CN206569267U - Supersonic speed unmanned plane - Google Patents
Supersonic speed unmanned plane Download PDFInfo
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- CN206569267U CN206569267U CN201620921501.8U CN201620921501U CN206569267U CN 206569267 U CN206569267 U CN 206569267U CN 201620921501 U CN201620921501 U CN 201620921501U CN 206569267 U CN206569267 U CN 206569267U
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- fuselage
- booster
- unmanned plane
- host wing
- supersonic speed
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Abstract
The utility model discloses a kind of supersonic speed unmanned plane, including fuselage（1）, it is characterised in that：In fuselage（1）On be provided with dynamic canard entirely（2）And host wing（3）, in host wing（3）On be provided with aileron（4）, in fuselage（1）Rear end be provided with and host wing（3）Perpendicular vertical tail（5）And abdomeinal fin（6）, in fuselage（1）Front end be provided with nose cone（7）, nose cone（7）On be provided with paster antenna（8）, in fuselage（1）Booster-missile combination is inside provided with, in fuselage（1）Tail end also pass through radome fairing（9）It is connected with booster-missile combination（10）, in booster-missile combination（10）On be then provided with cross empennage（11）.
Description
Technical field
The utility model is related to a kind of unmanned plane, particularly a kind of supersonic speed unmanned plane.
Background technology
Referred to as " unmanned plane ", english abbreviation is " UAV " to UAV, using radio robot and providing for oneself
The not manned aircraft that presetting apparatus is manipulated.
Unmanned plane by application field can be divided into it is military with it is civilian.Military aspect, unmanned plane is divided into reconnaissance plane and target drone.It is civilian
Aspect, at present taking photo by plane, agricultural, plant protection, auto heterodyne, express transportation, disaster relief, observation wild animal, monitoring infectious disease, survey
Paint, news report, electric inspection process, the disaster relief, movies-making, manufacture romance etc. field are all widely used.Traditional nobody
Machine often has that speed is slow, navigability is poor in use, the problems such as flight stability, stability are poor.
The content of the invention
The utility model is that design is ingeniously in order to solve the above-mentioned deficiency present in prior art, propose that one kind is simple in construction
Wonderful, flight resistance is small, speed is fast, flight stability and the preferable supersonic speed unmanned plane of stability.
Technical solution of the present utility model is：A kind of supersonic speed unmanned plane, including fuselage 1, it is characterised in that：In machine
Dynamic canard 2 and host wing 3 entirely are provided with body 1, aileron 4 is provided with host wing 3, is provided with the rear end of fuselage 1 and master
Wing 3 perpendicular vertical tail 5 and abdomeinal fin 6, are provided with nose cone 7, nose cone 7 in the front end of fuselage 1 and are provided with paster antenna
8, booster-missile combination is provided with fuselage 1, booster-missile combination 10 is also connected with by radome fairing 9 in the tail end of fuselage 1, in two grades of fire
Cross empennage 11 is then provided with arrow 10.
Described host wing 3 is dalta wing.
The utility model compared with the existing technology, has the following advantages that：
The supersonic speed unmanned plane of this kind of structure type, its is simple in construction, ingenious in design, rationally distributed, and it uses canard cloth
The profile of office, is that fuselage is configured with the host wing with aileron, vertical tail and abdomeinal fin, in order to carry out pitching, horizontal appearance
State is adjusted and controlled, while the stability in flight course is can also ensure that, and also it uses one-stage rocket, booster-missile combination two-stage
The design of driving, so results in lasting high speed operation speed, and its speed can exceed velocity of sound.
Brief description of the drawings
Fig. 1 is the front view of the utility model embodiment.
Fig. 2 is the top view of the utility model embodiment.
Embodiment
Below in conjunction with brief description of the drawings embodiment of the present utility model.As shown in Figure 1 and Figure 2：A kind of supersonic speed without
It is man-machine, including fuselage 1, dynamic canard 2 entirely is provided with the front portion of fuselage 1, the middle part of fuselage 1 host wing 3 is provided with, here
Host wing 3 selects dalta wing, and aileron 4 is additionally provided with described host wing 3, and this aileron 4 can be put relative to host wing 3
It is dynamic, the vertical tail 5 and abdomeinal fin 6 perpendicular with above-mentioned host wing 3 is provided with the rear end of fuselage 1, and in the front end of fuselage 1 then
Nose cone 7 is provided with, the paster antenna 8 for receiving signal is provided with nose cone 7, booster-missile combination is provided with fuselage 1, and
Booster-missile combination 10 is then connected with by radome fairing 9 in the tail end of fuselage 1, and is additionally provided with booster-missile combination 10 cross empennage
11。
The supersonic speed unmanned plane of the utility model embodiment, its power profile uses canard configuration, in the rear portion cloth of nose cone 7
A pair of complete dynamic entirely dynamic canards are put, available for the control of pitch attitude, its mainpiston is a pair of dalta wings（That is host wing 3）,
And a pair of ailerons 4, the control available for horizontal course are also arranged on the outside of the trailing edge of this host wing 3；In the afterbody of fuselage 1
Arrange the vertical tail 5 and abdomeinal fin 6 vertical with host wing 3, it is ensured that the stabilization in course.In flight course, booster-missile combination
10 promotion unmanned planes are navigated by water in the air, self falling after the fuel combustion totally of booster-missile combination 10, by being arranged on inside fuselage 1
One-stage rocket continues to drive the navigation of this unmanned plane.
Claims (2)
1. a kind of supersonic speed unmanned plane, including fuselage（1）, it is characterised in that：In fuselage（1）On be provided with dynamic canard entirely（2）With
Host wing（3）, in host wing（3）On be provided with aileron（4）, in fuselage（1）Rear end be provided with and host wing（3）Perpendicular
Vertical tail（5）And abdomeinal fin（6）, in fuselage（1）Front end be provided with nose cone（7）, nose cone（7）On be provided with paster antenna（8）,
In fuselage（1）Booster-missile combination is inside provided with, in fuselage（1）Tail end also pass through radome fairing（9）It is connected with booster-missile combination（10）,
Booster-missile combination（10）On be then provided with cross empennage（11）.
2. supersonic speed unmanned plane according to claim 1, it is characterised in that：Described host wing（3）For dalta wing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620921501.8U CN206569267U (en) | 2016-08-23 | 2016-08-23 | Supersonic speed unmanned plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620921501.8U CN206569267U (en) | 2016-08-23 | 2016-08-23 | Supersonic speed unmanned plane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206569267U true CN206569267U (en) | 2017-10-20 |
Family
ID=60063404
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620921501.8U Expired - Fee Related CN206569267U (en) | 2016-08-23 | 2016-08-23 | Supersonic speed unmanned plane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206569267U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108820204A (en) * | 2018-08-02 | 2018-11-16 | 中国科学院工程热物理研究所 | Modularization supersonic speed unmanned plane |
| CN110589032A (en) * | 2019-09-25 | 2019-12-20 | 北京凌空天行科技有限责任公司 | Parachute system for aircraft recovery and parachute recovery method |
| CN110589033A (en) * | 2019-09-25 | 2019-12-20 | 北京凌空天行科技有限责任公司 | Deformable recovery aircraft and recovery method |
-
2016
- 2016-08-23 CN CN201620921501.8U patent/CN206569267U/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108820204A (en) * | 2018-08-02 | 2018-11-16 | 中国科学院工程热物理研究所 | Modularization supersonic speed unmanned plane |
| CN110589032A (en) * | 2019-09-25 | 2019-12-20 | 北京凌空天行科技有限责任公司 | Parachute system for aircraft recovery and parachute recovery method |
| CN110589033A (en) * | 2019-09-25 | 2019-12-20 | 北京凌空天行科技有限责任公司 | Deformable recovery aircraft and recovery method |
| CN110589033B (en) * | 2019-09-25 | 2022-02-22 | 北京凌空天行科技有限责任公司 | Deformable recovery aircraft and recovery method |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20171020 Termination date: 20210823 |