CN204264444U - Joined wing configuration aircraft during high lift length boat - Google Patents
Joined wing configuration aircraft during high lift length boat Download PDFInfo
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- CN204264444U CN204264444U CN201420655645.4U CN201420655645U CN204264444U CN 204264444 U CN204264444 U CN 204264444U CN 201420655645 U CN201420655645 U CN 201420655645U CN 204264444 U CN204264444 U CN 204264444U
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- wing
- fuselage
- high lift
- joined
- main
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- 210000001364 upper extremity Anatomy 0.000 claims abstract description 41
- 238000009434 installation Methods 0.000 claims description 9
- 230000003028 elevating effect Effects 0.000 claims description 6
- 230000000694 effects Effects 0.000 description 13
- 230000004927 fusion Effects 0.000 description 8
- 239000000295 fuel oil Substances 0.000 description 5
- 238000000034 method Methods 0.000 description 4
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 210000003414 extremity Anatomy 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/06—Aircraft not otherwise provided for having disc- or ring-shaped wings
- B64C39/068—Aircraft not otherwise provided for having disc- or ring-shaped wings having multiple wings joined at the tips
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/25—Fixed-wing aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/10—Wings
Abstract
The utility model discloses joined wing configuration aircraft when a kind of high lift length is navigated, comprise fuselage, be arranged on the main wing of fuselage both sides, the end of the main wing of described fuselage both sides is respectively arranged with 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.It is large that the utility model has effective lift, and induced drag is little, and the integral rigidity of wing is strong, and structure efficiency is high, and full machine load characteristic is good, the advantages such as damage tolerance is large.
Description
Technical field
The utility model belongs to field of flight vehicle design, is specifically related to joined wing configuration aircraft when a kind of high lift length is navigated.
Background technology
One of direction of aviation field exploration during high lift length boat always, during high lift length boat, aircraft has great effect in every field, during the flight of this aircraft requirements, there is high lift-drag ratio, possesses powerful flying power simultaneously, therefore such flying condition needs wing to have very large aspect ratio and lighter structural weight, under comparable size, the fuel oil amount of being loaded with is higher than other aircraft.
Utility model content
For solving the technical matters of existing existence, when the utility model embodiment provides a kind of high lift length to navigate, joined wing configuration aircraft, can improve the flying power of aircraft, increase aircraft effective lift face.
For achieving the above object, the technical scheme of the utility model embodiment is achieved in that
Joined wing configuration aircraft when the utility model embodiment provides a kind of high lift length to navigate, comprise fuselage, be arranged on the main wing of fuselage both sides, the end of the main wing of described fuselage both sides is respectively arranged with 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.
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 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 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:
Joined wing configuration aircraft when the utility model provides a kind of high lift length to navigate, comprise fuselage, be arranged on the main wing of fuselage both sides, the end of the main wing of described fuselage both sides is respectively arranged with 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, by adopting lifting body fuselage, 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, it is large that the utility model has effective lift, and induced drag is little, and the integral rigidity of wing is strong, and structure efficiency is high, and full machine load characteristic is good, the advantages such as damage tolerance is large.
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 back view 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 deployed condition structural representation of joined wing configuration aircraft when Fig. 9 is a kind of high lift that the utility model embodiment 5 provides long boat.
In figure, 1-fuselage; 2-main wing; 3-upper limb; 4-holds the wing; 5-wing flap; 6-aileron; 7-elevating rudder; 8-yaw rudder; 9-engine installation; 10-vertical fin; 11-rotor shaft; 12-folding rotor; 13-rotor hatchcover.
Detailed description of the invention
Below in conjunction with the drawings and specific embodiments, the utility model is described in detail.
Embodiment 1:
Joined wing configuration aircraft when the utility model embodiment provides a kind of high lift length to navigate, as shown in figures 1-4, this aircraft comprises fuselage 1, be arranged on the main wing 2 of fuselage 1 both sides, the end of the main wing 2 of described fuselage 1 both sides is respectively arranged with the end wing 4, the top of described two end wings 4 is connected with the vertical fin 10 being arranged on fuselage 1 afterbody respectively by the upper limb 3 be arranged on above fuselage 1, the main wing sweepback of aircraft, upper limb adopts 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 3 and main wing 2 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 1 and the main wing 2 of described aircraft have carried out the warm process of wing body, thus under the prerequisite improving its pneumatic usefulness, add the structural strength of fuselage wing junction; The wing of described main wing 2 slightly carries out fusion treatment with the lower aerofoil of the end wing 4, reaches the effect of wing and the combination of the end wing; Described vertical fin 10 carries out fusion with fuselage 1 and is connected, and gains in strength; The inner space degree of utilization of described aircraft is high, and sections bracing with connective positional such as the end wing, upper limb, main wing wing tip etc. can be arranged and carry heavier load or fuel oil and the large distortion of unlikely generation.
Embodiment 2:
Joined wing configuration aircraft when the utility model embodiment provides a kind of high lift length to navigate, as shown in Figure 5, this aircraft comprises fuselage 1, be arranged on the main wing 2 of fuselage 1 both sides, the end of the main wing 2 of described fuselage 1 both sides is respectively arranged with the end wing 4, the top of described two end wings 4 is connected with the vertical fin 10 being arranged on fuselage 1 afterbody respectively by the upper limb 3 be arranged on above fuselage 1, the main wing sweepback of aircraft, upper limb adopts 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 3 and main wing 2 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 1 and the main wing 2 of described aircraft have carried out the warm process of wing body, thus under the prerequisite improving its pneumatic usefulness, add the structural strength of fuselage wing junction; The wing of described main wing 2 slightly carries out fusion treatment with the lower aerofoil of the end wing 4, reaches the effect of wing and the combination of the end wing; Described vertical fin 10 carries out fusion with fuselage 1 and is connected, and gains in strength; The inner space degree of utilization of described aircraft is high, and sections bracing with connective positional such as the end wing, upper limb, main wing wing tip etc. can be arranged and carry heavier load or fuel oil and the large distortion of unlikely generation.
The afterbody of described two end wings 4 is provided with yaw rudder 8, described two upper limbs 3 is provided with elevating rudder 7, described two main wings 2 are provided with aileron 6.
Arranged direction rudder 8 on the end wing 4, 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:
Joined wing configuration aircraft when the utility model embodiment provides a kind of high lift length to navigate, as shown in Figure 6, this aircraft comprises fuselage 1, be arranged on the main wing 2 of fuselage 1 both sides, the end of the main wing 2 of described fuselage 1 both sides is respectively arranged with the end wing 4, the top of described two end wings 4 is connected with the vertical fin 10 being arranged on fuselage 1 afterbody respectively by the upper limb 3 be arranged on above fuselage 1, the main wing sweepback of aircraft, upper limb adopts 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 3 and main wing 2 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 1 and the main wing 2 of described aircraft have carried out the warm process of wing body, thus under the prerequisite improving its pneumatic usefulness, add the structural strength of fuselage wing junction; The wing of described main wing 2 slightly carries out fusion treatment with the lower aerofoil of the end wing 4, reaches the effect of wing and the combination of the end wing; Described vertical fin 10 carries out fusion with fuselage 1 and is connected, and gains in strength; The inner space degree of utilization of described aircraft is high, and sections bracing with connective positional such as the end wing, upper limb, main wing wing tip etc. can be arranged and carry heavier load or fuel oil and the large distortion of unlikely generation.
The afterbody of described two end wings 4 is provided with yaw rudder 8, and described two upper limbs 3 are provided with elevating rudder 7.
Described two main wings 2 are provided with wing flap 5, aileron 6, and on described main wing 2, the length of wing flap 5 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 ~ 3, the described end wing 4 is vertically set on the end wing stabilator at main wing 2 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 ~ 3, described upper limb 3 is arranged on the top of main wing 2, 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 ~ 3, described main wing 2, upper limb 3 and the end wing adopt early stage aerofoil profile, laminar f1ow airfoil profile, high lift aerofoil profile or supercritical airfoil.
Embodiment 4:
On the basis of embodiment 1, as shown in Figure 7, the afterbody of described fuselage 1 is provided with engine installation 9, and described engine installation 9 adopts airscrew engine or jet engine.
Further, on the basis of embodiment 4, the afterbody of described two end wings 4 is provided with yaw rudder 8, and described two upper limbs 3 are provided with elevating rudder 7.
Further, on the basis of embodiment 4, the afterbody of described two end wings 4 is provided with yaw rudder 8, and described two upper limbs 3 are provided with elevating rudder 7.Described two main wings 2 are provided with wing flap 5, aileron 6, and on described main wing 2, the length of wing flap 5 and the length of aileron 6 can be the same or different, and need to select according to the design of aircraft.
Embodiment 5:
Joined wing configuration aircraft when the utility model embodiment also provides a kind of high lift length to navigate, as Fig. 8, shown in 9, this aircraft comprises fuselage 1, be arranged on the main wing 2 of fuselage 1 both sides, the end of the main wing 2 of described fuselage 1 both sides is respectively arranged with the end wing 4, the top of described two end wings 4 is connected with the vertical fin 10 being arranged on fuselage 1 afterbody respectively by the upper limb 3 be arranged on above fuselage 1, the main wing sweepback of aircraft, upper limb adopts 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 3 and main wing 2 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 1 and the main wing 2 of described aircraft have carried out the warm process of wing body, thus under the prerequisite improving its pneumatic usefulness, add the structural strength of fuselage wing junction; The wing of described main wing 2 slightly carries out fusion treatment with the lower aerofoil of the end wing 4, reaches the effect of wing and the combination of the end wing; Described vertical fin 10 carries out fusion with fuselage 1 and is connected, and gains in strength; The inner space degree of utilization of described aircraft is high, and sections bracing with connective positional such as the end wing, upper limb, main wing wing tip etc. can be arranged and carry heavier load or fuel oil and the large distortion of unlikely generation;
The described end wing 4 is vertically set on the end wing stabilator at main wing 2 wingtip place, adopt the end wing stabilator at wingtip place, upper and lower aerofoil is integrally formed, arranged direction rudder 8 on the end wing 4 simultaneously, increase course stability and the rudder face driving efficiency of aircraft, improve the anti-side wind performance of aircraft, reduce junction complex structural designs degree.
Described upper limb 3 is arranged on the top of main wing 2, and is provided with spacing between the two, and both wings interplanar distance is enough, within the scope of comparatively At High Angle of Attack, unfavorable interference ratio is each other little, gives 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 main wing 2, upper limb 3 and the end wing 4 adopt early stage aerofoil profile, laminar f1ow airfoil profile, high lift aerofoil profile or supercritical airfoil.
Described fuselage 1 inside is provided with telescopic rotor shaft 11, and the top of described rotor shaft 11 is provided with two leaf folding rotors 12, and described fuselage 1 is also provided with rotor hatchcover 13, 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 13, drives rotor shaft 11 to rise, stretches out completely and lock when rotor shaft 11, and open the latching device of folding rotor 12, folding rotor 12 is launched under the effect of predetermincd tension; Power plant 9 disconnects with the connection of engine drive axle simultaneously, adopt power switching device, engine drive axle and the rotor shaft 11 being used for vertical landing are connect, drives rotor shaft 11 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 12 folds, and rotor shaft 11 is taken in fuselage, rotor hatchcover 13 is closed, and aircraft completes vertical landing.
Further, on the basis of embodiment 5, the afterbody of described fuselage 1 is provided with engine installation 9, and described engine installation 9 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 (9)
1. joined wing configuration aircraft during a high lift length boat, it is characterized in that: comprise fuselage (1), be arranged on the main wing (2) of fuselage (1) both sides, the end of the main wing (2) of described fuselage (1) both sides is respectively arranged with the end wing (4), and the top of described two ends wing (4) is connected with the vertical fin (10) being arranged on fuselage (1) afterbody respectively by the upper limb (3) being arranged on fuselage (1) top.
2. joined wing configuration aircraft during high lift length boat according to claim 1, it is characterized in that: the afterbody of described two ends wing (4) is provided with yaw rudder (8), and described two upper limbs (3) are provided with elevating rudder (7); Described two main wings (2) are provided with aileron (6).
3. joined wing configuration aircraft during high lift length boat according to claim 2, is characterized in that: described two main wings (2) are provided with wing flap (5).
4. when the high lift length according to claim 1 or 2 or 3 is navigated, joined wing configuration aircraft, is characterized in that: the described end wing (4) is vertically set on the end wing stabilator at main wing (2) wingtip place.
5. when the high lift length according to claim 1 or 2 or 3 is navigated, joined wing configuration aircraft, is characterized in that: described upper limb (3) is arranged on the top of main wing (2), and is provided with spacing between the two.
6. joined wing configuration aircraft when the high lift length according to claim 1 or 2 or 3 is navigated, is characterized in that: described main wing (2), upper limb (3) and the end wing (4) adopt early stage aerofoil profile, laminar f1ow airfoil profile, high lift aerofoil profile or supercritical airfoil.
7. when the high lift length according to claim 1 or 2 or 3 is navigated, joined wing configuration aircraft, is characterized in that: the afterbody of described fuselage (1) is provided with engine installation (9).
8. joined wing configuration aircraft during high lift length boat according to claim 7, is characterized in that: described engine installation (9) adopts airscrew engine or jet engine.
9. joined wing configuration aircraft when the high lift length according to claim 1 or 2 or 3 is navigated, it is characterized in that: described fuselage (1) inside is provided with telescopic rotor shaft (11), the top of described rotor shaft (11) is provided with two leaf folding rotors (12), described fuselage (1) is also provided with rotor hatchcover (13).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420655645.4U CN204264444U (en) | 2014-11-05 | 2014-11-05 | Joined wing configuration aircraft during high lift length boat |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420655645.4U CN204264444U (en) | 2014-11-05 | 2014-11-05 | Joined wing configuration aircraft during high lift length boat |
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| CN204264444U true CN204264444U (en) | 2015-04-15 |
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| CN201420655645.4U Active CN204264444U (en) | 2014-11-05 | 2014-11-05 | Joined wing configuration aircraft during high lift length boat |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105882961A (en) * | 2016-04-13 | 2016-08-24 | 邓阳平 | High-speed aircraft capable of taking off and landing vertically as well as control method of high-speed aircraft |
| CN106143876A (en) * | 2015-04-24 | 2016-11-23 | 空客(北京)工程技术中心有限公司 | Thrustor, movable device and aircraft |
| FR3078683A1 (en) * | 2018-03-07 | 2019-09-13 | Francois Geli | LOW COST OPTION OF A SECOND WING TO ULTRA-SOBRE A PLANE AIRPLANE |
| CN113044199A (en) * | 2021-04-20 | 2021-06-29 | 西北工业大学 | High-performance low Reynolds number tandem laminar flow wing section based on connecting wing layout unmanned aerial vehicle |
-
2014
- 2014-11-05 CN CN201420655645.4U patent/CN204264444U/en active Active
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106143876A (en) * | 2015-04-24 | 2016-11-23 | 空客(北京)工程技术中心有限公司 | Thrustor, movable device and aircraft |
| CN106143876B (en) * | 2015-04-24 | 2023-11-24 | 空客(北京)工程技术中心有限公司 | Pushing device, moving mechanism and aircraft |
| CN105882961A (en) * | 2016-04-13 | 2016-08-24 | 邓阳平 | High-speed aircraft capable of taking off and landing vertically as well as control method of high-speed aircraft |
| FR3078683A1 (en) * | 2018-03-07 | 2019-09-13 | Francois Geli | LOW COST OPTION OF A SECOND WING TO ULTRA-SOBRE A PLANE AIRPLANE |
| CN113044199A (en) * | 2021-04-20 | 2021-06-29 | 西北工业大学 | High-performance low Reynolds number tandem laminar flow wing section based on connecting wing layout unmanned aerial vehicle |
| CN113044199B (en) * | 2021-04-20 | 2023-12-15 | 西北工业大学 | High-performance low-Reynolds number serial laminar flow wing profile based on coupling wing layout unmanned aerial vehicle |
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