CN202935570U - Portable mapping unmanned aerial plane - Google Patents

Portable mapping unmanned aerial plane Download PDF

Info

Publication number
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
Authority
CN
China
Prior art keywords
unmanned plane
fuselage
cabin
wing
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
Application number
CN 201220367609
Other languages
Chinese (zh)
Inventor
刘铁军
关雅雯
宋晓明
张超
史锋
庞小娟
郭伟
董泽辉
齐欣
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Sea hawk aviation general equipment limited liability company
Original Assignee
Shenyang Aerospace Xinguang Group Co Ltd
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Shenyang Aerospace Xinguang Group Co Ltd filed Critical Shenyang Aerospace Xinguang Group Co Ltd
Priority to CN 201220367609 priority Critical patent/CN202935570U/en
Application granted granted Critical
Publication of CN202935570U publication Critical patent/CN202935570U/en
Expired - Fee Related legal-status Critical Current
Anticipated expiration legal-status Critical

Links

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

Portable type mapping unmanned plane
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.
Elevating rudder 23 deflecting facets are controlled the pitch attitude of aircraft, and the roll attitude of aircraft is controlled in the aileron 22 reverse deflections of rudder face.The both direction rudder is controlled the course of aircraft.Two wing flaps provide booster action for flight, improve lift when taking off and land.Design flying speed 15m/s~40m/s, design flying height 100m~5000m.Wing 17 aerofoil profiles are; Clark Y 12%; Tailplane 18 and vertical tail 19 aerofoil profiles are NACA 0008, and center of gravity is positioned at 85mm after the leading edge of a wing.Compare with existing unmanned plane, the utility model carries out dismounting by fuselage 16, wing 17, tailplane 18, vertical tail 19 and shoe 20, the steering wheel of wing flap 21, aileron 22, elevating rudder 23 and yaw rudder 24 all is built in shoe 20, all adopt latch to connect between fuselage 16, wing 17, tailplane 18, vertical tail 19 and shoe 20, drop to the screw connection minimum, make to the utlity model has easy accessibility advantage simple to operate.Simultaneously, the utility model can require lowly to controlling workmanship, is more suitable for the layman and uses.
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.
CN 201220367609 2012-07-27 2012-07-27 Portable mapping unmanned aerial plane Expired - Fee Related CN202935570U (en)

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

Publications (1)

Publication Number Publication Date
CN202935570U true CN202935570U (en) 2013-05-15

Family

ID=48319824

Family Applications (1)

Application Number Title Priority Date Filing Date
CN 201220367609 Expired - Fee Related CN202935570U (en) 2012-07-27 2012-07-27 Portable mapping unmanned aerial plane

Country Status (1)

Country Link
CN (1) CN202935570U (en)

Cited By (4)

* Cited by examiner, † Cited by third party
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

Cited By (6)

* Cited by examiner, † Cited by third party
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

Similar Documents

Publication Publication Date Title
CN102806990B (en) Portable type mapping unmanned plane
EP3033272B1 (en) Convertiplane with new aerodynamic and technical solutions which make the aircraft safe and usable
CN103051373B (en) Self-rotor unmanned aerial vehicle-based air emergency communication system
CN104364154A (en) Aircraft, preferably unmanned
CN102520727B (en) Reconnaissance system with unmanned plane
Risch et al. X-48B flight test progress overview
US9849983B2 (en) Aerodynamically shaped, active towed body
CN200939356Y (en) Small remote monitoring pilotless plane
CN202935570U (en) Portable mapping unmanned aerial plane
EP3489139B1 (en) Systems and methods for powering an electric aerial vehicle
CN202046437U (en) Small-sized electric tailless type unmanned plane for remote sensing and monitoring of emergency
CN205293058U (en) Conveniently carry on fixed wing uavs of jumbo size loading device
US20180222583A1 (en) UAV Booster Aircraft for Takeoff and Climb Assist
CN205168905U (en) Stationary vane aerial survey unmanned aerial vehicle
CN202453736U (en) Unmanned aerial vehicle reconnaissance system
CN205615699U (en) General type fixed wing uavs
CN204021249U (en) The soft wing unmanned plane of high-mobility, multipurpose, wheeled vehicle
CN203528810U (en) Unmanned plane
CN107539453A (en) A kind of low-latitude flying operation unmanned plane and its control system and application
Pisanich et al. Fielding an amphibious UAV: development, results, and lessons learned
CN205293099U (en) Use coaxial tandem twin engine's fixed wing uavs
CN208134595U (en) A kind of 20 feather weight long endurance unmanned aircraft of load
Martı́nez-Val et al. Preliminary design of a low speed, long endurance remote piloted vehicles (RPV) for civil applications
CN204979212U (en) Remote sensing fixed wing uavs
Harasani Design, build and test an unmanned air vehicle

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

COR Change of bibliographic data

Free format text: CORRECT: ADDRESS; FROM: 110043 SHENYANG, LIAONING PROVINCE TO: 100070 FENGTAI, BEIJING

C41 Transfer of patent application or patent right or utility model
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
CF01 Termination of patent right due to non-payment of annual fee

Granted publication date: 20130515

Termination date: 20160727