CN203767063U - Integrated investigating and striking unmanned aerial vehicle with changeable span-chord ratio - Google Patents
Integrated investigating and striking unmanned aerial vehicle with changeable span-chord ratio Download PDFInfo
- Publication number
- CN203767063U CN203767063U CN201420040752.6U CN201420040752U CN203767063U CN 203767063 U CN203767063 U CN 203767063U CN 201420040752 U CN201420040752 U CN 201420040752U CN 203767063 U CN203767063 U CN 203767063U
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- wing
- stage casing
- aerial vehicle
- unmanned aerial
- outer section
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Abstract
The utility model discloses an integrated investigating and striking unmanned aerial vehicle with a changeable span-chord ratio. The unmanned aerial vehicle comprises a body, an outer wing of a wing, a middle wing of the wing, a tail wing and a power system, and further comprises a connecting mechanism of the outer wing of the wing and the middle wing of the wing, wherein the outer wing of the wing and the middle wing of the wing are connected through the connecting mechanism which can be separated. The integrated investigating and striking unmanned aerial vehicle can carry out strategic, battle-like and tactical reconnaissance to provide intelligence for operation of troops. The integrated investigating and striking unmanned aerial vehicle can serve as a striking unmanned aerial vehicle according to change of the operational mission to attach and intercept ground and aerial targets. After the outer wing is abandoned, the unmanned aerial vehicle has two modes of operation.
Description
Technical field
The utility model relates to a kind of great Zhan string aircraft that not only can carry out HAE investigation tasks but also have the ability of closely grappling, belongs to variable aspect ratio and examines and beat one unmanned plane and aviation aircraft design field.
Background technology
Replacing and have people's aircraft to carry out excessive risk combat duty with unmanned plane, is important development aspect, one, current international airline field.Following land, sea, air, sky, electricity five are tieed up in the war of one, and the use of military unmanned machine will be very extensive, can not only carry out various non-lethal tasks (scouting, supervision etc.), can carry out again various soft, firmly kill and wound task.Therefore in the urgent need to developing a kind of multi-purpose unmanned aerial vehicle, to meet the needs of different strategies, the task of a campaign.
Summary of the invention
In order to meet the multi-functional operational need of modern military secret, carry out principle and integration innovation, provide a kind of variable aspect ratio to examine and beat one unmanned plane, realize scouting and hit integrated.
The utility model solves the technical scheme that its technical matters adopts:
A kind of variable aspect ratio is examined and is beaten one unmanned plane, comprises fuselage, the outer section of the wing wing, the wing stage casing wing, empennage, and power system; Also comprise the bindiny mechanism of the wing outer section wing and the wing stage casing wing, the outer section of the wing wing is connected by bindiny mechanism with the wing stage casing wing, and described connection structure is separable.
Described connection structure comprises steel cylinder, and steel cylinder one end is fixedly installed on the outer section of the wing wing, and the wing stage casing wing comprises beam, and the other end of steel cylinder inserts in the beam of the wing stage casing wing; Bindiny mechanism also comprises hook mechanism, and described hook mechanism is for locking and the release of steel cylinder and beam.
Described hook mechanism comprises edge strip, and upper edge strip is arranged on the wing of wing stage casing, and upper edge strip one end is by being fixed on the top of the stage casing wing around axle, and the other end is fixed on steel cylinder by hook, on described hook, arranges and can pull steel wire.
The beneficial effects of the utility model are, as an integrated unmanned plane of investigation strike, can carry out strategy, campaign and tactical reconnaissance, monitor battlefield, for the operation of army provides intelligence, can be used as attack unmanned plane according to the change of combat duty, attack, tackle ground and aerial target; Outside jettisoning, after the section wing, can have two kinds of modes of operation, one is disposable attack unmanned plane, in the time carrying out reconnaissance mission, once find enemy important goal, it can the outer section of the jettisoning wing, utilizes it at a high speed, high motor-driven airworthiness directly hits target, realizes " examining knotting closes "; Another is reusable attack unmanned plane, in the plug-in warhead of aircraft, finds after target guided missile target and is destroyed, and can carry additionally guided missile and reuse after unmanned plane makes a return voyage.
Brief description of the drawings
Fig. 1 is that the variable aspect ratio of the utility model is examined dozen one unmanned plane structural representation;
Fig. 2 is birds-eye view before the outer section of wing skimmed;
Fig. 3 is birds-eye view after the outer section of wing skimmed;
Fig. 4 is bindiny mechanism's structural representation of the outer section of wing and the stage casing wing.
In figure: 1. fuselage, the 2. outer section of the wing wing, the 3. wing stage casing wing, 4. bindiny mechanism, 5. empennage, 6. steel wire, 7. goes up edge strip, 8. hook.
Detailed description of the invention
Variable aspect ratio is examined and is beaten one unmanned plane as shown in Fig. 1～4, comprise fuselage 1, the outer section of the wing wing 2, the wing stage casing wing 3, the wing outer section wing and wing stage casing wing linkage section 4, empennage 5, power system, in Fig. 1, the outer section of the described wing wing 2 is connected with stage casing wing bindiny mechanism 4 by the outer section of the wing wing with the wing stage casing wing 3.
In the embodiment shown in fig. 4, adopt 5mm steel cylinder to insert in the beam of the wing stage casing wing 3, the upper edge strip 7 of the stage casing wing is movable, relies at ordinary times hook 8 to catch on.When section outside needs jettisoning wing when the wing 2, pulls steel wire 6 releases by steering wheel, upper edge strip 7 upwards rotates, outer panel 2 will be under lift effect jettisoning.
The outer section of wing of throwing that the wing of this machine is divided into inner side canned paragraph and both sides, according to the change of combat duty, the outer section of wing can separate with main frame, thereby changes the aspect ratio of aircraft.Before the outer section of wing do not thrown, aircraft length 2.8 m, aspect ratio 14, blade area 0.56 ㎡, after the outer section of wing thrown, aircraft length 1.4 m, aspect ratio 5.6, blade area 0.35 ㎡.The outer section of wing inserts in the beam of the stage casing wing with adopting the steel cylinder of diameter 5mm being connected of the stage casing wing, and the upper edge strip of the stage casing wing is movable, relies at ordinary times hook mechanism to pin.In the time of needs jettisoning outer panel, give signal of steering wheel, pull hook mechanism release, upper edge strip is opened, outer panel will be under lift effect jettisoning.
Claims (3)
1. variable aspect ratio is examined and is beaten an one unmanned plane, it is characterized in that: comprise fuselage, the outer section of the wing wing, the wing stage casing wing, empennage, and power system; Also comprise the bindiny mechanism of the wing outer section wing and the wing stage casing wing, the outer section of the wing wing is connected by bindiny mechanism with the wing stage casing wing, and described connection structure is separable.
2. variable aspect ratio according to claim 1 is examined and is beaten one unmanned plane, it is characterized in that: described connection structure comprises steel cylinder, steel cylinder one end is fixedly installed on the outer section of the wing wing, and the wing stage casing wing comprises beam, and the other end of steel cylinder inserts in the beam of the wing stage casing wing; Bindiny mechanism also comprises hook mechanism, and described hook mechanism is for locking and the release of steel cylinder and beam.
3. variable aspect ratio according to claim 2 is examined and is beaten one unmanned plane, it is characterized in that: described hook mechanism comprises edge strip, upper edge strip is arranged on the wing of wing stage casing, upper edge strip one end is by being fixed on the top of the stage casing wing around axle, the other end is fixed on steel cylinder by hook, on described hook, arranges and can pull steel wire.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420040752.6U CN203767063U (en) | 2014-01-22 | 2014-01-22 | Integrated investigating and striking unmanned aerial vehicle with changeable span-chord ratio |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420040752.6U CN203767063U (en) | 2014-01-22 | 2014-01-22 | Integrated investigating and striking unmanned aerial vehicle with changeable span-chord ratio |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203767063U true CN203767063U (en) | 2014-08-13 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420040752.6U Expired - Fee Related CN203767063U (en) | 2014-01-22 | 2014-01-22 | Integrated investigating and striking unmanned aerial vehicle with changeable span-chord ratio |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203767063U (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106043735A (en) * | 2016-05-31 | 2016-10-26 | 中国航空工业集团公司西安飞机设计研究所 | Rigidity-equivalent wing static gas spring model |
| CN107885230A (en) * | 2016-09-29 | 2018-04-06 | 北京理工大学 | Depopulated helicopter control system and its control method with laser guided weapon |
| CN110763090A (en) * | 2019-10-11 | 2020-02-07 | 南京理工大学 | Combinable and deformable primary-secondary type patrol and play integrated flying bomb and working method thereof |
| CN112977879A (en) * | 2021-04-01 | 2021-06-18 | 中国航天空气动力技术研究院 | Aeroelastic test platform |
| CN113443145A (en) * | 2021-05-31 | 2021-09-28 | 中航(成都)无人机系统股份有限公司 | Military unmanned aerial vehicle |
-
2014
- 2014-01-22 CN CN201420040752.6U patent/CN203767063U/en not_active Expired - Fee Related
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106043735A (en) * | 2016-05-31 | 2016-10-26 | 中国航空工业集团公司西安飞机设计研究所 | Rigidity-equivalent wing static gas spring model |
| CN107885230A (en) * | 2016-09-29 | 2018-04-06 | 北京理工大学 | Depopulated helicopter control system and its control method with laser guided weapon |
| CN107885230B (en) * | 2016-09-29 | 2021-01-05 | 北京理工大学 | Unmanned helicopter control system with laser guided weapon and control method thereof |
| CN110763090A (en) * | 2019-10-11 | 2020-02-07 | 南京理工大学 | Combinable and deformable primary-secondary type patrol and play integrated flying bomb and working method thereof |
| CN110763090B (en) * | 2019-10-11 | 2022-04-08 | 南京理工大学 | Combinable and deformable primary-secondary type patrol and play integrated flying bomb and working method thereof |
| CN112977879A (en) * | 2021-04-01 | 2021-06-18 | 中国航天空气动力技术研究院 | Aeroelastic test platform |
| CN113443145A (en) * | 2021-05-31 | 2021-09-28 | 中航(成都)无人机系统股份有限公司 | Military unmanned aerial vehicle |
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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: 20140813 Termination date: 20160122 |
|
| EXPY | Termination of patent right or utility model |