CN212512733U - Unmanned aerial vehicle training target drone of high aerodynamic performance - Google Patents
Unmanned aerial vehicle training target drone of high aerodynamic performance Download PDFInfo
- Publication number
- CN212512733U CN212512733U CN202020611506.7U CN202020611506U CN212512733U CN 212512733 U CN212512733 U CN 212512733U CN 202020611506 U CN202020611506 U CN 202020611506U CN 212512733 U CN212512733 U CN 212512733U
- Authority
- CN
- China
- Prior art keywords
- fuselage
- wing
- tail
- antenna
- training target
- 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.)
- Active
Links
Images
Landscapes
- Toys (AREA)
Abstract
The utility model provides an unmanned aerial vehicle training target drone of high aerodynamic performance, the reciprocating impact tunnel drilling machine comprises a machine body, the fuselage divide into the fuselage front end, fuselage middle-end and fuselage rear end, what load in the fuselage anterior segment has: the recovery umbrella, the airborne computer, the Beidou receiver, the Beidou antenna, the radio altimeter, the front airbag and the like; an air inlet channel is arranged in the rear end of the body, an airborne data terminal, an engine, a steering engine controller, a battery, an oil pump and a rear airbag are arranged below the air inlet channel, and the engine is connected with the air inlet channel; the outer wall of the rear end of the fuselage is provided with a V-shaped tail, the outer wall of the middle end of the fuselage is provided with wings, and the wings adopt a front edge sweepback type middle single wing structure; by arranging the middle single wing layout, the interference resistance of the wing body can be reduced, and the lift force when the attack angle is increased; the sweepback type wing and the tail wing can reduce transonic speed resistance. In addition: the V-shaped tail wing can reduce the interference of the tail wing on the guiding umbrella during recovery, thereby improving the aerodynamics of the target drone.
Description
Technical Field
The utility model relates to an unmanned aerial vehicle training target drone of high aerodynamic performance belongs to the training target drone field.
Background
A drone is broadly a military aircraft that is targeted for shooting training. The aircraft simulates the aircrafts of enemy army or incoming missiles during military exercises or weapon missions by utilizing remote control or preset flight paths and modes, provides imaginary targets and shooting opportunities for various artillery or missile systems, and belongs to one type of unmanned planes. The target drone is specially manufactured and is also refitted by old airplanes; have disposable, also have used many times, current unmanned aerial vehicle target drone is usually pneumatic performance relatively poor, and is slower in the use, is unfavorable for the training to use, does not play due training effect.
SUMMERY OF THE UTILITY MODEL
The utility model provides an unmanned aerial vehicle training target drone of high aerodynamic performance has solved that current unmanned aerial vehicle target drone is generally relatively poor in aerodynamic performance, and speed is slower in the use, is unfavorable for the training to use, does not play the problem of due training effect.
In order to solve the technical problem, the utility model provides a following technical scheme:
the utility model provides an unmanned aerial vehicle training target drone of high aerodynamic performance, the reciprocating impact tunnel drilling machine comprises a machine body, the fuselage divide into the fuselage front end, fuselage middle-end and fuselage rear end, what load in the fuselage anterior segment has: the recovery umbrella, the airborne computer, the Beidou receiver, the Beidou antenna, the radio altimeter, the front airbag and the like; an air inlet channel is arranged in the rear end of the body, an airborne data terminal 20, an engine 25, a steering engine controller 19, a battery 21, an oil pump and a rear airbag 26 are arranged below the air inlet channel, and the engine is connected with the air inlet channel; a V-tail is arranged on the outer wall of the rear end of the machine body, the airborne data terminal antenna 27 is arranged in the V-tail 3, and the airborne data terminal antenna is electrically connected with the airborne data terminal 20; the aircraft body is characterized in that wings are arranged on the outer wall of the middle end of the aircraft body, a V-tail steering engine is arranged at the rear end of the aircraft body and connected with a V tail through a pull rod rocker arm, and the wings are of a front-edge sweepback type middle single-wing structure.
Preferably, the sweep angle of the wing and the V tail leading edge is 33 degrees.
Preferably, the interior of the wing is provided with an aileron, the aileron is coaxially connected with a rotating shaft of an aileron steering engine through an output shaft, and the aileron steering engine is arranged in the fuselage.
Preferably, the duct shape of the air inlet duct is S-shaped.
Preferably, an antenna opening is formed in the upper portion of the airborne data terminal antenna, an antenna opening cover covers the antenna opening, and the antenna opening cover is made of glass fiber reinforced plastic composite materials to guarantee wave transmission rate.
Preferably, the radio altimeter is connected with the radio altimeter antennas through a line, and the number of the radio altimeter antennas 4 is two, and the two radio altimeter antennas are respectively arranged on wings on two sides of the fuselage.
Through the technical scheme, the utility model discloses beneficial effect: by arranging the middle single wing layout, the interference resistance of the wing body can be reduced, and the lift force when the attack angle is increased; the sweepback type wing and the tail wing can reduce transonic speed resistance. In addition: the V-shaped tail wing can reduce the interference of the tail wing on the guiding umbrella during recovery, thereby improving the aerodynamics of the target drone.
Drawings
FIG. 1 is a schematic structural view of the present invention;
fig. 2 is an internal schematic view of the present invention.
Detailed Description
The preferred embodiments of the present invention will be described in conjunction with the accompanying drawings, and it will be understood that they are presented herein only to illustrate and explain the present invention, and not to limit the present invention.
According to the unmanned aerial vehicle training target drone of high aerodynamic performance shown in the figure, including fuselage 1, fuselage 1 divide into fuselage front end 7, fuselage middle-end 8 and fuselage rear end 9, what load in the fuselage anterior segment 7 has: the recovery umbrella 16, the onboard computer 15, the Beidou receiver 12, the Beidou antenna 14, the radio altimeter 13, the front airbag 11 and the like; an air inlet channel 5 is arranged in the rear end 9 of the machine body, and an airborne data terminal 20, an engine 25, a steering engine controller 19, a battery 21, an oil pump 24 and a rear airbag 26 are arranged below the air inlet channel 5; the outer wall of the rear end 9 of the fuselage is provided with a V-tail 3, the airborne data terminal antenna 27 is arranged in the V-tail 3, and the airborne data terminal antenna 27 is electrically connected with the airborne data terminal 20; the outer wall of the middle end 8 of the machine body is provided with a wing 2, the inner part of the rear end 9 of the machine body is provided with a V-tail steering engine 22, the V-tail steering engine 22 is connected with the V-tail 3 through a pull rod rocker arm 23, an aileron 17 is arranged inside the wing 2, the aileron 17 is coaxially connected with a rotating shaft of an aileron steering gear 18 through an output shaft, the aileron steering gear 18 is arranged on the fuselage 1, an antenna port is arranged above the airborne data terminal antenna 27, an antenna port cover 6 is covered on the antenna port, the antenna opening cover 6 is made of glass fiber reinforced plastic composite materials, the wing 2 adopts a front edge sweepback type middle single wing structure, the front edge sweepback angle of the wing 2 and the V tail 3 is 33 degrees, the pipeline shape of the air inlet 5 is S-shaped, the requirement of the maximum flat flying speed of the airplane and the requirement of the small RCS of the airplane body can be met, and the 33-degree backswept of the leading edges of the wings 2 and the V-tail 3 can control the reflection direction of the electromagnetic wave mirror surface of the blunt leading edge outside a radar threat area; the V tail 3 with an elevation angle of 45 degrees can reduce the radar scattering cross section on the right side; the air inlet at the back can lead the wings and the fuselage to form certain shielding on the air inlet; the S-shaped air inlet channel 5 can shield the compressor, and electromagnetic waves are prevented from directly irradiating the compressor. In addition, in the manufacturing process, discontinuous points on the surface of the machine body are avoided as much as possible, so that diffraction of electromagnetic waves at the discontinuous positions of the surface is reduced; wave-transmitting materials are used for the ailerons and the V-tail rudder surface to reduce radar wave scattering generated when the rudder surface deflects, the radio altimeter 13 is connected with the radio altimeter antennas 4 through lines, and the number of the radio altimeter antennas 4 is two, and the two radio altimeter antennas are respectively arranged on the wings 2 on two sides of the fuselage 1.
Finally, it should be noted that: although the present invention has been described in detail with reference to the foregoing embodiments, it will be apparent to those skilled in the art that modifications and variations can be made in the embodiments or in part of the technical features of the embodiments without departing from the spirit and the scope of the invention.
Claims (6)
1. The utility model provides an unmanned aerial vehicle training target drone of high aerodynamic performance, includes the fuselage, its characterized in that: the fuselage divide into the fuselage front end, fuselage middle-end and fuselage rear end, what load in the fuselage anterior segment has: the recovery umbrella, the airborne computer, the Beidou receiver, the Beidou antenna, the radio altimeter and the front airbag are arranged on the front side of the recovery umbrella; an air inlet channel is arranged in the rear end of the body, an airborne data terminal, an engine, a steering engine controller, a battery, an oil pump and a rear airbag are arranged below the air inlet channel, and the engine is connected with the air inlet channel; the outer wall of the rear end of the machine body is provided with a V tail, the airborne data terminal antenna is arranged in the V tail, and the airborne data terminal antenna is electrically connected with the airborne data terminal; the aircraft body is characterized in that wings are arranged on the outer wall of the middle end of the aircraft body, a V-tail steering engine is arranged inside the rear end of the aircraft body and connected with a V-tail through a pull rod rocker arm, and the wings are of a front-edge sweepback type middle single-wing structure.
2. The drone training target of claim 1, wherein: the sweep angle of the wing and the V tail leading edge is 33 degrees.
3. The drone training target of claim 1, wherein: the interior of the wing is provided with an aileron, the aileron is coaxially connected with a rotating shaft of an aileron steering engine through an output shaft, and the aileron steering engine is arranged in the fuselage.
4. The drone training target of claim 1, wherein: the pipeline shape of intake duct is the S-shaped.
5. The drone training target of claim 1, wherein: an antenna opening is formed in the upper portion of the airborne data terminal antenna, an antenna opening cover covers the antenna opening, and the antenna opening cover is made of glass fiber reinforced plastic composite materials.
6. The drone training target of claim 1, wherein: the radio altimeter is connected with the radio altimeter antenna through a line, and the number of the radio altimeters is two, and the two radio altimeters are respectively arranged on wings on two sides of the fuselage.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020611506.7U CN212512733U (en) | 2020-04-20 | 2020-04-20 | Unmanned aerial vehicle training target drone of high aerodynamic performance |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020611506.7U CN212512733U (en) | 2020-04-20 | 2020-04-20 | Unmanned aerial vehicle training target drone of high aerodynamic performance |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN212512733U true CN212512733U (en) | 2021-02-09 |
Family
ID=74435483
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202020611506.7U Active CN212512733U (en) | 2020-04-20 | 2020-04-20 | Unmanned aerial vehicle training target drone of high aerodynamic performance |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN212512733U (en) |
-
2020
- 2020-04-20 CN CN202020611506.7U patent/CN212512733U/en active Active
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN107472509B (en) | A kind of stealthy unmanned plane of Flying-wing | |
| CN108100212B (en) | Small aspect ratio self-adaptive variant flying wing layout fighter | |
| CN108639339B (en) | Pneumatic layout of unmanned aerial vehicle | |
| EP3751227A1 (en) | Stealth large maneuvering target aircraft and control method for stealth large maneuvering target aircraft | |
| CN111516871A (en) | Supersonic stealth unmanned aerial vehicle with pneumatic stealth integrated design | |
| CN110775249B (en) | Aircraft with invisible double wings | |
| CN111976946B (en) | Pneumatic layout of combat bomber with sectional strake | |
| CN211107954U (en) | Variant stealth aircraft | |
| CN111976948B (en) | Pneumatic layout of unmanned combat bomber of flying wing formula | |
| CN108583849B (en) | Pneumatic overall arrangement of supersonic speed silence unmanned aerial vehicle | |
| CN105564638A (en) | Special airplane pneumatic configuration | |
| CN212512733U (en) | Unmanned aerial vehicle training target drone of high aerodynamic performance | |
| CN210047622U (en) | Unmanned aerial vehicle pneumatic layout | |
| CN111422348B (en) | Vertical take-off and landing unmanned aerial vehicle and control method thereof | |
| CN113148105A (en) | Double-head wing body fusion low-detectable layout | |
| CN113335499B (en) | High-mobility unmanned aerial vehicle based on solid rocket auxiliary power | |
| CN215475744U (en) | Stealth unmanned aerial vehicle | |
| CN115507707A (en) | Pneumatic layout of supersonic speed large mobile stealth target | |
| CN214057884U (en) | Combined aircraft layout | |
| RU2754277C1 (en) | Unmanned aerial vehicle | |
| CN215972072U (en) | Unmanned aerial vehicle pneumatic layout | |
| CN114104254A (en) | Pneumatic appearance structure of supersonic speed large maneuvering target | |
| CN112595177B (en) | Supersonic stealth target drone | |
| CN112611268A (en) | Small high-speed flying patrol bomb based on visual image accurate guidance | |
| CN106741846A (en) | A kind of swing-wing fighter plane |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CP03 | Change of name, title or address |
Address after: No. 39, Jianshe South Road, Huainan Economic and Technological Development Zone, Anhui 232,000 Patentee after: Anhui Huayin Electromechanical Co.,Ltd. Address before: 232000 Huainan economic and Technological Development Zone, Anhui Patentee before: ANHUI PRINTING MECHANICAL AND ELECTRICAL Co.,Ltd. |
|
| CP03 | Change of name, title or address |