CN205293099U - Use coaxial tandem twin engine's fixed wing uavs - Google Patents
Use coaxial tandem twin engine's fixed wing uavs Download PDFInfo
- Publication number
- CN205293099U CN205293099U CN201620002463.6U CN201620002463U CN205293099U CN 205293099 U CN205293099 U CN 205293099U CN 201620002463 U CN201620002463 U CN 201620002463U CN 205293099 U CN205293099 U CN 205293099U
- Authority
- CN
- China
- Prior art keywords
- wing
- fuselage
- engine
- tailplane
- unmanned plane
- 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.)
- Expired - Fee Related
Links
Landscapes
- Toys (AREA)
Abstract
The utility model relates to an unmanned aerial vehicle equipment technical field, in particular to use coaxial tandem twin engine's fixed wing uavs, it includes the organism, this organism adopts stationary vane H tail formula aerodynamic layout, the organism includes and is provided with the wing on this fuselage by the fuselage that this wing trailing edge is provided with wing flap and aileron, the leading edge is provided with the de -icer, start installing support and rear engine installing support before fuselage front end and tail end are provided with respectively, mobilize to install respectively on installing support and the rear engine installing support front -mounted engine and rear engine before should, it has simple structure, and is with low costs, the easy maintenance, and stability is high, environmental suitability is strong, and flight safety check is guaranteed to its twin engine structure, eliminates incident hidden danger, and can have advantages such as strong advantage in high height above sea level operation area in smooth flight under the big weather of low humidity temperature.
Description
Technical field
This utility model relates to unmanned plane equipment technical field, uses the bimotored fixed-wing unmanned plane of coaxial tandem particularly to one.
Background technology
Unmanned plane is to carry out, by radio robot or airborne computer stored program controlled, the not manned vehicle that manipulates. Unmanned plane not only can complete the task that manned aircraft performs, and is more suitable for the task that people's aircraft should not perform.
Existing fixed-wing unmanned plane is owing to using single-shot life as power source, its dynamical system is substantially free of aerial restarting ability, electromotor long working probably breaks down speed of turning round, safety is low, particularly High aititude working environment, engine misses probability is higher, and the safety of unmanned plane can not get ensureing; Low temperature environment temperature is low, and wing icing problem is serious; Under wet environment, electronic operating failure rate is high.
Utility model content
The purpose of this utility model is in that the defect for prior art and deficiency, thering is provided a kind of simple in construction, one reasonable in design, easy to use uses the bimotored fixed-wing unmanned plane of coaxial tandem, and it has simple in construction, cost is low, easy care, stability is high, environmental suitability is strong, its twin-engined structures, ensure flight safety inspection, eliminate safety hazards, and can smooth flight under the climatic environment that low wet temp is big, have the advantages such as stronger advantage at High aititude scene of operations.
For achieving the above object, the technical solution adopted in the utility model is:
Described in the utility model a kind of using the bimotored fixed-wing unmanned plane of coaxial tandem, it includes body, and this body adopts fixed-wing H Wei Shi aerodynamic arrangement; Described body includes fuselage, and this fuselage is provided with wing, and this trailing edge is provided with wing flap and aileron; The described leading edge of a wing is provided with ice removal; Described front fuselage and tail end start mounting bracket and rear engine mounting bracket before being respectively arranged with, start before this mounting bracket and rear engine mounting bracket are separately installed with front-mounted engine and rear engine, this front-mounted engine and rear engine are separately installed with pulling force propeller and thrust propeller; Described wing is provided with H-shaped tailplane, this H-shaped tailplane is made up of two parallel shoes and tailplane main body, tailplane trailing edge arranges elevator, and the both sides of this tailplane main body are correspondingly arranged on vertical tail, and this vertical tail trailing edge is provided with rudder;Equipment compartment and load cabin it is provided with from front to back in described fuselage; Automatic pilot, airborne data radio station, power supply unit are installed in described equipment compartment; Installed load members in described load cabin.
After adopting said structure, this utility model has the beneficial effect that a kind of use bimotored fixed-wing unmanned plane of coaxial tandem described in the utility model, it solving existing single-shot unmanned plane can not the problem of restarting in the air, use the bimotored layout structure of coaxial tandem, when engine misses, another electromotor also can ensure normal flight operation, solves the problem that electromotor easily stops working. The automatic de-icing device that it increases at the leading edge of a wing, also make the unmanned plane at low ambient temperatures can smooth flight, fuselage equipment compartment adopts waterproofing design simultaneously, aircraft can be prevented effectively from equipment compartment water inlet when the region job that humidity is bigger, it has simple in construction, cost is low, easy care, stability is high, environmental suitability is strong, its twin-engined structures, it is ensured that flight safety inspection, eliminate safety hazards, and can smooth flight under the weather that low wet temp is big, have the advantages such as stronger advantage at High aititude scene of operations.
Accompanying drawing explanation
Fig. 1 is structural representation of the present utility model;
Fig. 2 is side structure schematic diagram of the present utility model.
Description of reference numerals:
1, wing; 2, pulling force propeller; 3, front-mounted engine; 4, front mounting bracket is started; 5, ice removal; 6, aileron; 7, wing flap; 8, load cabin; 9, rear engine mounting bracket; 10, rear engine; 11, thrust propeller; 12, H-shaped tailplane; 13, rudder; 14, elevator; 15, shoe; 16, vertical tail; 17, equipment compartment.
Detailed description of the invention
Below in conjunction with accompanying drawing, this utility model is further described.
As shown in Figure 1 and Figure 2, described in the utility model a kind of using the bimotored fixed-wing unmanned plane of coaxial tandem, it includes body, and this body adopts fixed-wing H Wei Shi aerodynamic arrangement; Described body includes fuselage, and this fuselage is provided with wing 1, and this wing 1 trailing edge is provided with wing flap 7 and aileron 6; Described wing 1 leading edge is provided with ice removal 5; Described front fuselage and tail end start mounting bracket 4 and rear engine mounting bracket 9 before being respectively arranged with, start mounting bracket 4 and rear engine mounting bracket 9 are separately installed with front-mounted engine 3 and rear engine 10 before this, this front-mounted engine 3 and rear engine 10 are separately installed with pulling force propeller 2 and thrust propeller 11;
Described wing 1 is provided with H-shaped tailplane 12, this H-shaped tailplane 12 is made up of two parallel shoes 15 and tailplane main body, tailplane trailing edge arranges elevator 14, the both sides of this tailplane main body are correspondingly arranged on vertical tail 16, and this vertical tail 16 trailing edge is provided with rudder 13;
Equipment compartment 17 and load cabin 8 it is provided with from front to back in described fuselage;
Automatic pilot, airborne data radio station, power supply unit are installed in described equipment compartment 17;
Installed load members in described load cabin 8.
In this utility model, the explanation of each parts:
1), automatic pilot possesses automatic Pilot and Autonomous Control unmanned plane function, adopt PID control method, by the control signal that the ground remote control information retrieval of data link transmission is correct, to 3 to acceleration, 3 be received to the data of gyro data, baroceptor and navigator collection and feed back to ground control station; In unmanned plane take-off process, can Autonomous Control unmanned plane rolling start, process according to the route task planned in advance in flight course, send instruction to actuator, control actuator and perform corresponding task, and need to carry out in real time change and the planning of flight path route according to actual task. Parking order can be performed according to mission requirements during landing.
2), electromotor is gasoline type piston engine.
3), preposition propeller be wooden spacing pulling force propeller, rear-mounted propeller is wooden spacing thrust propeller.
4), fuel tank is ABS engineering plastics fuel tank
5), payload segment assembly can adopt multiple low-altitude remote sensing equipment, employing video camera or camera to obtain image data, employing EO-1 hyperion camera acquisition spectroscopic data etc. Simultaneously also can carry below wing, for instance external fuel cell, miniature video camera equipment etc.
6), payload segment assembly is arranged on the damping device in fuselage, it is ensured that task device minimum degree is subject to the impact of fuselage vibrations.
7), unmanned plane tricycle landing gear is set, nose-gear is arranged on below equipment compartment, and rear undercarriage is arranged on load cabin obliquely downward.
As it is shown in figure 1, body in the design adopts fixed-wing H Wei Shi aerodynamic arrangement, pulling in front and others push behind double engine automobile power system, body includes the fuselage, wing, tailplane, vertical tail and the shoe that adopt bolt and carbon pipe to connect; Fuselage interior is divided into two cabin sections according to function, is followed successively by equipment compartment, load cabin from front to back, and the power supply unit such as automatic pilot, airborne data radio station, battery is arranged on equipment compartment; Payload segment is arranged in load cabin, and front and back electromotor and corresponding propeller are arranged in mounting seat, are connected with body by engine mounting bracket.
Unmanned plane dismounts according to fuselage, wing, shoe, tailplane, vertical tail, fixed by carbon pipe and screw between fuselage, wing, tailplane, vertical tail are connected with fuselage by shoe, use structural member is fixed, ensure stability and the safety of aircraft to greatest extent, aileron, wing flap, elevator, rudder steering wheel be placed in body. Elevator deflecting facet controls the pitch attitude of aircraft, and aileron control surface deflection controls the roll attitude of aircraft, and rudder surface controls the course of aircraft. The wing of full composite material mechanism can increase leading edge of a wing automatic de-icing function as required, designs flight speed 20m/s��35m/s, designs flying height 100m��5000m. Aircraft handling performance is high, and to handling, hands skill set requirements is low, and safety is operation easily.
Dynamical system has mainly comprised gasoline type piston engine, wooden constant pitch airscrew and fuel tank, gasoline type piston engine and wooden constant pitch airscrew are arranged in mounting seat, it is connected with body by engine mounting bracket, centre arranges fire wall, the impact of aircraft is preferably minimized by engine vibration, front engine propeller is wooden spacing pulling force propeller, rear engine propeller is wooden spacing thrust propeller, fuel tank is the ABS engineering plastics fuel tank of customization, convenient to operation, provide enough fuel oils for electromotor. Electromotor is gasoline type piston engine, and in conjunction with the layout of aircraft, distance of taking off only needs 50m��80m, hence it is evident that be better than the unmanned plane of same type. The dynamical system of this unmanned plane is simple to operate, easy to maintenance, and the flight preparation time is short, it is possible to rapidly enter aerial mission state.
Remote controller and automatic pilot are Flight Control Section, remote controller is for closely intervention to the adjustment of flight attitude and emergency case, especially the takeoff and landing stage, during use, freely switching between remote manual control state and automatic Pilot state can be completed by remote controller. Automatic pilot is arranged on equipment compartment, possess automatic Pilot and Autonomous Control unmanned plane function, adopt PID control method, by the control signal that the ground remote control information retrieval of data link transmission is correct, to 3 to acceleration, 3 be received to the data of gyro data, baroceptor and navigator collection and feed back to ground control station.Control program adopts the angle of attack to control the height of unmanned plane, and elevator controls the angle of attack of unmanned plane, the speed of Throttle Opening Control unmanned plane. Crosswise joint adopts elevon combination control mode, and after deviation occur in the flight route point of unmanned plane and the way point of setting, aileron exports, by control rate, the gradient that rudder amount makes unmanned plane maintenance fixing, and elevator keeps the height of unmanned plane. In unmanned plane take-off process, automatic pilot can take off by Autonomous Control unmanned aerial vehicle ejecting, flight course sends instruction according to the task route planned in advance to actuator, control actuator and perform corresponding task, and change and the planning of flight path route can be carried out in real time according to actual task demand, operator can carry out the control execution of more important task business by trajectory planning and path adjustment, autonomous flight can be carried out by the prebriefed pattern that mission requirements is arranged in advance, complete the data acquisition to mission area by Autonomous Control task device and work. Earth station can show the electronic chart of flight range, flight path, flight parameter, aspect etc. in unmanned plane during flying process, all parameters and number boat data can be downloaded in real time in-flight, task complete after by prebriefed pattern autonomous flight to predetermined drop zone, and Autonomous Control unmanned plane releases a parachute stable landing, additionally needing, by remote controller, airborne automatic pilot is switched back into remote state also dependent on actual space enrironment and use, visual control unmanned plane carries out sliding landing.
On-board data transmission radio station is installed in fuselage equipment compartment, and the number of on-board data transmission radio station passes antenna and adopts columnar antenna.
Payload portion can adopt multiple low-altitude remote sensing equipment, adopts video camera or camera to obtain image data, adopts EO-1 hyperion camera to obtain spectroscopic data etc. Simultaneously also can carry below wing, for instance external fuel cell, miniature video camera equipment etc.
Running through into taking off of unmanned plane by sliding, when launching, unmanned plane is mainly completed unmanned plane Non-follow control by ground system, is switched to automatic navigation mode after unmanned plane rises to safe altitude. Completed the autonomous flight control in unmanned plane preplanned mission course line by navigation control system, arrive mission area and obtain remotely-sensed data. Can realize independently taking off simultaneously, rely on automatic pilot to complete the autonomous rolling start of unmanned plane. Unmanned plane can complete the application of different field by carrying different mission payload equipment, performs corresponding task.
Way of recycling can adopt downhill race mode, adopts the way point of automatic pilot to arrange in advance, it is possible to is set as that namely arrive set point coordinate completes downhill race. Employing tricycle landing gear lands, and undercarriage is processed with carbon fiber for main material, carries out bumper and absorbing shock by undercarriage and three rubber wheels during undercarriage landing, completes the aircraft grounding by skidding.
It is as shown in the table for its total technical index:
A kind of use bimotored fixed-wing unmanned plane of coaxial tandem described in the utility model, it solving existing single-shot unmanned plane can not the problem of restarting in the air, use the bimotored layout structure of coaxial tandem, when engine misses, another electromotor also can ensure normal flight operation, solves the problem that electromotor easily stops working. The automatic de-icing device that it increases at the leading edge of a wing, also make the unmanned plane at low ambient temperatures can smooth flight, fuselage equipment compartment adopts waterproofing design simultaneously, aircraft can be prevented effectively from equipment compartment water inlet when the region job that humidity is bigger, it has simple in construction, cost is low, easy care, stability is high, environmental suitability is strong, its twin-engined structures, it is ensured that flight safety inspection, eliminate safety hazards, and can smooth flight under the weather that low wet temp is big, have the advantages such as stronger advantage at High aititude scene of operations.
The above is only better embodiment of the present utility model, therefore all equivalences done according to the structure described in this utility model patent claim, feature and principle change or modify, and are all included in this utility model patent claim.
Claims (1)
1. one kind uses the bimotored fixed-wing unmanned plane of coaxial tandem, it is characterised in that: it includes body, and this body adopts fixed-wing H Wei Shi aerodynamic arrangement; Described body includes fuselage, and this fuselage is provided with wing, and this trailing edge is provided with wing flap and aileron; The described leading edge of a wing is provided with ice removal; Described front fuselage and tail end start mounting bracket and rear engine mounting bracket before being respectively arranged with, start before this mounting bracket and rear engine mounting bracket are separately installed with front-mounted engine and rear engine, this front-mounted engine and rear engine are separately installed with pulling force propeller and thrust propeller; Described wing is provided with H-shaped tailplane, this H-shaped tailplane is made up of two parallel shoes and tailplane main body, tailplane trailing edge arranges elevator, and the both sides of this tailplane main body are correspondingly arranged on vertical tail, this vertical tail trailing edge setting direction rudder; Equipment compartment and load cabin it is provided with from front to back in described fuselage; Automatic pilot, airborne data radio station, power supply unit are installed in described equipment compartment; Installed load members in described load cabin.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620002463.6U CN205293099U (en) | 2016-01-05 | 2016-01-05 | Use coaxial tandem twin engine's fixed wing uavs |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620002463.6U CN205293099U (en) | 2016-01-05 | 2016-01-05 | Use coaxial tandem twin engine's fixed wing uavs |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205293099U true CN205293099U (en) | 2016-06-08 |
Family
ID=56484825
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620002463.6U Expired - Fee Related CN205293099U (en) | 2016-01-05 | 2016-01-05 | Use coaxial tandem twin engine's fixed wing uavs |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205293099U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107891985A (en) * | 2017-12-15 | 2018-04-10 | 青岛港湾职业技术学院 | A kind of switchable type tilting rotor unmanned plane |
| CN109896022A (en) * | 2019-03-28 | 2019-06-18 | 河南机电职业学院 | A kind of light-duty unmanned plane high-pressure pneumatic accelerated take-off device |
| CN110228581A (en) * | 2019-06-06 | 2019-09-13 | 天峋创新（北京）科技有限公司 | A kind of high speed Bi-Tail-Boom Layout unmanned plane |
| CN112124589A (en) * | 2020-10-14 | 2020-12-25 | 李勇霖 | Two rotor vector unmanned aerial vehicle that verts |
-
2016
- 2016-01-05 CN CN201620002463.6U patent/CN205293099U/en not_active Expired - Fee Related
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107891985A (en) * | 2017-12-15 | 2018-04-10 | 青岛港湾职业技术学院 | A kind of switchable type tilting rotor unmanned plane |
| CN109896022A (en) * | 2019-03-28 | 2019-06-18 | 河南机电职业学院 | A kind of light-duty unmanned plane high-pressure pneumatic accelerated take-off device |
| CN109896022B (en) * | 2019-03-28 | 2023-12-08 | 河南机电职业学院 | High-pressure pneumatic booster take-off device of light unmanned aerial vehicle |
| CN110228581A (en) * | 2019-06-06 | 2019-09-13 | 天峋创新（北京）科技有限公司 | A kind of high speed Bi-Tail-Boom Layout unmanned plane |
| CN112124589A (en) * | 2020-10-14 | 2020-12-25 | 李勇霖 | Two rotor vector unmanned aerial vehicle that verts |
| CN112124589B (en) * | 2020-10-14 | 2022-01-25 | 李勇霖 | Two rotor vector unmanned aerial vehicle that verts |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102806990B (en) | Portable type mapping unmanned plane | |
| US10124890B2 (en) | Modular nacelles to provide vertical takeoff and landing (VTOL) capabilities to fixed wing aerial vehicles, and associated systems and methods | |
| US20160167780A1 (en) | Convertiplane with new aerodynamic and technical solutions which make theaircraft safe and usable | |
| CN205293099U (en) | Use coaxial tandem twin engine's fixed wing uavs | |
| CN104364154A (en) | Aircraft, preferably unmanned | |
| CN102520727B (en) | Reconnaissance system with unmanned plane | |
| CA2870808C (en) | An aerospace plane system | |
| US20180222583A1 (en) | UAV Booster Aircraft for Takeoff and Climb Assist | |
| CN205168905U (en) | Stationary vane aerial survey unmanned aerial vehicle | |
| CN202046437U (en) | Small-sized electric tailless type unmanned plane for remote sensing and monitoring of emergency | |
| CN105905295A (en) | Vertical take-off and landing fixed wing aircraft | |
| CN202935570U (en) | Portable mapping unmanned aerial plane | |
| CN205293058U (en) | Conveniently carry on fixed wing uavs of jumbo size loading device | |
| CN103350624A (en) | Propelling type flying car with spiral wings | |
| CN202453736U (en) | Unmanned aerial vehicle reconnaissance system | |
| RU2370414C1 (en) | Multipurpose helicopter airplane with remote control | |
| CN205615699U (en) | General type fixed wing uavs | |
| RU83483U1 (en) | UNMANNED AERIAL VEHICLE | |
| Siddique et al. | Development of an Experimental Unmanned-Aerial System (UAS) to Study the Effects of Adverse Weathers on its Flight Performance | |
| RU2710317C1 (en) | Air missile system with an unmanned percussive aircraft helicopter | |
| CN101734376A (en) | Small multipurpose unmanned aerial vehicle capable of realizing modularized load and parachute recovery | |
| Gibson et al. | Development and flight test of the X-43A-LS hypersonic configuration UAV | |
| CN108033025B (en) | Thrust control system of aircraft engine | |
| Harasani | Design, build and test an unmanned air vehicle | |
| RU2380286C1 (en) | Pilotless aircraft |
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: 20160608 Termination date: 20200105 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |