CN109094769A - Mini foldable unmanned plane - Google Patents
Mini foldable unmanned plane Download PDFInfo
- Publication number
- CN109094769A CN109094769A CN201710469673.5A CN201710469673A CN109094769A CN 109094769 A CN109094769 A CN 109094769A CN 201710469673 A CN201710469673 A CN 201710469673A CN 109094769 A CN109094769 A CN 109094769A
- Authority
- CN
- China
- Prior art keywords
- wing
- unmanned plane
- backward
- expansion
- folding
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
- B64C3/56—Folding or collapsing to reduce overall dimensions of aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Toys (AREA)
Abstract
The present invention discloses a kind of mini foldable unmanned plane, including fuselage, preceding wing and rear wing, and the preceding wing can rotate backward folding, rotation expansion forward；The rear wing can turn folding forward, and rotate backward expansion；Rear is provided with primary control surface in the middle part of preceding wing and rear wing；Fixed fin is slightly provided in the rear wing wing.The unmanned plane is forward and backward wing " lift formula " layout, the preceding wing aircraft above the horizon, rear wing is under aircraft horizontal line.Novel unmanned plane provided by the invention, wing-folding can be got up, compact-sized, be occupied little space, and multiple collapsible unmanned planes are transported to target proximity region using delivery vehicle and are launched；Launching, external environment is complicated, under the unfavorable conditions more than disturbing factor, unmanned plane course-stability in length and breadth, ensure that unmanned plane can be safely unfolded under complicated initial fixed condition, pull-up, reach scheduled stable state.
Description
Technical field
The present invention relates to Flight Vehicle Design, in particular to collapsible unmanned plane.
Background technique
When needing multi rack miniature drone to be jointly acted, the voyage of miniature drone is difficult to meet the requirements, therefore,
Using machine tool as carrier, the deficiency for making up miniature drone voyage is effective solution scheme.In order to allow a frame machine tool can be with
Multi rack miniature drone is carried, miniature drone, which needs to fold, to be put into the equipment of machine tool, thus, it is desirable to using unconventional pneumatic
The unmanned plane of distribution form.
Summary of the invention
The task of the present invention is according to mission payload, one kind being provided and meets pneumatic principle, lift resistance ratio is higher, meets mission requirements,
Guarantee that unmanned plane during flying performance, quality are laid out the novel pneumatic of unmanned plane.
The object of the present invention is achieved like this:
Mini foldable unmanned plane, including fuselage, preceding wing and rear wing, the preceding wing can rotate backward folding, forward
Rotation expansion；The rear wing can turn folding forward, and rotate backward expansion；Rear is arranged in the middle part of preceding wing and rear wing
There is primary control surface；Fixed fin is slightly provided in the rear wing wing.
The unmanned plane is forward and backward wing " lift formula " layout, the preceding wing aircraft above the horizon, rear wing is flying
Under machine horizontal line, the flat shape of the preceding wing and rear wing is approximately rectangle, and rear wing is than preceding chord 0.2m ± 0.1m；
When expansion, the upper counterangle of the forward and backward wing is 2 ° ± 0.5 °, and the established angle of the preceding wing is 3 ° ± 0.5 °, described
Rear wing established angle be 1.5 ° ± 0.5 °.
The fuselage uses elliptic cross-section, both ends ellipsoid correction of the flank shape.
The fixed fin root chord length is identical as rear wing slightly chord length, 15 ° ± 2 ° of the fin sweep,
0 ° to 5 ° of the fixed fin camber angle.
The primary control surface maximum degree of bias is -30 ° to+30 °.
The invention has the following beneficial effects:
Novel unmanned plane provided by the invention, wing-folding can be got up, compact-sized, occupied little space, utilized delivery
Multiple collapsible unmanned planes are transported to target proximity region and launched by tool；Launching, external environment is complicated, more than disturbing factor
Under unfavorable conditions, unmanned plane course-stability in length and breadth, ensure that unmanned plane under complicated initial fixed condition can safely into
Row expansion, pull-up, reach scheduled stable state.
Detailed description of the invention
Wing-folding state Fig. 1 of the invention.
Wing unfolded state Fig. 2 of the invention.
In figure: fuselage 1, preceding wing 2, rear wing 3, primary control surface 4, fixed fin 5.
Specific embodiment
The present invention will be further explained below with reference to the attached drawings.
See Fig. 1, Fig. 2, a kind of mini foldable unmanned plane of the invention is using " lift formula " layout, including fuselage 1, preceding wing
2 and rear wing 3, preceding wing 1 can rotate backward folding, rotation expansion forward；Wing 3 can turn folding forward afterwards, rotate backward
Expansion；Preceding wing 2 and 3 middle part rear of rear wing are provided with primary control surface 4；Fixed fin is slightly provided in rear 3 wing of wing
5.Preceding wing 2 aircraft above the horizon, rear wing 3 is under aircraft horizontal line, the planar shaped of 2 wing of preceding machine, rear wing 3
Shape is rectangle, and rear wing 3 is than 2 long 0.2 meters of preceding wing；When expansion, the preceding wing 2, rear wing 3 the upper counterangle be 2 °, institute
The established angle for the preceding wing stated is 3 °, and the established angle of the rear wing is 1.5 °.
Fuselage 1 uses elliptic cross-section, both ends ellipsoid correction of the flank shape.5 string chord lengths of fixed fin and rear 3 wing of wing slightly string
Long identical, 15 ° of 5 angle of sweep of fixed fin, 0 ° of 5 camber angle of fixed fin.Primary control surface 4 is arranged in the middle part of forward and backward wing
Rear, primary control surface 4 can be used as aileron, can also be used as elevator, the 4 maximum degree of bias of primary control surface be -30 ° extremely+
30°。
Claims (5)
1. mini foldable unmanned plane, which is characterized in that including fuselage, preceding wing and rear wing, the preceding wing can be backward
It turns folding, forward rotation expansion；The rear wing can turn folding forward, and rotate backward expansion；In preceding wing and rear machine
Rear is provided with primary control surface in the middle part of the wing；Fixed fin is slightly provided in the rear wing wing.
2. mini foldable unmanned plane according to claim 1, it is characterised in that: the unmanned plane uses forward and backward machine
The wing " lift formula " layout, the preceding wing aircraft above the horizon, rear wing under aircraft horizontal line, the preceding wing and after
The flat shape of wing is approximately rectangle, and rear wing is than preceding chord 0.2m ± 0.1m；When expansion, the forward and backward wing it is upper
Dihedral is 2 ° ± 0.5 °, and the established angle of the preceding wing is 3 ° ± 0.5 °, and the established angle of the rear wing is 1.5 ° ± 0.5 °.
3. mini foldable unmanned plane according to claim 1, it is characterised in that: the fuselage uses elliptic cross-section,
Both ends ellipsoid correction of the flank shape.
4. mini foldable unmanned plane according to claim 1, which is characterized in that the fixed fin root chord length is with after
Wing slightly chord length is identical, and 15 ° ± 2 ° of the fin sweep, 0 ° to 5 ° of the fixed fin camber angle.
5. mini foldable unmanned plane according to claim 1, which is characterized in that the primary control surface maximum degree of bias is-
30 ° to+30 °.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710469673.5A CN109094769A (en) | 2017-06-20 | 2017-06-20 | Mini foldable unmanned plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710469673.5A CN109094769A (en) | 2017-06-20 | 2017-06-20 | Mini foldable unmanned plane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109094769A true CN109094769A (en) | 2018-12-28 |
Family
ID=64795593
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710469673.5A Pending CN109094769A (en) | 2017-06-20 | 2017-06-20 | Mini foldable unmanned plane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109094769A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110539877A (en) * | 2019-08-21 | 2019-12-06 | 成都飞机工业（集团）有限责任公司 | Rotatable flexible wing connection structure |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106507761B (en) * | 2012-12-24 | 2014-11-05 | 成都飞机工业（集团）有限责任公司 | Mini foldable unmanned plane |
| GB2534435A (en) * | 2015-08-13 | 2016-07-27 | Wirth Res Ltd | An unmanned aerial vehicle |
-
2017
- 2017-06-20 CN CN201710469673.5A patent/CN109094769A/en active Pending
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106507761B (en) * | 2012-12-24 | 2014-11-05 | 成都飞机工业（集团）有限责任公司 | Mini foldable unmanned plane |
| GB2534435A (en) * | 2015-08-13 | 2016-07-27 | Wirth Res Ltd | An unmanned aerial vehicle |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110539877A (en) * | 2019-08-21 | 2019-12-06 | 成都飞机工业（集团）有限责任公司 | Rotatable flexible wing connection structure |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20181228 |