CN200967562Y - High subsonic speed unmanned plane - Google Patents
High subsonic speed unmanned plane Download PDFInfo
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- CN200967562Y CN200967562Y CN 200620094175 CN200620094175U CN200967562Y CN 200967562 Y CN200967562 Y CN 200967562Y CN 200620094175 CN200620094175 CN 200620094175 CN 200620094175 U CN200620094175 U CN 200620094175U CN 200967562 Y CN200967562 Y CN 200967562Y
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Abstract
The utility model discloses a high subsonic pilotless aircraft, containing a craft body (3), a pair of aerofoil (4), a flat tail (6) and a vertical tail (12). The utility model is characterized in that a head pyramid (2) and a tail pyramid (10) are provided respectively in the front and the rear of the craft body (3); an air speed tube (1) is arranged in the center of the head pyramid (2); an air inlet pipe (11) is arranged in the upper rear part of the craft body (3); the flat tail (6) and the vertical tail (12) are positioned over the rear part of the air inlet pipe (11); a rocket booster (9) is provided under the rear part of the craft body (3); an assessorial aerofoil (5) is positioned on the aerofoil (4); an elevator (7) is positioned on the flat tail (6) and a rudder (13) is positioned on the vertical tail (12). The utility model according to the characteristics of the modern war equipment adopts a pneumatic form and the speed can reach 800 miles per hour based a long flying duration time. Through replacing different signal equipment, the utility model can simulate various aerocrafts such as the cruise missile, has a good recycling performance, can be used many times and has a low manufacturing cost and flight cost.
Description
Technical field:
The utility model relates to a kind of unmanned plane, especially a kind of dual-use high subsonic speed unmanned plane.
Background technology:
At present, China is compared with developed countries technical at unmanned plane, and integral level is also lower.Domestic nearly 200 tame scientific research institutions, enterprise and research institution, the product speed per hour is no more than 300 kilometers mostly.In the modern military equipment, it is out-of-date fully that speed per hour is lower than 300 kilometers attack aircraft.Therefore, adopt low-speed unmanned aerial vehicle to simulate cruise missile manoeuvre, training, lost the training meaning as target drone.
Summary of the invention:
The utility model waits not enoughly at the speed per hour of prior art is too low, provides a kind of speed per hour can reach high subsonic speed unmanned plane more than 800 kilometers.
Technical solution of the present utility model is: a kind of high subsonic speed unmanned plane, be provided with fuselage 3, fuselage 3 is provided with wing 4, horizontal tail 6 and vertical tail 12, it is characterized in that: the front and back ends at fuselage 3 is respectively equipped with nose cone 2 and tail cone 10, the center of nose cone 2 is provided with pitot 1, the rear portion is provided with inlet channel 11 on fuselage 3, and horizontal tail 6 and vertical tail 12 are arranged on the back upper place of inlet channel 11, is provided with rocket booster 9 at the following rear portion of fuselage 3; On wing 4, be provided with the attached wing 5, on horizontal tail 6, be provided with elevating rudder 7, on vertical tail 12, be provided with yaw rudder 13.
Described wing 4 is a missile wing in the 35 degree sweepback.
The utility model is according to the modern war installation feature, the aerodynamic configuration design of adopting, on the basis in longer cruise duration, speed per hour can reach more than 800 kilometers, by changing unlike signal equipment, can simulate various aircraft such as cruise missile, and reclaim the reliability height, can be repeatedly used, cost is lower, and flight cost is low.Uses such as cruise missile manoeuvre, training and military enterprise's verification armament systems are simulated by suitable land, sea and air force.Also can be used as the bait bullet, under battlefield surroundings, cooperate guided missile to use, reach the effect of mixing the spurious with the genuine.Portability video reconnaissance equipment, communication facilities, aerological sounding equipment etc. are finished multiple-task.
Description of drawings:
Fig. 1 is a structural representation of the present utility model.
Fig. 2 is the lateral plan of Fig. 1.
The specific embodiment:
Below in conjunction with the description of drawings specific embodiment of the present utility model.As shown in Figure 1, 2, a kind of high subsonic speed unmanned plane, be provided with fuselage 3, fuselage 3 is provided with wing 4, horizontal tail 6 and vertical tail 12, it is characterized in that: the front and back ends at fuselage 3 is respectively equipped with nose cone 2 and tail cone 10, and the center of nose cone 2 is provided with pitot 1, and the rear portion is provided with inlet channel 11 on fuselage 3, horizontal tail 6 and vertical tail 12 are arranged on the back upper place of inlet channel 11, are provided with rocket booster 9 at the following rear portion of fuselage 3; Be provided with the attached wing 5 on wing 4, wing 4 is a missile wing in the 35 degree sweepback, is provided with elevating rudder 7 on horizontal tail 6, is provided with yaw rudder 13 on vertical tail 12.
Claims (2)
1. high subsonic speed unmanned plane, be provided with fuselage (3), fuselage (3) is provided with wing (4), horizontal tail (6) and vertical tail (12), it is characterized in that: the front and back ends at fuselage (3) is respectively equipped with nose cone (2) and tail cone (10), the center of nose cone (2) is provided with pitot (1), be provided with inlet channel (11) at the last rear portion of fuselage (3), horizontal tail (6) and vertical tail (12) are arranged on the back upper place of inlet channel (11), are provided with rocket booster (9) at the following rear portion of fuselage (3); On wing (4), be provided with the attached wing (5), on horizontal tail (6), be provided with elevating rudder (7), on vertical tail (12), be provided with yaw rudder (13).
2. high subsonic speed unmanned plane according to claim 1 is characterized in that: described wing (4) is a missile wing in the 35 degree sweepback.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200620094175 CN200967562Y (en) | 2006-11-20 | 2006-11-20 | High subsonic speed unmanned plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200620094175 CN200967562Y (en) | 2006-11-20 | 2006-11-20 | High subsonic speed unmanned plane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN200967562Y true CN200967562Y (en) | 2007-10-31 |
Family
ID=38967130
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 200620094175 Expired - Lifetime CN200967562Y (en) | 2006-11-20 | 2006-11-20 | High subsonic speed unmanned plane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN200967562Y (en) |
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101774429A (en) * | 2010-02-26 | 2010-07-14 | 成都飞机设计研究所 | Small UAV aerodynamic layout for vertical rope-type recovery |
| CN102362141A (en) * | 2009-02-02 | 2012-02-22 | 威罗门飞行公司 | Multimode unmanned aerial vehicle |
| CN102923305A (en) * | 2012-11-30 | 2013-02-13 | 贵州新视界航拍科技有限公司 | Fixed-wing aircraft for aerial photography and method for taking off and landing |
| CN104121827A (en) * | 2014-07-01 | 2014-10-29 | 河南科技大学 | Recyclable invisible bombing guided missile |
| CN104897006A (en) * | 2015-04-24 | 2015-09-09 | 江西洪都航空工业集团有限责任公司 | Aerodynamic layout of drone aircraft |
| CN105346702A (en) * | 2015-11-16 | 2016-02-24 | 清华大学 | Deformation nose cone of aircraft |
| CN105620764A (en) * | 2016-02-16 | 2016-06-01 | 李和坤 | Aircraft with rocket thruster |
| CN107054647A (en) * | 2017-03-16 | 2017-08-18 | 成都飞机工业（集团）有限责任公司 | A kind of sky penetrates bait machine |
| CN109747822A (en) * | 2017-11-06 | 2019-05-14 | 南京福尔摩斯智能科技有限公司 | Implicitly hung down fixed-wing unmanned plane |
| US10703506B2 (en) | 2009-09-09 | 2020-07-07 | Aerovironment, Inc. | Systems and devices for remotely operated unmanned aerial vehicle report-suppressing launcher with portable RF transparent launch tube |
| CN112572788A (en) * | 2020-12-04 | 2021-03-30 | 中国航空工业集团公司成都飞机设计研究所 | Aircraft with cross-over supersonic pneumatic performance |
-
2006
- 2006-11-20 CN CN 200620094175 patent/CN200967562Y/en not_active Expired - Lifetime
Cited By (19)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10222177B2 (en) | 2009-02-02 | 2019-03-05 | Aerovironment, Inc. | Multimode unmanned aerial vehicle |
| CN102362141A (en) * | 2009-02-02 | 2012-02-22 | 威罗门飞行公司 | Multimode unmanned aerial vehicle |
| US12013212B2 (en) | 2009-02-02 | 2024-06-18 | Aerovironment, Inc. | Multimode unmanned aerial vehicle |
| US9127908B2 (en) | 2009-02-02 | 2015-09-08 | Aero Vironment, Inc. | Multimode unmanned aerial vehicle |
| US10494093B1 (en) | 2009-02-02 | 2019-12-03 | Aerovironment, Inc. | Multimode unmanned aerial vehicle |
| US11731784B2 (en) | 2009-09-09 | 2023-08-22 | Aerovironment, Inc. | Systems and devices for remotely operated unmanned aerial vehicle report-suppressing launcher with portable RF transparent launch tube |
| US11319087B2 (en) | 2009-09-09 | 2022-05-03 | Aerovironment, Inc. | Systems and devices for remotely operated unmanned aerial vehicle report-suppressing launcher with portable RF transparent launch tube |
| US10703506B2 (en) | 2009-09-09 | 2020-07-07 | Aerovironment, Inc. | Systems and devices for remotely operated unmanned aerial vehicle report-suppressing launcher with portable RF transparent launch tube |
| CN101774429A (en) * | 2010-02-26 | 2010-07-14 | 成都飞机设计研究所 | Small UAV aerodynamic layout for vertical rope-type recovery |
| CN102923305A (en) * | 2012-11-30 | 2013-02-13 | 贵州新视界航拍科技有限公司 | Fixed-wing aircraft for aerial photography and method for taking off and landing |
| CN104121827B (en) * | 2014-07-01 | 2016-08-17 | 河南科技大学 | A kind of stealthy bombing guided missile of repeatable utilization |
| CN104121827A (en) * | 2014-07-01 | 2014-10-29 | 河南科技大学 | Recyclable invisible bombing guided missile |
| CN104897006A (en) * | 2015-04-24 | 2015-09-09 | 江西洪都航空工业集团有限责任公司 | Aerodynamic layout of drone aircraft |
| CN105346702B (en) * | 2015-11-16 | 2017-08-11 | 清华大学 | The deformation nose cone of aircraft |
| CN105346702A (en) * | 2015-11-16 | 2016-02-24 | 清华大学 | Deformation nose cone of aircraft |
| CN105620764A (en) * | 2016-02-16 | 2016-06-01 | 李和坤 | Aircraft with rocket thruster |
| CN107054647A (en) * | 2017-03-16 | 2017-08-18 | 成都飞机工业（集团）有限责任公司 | A kind of sky penetrates bait machine |
| CN109747822A (en) * | 2017-11-06 | 2019-05-14 | 南京福尔摩斯智能科技有限公司 | Implicitly hung down fixed-wing unmanned plane |
| CN112572788A (en) * | 2020-12-04 | 2021-03-30 | 中国航空工业集团公司成都飞机设计研究所 | Aircraft with cross-over supersonic pneumatic performance |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| ASS | Succession or assignment of patent right |
Owner name: SHENYANG CASIC CHINA TOPRS TECHNOLOGY CO., LTD. Free format text: FORMER OWNER: DALIAN SANKE AVIATION TECHNOLOGY CO., LTD. Effective date: 20120315 |
|
| C41 | Transfer of patent application or patent right or utility model | ||
| COR | Change of bibliographic data |
Free format text: CORRECT: ADDRESS; FROM: 116025 DALIAN, LIAONING PROVINCE TO: 110030 SHENYANG, LIAONING PROVINCE |
|
| TR01 | Transfer of patent right |
Effective date of registration: 20120315 Address after: 110030 Liaoning city of Shenyang province Shenbei New Area Huishan Street No. 123-7 Patentee after: Shenyang Aerospace ChinaTopRs Science & Technology Co., Ltd. Address before: 116025 Liaoning Province, Dalian City High-tech Park XinDa Qixianling Street No. 57 Patentee before: Dalian Sanke Aviation Technology Co., Ltd. |
|
| ASS | Succession or assignment of patent right |
Owner name: DALIAN SANKE AVIATION TECHNOLOGY CO., LTD. Free format text: FORMER OWNER: SHENYANG AEROSPACE ZHONGCE TECHNOLOGY CO., LTD. Effective date: 20120502 |
|
| C41 | Transfer of patent application or patent right or utility model | ||
| COR | Change of bibliographic data |
Free format text: CORRECT: ADDRESS; FROM: 110030 SHENYANG, LIAONING PROVINCE TO: 116000 DALIAN, LIAONING PROVINCE |
|
| TR01 | Transfer of patent right |
Effective date of registration: 20120502 Address after: 116000 No. 57 XinDa street, hi tech park, Liaoning, Dalian Patentee after: Dalian Sanke Aviation Technology Co., Ltd. Address before: 110030 Liaoning city of Shenyang province Shenbei New Area Huishan Street No. 123-7 Patentee before: Shenyang Aerospace ChinaTopRs Science & Technology Co., Ltd. |
|
| CX01 | Expiry of patent term |
Granted publication date: 20071031 |
|
| EXPY | Termination of patent right or utility model |