CN204264454U - Novel high lift canard configuration connects rotor aircraft - Google Patents
Novel high lift canard configuration connects rotor aircraft Download PDFInfo
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- CN204264454U CN204264454U CN201420655954.1U CN201420655954U CN204264454U CN 204264454 U CN204264454 U CN 204264454U CN 201420655954 U CN201420655954 U CN 201420655954U CN 204264454 U CN204264454 U CN 204264454U
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Abstract
The utility model discloses a kind of novel high lift canard configuration and connect rotor aircraft, comprise: fuselage, the main wing being arranged on fuselage both sides, upper limb, the end wing, vertical fin, the described end being arranged on the main wing of fuselage both sides all arranges the end wing, and the top of described two end wings is connected with the vertical fin being arranged on afterbody respectively by the upper limb being arranged on body upper; The head both sides of described fuselage are provided with canard.The utility model can give full play to the lift-rising effect of two groups of aerofoils, and simultaneously under At High Angle of Attack condition, full facility have good stalling characteristics; Fuselage, as the vitals of aircraft, is unified into an entirety wing, vertical fin, canard and driving engine, and the design of its fleetline decreases aerodynamic drag, provides lift simultaneously.
Description
Technical field
The utility model belongs to field of flight vehicle design, is specifically related to a kind of novel high lift canard configuration and connects rotor aircraft.
Background technology
Along with the fast development of aeronautical technology and composite material, adopt the aircraft research connecting wing structure to obtain and develop faster, connect wing structure tool and have the following advantages: lightweight construction, good rigidity, induced drag compared with little, trim lift is large; Have the potential producing By Using Active Lift, Direct Side Force, stability and control is good; There is good anti-mistake pendant characteristic, be extremely conducive to the capacity weight improving aircraft, there is very high using value and economic benefit.
Owing to connecting the centre of lift that formed of the wing relatively rearward, be easy to produce larger nose-down pitching moment, be unfavorable for that the longitudinal moment balance of full machine controls, the problem of the qualitative deficiency in longitudinal Jing'an of full machine can be brought thus.
Utility model content
For solving the technical matters of existing existence, the utility model embodiment provides a kind of novel high lift canard configuration to connect rotor aircraft.
For achieving the above object, the technical scheme of the utility model embodiment is achieved in that
The utility model embodiment provides a kind of novel high lift canard configuration to connect rotor aircraft, this aircraft comprises: fuselage, the main wing being arranged on fuselage both sides, upper limb, the end wing, vertical fin, the described end being arranged on the main wing of fuselage both sides all arranges the end wing, and the top of described two end wings is connected with the vertical fin being arranged on afterbody respectively by the upper limb being arranged on body upper; The head both sides of described fuselage are provided with canard.
In such scheme, the afterbody of described two end wings is provided with yaw rudder, and described two upper limbs are provided with elevating rudder; Described two main wings are provided with aileron.
In such scheme, described head is flat duckbilled head.
In such scheme, described two main wings are provided with wing flap.
In such scheme, the described end wing is vertically set on the end wing stabilator at main wing wingtip place.
In such scheme, described upper limb is arranged on the top of main wing, and is provided with spacing between the two.
In such scheme, described canard, main wing, upper limb and the end wing adopt early stage aerofoil profile, laminar f1ow airfoil profile, high lift aerofoil profile or supercritical airfoil.
In such scheme, the afterbody of described fuselage is provided with engine installation.
In such scheme, described engine installation adopts airscrew engine or jet engine.
In such scheme, described fuselage interior is provided with telescopic rotor shaft, and the top of described rotor shaft is provided with two leaf folding rotors, and described fuselage is also provided with rotor hatchcover.
Compared with prior art, the beneficial effects of the utility model:
The utility model embodiment provides a kind of novel high lift canard configuration to connect rotor aircraft, this aircraft comprises: fuselage, the main wing being arranged on fuselage both sides, upper limb, the end wing, vertical fin, the described end being arranged on the main wing of fuselage both sides all arranges the end wing, and the top of described two end wings is connected with the vertical fin being arranged on afterbody respectively by the upper limb being arranged on body upper, the head both sides of described fuselage are provided with canard, the design of its fleetline decreases aerodynamic drag, by main wing sweepback, upper limb adopts sweepforward, the upper anti-swept back wing of aircraft and lower anti-sweepforward upper limb link together formed tandem wing configurations form, make the profile of the birds-eye view of aircraft and front view all close to rhombus, pneumatic efficiency is higher, upper limb and main wing have the aerodynamic characteristic of buzzard-type wing and swept wing respectively, both wings interplanar distance is enough, within the scope of comparatively At High Angle of Attack, unfavorable interference ratio is each other little, give full play to the lift-rising effect of two groups of aerofoils, simultaneously under At High Angle of Attack condition, full facility have good stalling characteristics, fuselage, as the vitals of aircraft, is unified into an entirety wing, vertical fin, canard and driving engine, and the design of its fleetline decreases aerodynamic drag, provides lift simultaneously.
Accompanying drawing explanation
The structural representation of joined wing configuration aircraft when Fig. 1 is a kind of high lift that the utility model embodiment 1 provides long boat;
The birds-eye view of joined wing configuration aircraft when Fig. 2 is a kind of high lift that the utility model embodiment 1 provides long boat;
The front elevation of joined wing configuration aircraft when Fig. 3 is a kind of high lift that the utility model embodiment 1 provides long boat;
The lateral plan of joined wing configuration aircraft when Fig. 4 is a kind of high lift that the utility model embodiment 1 provides long boat;
The structural representation of joined wing configuration aircraft when Fig. 5 is a kind of high lift that the utility model embodiment 2 provides long boat;
The structural representation of joined wing configuration aircraft when Fig. 6 is a kind of high lift that the utility model embodiment 3 provides long boat;
The structural representation of joined wing configuration aircraft when Fig. 7 is a kind of high lift that the utility model embodiment 4 provides long boat;
The structural representation of joined wing configuration aircraft when Fig. 8 is a kind of high lift that the utility model embodiment 5 provides long boat;
The structural representation of joined wing configuration aircraft when Fig. 9 is a kind of high lift that the utility model embodiment 6 provides long boat;
The deployed condition structural representation of joined wing configuration aircraft when Figure 10 is a kind of high lift that the utility model embodiment 6 provides long boat.
In figure: 1-fuselage; 2-canard; 3-main wing; 4-upper limb; 5-holds the wing; 6-aileron; 7-elevating rudder; 8-yaw rudder; 9-vertical fin; 10-engine installation; 11-head; 12-moves rotor shaft; 13-folding rotor; 14-rotor hatchcover; 15-wing flap.
Detailed description of the invention
Below in conjunction with the drawings and specific embodiments, the utility model is described in detail.
Embodiment 1:
The utility model embodiment provides a kind of novel high lift canard configuration to connect rotor aircraft, as shown in figures 1-4, this aircraft comprises: fuselage 1, the main wing 3 being arranged on fuselage 1 both sides, upper limb 4, the end wing 5, vertical fin 9, the described end being arranged on the main wing 3 of fuselage 1 both sides all arranges the end wing 5, and the top of described two end wings 5 is connected with the vertical fin 9 being arranged on fuselage 1 afterbody respectively by the upper limb 4 be arranged on above fuselage 1; Head 11 both sides of described fuselage 1 are provided with canard 2; Main wing 3 sweepback of aircraft, upper limb 4 adopt sweepforward, upper anti-swept back wing and lower anti-sweepforward upper limb link together formed tandem wing configurations form, this layout makes the profile of the birds-eye view of aircraft and front view all close to rhombus, pneumatic efficiency is higher, upper limb 4 and main wing 3 have the aerodynamic characteristic of buzzard-type wing and swept wing respectively, both wings interplanar distance is enough, within the scope of comparatively At High Angle of Attack, unfavorable interference ratio is each other little, give full play to the lift-rising effect of two groups of aerofoils, simultaneously under At High Angle of Attack condition, full facility have good stalling characteristics.
Described canard 2 sweepback or flat design are determined depending on wing specific design parameter.
Described canard 2 is determined depending on wing specific design parameter for upper anti-or lower anti-or flat design, adopts canard 2 to increase the nose-up pitching moment of full machine, and adopts active control technology, solve the problem of the qualitative deficiency in longitudinal Jing'an of full machine in prior art.
Described fuselage 1 and main wing 3 and canard 2 have carried out the warm process of wing body respectively, thus under the prerequisite improving its pneumatic usefulness, add the structural strength of fuselage wing junction, the wing of described main wing 3 slightly merges with the lower aerofoil of the end wing 5, reach the effect of wing and the combination of the end wing, described vertical fin 9 and fuselage 1 have carried out merging being connected, and add intensity.
Embodiment 2:
The utility model embodiment provides a kind of novel high lift canard configuration to connect rotor aircraft, as shown in Figure 5, this aircraft comprises: fuselage 1, the main wing 3 being arranged on fuselage 1 both sides, upper limb 4, the end wing 5, vertical fin 9, the described end being arranged on the main wing 3 of fuselage 1 both sides all arranges the end wing 5, and the top of described two end wings 5 is connected with the vertical fin 9 being arranged on fuselage 1 afterbody respectively by the upper limb 4 be arranged on above fuselage 1; Head 11 both sides of described fuselage 1 are provided with canard 2; Main wing 3 sweepback of aircraft, upper limb 4 adopt sweepforward, upper anti-swept back wing and lower anti-sweepforward upper limb link together formed tandem wing configurations form, this layout makes the profile of the birds-eye view of aircraft and front view all close to rhombus, pneumatic efficiency is higher, upper limb 4 and main wing 3 have the aerodynamic characteristic of buzzard-type wing and swept wing respectively, both wings interplanar distance is enough, within the scope of comparatively At High Angle of Attack, unfavorable interference ratio is each other little, give full play to the lift-rising effect of two groups of aerofoils, simultaneously under At High Angle of Attack condition, full facility have good stalling characteristics.
Described canard 2 sweepback or flat design are determined depending on wing specific design parameter.
Described canard 2 is determined depending on wing specific design parameter for upper anti-or lower anti-or flat design, adopts canard 2 to increase the nose-up pitching moment of full machine, and adopts active control technology, solve the problem of the qualitative deficiency in longitudinal Jing'an of full machine in prior art.
Described fuselage 1 and main wing 3 and canard 2 have carried out the warm process of wing body respectively, thus under the prerequisite improving its pneumatic usefulness, add the structural strength of fuselage wing junction, the wing of described main wing 3 slightly merges with the lower aerofoil of the end wing 5, reach the effect of wing and the combination of the end wing, described vertical fin 9 and fuselage 1 have carried out merging being connected, and add intensity.
The afterbody of described two end wings 5 is provided with yaw rudder 8, and described two upper limbs 4 are provided with elevating rudder 7; Described two main wings 3 are provided with aileron 6.
Arranged direction rudder 8 on the end wing 5, increases course stability and the rudder face driving efficiency of aircraft, improves the anti-side wind performance of aircraft simultaneously, reduces junction complex structural designs degree.
Embodiment 3:
The utility model embodiment provides a kind of novel high lift canard configuration to connect rotor aircraft, as shown in Figure 6, this aircraft comprises: fuselage 1, the main wing 3 being arranged on fuselage 1 both sides, upper limb 4, the end wing 5, vertical fin 9, the described end being arranged on the main wing 3 of fuselage 1 both sides all arranges the end wing 5, and the top of described two end wings 5 is connected with the vertical fin 9 being arranged on fuselage 1 afterbody respectively by the upper limb 4 be arranged on above fuselage 1; Head 11 both sides of described fuselage 1 are provided with canard 2; Main wing 3 sweepback of aircraft, upper limb 4 adopt sweepforward, upper anti-swept back wing and lower anti-sweepforward upper limb link together formed tandem wing configurations form, this layout makes the profile of the birds-eye view of aircraft and front view all close to rhombus, pneumatic efficiency is higher, upper limb 4 and main wing 3 have the aerodynamic characteristic of buzzard-type wing and swept wing respectively, both wings interplanar distance is enough, within the scope of comparatively At High Angle of Attack, unfavorable interference ratio is each other little, give full play to the lift-rising effect of two groups of aerofoils, simultaneously under At High Angle of Attack condition, full facility have good stalling characteristics.
Described canard 2 sweepback or flat design are determined depending on wing specific design parameter.
Described canard 2 is determined depending on wing specific design parameter for upper anti-or lower anti-or flat design.
Described fuselage 1 and main wing 3 and canard 2 have carried out the warm process of wing body respectively, thus under the prerequisite improving its pneumatic usefulness, add the structural strength of fuselage wing junction, the wing of described main wing 3 slightly merges with the lower aerofoil of the end wing 5, reach the effect of wing and the combination of the end wing, described vertical fin 9 and fuselage 1 have carried out merging being connected, and add intensity.
The afterbody of described two end wings 5 is provided with yaw rudder 8, and described two upper limbs 4 are provided with elevating rudder 7; Described two main wings 3 are provided with aileron 6.
Arranged direction rudder 8 on the end wing 5, increases course stability and the rudder face driving efficiency of aircraft, improves the anti-side wind performance of aircraft simultaneously, reduces junction complex structural designs degree.
Controlled by the combination of elevating rudder 7, canard 2, be conducive to the direct lift force control obtaining full machine; By two yaw rudders and aileron 6 combination control, the Direct Side Force being conducive to producing full machine controls, thus makes the unconventional mode of motion of aircraft control to become possibility, and improves the control response quality of aircraft.
Described head 11 is flat duckbilled head, and the flat Die Design of duck-beak type takes full advantage of biosimulation, and flat lip is the common feature of the biologies such as wild goose, decreases air resistance, is beneficial to biological flight.
The utility model adopts canard 2 and flat duckbilled head, can make aircraft in flight course, substantially be in positive trim condition, that is: in trimmed flight, canard 2 can be controlled and elevating rudder 7 produces positive lift force simultaneously, increase the lift efficiency of full machine further, more increase the capacity weight of aircraft.
Embodiment 4:
The utility model embodiment provides a kind of novel high lift canard configuration to connect rotor aircraft, as shown in Figure 7, this aircraft comprises: fuselage 1, the main wing 3 being arranged on fuselage 1 both sides, upper limb 4, the end wing 5, vertical fin 9, the described end being arranged on the main wing 3 of fuselage 1 both sides all arranges the end wing 5, and the top of described two end wings 5 is connected with the vertical fin 9 being arranged on fuselage 1 afterbody respectively by the upper limb 4 be arranged on above fuselage 1; Head 11 both sides of described fuselage 1 are provided with canard 2; Main wing 3 sweepback of aircraft, upper limb 4 adopt sweepforward, upper anti-swept back wing and lower anti-sweepforward upper limb link together formed tandem wing configurations form, this layout makes the profile of the birds-eye view of aircraft and front view all close to rhombus, pneumatic efficiency is higher, upper limb 4 and main wing 3 have the aerodynamic characteristic of buzzard-type wing and swept wing respectively, both wings interplanar distance is enough, within the scope of comparatively At High Angle of Attack, unfavorable interference ratio is each other little, give full play to the lift-rising effect of two groups of aerofoils, simultaneously under At High Angle of Attack condition, full facility have good stalling characteristics.
Described canard 2 sweepback or flat design are determined depending on wing specific design parameter.
Described canard 2 is determined depending on wing specific design parameter for upper anti-or lower anti-or flat design.
Described fuselage 1 and main wing 3 and canard 2 have carried out the warm process of wing body respectively, thus under the prerequisite improving its pneumatic usefulness, add the structural strength of fuselage wing junction, the wing of described main wing 3 slightly merges with the lower aerofoil of the end wing 5, reach the effect of wing and the combination of the end wing, described vertical fin 9 and fuselage 1 have carried out merging being connected, and add intensity.
The afterbody of described two end wings 5 is provided with yaw rudder 8, and described two upper limbs 4 are provided with elevating rudder 7.
Arranged direction rudder 8 on the end wing 5, increases course stability and the rudder face driving efficiency of aircraft, improves the anti-side wind performance of aircraft simultaneously, reduces junction complex structural designs degree.
Described head 11 is flat duckbilled head, and the flat Die Design of duck-beak type takes full advantage of biosimulation, and flat lip is the common feature of the biologies such as wild goose, decreases air resistance, is beneficial to biological flight.
Described two main wings 3 are provided with wing flap 15, aileron 6.On described main wing 3, the length of wing flap 15 and the length of aileron 6 can be the same or different, and need to select according to the design of aircraft.
Further, on the basis of any one embodiment of embodiment 1 ~ 4, the described end wing 5 is vertically set on the end wing stabilator at main wing 3 wingtip place, adopts the end wing stabilator at wingtip place, upper and lower aerofoil is integrally formed.
Further, on the basis of any one embodiment of embodiment 1 ~ 4, described upper limb 4 is arranged on the top of main wing 3, and be provided with spacing between the two, both wings interplanar distance is enough, within the scope of comparatively At High Angle of Attack, unfavorable interference ratio is each other little, give full play to the lift-rising effect of two groups of aerofoils, simultaneously under At High Angle of Attack condition, full facility have good stalling characteristics.
Further, on the basis of any one embodiment of embodiment 1 ~ 4, described canard 2, main wing 3, upper limb 4 and the end wing 5 adopt early stage aerofoil profile, laminar f1ow airfoil profile, high lift aerofoil profile or supercritical airfoil.
Embodiment 5:
On the basis of embodiment 1, as shown in Figure 8, the afterbody of described fuselage 1 is provided with engine installation 10, and described engine installation 10 adopts airscrew engine or jet engine.
Further, on the basis of embodiment 5, the afterbody of described two end wings 5 is provided with yaw rudder 8, described two upper limbs 4 is provided with elevating rudder 7, described main wing 3 is provided with aileron 6.
Further, on the basis of embodiment 5, the afterbody of described two end wings 5 is provided with yaw rudder 8, and described two upper limbs 4 are provided with elevating rudder 7.Described two main wings 3 are provided with wing flap 15, aileron 6, and on described main wing 3, the length of wing flap 15 and the length of aileron 6 can be the same or different, and need to select according to the design of aircraft.
Embodiment 6:
The utility model embodiment provides a kind of novel high lift canard configuration to connect rotor aircraft, as shown in Fig. 9,10, this aircraft comprises: fuselage 1, the main wing 3 being arranged on fuselage 1 both sides, upper limb 4, the end wing 5, vertical fin 9, the described end being arranged on the main wing 3 of fuselage 1 both sides all arranges the end wing 5, and the top of described two end wings 5 is connected with the vertical fin 9 being arranged on fuselage 1 afterbody respectively by the upper limb 4 be arranged on above fuselage 1; Head 11 both sides of described fuselage 1 are provided with canard 2; Main wing 3 sweepback of aircraft, upper limb 4 adopt sweepforward, upper anti-swept back wing and lower anti-sweepforward upper limb link together formed tandem wing configurations form, this layout makes the profile of the birds-eye view of aircraft and front view all close to rhombus, pneumatic efficiency is higher, upper limb 4 and main wing 3 have the aerodynamic characteristic of buzzard-type wing and swept wing respectively, both wings interplanar distance is enough, within the scope of comparatively At High Angle of Attack, unfavorable interference ratio is each other little, give full play to the lift-rising effect of two groups of aerofoils, simultaneously under At High Angle of Attack condition, full facility have good stalling characteristics.
Described canard 2 sweepback or flat design are determined depending on wing specific design parameter.
Described canard 2 is determined depending on wing specific design parameter for upper anti-or lower anti-or flat design.
Described fuselage 1 and main wing 3 and canard 2 have carried out the warm process of wing body respectively, thus under the prerequisite improving its pneumatic usefulness, add the structural strength of fuselage wing junction, the wing of described main wing 3 slightly merges with the lower aerofoil of the end wing 5, reach the effect of wing and the combination of the end wing, described vertical fin 9 and fuselage 1 have carried out merging being connected, and add intensity.
Described fuselage 1 inside is provided with telescopic rotor shaft 12, and the top of described rotor shaft 12 is provided with two leaf folding rotors 13, and described fuselage 1 is also provided with rotor hatchcover 14, makes aircraft have short takeoff vertical landing function.
When preparing to land, reduce the mode of operation of pusher engine gradually, aircraft reduces speed now, when flying speed reaches certain threshold value, flight control system controls to open rotor hatchcover 14, drives rotor shaft 12 to rise, stretches out completely and lock when rotor shaft 12, and open the latching device of folding rotor 13, folding rotor 13 is launched under the effect of predetermincd tension; Power plant 10 disconnects with the connection of engine drive axle simultaneously, adopt power switching device, engine drive axle and the rotor shaft 12 being used for vertical landing are connect, drives rotor shaft 12 to work, produce the landing lift needed for full machine, aircraft vertical is made to drop to the predetermined area, rotor slows down until quit work, and folding rotor 13 folds, and rotor shaft 12 is taken in fuselage, described rotor hatchcover 14 is closed, and aircraft completes vertical landing.
Further, on the basis of embodiment 6, the afterbody of described fuselage 1 is provided with engine installation 10, and described engine installation 10 adopts airscrew engine or jet engine.
The above; be only preferred embodiment of the present utility model; be not intended to limit protection domain of the present utility model, all do in spirit of the present utility model and principle any amendment, equivalent to replace and improvement etc., all should be included within protection domain of the present utility model.
Claims (10)
1. a novel high lift canard configuration connects rotor aircraft, it is characterized in that, this aircraft comprises: fuselage (1), the main wing (3) being arranged on fuselage (1) both sides, upper limb (4), the end wing (5), vertical fin (9), the described end being arranged on the main wing (3) of fuselage (1) both sides all arranges the end wing (5), and the top of described two ends wing (5) is connected with the vertical fin (9) being arranged on fuselage (1) afterbody respectively by the upper limb (4) being arranged on fuselage (1) top; Head (11) both sides of described fuselage (1) are provided with canard (2).
2. novel high lift canard configuration according to claim 1 connects rotor aircraft, it is characterized in that: the afterbody of described two ends wing (5) is provided with yaw rudder (8), and described two upper limbs (4) are provided with elevating rudder (7); Described two main wings (3) are provided with aileron (6).
3. novel high lift canard configuration according to claim 2 connects rotor aircraft, it is characterized in that: described head (11) is flat duckbilled head.
4. novel high lift canard configuration according to claim 3 connects rotor aircraft, it is characterized in that: described two main wings (2) are provided with wing flap (15).
5. the novel high lift canard configuration according to claim 1 or 2 or 3 or 4 connects rotor aircraft, it is characterized in that: the described end wing (5) is vertically set on the end wing stabilator at main wing (3) wingtip place.
6. the novel high lift canard configuration according to claim 1 or 2 or 3 or 4 connects rotor aircraft, it is characterized in that: described upper limb (4) is arranged on the top of main wing (3), and is provided with spacing between the two.
7. the novel high lift canard configuration according to claim 1 or 2 or 3 or 4 connects rotor aircraft, it is characterized in that: described canard (2), main wing (3), upper limb (4) and the end wing (5) adopt early stage aerofoil profile, laminar f1ow airfoil profile, high lift aerofoil profile or supercritical airfoil.
8. the novel high lift canard configuration according to claim 1 or 2 or 3 or 4 connects rotor aircraft, it is characterized in that: the afterbody of described fuselage (1) is provided with engine installation (10).
9. novel high lift canard configuration according to claim 8 connects rotor aircraft, it is characterized in that: described engine installation (10) adopts airscrew engine or jet engine.
10. the novel high lift canard configuration according to claim 1 or 2 or 3 or 4 connects rotor aircraft, it is characterized in that: described fuselage (1) inside is provided with telescopic rotor shaft (12), the top of described rotor shaft (12) is provided with two leaf folding rotors (13), described fuselage (1) is also provided with rotor hatchcover (14).
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420655954.1U CN204264454U (en) | 2014-11-05 | 2014-11-05 | Novel high lift canard configuration connects rotor aircraft |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201420655954.1U CN204264454U (en) | 2014-11-05 | 2014-11-05 | Novel high lift canard configuration connects rotor aircraft |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105129090A (en) * | 2015-08-13 | 2015-12-09 | 中国航空工业集团公司西安飞机设计研究所 | Low resistance and low sonic boom layout supersonic aircraft |
| CN105818980A (en) * | 2016-05-06 | 2016-08-03 | 刘行伟 | Novel large-lift-force vertical take-off and landing aircraft |
| CN106043684A (en) * | 2016-06-01 | 2016-10-26 | 北京航空航天大学 | Combined type aircraft with rotor and wings capable of being linked |
-
2014
- 2014-11-05 CN CN201420655954.1U patent/CN204264454U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105129090A (en) * | 2015-08-13 | 2015-12-09 | 中国航空工业集团公司西安飞机设计研究所 | Low resistance and low sonic boom layout supersonic aircraft |
| CN105818980A (en) * | 2016-05-06 | 2016-08-03 | 刘行伟 | Novel large-lift-force vertical take-off and landing aircraft |
| CN106043684A (en) * | 2016-06-01 | 2016-10-26 | 北京航空航天大学 | Combined type aircraft with rotor and wings capable of being linked |
| CN106043684B (en) * | 2016-06-01 | 2018-09-11 | 北京航空航天大学 | A kind of connectible combined type aircraft of rotor wing |
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