CN207902734U - A kind of unmanned plane of aerodynamic arrangement - Google Patents
A kind of unmanned plane of aerodynamic arrangement Download PDFInfo
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- CN207902734U CN207902734U CN201721782581.4U CN201721782581U CN207902734U CN 207902734 U CN207902734 U CN 207902734U CN 201721782581 U CN201721782581 U CN 201721782581U CN 207902734 U CN207902734 U CN 207902734U
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- wing
- unmanned plane
- fuselage
- aspect ratio
- aerodynamic arrangement
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Abstract
The utility model provides a kind of unmanned plane of aerodynamic arrangement.The unmanned plane includes the fuselage of elliptic cross-section and the wing for being fixed on the fuselage roof, and the aspect ratio of the wing is 12~25, and the air-foil is E 193.A kind of unmanned plane of aerodynamic arrangement provided by the utility model, by the unmanned plane wing for designing high aspect ratio, and winglet has been smoothly connected it in the point of wing, the useful lift coefficient that wing is improved while induced drag can be effectively reduced, to improve the whole flight efficiency of unmanned plane.
Description
Technical field
The utility model is related to unmanned plane fields, more particularly, to a kind of unmanned plane of aerodynamic arrangement.
Background technology
Altitude Long Endurance Unmanned Air Vehicle can complete long-range scouting, targeted surveillance, communication relay, electronic interferences, high Nuisance alarms
Equal military missions are the bases for building high-altitude strategy and tactics platform, have important strategy and tactics meaning.But high altitude long time
Unmanned plane is more demanding to flying quality, pneumatic quality etc., especially requires under the premise of enough lift, has larger
Lift resistance ratio.
For subsonic speed low reynolds number normal arrangement unmanned plane, in order to realize long endurance continuation of the journey, to improve as possible
Lift coefficient reduces resistance coefficient, that is, improves lift resistance ratio.It is the most effective mode for improving lift resistance ratio to increase aspect ratio.At present
The wing aspect ratio of the UAV aerodynamic layout for the high-altitude long-endurance being applied to is less than 10 mostly, and resistance coefficient is larger.
Utility model content
The utility model provides a kind of aerodynamic arrangement for overcoming the above problem or solving the above problems at least partly
Unmanned plane.
The utility model provides a kind of unmanned plane of aerodynamic arrangement.A kind of unmanned plane of aerodynamic arrangement, including ellipse are cut
The aspect ratio of the fuselage in face and the wing for being fixed on the fuselage roof, the wing is 12~25.
Preferably, the point of the wing has been smoothly connected winglet.
Preferably, the tail portion rear of the fuselage is equipped with the inverted " V " type structure that is made of two empennages, the empennage from
It is fixed on the wing by horizontal support bar respectively by holding, the angle of the inverted " V " type structure is 100~120 °, described
Empennage aerofoil profile is NACA0009.
Preferably, the upper counterangle of the wing is 0~25 °.
Preferably, the established angle of the wing is 0~5 °.
Preferably, the wing includes stage casing wing and the outside wing for being connected to stage casing wing both sides, described
Stage casing wing is fixed on the fuselage roof.
Preferably, on the outside wing aileron is equipped with close to the side of the afterbody.
A kind of unmanned plane of aerodynamic arrangement provided by the utility model, by designing the unmanned plane wing of high aspect ratio, and
And it has been smoothly connected that wing tip is small slightly in the point of wing, improve the effective of wing while induced drag can be effectively reduced
Lift coefficient to improve the whole flight efficiency of unmanned plane, while using inverted " V " type tail, ensures unmanned plane during flying direction
Stability.
Description of the drawings
Fig. 1 is the structural schematic diagram according to a kind of unmanned plane of aerodynamic arrangement of the utility model；
Fig. 2 is the side view according to a kind of unmanned plane of aerodynamic arrangement of the utility model；
Reference numeral：
1- wings；2- fuselages；The stage casings 3- wing；
Wing on the outside of 4-；5- wing tips are small slightly；6- ailerons；
7- supporting rods；8- empennages.
Specific implementation mode
With reference to the accompanying drawings and examples, specific embodiment of the present utility model is described in further detail.Below
Embodiment is not intended to limit the scope of the present invention for illustrating the utility model.
Fig. 1 is according to a kind of unmanned plane structural schematic diagram of aerodynamic arrangement of the utility model, as shown in Figure 1, the nothing
Man-machine fuselage 2 including elliptic cross-section and the wing 1 for being fixed on the fuselage roof, the aspect ratio of the wing is 12~
25。
Specifically, since high aspect ratio effectively controls induced drag, under high coefficient of lift combined, cruising power is reduced, because
Between the aspect ratio of the wing 1 selected in this present embodiment is 12~25, aspect ratio is the ratio between wing span and chord length, wherein opening up
String than size have apparent influence to the flying quality of fuselage 2.When aspect ratio increases, the induced drag of wing can reduce.Mesh
Common string exhibition ratio is as follows on preceding aircraft：Big voyage, low mobility aircraft B-52 bomber aspect ratios are 6.5, U-2 reconnaissance planes
Aspect ratio 10.6, small voyage, highly maneuverable aircraft J-8 aspect ratios 2, Su-27 aspect ratios 3.5, F-117 aspect ratios 1.65.High-altitude
Long endurance unmanned aircraft flying height is high, speed is low, and flight Reynolds (Re) number is small.In low cruise flight, the Re numbers of unmanned plane
500,000 or so, 200,000 or so are reduced to Re numbers when 20km altitudes, even 10 are dropped to Re numbers when 30km altitudes
Ten thousand hereinafter, far smaller than large-scale unmanned plane reaches tens million of flight Re numbers.In small Re numbers, flow boundary layer air disturbance is small,
Aerofoil surface is based on laminar flow.Although Altitude Long Endurance Unmanned Air Vehicle aerofoil has a condition to form stably stratified flow, under low Re
Laminar flow is a kind of unstable fluidised form, is easier to generate the separation of air-flow aerofoil, pneumatic efficiency is caused to reduce.Therefore the wing of unmanned plane
Type thickness is big, and to meet light-weighted Structural Design Requirement, uses small blunt configuration in the leading edge of a wing, can exist to avoid air-flow
Leading edge detaches, and has large range of favorable pressure gradient in top airfoil front, can keep longer laminar flow zone；Lower aerofoil rear camber compared with
Greatly, to improve design lift coefficient.Therefore, wing design need optimize wing open up to lift distribution, so as to be maintained on aerofoil
More laminar flow zones, and avoid the issuable flow separation of rear.Aerofoil profile E193 is selected according to the requirement of above-mentioned wing, most
Big thickness is located at 12% at 30.9 chord lengths.
The unmanned plane for the aerodynamic arrangement that above-described embodiment provides, by designing the unmanned plane wing of high aspect ratio, Neng Gouyou
The reduction induced drag of effect, to improve the flight performance of unmanned plane.
Content based on above-described embodiment, as shown in Figure 1, the wing tip of the wing 1 has been smoothly connected winglet 5.
Specifically, unmanned plane, which maintains lift required when normal flight, is generated by the pressure difference of 1 upper and lower surface of wing,
Due to the presence of upper and lower surface pressure difference, nearby wing lower surface air can form wing tip to 1 wing tip of wing around upper surface is flowed to
Whirlpool causes the pressure difference of wing tip near zone wing upper and lower surface to reduce, and is reduced so as to cause the lift that this region generates.In order to
Weaken this influence around flow phenomenon to lift, winglet 5 is smoothly installed in the wing tip of unmanned plane, to hinder upper following table
The air in face streams, and reduces the lift induced drag caused by wingtip vortex, reduces the destruction streamed to lift, improves lift resistance ratio,
Achieve the purpose that increase lift.
The unmanned plane for the aerodynamic arrangement that above-described embodiment provides, by the unmanned plane wing of design high aspect ratio, and
The point of wing has been smoothly connected winglet, and the useful lift of wing is improved while capable of effectively reducing induced drag
Coefficient, to improve the whole flight efficiency of unmanned plane.
Content based on the various embodiments described above, Fig. 2 are the side according to a kind of unmanned plane of aerodynamic arrangement of the utility model
View, in conjunction with shown in Fig. 1 and Fig. 2, the tail portion rear of fuselage 1 is equipped with the inverted " V " type structure being made of two empennages 8, empennage 8
Free end is fixed on by horizontal support bar 7 on the wing respectively, and the angle of inverted " V " type structure empennage is 100~120 °, institute
It is NACA0009 to state 8 aerofoil profile of empennage.
Specifically, it in order to increase the directional stability and pitch control ability of unmanned plane, is set at the tail portion rear of fuselage 1
By the inverted " V " type being made of two empennages 8, one end of two 8 points of empennages is fixed together and forms inverted " V " type angle, inverted " V "
Type tail is designed to ensure pitching and the directional stability of unmanned plane, and the rudder face on empennage 8 is controlling unmanned plane
Pitching and yaw.The angle of inverted " V " type structure empennage can influence the directionality of unmanned plane, generally 100~120 °.The empennage wing
Type be NACA0009 symmetrical airfoil, resistance of the symmetrical airfoil in all aerofoil profiles is minimum, but simultaneously, under low incidence he
Lift coefficient it is also very low.Under High Angle of Attack, the lift coefficient and resistance coefficient of symmetrical airfoil steeply rise, while symmetrical
Aerofoil profile also possesses maximum stalling angle, and the lift coefficient of aerofoil profile still maintains in higher level after stall, therefore right
Claim aerofoil profile that can obtain preferable stall performance and lift-rising effect.NACA0009 symmetrical airfoils are chiefly used in the horizontal tail of unmanned plane
Aerofoil profile, to obtain best effect of the manipulation.
The unmanned plane for the aerodynamic arrangement that above-described embodiment provides crosses the unmanned plane wing for designing high aspect ratio, and in machine
The point of the wing has been smoothly connected that wing tip is small slightly, and the useful lift system of wing is improved while capable of effectively reducing induced drag
Number to improve the whole flight efficiency of unmanned plane, while using the symmetrical empennage of inverted " V " type, ensures unmanned plane during flying direction
Stability increases handling.
The upper counterangle of content based on the various embodiments described above, the wing is 0~25 °.The upper counterangle refers to wing reference plane
When wing has torsion refer to then the angle of torsional axis and horizontal plane with the angle of horizontal plane.All aircraft less than velocity of sound its
Wing installation is typically all to tilt upward outward from root, this angle upwarped just calls dihedral.The effect at the upper counterangle is flight
When if there is sideslip phenomenon, meeting will be than front face area from the wing of the other side to the side wing in sideslip direction and the angle of attack
Much larger, this will make aircraft generate the strength reversely breakked away, that is, achieve the purpose that correct rapidly and break away.So aircraft is upper anti-
Angle is designed to make aircraft have the automatic function of correcting flight attitude exception.The excessive upper counterangle can inhibit winged instead
The ability that machine maintenance is just being breakked away generally selects 0~25 °.
The established angle of content based on the various embodiments described above, the wing is 0~5 °.The established angle of wing is the string of wing
The angle of line and fuselage central axis, established angle is one of the parameter for influencing high-lift systems, to lift coefficient, zero lift
Angle, stalling angle and cruise drag are influenced, and the unmanned plane true angle of incidence is generally less than 5 °.
Content based on the various embodiments described above, as shown in Figure 1, wing 1 is including stage casing wing 3 and is connected to stage casing machine
The outside wing 4 of 3 both sides of the wing, stage casing wing 3 are fixed on 2 top of fuselage.Side on outside wing 4 close to 2 tail portion of fuselage is set
There is aileron 6.
Specifically, high aspect ratio wing 1 includes three sections：Stage casing wing 3 and the outside machine for being connected to 3 both sides of stage casing wing
The wing 4.In embodiment, by taking aspect ratio is the wing that aspect ratio is 15.6 as an example, span overall length be 4.38m, chord length 0.28m,
The length of stage casing wing 3 is 1.58m, and wing 2 length in outside is 1.4m.Meanwhile the aileron 6 being arranged on outside wing 4 passes through
The differential deflection of left and right aileron 6 generates rolling moment, to control aircraft rolling.
A kind of unmanned plane of aerodynamic arrangement provided by the utility model, by designing the unmanned plane wing of high aspect ratio, and
And it has been smoothly connected that wing tip is small slightly in the point of wing, improve the effective of wing while induced drag can be effectively reduced
Lift coefficient to improve the whole flight efficiency of unmanned plane, while using inverted " V " type tail, ensures unmanned plane during flying direction
Stability.
Finally, the device in the utility model is only preferable embodiment, is not intended to limit the guarantor of the utility model
Protect range.Within the spirit and principle of the utility model, any modification, equivalent replacement, improvement and so on should all include
It is within the protection scope of the utility model.
Claims (6)
1. a kind of unmanned plane of aerodynamic arrangement, which is characterized in that fuselage including elliptic cross-section and be fixed on the fuselage
The aspect ratio of the wing at top, the wing is 12~25；
The point of the wing has been smoothly connected winglet.
2. unmanned plane according to claim 1, which is characterized in that the tail portion rear of the fuselage is equipped with by two empennage groups
At inverted " V " type structure, the free end of the empennage is fixed on by horizontal support bar on the wing respectively, the inverted " V "
The angle of type structure is 100~120 °, and the empennage aerofoil profile is NACA0009.
3. unmanned plane according to claim 2, which is characterized in that the upper counterangle of the wing is 0~25 °.
4. unmanned plane according to claim 2, which is characterized in that the established angle of the wing is 0~5 °.
5. unmanned plane according to claim 1, which is characterized in that the wing includes stage casing wing and is connected to described
The outside wing of stage casing wing both sides, the stage casing wing are fixed on the fuselage roof.
6. unmanned plane according to claim 5, which is characterized in that close to the one of the afterbody on the outside wing
Side is equipped with aileron.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721782581.4U CN207902734U (en) | 2017-12-19 | 2017-12-19 | A kind of unmanned plane of aerodynamic arrangement |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721782581.4U CN207902734U (en) | 2017-12-19 | 2017-12-19 | A kind of unmanned plane of aerodynamic arrangement |
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| Publication Number | Publication Date |
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| CN207902734U true CN207902734U (en) | 2018-09-25 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116186904A (en) * | 2023-04-14 | 2023-05-30 | 北京舯迦科技有限公司 | Mechanical overall aerodynamic layout method with lifting surface moving in fluid |
-
2017
- 2017-12-19 CN CN201721782581.4U patent/CN207902734U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116186904A (en) * | 2023-04-14 | 2023-05-30 | 北京舯迦科技有限公司 | Mechanical overall aerodynamic layout method with lifting surface moving in fluid |
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