CN105460202A - Variable-wing unmanned aerial vehicle - Google Patents
Variable-wing unmanned aerial vehicle Download PDFInfo
- Publication number
- CN105460202A CN105460202A CN201510850954.6A CN201510850954A CN105460202A CN 105460202 A CN105460202 A CN 105460202A CN 201510850954 A CN201510850954 A CN 201510850954A CN 105460202 A CN105460202 A CN 105460202A
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- China
- Prior art keywords
- host wing
- wing
- fuselage
- outer section
- inner segment
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/36—Structures adapted to reduce effects of aerodynamic or other external heating
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/08—Undercarriages non-fixed, e.g. jettisonable
- B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
- B64C3/385—Variable incidence wings
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
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- 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
- B64U30/12—Variable or detachable wings, e.g. wings with adjustable sweep
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Toys (AREA)
Abstract
The invention relates to a variable-wing unmanned aerial vehicle. The variable-wing unmanned aerial vehicle comprises an upper main wing, a lower main wing, a streamline-shaped vehicle body, a foldable undercarriage, front duck wings and a propeller, wherein the upper dihedral angle of the upper main wing can be adjusted, the lower dihedral angle of the lower main wing can be adjusted, and the propeller is arranged at the rear end of the vehicle body. According to the pneumatic contour characteristics of the variable-wing unmanned aerial vehicle, the upper main swing with the adjustable upper dihedral angle and the lower main wing with the adjustable lower dihedral angle are arranged, and the upper dihedral angle of the upper main wing and the lower dihedral angle of the lower main wing can be adjusted according to different flight postures, so that the pneumatic requirement for adapting to the contour of the variable-wing unmanned aerial vehicle having different flight postures is met. By the adoption of the pneumatic contour, the variable-wing unmanned aerial vehicle has the advantages that the structure is simple, pneumatic layout is simple and smooth, and the flight performance is good.
Description
Technical field
The invention belongs to technical field of aerospace, be specifically related to a kind of variable geometry unmanned plane.
Background technology
In airplane design, one is had not easily to overcome and contradiction: to want to improve flying speed, the wing of large sweepback angle, low aspect ratio must be selected, to reduce the drag due to shock wave of aircraft, but this type of wing lift when lower-speed state is less, and induced drag is larger, efficiency is not high, takeoff and landing poor-performing.Existing terms of settlement is at present, employing variable swept back wing designs, and general swing-wing interior wing panel is fixing, and outer wing connects with inner wing hinge axis, handled before and after outer wing by hydraulic booster and rotate, with the aspect ratio at the rear wiping angle and whole wing that change outer panel.
Meanwhile, biplane has good takeoff and landing performance ,/landing the ability of taking off of short distance, and good maneuvering performance, and what the aircraft of Earlier designs was more have employed twin designs.But because structural weight is too large, the shortcomings such as resistance is large, at present except a small amount of acrobatic aircraft and agrisilviculture aircraft, without this design of employing.
Summary of the invention
The object of the present invention is to provide a kind of variable geometry unmanned plane, this aerodynamic configuration makes unmanned plane all have good airworthiness, manoevreability under each state of flight, and has excellent short takeoff/landing ability.
For achieving the above object, the technical solution used in the present invention is:
A kind of variable geometry unmanned plane, it comprise fuselage, afterbody screw propeller, be arranged on front fuselage both sides preposition canard and be arranged in pairs in the upper host wing of waist and lower host wing; The same position that described upper host wing and lower host wing are positioned at fuselage radial direction is evenly arranged; Described upper host wing comprises host wing inner segment and the outer section of upper host wing, one end of described upper host wing inner segment and the outer section of upper host wing are hinged, the other end of described upper host wing inner segment is fixedly connected with fuselage, and the rear side of described upper host wing inner segment is provided with controlled rudder face; Two described upper host wing inner segments and two described lower host wings are along the distribution in " X " of fuselage radial direction; Lower controlled rudder face is provided with on rear side of described lower host wing.
Furtherly, described lower host wing comprises lower host wing inner segment and the outer section of lower host wing, one end of described lower host wing inner segment and the outer section of lower host wing are hinged, and the described lower host wing inner segment other end is fixedly connected with fuselage, and described lower controlled rudder face is arranged on lower host wing inner segment; Two described upper host wing inner segments and two described lower host wing inner segments are along the distribution in " X " of fuselage radial direction.
Furtherly, the outer section of described lower host wing and the outer section of upper host wing drive respectively by hydraulic booster.
Furtherly, the underside of forward of described fuselage is provided with nose-gear, is provided with main landing gear on the downside of the rear portion of described fuselage.
Compared with prior art, the beneficial effect that the present invention obtains is:
The aerodynamic configuration that inventing provides is characterized as has the upper host wing at the adjustable dihedral angle and the main lower wing of adjustable inverted diherdral, the dihedral angle of Your Majesty's wing and the inverted diherdral of main lower wing can regulate according to the difference of flight attitude, to adapt to the pneumatic requirement of the unmanned plane profile of different flight attitude.The advantages such as aerodynamic configuration provided by the invention, possesses structure simple, and the succinct smoothness of aerodynamic arrangement, airworthiness are good; Therefore short takeoff/landing ability increases greatly.
By the change to the outer section of host wing on unmanned plane and the outer section deflection angle of lower host wing, to adapt to the requirement to unmanned plane aerodynamic configuration under each state of flight.
The change of the outer section of host wing and the outer section deflection angle of lower host wing, makes the configuration of unmanned plane main wing change between class " work " word configuration and class " X " word configuration.Class " work " word configuration is similar to double-vane wing, has high lift, high maneuverability, the aerodynamic characteristicss such as good low-altitude low-speed performance.Class " X " word configuration air resistance is little, and flight stability is good, suitable cooperative level boning out high speed cruise flight.When host wing configuration changes between class " work " word configuration and class " X " word configuration, the requirement of other state of flights can be adapted to.
Accompanying drawing explanation
Fig. 1 is the axle geodesic structure schematic diagrams such as lower-speed state front of the present invention;
Fig. 2 is the axle geodesic structure schematic diagrams such as the lower-speed state back side of the present invention;
Fig. 3 is the axle geodesic structure schematic diagrams such as high-speed flight state of the present invention;
Fig. 4 is lower-speed state side-looking structural representation of the present invention;
Fig. 5 is that lower-speed state of the present invention faces structural representation;
Fig. 6 is lower-speed state plan structure schematic diagram of the present invention;
Fig. 7 is the outer section angle structural representation of host wing of the present invention.
In the accompanying drawings: controlled rudder face, 4 times outer sections of host wings, 5 times host wing inner segments, 6 times controlled rudder faces, 7 nose-gears, 8 main landing gears, 9 preposition canards, 10 fuselages, 11 screw propellers on host wing inner segment, 3 in the outer section, 2 of host wing on 1.
Detailed description of the invention
Below in conjunction with accompanying drawing 1-7, the present invention is described in more detail.
As shown in figures 1-6, a kind of variable geometry unmanned plane, it comprises fuselage 10, the screw propeller 11 of fuselage 10 afterbody, the preposition canard 9 being arranged on both sides, fuselage 10 front end and the upper host wing be arranged in pairs in the middle part of fuselage 10 and lower host wing; The same position that described upper host wing and lower host wing are positioned at fuselage 10 radial direction is uniformly distributed; Described upper host wing comprises host wing inner segment 2 and the outer section 1 of upper host wing, one end of described upper host wing inner segment 2 and the outer section 1 of upper host wing are hinged, the other end of described upper host wing inner segment 2 is fixedly connected with fuselage 10, and the rear side of described upper host wing inner segment 2 is provided with controlled rudder face 3; Two described upper host wing inner segments 2 and two described lower host wings are along the distribution in " X " of fuselage 10 radial direction; Lower controlled rudder face 6 is provided with on rear side of described lower host wing.Described lower host wing comprises lower host wing inner segment 5 and the outer section 4 of lower host wing, one end of described lower host wing inner segment 5 and the outer section 4 of lower host wing are hinged, described lower host wing inner segment 5 other end is fixedly connected with fuselage 10, and described lower controlled rudder face 6 is arranged on lower host wing inner segment 5; Two described upper host wing inner segments 2 and two described lower host wing inner segments 5 are along the distribution in " X " of fuselage 10 radial direction.The outer section 4 of described lower host wing and the outer section 1 of upper host wing swing respectively by hydraulic booster.The underside of forward of described fuselage 10 is provided with nose-gear 7, is provided with main landing gear 8 on the downside of the rear portion of described fuselage 10.
Variable geometry unmanned plane comprises the outer section 1 of the upper host wing that can upward deflect angle and can deflect down the outer section 4 of lower host wing of angle, upper host wing inner segment 2 and lower host wing inner segment 5 are immovable wing section, and its rear is provided with controlled rudder face 3 and lower controlled rudder face 6 for controlling flight attitude during aircraft flight.Described fuselage 10 has cleanliness profile, and front portion is provided with the preposition canard 9 for Balance Air kinetic moment, and rear portion is provided with the screw propeller 11 providing flying power.Underbelly is provided with the nose-gear 7 and main landing gear 8 that to take off for unmanned plane and land.
Inorganic be in take off or land state time, the outer section 1 of upper host wing section 4 zero deflection (as shown in Figure 5) outer with lower host wing.Now, the outer section 1 of upper host wing is substantially parallel with the outer section 4 of lower host wing, forms the dual wing configuration of class " work " word, can provide maximum lift and stability, unmanned plane can be made to have the ability of short field take-off or landing.
Inorganic be in high speed cruise conditions time, the outer section 1 of upper host wing upward deflects, until its leading edge is located along the same line to fixed upper host wing inner segment 2 leading edge, the outer section 4 of lower host wing deflects down, until its leading edge is located along the same line (as shown in Figure 5) to fixed lower host wing inner segment 6 leading edge.This state of flight, it is inner that unmanned plane nose-gear 7 and main landing gear 8 take in fuselage 10.Now, unmanned plane has minimum flight resistance, and the outer section 1 of upper host wing and the outer section 4 of lower host wing are all opened, and form one large-scale " X " shape wing configuration, provide the lift of high-speed flight, and flight stability.
Be in task phase at unmanned plane, now, unmanned plane wing configuration with take off/landing state is identical, forms the dual wing configuration of class " work " word, it is inner that nose-gear 7 and main landing gear 8 take in fuselage 10.There is the turn radius that maximum lift and biplane bring compared with large wing area little, the good manoevreability of the little grade of stalling speed.
Be in other state of flights at unmanned plane, as shown in Figure 7, the outer section 1 of upper host wing can deflect upward into a certain position being applicable to this state of flight.Meanwhile, the outer section 4 of lower host wing deflects down with a certain applicable position, to adapt to the aeroperformance required for this state of flight.
Want under any state of flight, unmanned plane is by the deflection of upper controlled rudder face 3 and lower controlled rudder face 6, thus change aerodynamic torque, to realize the change of unmanned plane during flying attitude.
Preposition canard 9 has under any state of flight, (upper host wing is made up of the outer section 1 of upper host wing and upper host wing inner segment 2 aerodynamic torque that in trim, host wing and lower host wing produce, lower host wing is made up of the outer section 4 of lower host wing and lower host wing inner segment 5), make unmanned plane have fore-and-aft stability.Fixed upper host wing inner segment 2 and lower host wing inner segment 5 can provide aerodynamic force to have lateral stability to make unmanned plane in any state of flight.
The present invention realizes based on following principle:
By the change to the outer section of host wing on unmanned plane and the outer section deflection angle of lower host wing, to adapt to the requirement to unmanned plane aerodynamic configuration under each state of flight.
The change of the outer section of host wing and the outer section deflection angle of lower host wing, makes the configuration of unmanned plane main wing change between class " work " word configuration and class " X " word configuration.Class " work " word configuration is similar to double-vane wing, has high lift, high maneuverability, the aerodynamic characteristicss such as good low-altitude low-speed performance.Class " X " word configuration air resistance is little, and flight stability is good, suitable cooperative level boning out high speed cruise flight.When host wing configuration changes between class " work " word configuration and class " X " word configuration, the requirement of other state of flights can be adapted to.
Compared with general configuration aircraft, aerodynamic configuration proposed by the invention is except adapting to the requirement to unmanned plane aerodynamic configuration under each state of flight, due to the outer section of host wing has can be deflection, host wing is therefore collapsible, and class " work " word configuration is compared with other applicable low-speed operations wing configuration, there is the characteristic of low aspect ratio, make it be conducive to using in narrow environment.The short distance of class " work " word configuration plays/falls performance, is also conducive to unmanned plane and uses in the conditions such as narrow environment or runway deficiency.
So-called " work " word configuration is exactly that two outer sections 1 of upper host wing and two outer sections 4 of lower host wing are all in horizontality, and viewed from unmanned plane front, host wing is as " work " word, and therefore this state is referred to as " work " word configuration.
So-called " X " word configuration is exactly that two outer sections 1 of upper host wing stretch out along upper host wing inner segment 2, extend with the aerofoil of upper host wing inner segment 2 and overlap, two outer sections 4 of lower host wing stretch out along lower host wing inner segment 5, extend with the aerofoil of lower host wing inner segment 5 and overlap, because two described upper host wing inner segments 2 and two described lower host wing inner segments 5 are along the distribution in " X " of fuselage 10 radial direction, therefore from host wing viewed from unmanned plane front as " X " word, therefore this state is referred to as " X " word configuration.
The outer section 1 of upper host wing and the outer section 4 of lower host wing are all controlled by the flight control system of unmanned plane, realized the change of attitude by hydraulic efficiency pressure system, controlled rudder face, screw propeller, alighting gear that wherein the technical program is mentioned can be that common structure is by flight control system cooperation control.
The above embodiment is only the preferred embodiments of the present invention, and and the feasible enforcement of non-invention exhaustive.For persons skilled in the art, to any apparent change done by it under the prerequisite not deviating from the principle of the invention and spirit, all should be contemplated as falling with within claims of the present invention.
Claims (4)
1. a variable geometry unmanned plane, is characterized in that: it comprises fuselage (10), the screw propeller (11) of fuselage (10) afterbody, the preposition canard (9) being arranged on fuselage (10) both sides, front end and the upper host wing be arranged in pairs in the middle part of fuselage (10) and lower host wing; The same position that described upper host wing and lower host wing are positioned at fuselage (10) radial is evenly arranged; Described upper host wing comprises host wing inner segment (2) and the outer section (1) of upper host wing, one end of described upper host wing inner segment (2) and the outer section (1) of upper host wing are hinged, the other end of described upper host wing inner segment (2) is fixedly connected with fuselage (10), and the rear side of described upper host wing inner segment (2) is provided with controlled rudder face (3); Two described upper host wing inner segments (2) and two described lower host wings are along the distribution in " X " of fuselage (10) radial direction;
Lower controlled rudder face (6) is provided with on rear side of described lower host wing.
2. a kind of variable geometry unmanned plane according to claim 1, it is characterized in that: described lower host wing comprises lower host wing inner segment (5) and the outer section (4) of lower host wing, one end of described lower host wing inner segment (5) and the outer section (4) of lower host wing are hinged, described lower host wing inner segment (5) other end is fixedly connected with fuselage (10), and described lower controlled rudder face (6) is arranged on lower host wing inner segment (5); Two described upper host wing inner segments (2) and two described lower host wing inner segments (5) are along the distribution in " X " of fuselage (10) radial direction.
3. a kind of variable geometry unmanned plane according to claim 2, is characterized in that: the outer section (4) of described lower host wing and the outer section (1) of upper host wing drive respectively by hydraulic booster.
4. a kind of variable geometry unmanned plane according to any one of claim 1-3, is characterized in that: the underside of forward of described fuselage (10) is provided with nose-gear (7), is provided with main landing gear (8) on the downside of the rear portion of described fuselage (10).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510850954.6A CN105460202B (en) | 2015-11-30 | 2015-11-30 | A kind of variable geometry unmanned plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510850954.6A CN105460202B (en) | 2015-11-30 | 2015-11-30 | A kind of variable geometry unmanned plane |
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| Publication Number | Publication Date |
|---|---|
| CN105460202A true CN105460202A (en) | 2016-04-06 |
| CN105460202B CN105460202B (en) | 2018-06-22 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201510850954.6A Active CN105460202B (en) | 2015-11-30 | 2015-11-30 | A kind of variable geometry unmanned plane |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106081106A (en) * | 2016-06-17 | 2016-11-09 | 深圳市元征科技股份有限公司 | Wireless charging unmanned plane |
| CN106428525A (en) * | 2016-11-11 | 2017-02-22 | 哈尔滨工业大学 | Flying robot with variable sweep angle launch tandem wings |
| CN106569501A (en) * | 2016-10-19 | 2017-04-19 | 广东容祺智能科技有限公司 | Dihedral-angle-controllable vehicle arm system and control method thereof |
| CN108408031A (en) * | 2018-01-18 | 2018-08-17 | 倪惠芳 | A kind of collapsible undercarriage of unmanned plane high stability |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN87206145U (en) * | 1987-04-03 | 1988-02-24 | 任世钧 | Flying toy with various wings |
| DE102008004054A1 (en) * | 2008-01-11 | 2009-07-23 | Lfk-Lenkflugkörpersysteme Gmbh | Unmanned monitoring and surveillance aircraft for use with mobile aircraft basis, comprises propeller for driving surveillance aircraft, navigation, steering and regulation electronics, and power supply unit |
| CN102381467A (en) * | 2011-08-31 | 2012-03-21 | 中国航天空气动力技术研究院 | Sweep-changing method of variable aircraft wing |
| CN103979104A (en) * | 2014-05-29 | 2014-08-13 | 西北工业大学 | Vertical take-off and landing miniature air vehicle with variable X-type wing |
-
2015
- 2015-11-30 CN CN201510850954.6A patent/CN105460202B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN87206145U (en) * | 1987-04-03 | 1988-02-24 | 任世钧 | Flying toy with various wings |
| DE102008004054A1 (en) * | 2008-01-11 | 2009-07-23 | Lfk-Lenkflugkörpersysteme Gmbh | Unmanned monitoring and surveillance aircraft for use with mobile aircraft basis, comprises propeller for driving surveillance aircraft, navigation, steering and regulation electronics, and power supply unit |
| CN102381467A (en) * | 2011-08-31 | 2012-03-21 | 中国航天空气动力技术研究院 | Sweep-changing method of variable aircraft wing |
| CN103979104A (en) * | 2014-05-29 | 2014-08-13 | 西北工业大学 | Vertical take-off and landing miniature air vehicle with variable X-type wing |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106081106A (en) * | 2016-06-17 | 2016-11-09 | 深圳市元征科技股份有限公司 | Wireless charging unmanned plane |
| CN106569501A (en) * | 2016-10-19 | 2017-04-19 | 广东容祺智能科技有限公司 | Dihedral-angle-controllable vehicle arm system and control method thereof |
| CN106428525A (en) * | 2016-11-11 | 2017-02-22 | 哈尔滨工业大学 | Flying robot with variable sweep angle launch tandem wings |
| CN106428525B (en) * | 2016-11-11 | 2019-09-13 | 哈尔滨工业大学 | A kind of variable sweep angle ejection tandem arrangement rotor flying robot |
| CN108408031A (en) * | 2018-01-18 | 2018-08-17 | 倪惠芳 | A kind of collapsible undercarriage of unmanned plane high stability |
| CN108408031B (en) * | 2018-01-18 | 2022-05-20 | 浙江南瑞飞翼航空技术有限公司 | High-stability folding undercarriage for unmanned aerial vehicle |
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| Publication number | Publication date |
|---|---|
| CN105460202B (en) | 2018-06-22 |
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