CN202935570U - Portable mapping unmanned aerial plane - Google Patents
Portable mapping unmanned aerial plane Download PDFInfo
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- CN202935570U CN202935570U CN 201220367609 CN201220367609U CN202935570U CN 202935570 U CN202935570 U CN 202935570U CN 201220367609 CN201220367609 CN 201220367609 CN 201220367609 U CN201220367609 U CN 201220367609U CN 202935570 U CN202935570 U CN 202935570U
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Abstract
The utility model relates to a portable mapping unmanned plane which executes a mapping task by an unmanned plane instead of a manned plane and can form visible image data and video data. The structure of the unmanned plane is as follows: a plane body employs a fixed wing H-shaped tail pneumatic layout. The plane body comprises a body, a wing, a horizontal tail wing, a vertical tail wing and a tail boom which are connected with one another through inserted pins; the plane body is a lifting body plane body, and the interior of the plane body is sequentially divided into four cabins, namely an equipment cabin, a loading cabin, a parachute cabin and a power cabin from front to back according to functions; an airborne data transmission radio station and a loading part are respectively arranged in the equipment cabin and the loading cabin; an engine and a propeller are arranged at the back end of the power cabin, and an autopilot is arranged on the upper part of an oil tank in the power cabin; and a flap, an auxiliary wing, and steering engines of an elevating rudder and a yaw rudder are arranged in the tail boom. The unmanned plane is convenient to carry, easy to maintain and use, low in cost, reusable and the like, has great advantages in the aspect of emergency rescues, has broad market demands and is easy to popularize and to apply.
Description
Technical field
The utility model relates to a kind of unmanned plane, relates in particular to a kind of easy to usely, replaces having people's aircraft to carry out the portable type mapping unmanned plane of mapping task by unmanned plane.
Background technology
Unmanned plane is the not manned craft of controlling by radio robot or airborne computer stored program controlled.Unmanned plane not only can be completed the task that manned aircraft is carried out, and more is applicable to the task that people's aircraft should not be carried out.
Current most photogrammetric unit all is in and " measurement " is arranged and without the state of " photography ", zonule high precision landform figure surveys and draws, and depends on the manual work mode in full field always.As replenishing of traditional aerospace remote sensing, the unmanned plane surveying and mapping technology becomes the new study hotspot in remote sensing field.Present unmanned aerial vehicle is very large for different mission requirementses and usage condition difference, and mostly carries and use inconvenience, and cost is higher.
Summary of the invention
The utility model provides a kind of portable type mapping unmanned plane for above-mentioned problems of the prior art, solved to exist in prior art to use and limited to, carry and awkward problem, and the utility model cost is lower.
To achieve these goals, the technical solution of the utility model is as follows:
Body employing fixed-wing H tail formula aerodynamic arrangement, body comprises fuselage, wing, tailplane, vertical tail and shoe, all adopts latch to connect between fuselage, wing, tailplane, vertical tail and shoe; Fuselage is the lifting body fuselage, and fuselage interior is divided into four cabin sections by function, is followed successively by from front to back equipment compartment, load cabin, umbrella cabin, piggyback pod; On-board data transmission radio station and payload portion are arranged on respectively in equipment compartment and load cabin; Driving engine and screw propeller are arranged on the piggyback pod rear end, and autopilot is arranged on the top of fuel tank in piggyback pod; The steering wheel of wing flap, aileron, elevating rudder and yaw rudder all is built in shoe.
Described driving engine is the gasoline type piston engine.
Described screw propeller is wooden fixed pitch propeller.
Described fuel tank is flexible oil tank.
Described payload portion adopts pick up camera or camera, and load camera lens installation site is for when aircraft carries out normal flight, and the load camera lens remains attitude perpendicular to the ground.
Described payload portion is placed in damping die cavity in the fuselage load cabin.
Described payload portion is fixed on three axle The Cloud Terraces of configuration in the fuselage load cabin.
Described fuselage is provided with tricycle landing gear, and rear alighting gear is arranged on the fuselage lower surface, below piggyback pod.
Described autopilot possesses automatic Pilot and reaches from master control unmanned plane function, adopt the PID control method, carry out data solver by the Kalman filtering of revising with GPS, the remote information that transmits by data link also extracts correct control signal, receives to the data of acceleration/accel, 3 in the scouting platform flight course of gyro data acquisition process, baroceptor and navigational aid collection 3; In the unmanned plane take-off process, take off from the master control unmanned aerial vehicle ejecting, process according to the route task of planning in advance in flight course, send instruction to actuating unit, control actuating unit and carry out corresponding task, and can carry out in real time according to the actual task needs change and the planning of flight path route.
Described aileron makes aircraft keep the fixing gradient by inverse amplification factor output rudder amount.
The utility model has the advantages of as follows:
The utility model is a small-sized portable type mapping unmanned plane for the demand development of the aspects such as the condition of a disaster assessment, emergency monitoring, geographical mapping, environmental assessment.Have the characteristics such as easy to carry, that maintenance is used simply, cost is low, reusable, have stronger advantage aspect emergency repair, the wide market demand is arranged, be easy to apply.
Description of drawings
Below, by reference to the accompanying drawings, the utility model is elaborated.
Fig. 1 is the airborne layout structure schematic diagram of the utility model.
Fig. 2 is the airborne layout plan structure of the utility model schematic diagram.
In figure, 1, nose-gear; 2, equipment compartment; 3, payload portion; 4, power supply; 5, fuel tank; 6, rear alighting gear; 7, driving engine; 8, radio antenna; 9, autopilot; 10, umbrella cabin; 11, on-board data transmission radio station; 12, switch; 13, pitot; 14, piggyback pod; 15, load cabin; 16, fuselage, 17, wing; 18, tailplane; 19, vertical tail; 20, shoe; 21, wing flap; 22, aileron; 23, elevating rudder; 24, yaw rudder.
The specific embodiment
Embodiment
As shown in Fig. 1-2, body employing fixed-wing H tail formula aerodynamic arrangement, body comprises fuselage 16, wing 17, tailplane 18, vertical tail 19 and shoe 20, all adopts latch to connect between fuselage 16, wing 17, tailplane 18, vertical tail 19 and shoe 20; Fuselage 16 is the lifting body fuselage, and fuselage 16 inside are divided into four cabin sections by function, is followed successively by from front to back equipment compartment 2, load cabin 15, umbrella cabin 10, piggyback pod 14; Pitot 13 is arranged on equipment compartment 2 front ends; Switch 12 and on-board data transmission radio station 11 are arranged in equipment compartment 2; Payload portion 3 is arranged in load cabin 15; Power supply 4 is arranged on fuselage interior, 10 belows, umbrella cabin; Fuselage is provided with tricycle landing gear, and rear alighting gear 6 is arranged on the fuselage lower surface, piggyback pod 14 belows.Gasoline type piston engine 7 and wooden fixed pitch propeller are arranged on piggyback pod 14 rear ends, and flexible oil tank 5 is arranged in piggyback pod 14; Autopilot 9 is arranged on the top of the interior flexible oil tank 5 of piggyback pod 14; The steering wheel of wing flap 21, aileron 22, elevating rudder 23 and yaw rudder 24 all is built in shoe 20.
Described gasoline type piston engine 7, wooden fixed pitch propeller and flexible oil tank 5 are power part of the present utility model, gasoline type piston engine 7 and wooden fixed pitch propeller are arranged on piggyback pod 14 rear ends, wooden fixed pitch propeller is the thrust slurry, and the gasoline type piston engine drives wooden fixed pitch propeller and provides flying platform power for unmanned plane; Fuel tank is flexible oil tank, is arranged in piggyback pod, for driving engine provides enough fuel oils.Power system adopts GF55 gasoline type piston engine, and its cost is low, superior performance, stable, reliable.The piston-engined thrust of gasoline type is 5.6ps, the efficient of the two wooden fixed pitch propellers of leaf can reach more than 75%, the gasoline type piston engine can provide for unmanned plane the thrust of 4ps at least by driving wooden fixed pitch propeller, under enough like this thrust, unmanned plane namely can be slided race again can catapult-assisted take-off, this compares with the single catapult-assisted take-off mode of in the past thrust paddle unmanned plane, and performance is more superior; And the unmanned plane of high thrust, its climbing performance is more superior, can enter fast cruising condition, the fuel tank fuel load surpasses 5kg, can guarantee that the aerial continuation of the journey of unmanned plane reaches 3h at least, and this gasoline type piston engine quality is less, can not distribute for the barycenter of whole Unmanned Aircraft Systems (UAS) and cause larger impact.Different from unmanned plane power system in the past, the power system of the utility model unmanned plane is simple to operate, and non-native system technical personnel just can skillfully use this power system through simple training; And easy to maintenance, quick, the front setup time of flying is shorter, can enter fast and carry out the aerial mission state, meets very much the development tendency of current unmanned plane industry.
Described remote controller and autopilot 9 are Navigation Control section, remote controller is used for flight course closely to guarantee adjustment and the emergency situations intervention of attitude of flight vehicle, especially take off and the landing stage, in use remote controller can carry out free switching between automatic Pilot state and remote manual control state.Autopilot 9 is arranged in piggyback pod 14, flexible oil tank 5 tops, possessing automatic Pilot reaches from master control unmanned plane function, adopt the PID control method, carry out data solver by Kalman (Kalman) filtering of revising with GPS, the remote information that transmits by data link also extracts correct control signal, the GPS location information in the scouting platform flight course that gathers to acceleration/accel, 3 acquisition process to gyro data, baroceptor and navigational aid 3, speed, highly, the reception of the data such as course, loading device state.Control program adopts the angle of attack to control the height of aircraft, and elevating rudder controlled the angle of attack of aircraft, the speed of Throttle Opening Control aircraft.Laterally control and adopt elevon combination mode, after deviation appearred in the way point of the flight way point of aircraft and setting, aileron made aircraft keep the fixing gradient by inverse amplification factor output rudder amount, the height of elevating rudder maintenance aircraft.in the unmanned plane take-off process, autopilot takes off from the master control unmanned aerial vehicle ejecting, process according to the route task of planning in advance in flight course, send instruction to actuating unit, control actuating unit and carry out corresponding task, and can carry out in real time according to the actual task needs change and the planning of flight path route, the operator can carry out by trajectory planning and route adjust the control execution of various tasks, can carry out autonomous flight by the contemplated route that mission requirements arranges in advance, by the work of autonomous control load equipment, needs are surveyed and drawn the zone and carry out picture or image data collecting work, simultaneously can be by pitching, lift-over and the three axle The Cloud Terraces of going off course guarantee the acquisition quality of load data.Ground station can show electronic chart, flight path, flight parameter, the aspect course parameter of flight range in the unmanned plane during flying process, all parameters and navigation data can pass down and record in real time in-flight, it is regional to predetermined landing by the contemplated route autonomous flight after task is completed, and automatically control the unmanned plane stable landing that releases a parachute, also can and use needs by remote controller, airborne autopilot to be switched back remote state according to actual place environment in addition, the visual control aircraft carries out remote control and slides landing.
Described on-board data transmission radio station 11 is installed in the fuselage equipment compartment, and the radio antenna 8 of on-board data transmission radio station 11 adopts columnar antenna.
Described payload portion 3 can adopt pick up camera or camera, payload portion can be placed on carries out fixing in the cabin and damping in the Special shock-absorbing die cavity in the load cabin, also can be in the load cabin configuration three axle The Cloud Terraces, fixing effective loading device also carries out the correction of real-time course and damping effect.Load camera lens installation site is for when aircraft carries out normal flight, and the load camera lens remains attitude perpendicular to the ground.For mapping coverage, the customized type course line can be set, make unmanned plane take photo by plane accordingly or navigate and take the photograph according to predetermined course line.
Recovery can be adopted automatic deployment and downhill race dual mode, adopts the way point of autopilot to arrange in advance, can be set as to arrive the set point coordinate and namely release a parachute and close simultaneously electrical motor.The utility model can adopt sled downhill race and alighting gear downhill race dual mode to carry out downhill race.Sled is with carbon fiber, and glass fibre is main material and adds a certain amount of Kevlar to process to have higher intensity, toughness preferably, lighter weight.Carry out bumper and absorbing shock by sled itself during the sled landing, complete the aircraft grounding by the friction on sled and ground.The utility model adopts tricycle landing gear 1 to carry out the alighting gear landing, and alighting gear is processed take carbon fiber as main material, carries out bumper and absorbing shock by alighting gear and three rubber wheels during the alighting gear landing, completes the aircraft grounding by skidding.
The utility model runs or launch dual mode by cunning makes unmanned plane keep the flight initial condition, and unmanned plane is mainly manually controlled by ground system when emission, switches to automatic navigation mode after unmanned plane climbs safe altitude.Complete the autonomous navigation control in the prefabricated task of unmanned plane course line by navigation control system, can carry out the task action of spiraling after unmanned plane arrives assigned address.The utility model can also be realized independently taking off, and namely unmanned plane takes off and only depends on pneumatic launching cradle to launch, and does not need manual intervention can realize that just unmanned plane takes off.The utility model can be completed the application of different field by carrying different capacity weight equipment, carries out corresponding task.When the recovery flight device, first by earth station system, unmanned plane is switched and turn round and stretch out the hand moving state, the then downhill race of visual control unmanned plane or parachuting.
The utility model total technical index is as shown in table 1.
Table 1 total technical index
| Sequence number | Title | Technical index | Remarks |
| 1 | Maximum take-off weight | 15kg | ? |
| 2 | Flying speed | 15m/s～40m/s | Cruising speed 30m/s |
| 3 | The span | 2.5m | ? |
| 4 | Fuselage is long | 1m | ? |
| 5 | Control Radius | ≥20km | ? |
| 6 | Cruise duration | ≥2h | ? |
| 7 | Image resolution ratio | ≥3500×2300 | ? |
| 8 | Power | Piston type gasoline engine | ? |
| 9 | The mode of taking off | Slide and run, launch | ? |
| 10 | Way of recycling | Parachuting, downhill race | ? |
Claims (8)
1. portable type mapping unmanned plane is characterized in that body adopts fixed-wing H tail formula aerodynamic arrangement, and body comprises fuselage, wing, tailplane, vertical tail and shoe, all adopts latch to connect between fuselage, wing, tailplane, vertical tail and shoe; Fuselage is the lifting body fuselage, and fuselage interior is divided into four cabin sections by function, is followed successively by from front to back equipment compartment, load cabin, umbrella cabin, piggyback pod; On-board data transmission radio station and payload portion are arranged on respectively in equipment compartment and load cabin; Driving engine and screw propeller are arranged on the piggyback pod rear end, and autopilot is arranged on the top of fuel tank in piggyback pod; The steering wheel of wing flap, aileron, elevating rudder and yaw rudder all is built in shoe.
2. portable type mapping unmanned plane according to claim 1, is characterized in that described driving engine is the gasoline type piston engine.
3. portable type mapping unmanned plane according to claim 1, is characterized in that described screw propeller is wooden fixed pitch propeller.
4. portable type mapping unmanned plane according to claim 1, is characterized in that described fuel tank is flexible oil tank.
5. portable type according to claim 1 mapping unmanned plane, is characterized in that described payload portion adopts pick up camera or camera, and load camera lens installation site is for when aircraft carries out normal flight, and the load camera lens remains attitude perpendicular to the ground.
6. portable type mapping unmanned plane according to claim 5, is characterized in that described payload portion is placed in the interior damping die cavity of fuselage.
7. portable type mapping unmanned plane according to claim 5, is characterized in that described payload portion is fixed on three axle The Cloud Terraces of configuration in fuselage compartment.
8. portable type mapping unmanned plane according to claim 1, is characterized in that described fuselage is provided with tricycle landing gear, and rear alighting gear is arranged on the fuselage lower surface, below piggyback pod.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220367609 CN202935570U (en) | 2012-07-27 | 2012-07-27 | Portable mapping unmanned aerial plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220367609 CN202935570U (en) | 2012-07-27 | 2012-07-27 | Portable mapping unmanned aerial plane |
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| CN202935570U true CN202935570U (en) | 2013-05-15 |
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| CN 201220367609 Expired - Fee Related CN202935570U (en) | 2012-07-27 | 2012-07-27 | Portable mapping unmanned aerial plane |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102806990A (en) * | 2012-07-27 | 2012-12-05 | 沈阳航天新光集团有限公司 | Portable mapping unmanned aerial plane |
| CN105373132A (en) * | 2015-11-26 | 2016-03-02 | 北京浩恒征途航空科技有限公司 | Low-altitude remote sensing system based on automatic cruise unmanned aerial vehicle and remote sensing method thereof |
| CN106114813A (en) * | 2016-08-31 | 2016-11-16 | 河南翱翔航空科技有限公司 | Unmanned plane body skeleton |
| CN106774431A (en) * | 2016-12-30 | 2017-05-31 | 深圳市九天创新科技有限责任公司 | One kind mapping unmanned plane route planning method and device |
| CN108725743A (en) * | 2018-06-14 | 2018-11-02 | 中国水利水电科学研究院 | One kind formula hand of raising one's head throws small-sized fixed-wing unmanned aerial vehicle body |
-
2012
- 2012-07-27 CN CN 201220367609 patent/CN202935570U/en not_active Expired - Fee Related
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102806990A (en) * | 2012-07-27 | 2012-12-05 | 沈阳航天新光集团有限公司 | Portable mapping unmanned aerial plane |
| CN102806990B (en) * | 2012-07-27 | 2016-01-20 | 海鹰航空通用装备有限责任公司 | Portable type mapping unmanned plane |
| CN105373132A (en) * | 2015-11-26 | 2016-03-02 | 北京浩恒征途航空科技有限公司 | Low-altitude remote sensing system based on automatic cruise unmanned aerial vehicle and remote sensing method thereof |
| CN106114813A (en) * | 2016-08-31 | 2016-11-16 | 河南翱翔航空科技有限公司 | Unmanned plane body skeleton |
| CN106774431A (en) * | 2016-12-30 | 2017-05-31 | 深圳市九天创新科技有限责任公司 | One kind mapping unmanned plane route planning method and device |
| CN106774431B (en) * | 2016-12-30 | 2020-01-17 | 深圳市九天创新科技有限责任公司 | Method and device for planning air route of surveying and mapping unmanned aerial vehicle |
| CN108725743A (en) * | 2018-06-14 | 2018-11-02 | 中国水利水电科学研究院 | One kind formula hand of raising one's head throws small-sized fixed-wing unmanned aerial vehicle body |
| CN108725743B (en) * | 2018-06-14 | 2023-07-14 | 中国水利水电科学研究院 | Unmanned aerial vehicle fuselage with head-leaning type hand-thrown small fixed wings |
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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: HIWING AVIATION GENERAL EQUIPMENT CO., LTD. Free format text: FORMER OWNER: SHENYANG AEROSPACE XINGUANG GROUP CO., LTD. Effective date: 20150318 |
|
| C41 | Transfer of patent application or patent right or utility model | ||
| COR | Change of bibliographic data |
Free format text: CORRECT: ADDRESS; FROM: 110043 SHENYANG, LIAONING PROVINCE TO: 100070 FENGTAI, BEIJING |
|
| TR01 | Transfer of patent right |
Effective date of registration: 20150318 Address after: Beijing Aerospace Haiying technology building 100070 Fengtai District Science City Hospital No. 1 layer 8 Seahawks Patentee after: Sea hawk aviation general equipment limited liability company Address before: 110043 Liaoning Province, Shenyang City District East Street No. 1 Patentee before: Shenyang Aerospace Xinguang Group Co., Ltd. |
|
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20130515 Termination date: 20160727 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |