CN207697985U - A kind of Novel connected wing unmanned plane - Google Patents
A kind of Novel connected wing unmanned plane Download PDFInfo
- Publication number
- CN207697985U CN207697985U CN201721831727.XU CN201721831727U CN207697985U CN 207697985 U CN207697985 U CN 207697985U CN 201721831727 U CN201721831727 U CN 201721831727U CN 207697985 U CN207697985 U CN 207697985U
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- wing
- buzzard
- unmanned plane
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- vertical tail
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Abstract
The utility model is a kind of Novel connected wing unmanned plane, including fuselage, vertical tail and two pairs of wings are equipped on fuselage, the vertical tail is arranged in fuselage afterbody, two pairs of wings include the buzzard-type wing being arranged above vertical tail and the swept-back wing for being fixed on waist, it is fixedly connected at the top of the wing root and vertical tail of the buzzard-type wing, the wing of the swept-back wing is slightly equipped with the end wing upwardly extended, and the wing of buzzard-type wing slightly connects with the top of the end wing.The utility model improves lift, reduces aircraft overall dimensions, saves space, and greatly enhance the overall construction intensity of aircraft by the connection wing structure of vertical tail and upper and lower two pairs of airfoil quadrangularlies；Bindiny mechanism's buzzard-type wing, which is finely tuned, by setting and the angle between the wing is held to realize finely tunes, compared to common Hard link structure, damage when can effectively reduce aircraft vibrations to connection buzzard-type wing and the connector and aircraft components of holding the wing.
Description
Technical field
The utility model is related to air vehicle technique field, especially a kind of Novel connected wing unmanned plane.
Background technology
The wing of unmanned plane directly determines the gas of aircraft as most important component in load plane system, its aerodynamic characteristic
Dynamic characteristic and main performance.Usually there is the lift that wing generates to account for 70% or more of full machine lift, the resistance of generation accounts for zero liter of full machine
30% or so of resistance.In addition to this, induced drag is substantially also to be generated by wing.Therefore, aerodynamic arrangement's design of aircraft
Key be exactly wing design.
Present unmanned plane mostly uses the layout designs of high aspect ratio, which has the following problems：Airfoil root load
Excessive, wing easily bends and torsional deflection, therefore very high to Structural strength calls；In wing structure Weight control condition
Under, wing increases with ram compression and is increased at flexible wing, the in-flight elastic deformation amount of wing, can lead to serious pneumatic/knot
Structure coupled problem；In addition, excessive aspect ratio often will be less than critical horse to reduce aerofoil profile chord length as cost when aircraft is in
When the speed flight of conspicuous number, the too small resistance that can increase aerofoil profile instead of aerofoil profile chord length reduces lift, and deteriorates stalling characteristics.
Invention content
The technical problems to be solved in the utility model is that in view of the deficiencies of the prior art, a kind of raising lift of proposition reduces
The Novel connected wing unmanned plane of aircraft overall dimensions.
The technical problems to be solved in the utility model is achieved through the following technical solutions, a kind of Novel connected wing nobody
Machine, including fuselage, its main feature is that, vertical tail and two pairs of wings are equipped on fuselage, the vertical tail is arranged in fuselage
Rear portion, described two pairs of wings include the buzzard-type wing being arranged above vertical tail and the swept-back wing for being fixed on waist, institute
It states and is fixedly connected at the top of the wing root and vertical tail of buzzard-type wing, the wing of the swept-back wing is slightly equipped with the end wing upwardly extended, preceding
The wing for plunderring the wing slightly connects with the top of the end wing.
The technical problems to be solved in the utility model can also further realize by the following technical programs, the sweepforward
The wing of the wing slightly by finely tune bindiny mechanism with hold the wing top connect, buzzard-type wing under the action of finely tuning bindiny mechanism with hold the wing it
Between angle realize fine tuning, to reduce aircraft vibrations when caused by wing damage.
The technical problems to be solved in the utility model can also further realize by the following technical programs, the fine tuning
Bindiny mechanism includes the axle sleeve being fixed on the wing of end and the oscillating bearing in axle sleeve, is cased in the oscillating bearing
The leading portion threaded portion of half tooth bolt, half tooth bolt is connect with the nut thread for being fixed on sweepforward tip extension.
The technical problems to be solved in the utility model can also further realize by the following technical programs, on the wing of end
Equipped with mounting hole, the axle sleeve is located at the interlude of mounting hole, and the outer nut intermediate plate for being stuck in axle sleeve both ends is equipped at axle sleeve both ends
With inner nut intermediate plate.
The technical problems to be solved in the utility model can also further realize by the following technical programs, the sweepforward
The sweep angle of the wing is 7 ° -9 °.
The technical problems to be solved in the utility model can also further realize by the following technical programs, the sweepback
The sweep angle of the wing is 28 ° -32 °.
The technical problems to be solved in the utility model can also further realize by the following technical programs, the end wing
Top is higher than buzzard-type wing.
Compared with prior art, the utility model in fuselage afterbody setting vertical tail and upper and lower two pairs of wings by forming
The connection wing structure of quadrangle also reduces aircraft overall dimensions while improving lift, saves space, and greatly enhance aircraft
Overall construction intensity；By finely tuning bindiny mechanism's connecting pin wing and buzzard-type wing, make sweepforward under the Self-aligning characteristic of oscillating bearing
Angle between the wing and the end wing, which is realized, finely tunes, compared to common Hard link structure, to connecting sweepforward when effectively reducing aircraft vibrations
The damage of the connector and aircraft components of the wing and the end wing.
Description of the drawings
Fig. 1 is the stereoscopic schematic diagram of the utility model；
Fig. 2 is the front view of the utility model；
Fig. 3 is the vertical view of the utility model；
Fig. 4 is the schematic diagram that bindiny mechanism is finely tuned in the utility model.
Specific implementation mode
The specific technical solution for further describing the utility model, in order to which those skilled in the art is further understood that
The utility model, without constituting the limitation to its right.
Embodiment 1, referring to Fig.1-4, a kind of Novel connected wing unmanned plane, including fuselage 1, it is equipped with vertical tail 5 on the fuselage 1
With two pairs of wings, the vertical tail 5 setting includes being arranged on vertical tail 5 in 1 rear portion of fuselage, described two pairs of wings
The buzzard-type wing 4 of side and the swept-back wing 2 for being fixed on 1 middle part of fuselage, the top of the wing root and vertical tail 5 of the buzzard-type wing 4 is fixed
Connect, the wing of the swept-back wing 2 is slightly equipped with the end wing 3 upwardly extended, and the end wing 3 is connected as one with 2 solid of swept-back wing, buzzard-type wing
4 wing slightly connects with the top of the end wing 3.
The wing of the buzzard-type wing 4 is slightly connected by finely tuning bindiny mechanism with the top of the wing 3 is held, and buzzard-type wing 4 is connected in fine tuning
Angle under the action of mechanism between the wing 3 of end, which is realized, finely tunes, the damage caused by wing when to reduce aircraft vibrations.
The fine tuning bindiny mechanism includes being fixed on to hold the axle sleeve 7 on the wing 3 and the oscillating bearing 8 in axle sleeve 7,
Half tooth bolt 9, half tooth bolt, 9 front end and the nut spiral shell for being fixed on sweepforward tip extension are cased in the oscillating bearing 8
Line connects.
It is equipped with mounting hole on the wing of end, the axle sleeve is located at the interlude of mounting hole, is equipped at 7 both ends of axle sleeve and is stuck in axle sleeve
The outer nut intermediate plate 6 and inner nut intermediate plate 10 at both ends, outboard nut intermediate plate 6 are fixedly connected with axle sleeve 7, outboard nut intermediate plate 6, interior
The outer end face of side nut clamp sheet 10 is arc-shaped, the aerofoil flush with the end wing, on the outside on nut clamp sheet and inner screw nut intermediate plate
Several bolt holes being correspondingly arranged, outboard nut intermediate plate and inner screw nut intermediate plate are equipped with by sequentially passing through outboard nut folder
The fastening bolt of piece, the end wing and inner screw nut intermediate plate is fixedly connected with the end wing.
There are gaps between the nuts and outboard nut intermediate plate of half tooth bolt, and buzzard-type wing is in oscillating bearing when aircraft shakes
Self-regulated under realize upper and lower by a small margin fine tuning, play cushioning effect, reduce the damage of double of tooth bolt and body parts.
It is every to be connected at least through two groups of fine tuning bindiny mechanisms between the side wing and buzzard-type wing.
The sweep angle of the buzzard-type wing is 7 ° -9 °, is preferably designed for 8.3 °.
The sweep angle of the swept-back wing is 28 ° -32 °, is preferably designed for 30 °.
It is higher than buzzard-type wing at the top of the end wing.
Claims (7)
1. a kind of Novel connected wing unmanned plane, including fuselage, it is characterised in that：Vertical tail and two pairs of wings are equipped on fuselage,
The vertical tail is arranged in fuselage afterbody, and described two pairs of wings include the buzzard-type wing being arranged above vertical tail and consolidate
It is scheduled on the swept-back wing of waist, is fixedly connected at the top of the wing root and vertical tail of the buzzard-type wing, the wing of the swept-back wing
It is slightly equipped with the end wing upwardly extended, the wing of buzzard-type wing slightly connects with the top of the end wing.
2. a kind of Novel connected wing unmanned plane according to claim 1, it is characterised in that：The wing of the buzzard-type wing is slightly by micro-
Bindiny mechanism is adjusted to connect with the top of the wing is held, angle of buzzard-type wing under the action of finely tuning bindiny mechanism between the wing of end is realized micro-
It adjusts, the damage caused by wing when to reduce aircraft vibrations.
3. a kind of Novel connected wing unmanned plane according to claim 2, it is characterised in that：The fine tuning bindiny mechanism includes solid
The axle sleeve and the oscillating bearing in axle sleeve being scheduled on the wing of end, are cased with half tooth bolt in the oscillating bearing, described
The leading portion threaded portion of half tooth bolt is connect with the nut thread for being fixed on sweepforward tip extension.
4. a kind of Novel connected wing unmanned plane according to claim 3, it is characterised in that：It is equipped with mounting hole, institute on the wing of end
The interlude that axle sleeve is located at mounting hole is stated, the outer nut intermediate plate and inner nut intermediate plate for being stuck in axle sleeve both ends are equipped at axle sleeve both ends.
5. a kind of Novel connected wing unmanned plane according to claim 1, it is characterised in that：The sweep angle of the buzzard-type wing be 7 °-
9°。
6. a kind of Novel connected wing unmanned plane according to claim 1, it is characterised in that：The sweep angle of the swept-back wing be 28 °-
32°。
7. a kind of Novel connected wing unmanned plane according to claim 1, it is characterised in that：It is higher than sweepforward at the top of the end wing
The wing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721831727.XU CN207697985U (en) | 2017-12-25 | 2017-12-25 | A kind of Novel connected wing unmanned plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721831727.XU CN207697985U (en) | 2017-12-25 | 2017-12-25 | A kind of Novel connected wing unmanned plane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207697985U true CN207697985U (en) | 2018-08-07 |
Family
ID=63028511
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201721831727.XU Active CN207697985U (en) | 2017-12-25 | 2017-12-25 | A kind of Novel connected wing unmanned plane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN207697985U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111572773A (en) * | 2020-05-22 | 2020-08-25 | 中国民用航空飞行学院 | Medium-sized tactical transporter |
| WO2021043336A3 (en) * | 2019-09-05 | 2021-04-22 | 深圳市道通智能航空技术股份有限公司 | Wing detachment assembly and aircraft |
-
2017
- 2017-12-25 CN CN201721831727.XU patent/CN207697985U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2021043336A3 (en) * | 2019-09-05 | 2021-04-22 | 深圳市道通智能航空技术股份有限公司 | Wing detachment assembly and aircraft |
| US12030613B2 (en) | 2019-09-05 | 2024-07-09 | Autel Robotics Co., Ltd. | Wing detachment assembly and aerial vehicle |
| CN111572773A (en) * | 2020-05-22 | 2020-08-25 | 中国民用航空飞行学院 | Medium-sized tactical transporter |
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