CN105460202B - A kind of variable geometry unmanned plane - Google Patents
A kind of variable geometry unmanned plane Download PDFInfo
- Publication number
- CN105460202B CN105460202B CN201510850954.6A CN201510850954A CN105460202B CN 105460202 B CN105460202 B CN 105460202B CN 201510850954 A CN201510850954 A CN 201510850954A CN 105460202 B CN105460202 B CN 105460202B
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- host wing
- fuselage
- wing
- inner segment
- unmanned plane
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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
-
- 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
-
- 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 present invention relates to a kind of variable geometry unmanned planes, include the upper host wing at the adjustable upper counterangle, and the lower host wing of inverted diherdral, streamlined fuselage, retractable landing gear, preposition canard and the propeller for being set to body rear end is adjusted.Aerodynamic configuration provided by the present invention is characterized by the upper host wing at the adjustable upper counterangle and the lower host wing of adjustable inverted diherdral, the inverted diherdral of the upper counterangle of upper host wing and lower host wing can be adjusted according to the difference of flight attitude, to adapt to the pneumatic requirement of the unmanned plane shape of different flight attitudes.Aerodynamic configuration provided by the invention has the advantages that simple in structure, aerodynamic arrangement is succinct smooth, flying quality is good.
Description
Technical field
The invention belongs to technical field of aerospace, and in particular to a kind of variable geometry unmanned plane.
Background technology
In airplane design, there are one be not easily overcome and contradiction：Want improve flying speed, it is necessary to select big angle of sweep,
The wing of low aspect ratio, to reduce the drag due to shock wave of aircraft, but such wing lift in lower-speed state is smaller, induced drag compared with
Greatly, it is inefficient, takeoff and landing poor-performing.Existing solution is designed using variable swept back wing at present, general change sweepback
The interior wing panel of the wing is fixed, and outer wing rotates, to change with inner wing hinge axis connection before and after manipulating outer wing by hydraulic booster
Become the rear wiping angle of outer panel and the aspect ratio of entire wing.
Meanwhile biplane has a good takeoff and landing performance, the taking off of short distance/landing ability and good motor-driven
Performance, the aircrafts of Earlier designs it is more employ twin designs.But since construction weight is too big, the shortcomings of resistance is big, at present
In addition to a small amount of acrobatic aircraft and agrisilviculture aircraft, without using this design.
Invention content
The purpose of the present invention is to provide a kind of variable geometry unmanned plane, which makes unmanned plane in each flight shape
Good flying quality, mobility are respectively provided under state and with excellent short takeoff/landing ability.
To achieve the above object, the technical solution used in the present invention is：
A kind of variable geometry unmanned plane, including fuselage, afterbody propeller, be arranged on front fuselage both sides before
It puts canard and is arranged in pairs in the upper host wing of waist and lower host wing；The upper host wing and lower host wing are located at machine
The same position of body radial direction is evenly arranged；The upper host wing includes upper host wing inner segment and the outer section of upper host wing, the upper master
One end of wing inner segment is hinged with the outer section of upper host wing, and the other end of the upper host wing inner segment is fixedly connected with fuselage, described
Controllable rudder face is provided on rear side of upper host wing inner segment；Two upper host wing inner segments and two lower host wings are along machine
Body is radially distributed in " X "；Lower controllable rudder face is provided on rear side of the lower host wing.
Furtherly, the lower host wing includes lower host wing inner segment and the outer section of lower host wing, the lower host wing inner segment
The outer section of one end and lower host wing be hinged, the lower host wing inner segment other end is fixedly connected with fuselage, the lower controllable rudder face
It is arranged on lower host wing inner segment；Two upper host wing inner segments and two lower host wing inner segments are in radially along fuselage
" X " is distributed.
Furtherly, the outer section of the lower host wing and the outer section of upper host wing are driven respectively by hydraulic booster.
Furtherly, the underside of forward of the fuselage is provided with nose-gear, and master is provided on the downside of the rear portion of the fuselage
Undercarriage.
Compared with prior art, what the present invention obtained has the beneficial effect that：
The there is provided aerodynamic configuration of invention is characterized by the upper host wing at the adjustable upper counterangle and adjustable inverted diherdral
Main lower wing, the inverted diherdral of the upper counterangle of Your Majesty's wing and main lower wing can be adjusted according to the difference of flight attitude, with
Adapt to the pneumatic requirement of the unmanned plane shape of different flight attitudes.Aerodynamic configuration provided by the invention, have it is simple in structure, pneumatically
The advantages that layout is succinct smooth, flying quality is good；Therefore short takeoff/landing ability greatly increases.
By the variation to section deflection angle outside section outside host wing on unmanned plane and lower host wing, to adapt to each flight
To the requirement of unmanned plane aerodynamic configuration under state.
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 in class " work " word
Change between configuration and class " X " word configuration.Class " work " word configuration is to be similar to double-vane wing, has high-lift, and high maneuverability is good
The aerodynamic characteristicses such as good low-altitude low-speed performance.Class " X " word configuration air drag is small, and flight stability is good, is suitable as level
Boning out high speed cruise flight.When host wing configuration changes between class " work " word configuration and class " X " word configuration, it is suitable for it
The requirement of his state of flight.
Description of the drawings
Fig. 1 is lower-speed state front isometric structure diagram of the present invention；
Fig. 2 is lower-speed state back side isometric structure diagram of the present invention；
Fig. 3 is high-speed flight state isometric structure diagram of the present invention；
Fig. 4 is lower-speed state side structure schematic view of the present invention；
Fig. 5 is lower-speed state positive structure diagram of the present invention；
Fig. 6 is lower-speed state overlooking the structure diagram of the present invention；
Fig. 7 is the outer section angle structure diagram of host wing of the present invention.
In the accompanying drawings：The outer section of host wing on 1, host wing inner segment on 2, controllable rudder face, 4 time host wings section, 5 outside on 3
Controllable rudder face, 7 nose-gears, 8 main landing gears, 9 preposition canards, 10 fuselages, 11 propellers under lower host wing inner segment, 6.
Specific embodiment
The present invention is described in more detail below in conjunction with attached drawing 1-7.
As shown in figures 1-6, a kind of variable geometry unmanned plane, including fuselage 10,10 tail portion of fuselage propeller 11, set
It puts in the preposition canard 9 of 10 front end both sides of fuselage and the upper host wing being arranged in pairs in the middle part of fuselage 10 and lower host wing；Institute
It states host wing and lower host wing is located at the same position of 10 radial direction of fuselage and is uniformly distributed；The upper host wing includes upper host wing
Inner segment 2 and the outer section 1 of upper host wing, one end and the outer section 1 of upper host wing of the upper host wing inner segment 2 are hinged, the upper host wing
The other end of inner segment 2 is fixedly connected with fuselage 10, and the rear side of the upper host wing inner segment 2 is provided with controllable rudder face 3；Two institutes
Host wing inner segment 2 and two lower host wings are stated to be distributed in " X " along 10 radial direction of fuselage；It is provided on rear side of the lower host wing
Controllable rudder face 6 down.The lower host wing includes lower host wing inner segment 5 and the outer section 4 of lower host wing, the lower host wing inner segment 5
One end is hinged with the outer section 4 of lower host wing, and lower 5 other end of host wing inner segment is fixedly connected with fuselage 10, the lower controllable rudder
Face 6 is arranged on lower host wing inner segment 5；Two upper host wing inner segments 2 and two lower host wing inner segments 5 are along fuselage 10
Radially it is distributed in " X ".The outer section 4 of the lower host wing and the outer section 1 of upper host wing are swung respectively by hydraulic booster.It is described
The underside of forward of fuselage 10 is provided with nose-gear 7, and main landing gear 8 is provided on the downside of the rear portion of the fuselage 10.
Variable geometry unmanned plane includes that the outer section 1 of upper host wing of angle can be upward deflected and can deflect down the lower master of angle
The outer section 4 of wing, upper host wing inner segment 2 and lower host wing inner segment 5 are immovable wing section, and rear is provided with controllable rudder face 3
And flight attitude of the lower controllable rudder face 6 when being used to control aircraft flight.The fuselage 10 has cleanliness shape, and forepart is provided with
For balancing the preposition canard 9 of aerodynamic moment, rear portion sets the propeller 11 for being provided with flying power.Underbelly setting is useful
In the nose-gear 7 of unmanned plane takeoff and landing and main landing gear 8.
It is inorganic in take off or land state when, the outer section 1 of upper host wing and lower host wing 4 zero deflection of section outside（It is such as attached
Shown in Fig. 5）.At this point, the outer section 1 of upper host wing is substantially parallel with the outer section 4 of lower host wing, the dual wing configuration of class " work " word is formed, it can
Maximum lift and stability are provided, the ability that can make unmanned plane that there is short field take-off or landing.
It is inorganic be in high speed cruise conditions when, the outer section 1 of upper host wing upward deflects, until its leading edge to it is fixed
Upper 2 leading edge of host wing inner segment be located along the same line, the outer section 4 of lower host wing deflects down, until its leading edge is arrived with fixation not
Dynamic lower 6 leading edge of host wing inner segment is located along the same line（As shown in Figure 5）.This state of flight, unmanned plane nose-gear 7 and
Main landing gear 8 is taken in inside fuselage 10.At this point, unmanned plane has minimum flight resistance, the outer section 1 of upper host wing and lower host wing
Outer section of 4 fully open, the large-scale X-shaped wing configurations of formation one provide the lift and flight stability of high-speed flight.
Be in task phase in unmanned plane, at this point, unmanned plane wing configuration with take off/landing state is identical, form class
The dual wing configuration of " work " word, nose-gear 7 and main landing gear 8 are taken in inside fuselage 10.Fly with maximum lift and double-vane
Turning radius caused by the larger wing area of machine is small, the small good mobility of grade of stalling speed.
Other state of flights are in unmanned plane, as shown in Figure 7, the outer section 1 of upper host wing can deflect upward into a certain
It is suitble to the position of the state of flight.Meanwhile the outer section 4 of lower host wing is deflected down with a certain suitable position, to adapt to the flight
The required aeroperformance of state.
It wants under arbitrary state of flight, unmanned plane is by the deflection of upper controllable rudder face 3 and lower controllable rudder face 6, so as to change
Aerodynamic moment, to realize the change of unmanned plane during flying posture.
Preposition canard 9 has under arbitrary state of flight, aerodynamic force caused by host wing and lower host wing in trim
Square（Upper host wing is made of section 1 outside upper host wing and upper host wing inner segment 2, and lower host wing is by section 4 outside lower host wing and lower host
Wing inner segment 5 forms）, make unmanned plane that there is longitudinal stability.Fixed upper host wing inner segment 2 and lower host wing inner segment 5 can
Aerodynamic force is provided in arbitrary state of flight so that unmanned plane has lateral stability.
The present invention is realized based on following principle：
By the variation to section deflection angle outside section outside host wing on unmanned plane and lower host wing, to adapt to each flight
To the requirement of unmanned plane aerodynamic configuration under state.
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 in class " work " word
Change between configuration and class " X " word configuration.Class " work " word configuration is to be similar to double-vane wing, has high-lift, and high maneuverability is good
The aerodynamic characteristicses such as good low-altitude low-speed performance.Class " X " word configuration air drag is small, and flight stability is good, is suitable as level
Boning out high speed cruise flight.When host wing configuration changes between class " work " word configuration and class " X " word configuration, it is suitable for it
The requirement of his state of flight.
Compared with general configuration aircraft, aerodynamic configuration proposed by the invention is right under each state of flight in addition to adapting to
Outside the requirement of unmanned plane aerodynamic configuration, since section has deflectable property, host wing therefore foldable and class " work " outside host wing
Word configuration with other be suitble to fly at low speed wing configuration compared with, have low aspect ratio characteristic, it is made to be conducive in stenosis ring
It is used in border.The short distance of class " work " word configuration plays/drop performance, is also beneficial to unmanned plane in the items such as narrow environment or runway deficiency
It is used in part.
So-called " work " word configuration is exactly that two upper outer sections 1 of host wing and the outer section 4 of two lower host wings are in horizontality,
From host wing in terms of unmanned machine face as " work " word, therefore the state is referred to as " work " word configuration.
So-called " X " word configuration is exactly that two upper outer sections 1 of host wing extend outwardly along upper host wing inner segment 2, with upper host
The aerofoil extension of wing inner segment 2 overlaps, and the outer section 4 of two lower host wings extends outwardly along lower host wing inner segment 5, in lower host wing
The aerofoil extension of section 5 overlaps, since two upper host wing inner segments 2 and two lower host wing inner segments 5 are along 10 diameter of fuselage
It is distributed in " X ", therefore from host wing in terms of unmanned machine face as " X " word, therefore the 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 the flight control system control by unmanned plane, pass through hydraulic system reality
The change of existing posture, controllable rudder face that wherein the technical program is mentioned, propeller, undercarriage can be common structures by flying
Control system coordination control.
Embodiment described above is merely a preferred embodiment of the present invention, and the simultaneously exhaustion of the feasible implementation of non-present invention.It is right
For persons skilled in the art, under the premise of without departing substantially from the principle of the invention and spirit to any aobvious made by it and
The change being clear to should be all contemplated as falling within the claims of the present invention.
Claims (4)
1. a kind of variable geometry unmanned plane, including fuselage（10）, fuselage（10）The propeller of tail portion（11）, be arranged on fuselage
（10）The preposition canard of front end both sides（9）And it is arranged in pairs in fuselage（10）The upper host wing at middle part and lower host wing；It is described
Upper host wing and lower host wing are located at fuselage（10）The same position of radial direction is evenly arranged；It is characterized in that：The upper host wing
Including upper host wing inner segment（2）With section outside upper host wing（1）, the upper host wing inner segment（2）The outer section of one end and upper host wing
（1）It is hinged, the upper host wing inner segment（2）The other end and fuselage（10）It is fixedly connected, the upper host wing inner segment（2）After
Side is provided with controllable rudder face（3）；Two upper host wing inner segments（2）With two lower host wings along fuselage（10）Radially
It is distributed in " X "；Lower controllable rudder face is provided on rear side of the lower host wing（6）.
2. a kind of variable geometry unmanned plane according to claim 1, it is characterised in that：The lower host wing includes lower host
Wing inner segment（5）With section outside lower host wing（4）, the lower host wing inner segment（5）The outer section of one end and lower host wing（4）It is hinged, institute
State lower host wing inner segment（5）The other end and fuselage（10）It is fixedly connected, the lower controllable rudder face（6）It is arranged on lower host wing inner segment
（5）On；Two upper host wing inner segments（2）With two lower host wing inner segments（5）Along fuselage（10）Radially in " X " point
Cloth.
3. a kind of variable geometry unmanned plane according to claim 2, it is characterised in that：The outer section of the lower host wing（4）With
The outer section of upper host wing（1）It is driven respectively by hydraulic booster.
4. according to a kind of variable geometry unmanned plane of claim 1-3 any one of them, it is characterised in that：The fuselage（10）'s
Underside of forward is provided with nose-gear（7）, the fuselage（10）Rear portion on the downside of be provided with main landing gear（8）.
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 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105460202A CN105460202A (en) | 2016-04-06 |
| CN105460202B true CN105460202B (en) | 2018-06-22 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510850954.6A Active CN105460202B (en) | 2015-11-30 | 2015-11-30 | A kind of variable geometry unmanned plane |
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Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106081106B (en) * | 2016-06-17 | 2021-02-05 | 深圳市元征科技股份有限公司 | Wireless unmanned aerial vehicle that charges |
| 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 |
| 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 |
| 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 |
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 |
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| Publication number | Publication date |
|---|---|
| CN105460202A (en) | 2016-04-06 |
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