CN205738137U - A kind of fixed-wing UAV Landing deceleration damping unit - Google Patents
A kind of fixed-wing UAV Landing deceleration damping unit Download PDFInfo
- Publication number
- CN205738137U CN205738137U CN201620389707.0U CN201620389707U CN205738137U CN 205738137 U CN205738137 U CN 205738137U CN 201620389707 U CN201620389707 U CN 201620389707U CN 205738137 U CN205738137 U CN 205738137U
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- unmanned plane
- wind spring
- fixed
- landing
- wing
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Abstract
Fixed-wing unmanned plane landing link is long due to ground run distance, the high many-sided reason of requirement to landing field, it is difficult in the area specified, unmanned plane is carried out short distance safe falling, this utility model passes through unmanned plane afterbody towing hook, the damping rope tangled when unmanned plane lands the damping action utilizing wind spring, the inertia force of rapid decay unmanned plane.This utility model fixed-wing UAV Landing deceleration damping unit is characterized in that: arrester wires (2) is mounted in two coilers on the free end of wind spring (8) respectively, the fixing end of wind spring (7) is installed in the same direction by arrester wires (2) installing port of bolt (5) tightening guard shield (6) on fixing seat (8), two coilers.When aircraft landing sliding race towing hook (1) hangs up arrester wires (2), wind spring plays damping action, it is achieved the short distance landing of fixed-wing unmanned plane.
Description
Technical field
This utility model relates to civilian unmanned plane equipment technical field, particularly relates to a kind of fixed-wing UAV Landing deceleration damping unit.
Background technology
In recent years, civilian unmanned air vehicle technique field has obtained development at full speed, the aspects such as particularly fixed-wing unmanned plane voyage is remote, airborne hours length, speed are fast are more with the obvious advantage compared with many rotor wing unmanned aerial vehicles, but fixed-wing unmanned plane is rising, is dropping link to runway environment requirement strictly, simultaneously the highest to the operation level requirement flying hands.Owing to fixed-wing unmanned plane is higher to open property, the length requirement of runway, most of urban districts all cannot meet the Normal Take-Off And Landing of fixed-wing unmanned plane, particularly landing link, due to many-sided reasons such as air-flows, is difficult at the runway specified, unmanned plane is carried out short distance safe falling.
In view of the above problems, the fixed-wing UAV Landing deceleration damping unit that the present utility model is created, putting down tail deceleration towing hook by unmanned plane when being landed, the damping rope that towing hook tangles carries out damping and slows down unmanned plane, it is achieved unmanned plane is short distance landing on runway.
Utility model content
As it was previously stated, in order to fixed-wing unmanned plane is realized short distance stable landing, the purpose of this utility model is to provide a kind of fixed-wing UAV Landing deceleration damping unit, is quickly decayed by inertia force during aircraft landing by wind spring and arrester wires.
This utility model fixed-wing UAV Landing deceleration damping unit is characterized in that: arrester wires (2) is articulated on the free end of the wind spring (7) in left coiler (3), right coiler (4) respectively, left coiler (3), right coiler (4) the fixing end of wind spring (7) by bolt (5) tightening in the center of fixing seat (8), wind spring (7) is outside is provided with guard shield (6).
For described fixed-wing UAV Landing deceleration damping unit, wind spring (7) free end of the guard shield (6) on left coiler (3), right coiler (4) is consistent with aircraft landing direction with the junction opening of arrester wires (2).
For described fixed-wing UAV Landing deceleration damping unit, when the wind spring (7) of left coiler (3), right coiler (4) inside is installed, wind spring direction of rotation is contrary.
Accompanying drawing explanation
Fig. 1 is fixed-wing UAV Landing deceleration damping unit structural representation.
Fig. 2 is winder structure schematic diagram
In accompanying drawing
1. the left coiler 4. of towing hook 2. arrester wires 3. right coiler 5. bolt 6. guard shield 7. wind spring 8. fixes seat.
Detailed description of the invention
With detailed description of the invention, the present invention is described in further detail below in conjunction with the accompanying drawings.
As shown in drawings, fixed-wing UAV Landing deceleration damping unit, left coiler (3), right coiler (4) by the hole, four location of fixing seat (8), are fixed on unmanned plane and specify on landing runway respectively.
As shown in drawings, the wind spring (7) of left coiler (3), right coiler (4) inside is rolled condition when not stressing, wind spring (7) free end mounting arrester wires (2), and fixing end is by bolt (5) tightening and fixing seat (8) center.
As shown in drawings, when unmanned plane lands from reservation course line, now by fly control put down airplane tail group land fall pintle (1), when aircraft slides the left coiler (3) of landing deceleration damping unit, right coiler (4) middle part run by being fixed on earth's surface, pintle (1) hangs up arrester wires (2), wind spring (7) will be stretched by after inertia force during aircraft landing, and wind spring plays damping action.
As shown in drawings, after aircraft pintle (1) hangs up arrester wires (2), owing to the stress of wind spring (7) is stretched, and possess certain buffer capacity, and under the retracting power effect of wind spring (7), fixed wing airplane will be decelerated, finally realize the short distance landing of fixed wing airplane.
Finally illustrate is, embodiment of above is only in order to illustrate the technical solution of the utility model and unrestricted, although present invention innovation being described in detail with reference to better embodiment, it will be understood by those within the art that, the technical scheme of the invention can be modified or equivalent, without deviating from objective and the scope of the present invention program, it is all because containing in the middle of right of the present utility model.
Claims (3)
1. a fixed-wing UAV Landing deceleration damping unit, it is characterized in that: arrester wires (2) is articulated on the free end of the wind spring (7) in left coiler (3), right coiler (4) respectively, left coiler (3), right coiler (4) the fixing end of wind spring (7) by bolt (5) tightening in the center of fixing seat (8), wind spring (7) is outside is provided with guard shield (6).
2. fixed-wing UAV Landing deceleration damping unit as claimed in claim 1, it is characterised in that: wind spring (7) free end of the guard shield (6) on left coiler (3), right coiler (4) is consistent with aircraft landing direction with the junction opening of arrester wires (2).
3. fixed-wing UAV Landing deceleration damping unit as claimed in claim 1, when the wind spring (7) of left coiler (3), right coiler (4) inside is installed, wind spring direction of rotation is contrary.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620389707.0U CN205738137U (en) | 2016-05-04 | 2016-05-04 | A kind of fixed-wing UAV Landing deceleration damping unit |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620389707.0U CN205738137U (en) | 2016-05-04 | 2016-05-04 | A kind of fixed-wing UAV Landing deceleration damping unit |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205738137U true CN205738137U (en) | 2016-11-30 |
Family
ID=57373045
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620389707.0U Expired - Fee Related CN205738137U (en) | 2016-05-04 | 2016-05-04 | A kind of fixed-wing UAV Landing deceleration damping unit |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205738137U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109552606A (en) * | 2018-12-26 | 2019-04-02 | 航天神舟飞行器有限公司 | A kind of unmanned slide landing obstruction hook |
-
2016
- 2016-05-04 CN CN201620389707.0U patent/CN205738137U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109552606A (en) * | 2018-12-26 | 2019-04-02 | 航天神舟飞行器有限公司 | A kind of unmanned slide landing obstruction hook |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20161130 Termination date: 20170504 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |