft stable transition and conversion flight between VTOL and horizontal flight.When this utility model has taken into account VTOL and long boat, the performance of big voyage, has the characteristic of bigger mission payload.When making high-speed flight, the propulsive efficiency of lifting resistance characteristic and dynamical system will be above helicopter and tiltrotor.
Described canard 7 is trapezoidal or sweepback or straight or sweepforward design regards wing specific design parameter determination.
Described canard 7 is lower anti-or upper anti-or flat design regards wing specific design parameter determination, canard 7 is used to increase full machine useful lift, increase the nose-up pitching moment of full machine, the nose-down pitching moment that balance is produced by main wing, and use active control technology, solve the problem that the longitudinal controllability of full machine in prior art is not enough.
Described head 6 is flat lifting body, and the both sides of head 6 are provided with the fusant strake wing 13 for lift-rising, and good effect is played in the longitudinal moment trim to aircraft that arranges of described fusant strake wing 13, improves maneuverability and the mobility of aircraft.
It is provided with aileron 8 on described outside main wing 3, described vertical fin 5 is provided with rudder 9.Increase course stability and the rudder face driving efficiency of aircraft, improve the anti-side wind performance of aircraft.
It is provided with elevator 10 on described tail 4, is controlled by the combination of elevator 4, canard 7, be conducive to obtaining the direct lift force control of full machine；By two rudders 9 and aileron 8 combination control, be conducive to the Direct Side Force producing full machine to control, so that the unconventional mode of motion of aircraft controls to be possibly realized, and improve the control response quality of aircraft.
It is provided with the precipitation fuselage motion of trousers 14, beneficially rotor down-wash flow between described fuselage 1 and rotor 11, reduces purling produced separation whirlpool on fuselage, increase the lift efficiency of rotor 11.
Aircraft of the present utility model has two kinds of offline mode, i.e. VTOL pattern and cruising level flight pattern, utilizes the uneoupled control of flight control system, it is possible to aloft realize the switch transition of both of which.During VTOL pattern, rotor wing rotation provides vertical lift, the periodicity displacement motion of rotor, using the teaching of the invention it is possible to provide aircraft pitch and rolling control moment；Utilize that to be arranged on the thrust of wing both sides electromotor poor, it is possible to make flat flying or during accelerated motion at aircraft, balance the reaction torque produced by rotor.During cruising level flight pattern, thered is provided forward direction horizontal thrust by the power set being arranged on wing, fixed wing provide prevailing lift, overcome full machine gravity, rotor rotates with minimum drag and minimal energy consumption state, thus realize aircraft efficient, at a high speed, at a distance, long boat time cruising level flight.
The above; it is only preferred embodiment of the present utility model; being not intended to limit protection domain of the present utility model, all any amendment, equivalent and improvement etc. made in spirit of the present utility model and principle, within should be included in protection domain of the present utility model.
Claims (10)
1. a novel high-lift vertically taking off and landing flyer, it is characterized in that, this aircraft includes: fuselage (1), it is arranged on the main wing of tail (4) both sides of fuselage (1), described main wing is by inner side main wing (2) and outside main wing (3) is conformal constitutes, described inner side main wing (2) is buzzard-type wing, sweepforward angle is 10 ° ~ 75 °, the tail (4) of described fuselage (1) is provided above two vertical fins (5), head (6) both sides of described fuselage (1) are provided with canard (7), described fuselage (1) be provided above rotor (11), power set (12) it are provided with between described inner side main wing (2) and outside main wing (3), the bottom of described fuselage (1) is provided with undercarriage (15).
One the most according to claim 1 novel high-lift vertically taking off and landing flyer, it is characterized in that: described head (6) is flat lifting body head, head (6) both sides and be positioned at the position in canard (7) front and be provided with the fusant strake wing (13) for lift-rising.
One the most according to claim 2 novel high-lift vertically taking off and landing flyer, it is characterised in that: it is provided with aileron (8) on two outsides main wing (3), said two vertical fin (5) is provided with rudder (9).
One the most according to claim 3 novel high-lift vertically taking off and landing flyer, it is characterised in that: it is provided with elevator (10) on described tail (4).
One the most according to claim 4 novel high-lift vertically taking off and landing flyer, it is characterised in that: it is provided with trousers (14) between described fuselage (1) and rotor (11).
6. according to the one novel high-lift vertically taking off and landing flyer described in claim 1 or 2 or 3 or 4 or 5, it is characterised in that: described rotor (11) is single rotor or DCB Specimen, and blade is two panels blade, three blades, four blades, five blades or six blades.
7. according to the one novel high-lift vertically taking off and landing flyer described in claim 1 or 2 or 3 or 4 or 5, it is characterised in that: described outside main wing (3) is buzzard-type wing, tapered airfoil, RECTANGULAR WINGS, dalta wing or swept-back wing.
8. according to the one novel high-lift vertically taking off and landing flyer described in claim 1 or 2 or 3 or 4 or 5, it is characterised in that: described canard (7) is tapered airfoil, RECTANGULAR WINGS, buzzard-type wing, dalta wing, swept-back wing or the S-shaped leading edge wing.
9. according to the one novel high-lift vertically taking off and landing flyer described in claim 1 or 2 or 3 or 4 or 5, it is characterised in that: described undercarriage (15) uses first three point type, bicycle type, rear bikini or cunning to stick up formula.
10. according to the one novel high-lift vertically taking off and landing flyer described in claim 1 or 2 or 3 or 4 or 5, it is characterised in that: described power set (12) use airscrew engine or turboprop or genemotor or turbojet or turbofan.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620406354.0U CN205602117U (en) | 2016-05-06 | 2016-05-06 | Novel high lift VTOL aircraft |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201620406354.0U CN205602117U (en) | 2016-05-06 | 2016-05-06 | Novel high lift VTOL aircraft |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105818980A (en) * | 2016-05-06 | 2016-08-03 | 刘行伟 | Novel large-lift-force vertical take-off and landing aircraft |
| RU2770389C2 (en) * | 2017-09-28 | 2022-04-15 | Винати С.Р.Л. | Rotary-wing aircraft with propulsion unit on rotating rod |
-
2016
- 2016-05-06 CN CN201620406354.0U patent/CN205602117U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105818980A (en) * | 2016-05-06 | 2016-08-03 | 刘行伟 | Novel large-lift-force vertical take-off and landing aircraft |
| RU2770389C2 (en) * | 2017-09-28 | 2022-04-15 | Винати С.Р.Л. | Rotary-wing aircraft with propulsion unit on rotating rod |
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