CN202453736U - Unmanned aerial vehicle reconnaissance system - Google Patents
Unmanned aerial vehicle reconnaissance system Download PDFInfo
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- CN202453736U CN202453736U CN2011205701705U CN201120570170U CN202453736U CN 202453736 U CN202453736 U CN 202453736U CN 2011205701705 U CN2011205701705 U CN 2011205701705U CN 201120570170 U CN201120570170 U CN 201120570170U CN 202453736 U CN202453736 U CN 202453736U
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- unmanned plane
- aerial vehicle
- unmanned aerial
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- reconnaissance system
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Abstract
The utility model relates to an unmanned aerial vehicle reconnaissance system for performing high-risk high-concealment reconnaissance mission by replacing a manned aerial vehicle by an unmanned aerial vehicle. The unmanned aerial vehicle reconnaissance system is mainly used for performing video reconnaissance mission aimed at forefront ground targets and providing real-time video data to ground-based monitoring station. The unmanned aerial vehicle reconnaissance system comprises a flight platform system and a ground-based station system. The unmanned aerial vehicle reconnaissance system is a small electric unmanned aerial vehicle aimed at meeting the requirement of disaster assessment, emergency monitoring, emergency reconnaissance and counter-terrorism. The unmanned aerial vehicle reconnaissance system has the advantages of convenience in carrying, simple maintenance and usage, low cost and reusing function, has a strong advantage in the field of emergency rescue, has a vast market demand, and is easy to popularize and apply.
Description
Technical field
The utility model relates to a kind of reconnaissance system, relates in particular to a kind of unmanned plane reconnaissance system through the reconnaissance mission that unmanned plane replaces that people's aircraft execution high-risk is arranged, disguise is strong.
Background technology
Unmanned plane is the not manned vehicle of controlling through radio robot or airborne computer stored program controlled.Unmanned plane not only can be accomplished the task that manned aircraft is carried out, and more is applicable to the task that people's aircraft should not be carried out.
Unmanned plane is mainly used in military field at present, and is still immature for fields such as emergency repairs, has certain use limitation, and present unmanned aerial vehicle requires for various tasks and the service condition difference is very big, and mostly carries inconvenience, and cost is higher.
Summary of the invention
The utility model provides a kind of unmanned plane reconnaissance system to the problem that exists in the above-mentioned prior art, solved to have the problem of using limitation, carrying inconvenience in the prior art, and the utility model cost is lower.
To achieve these goals, the technical scheme of the utility model is following:
Be provided with the flying platform system, guarantee the normal flight of aircraft; The flying platform system comprises structural portion, power part, Navigation Control portion, data link portion, payload portion and electrical part; Structural portion links to each other with power part, and power part links to each other with Navigation Control portion, and Navigation Control portion links to each other with electrical part, and electrical part links to each other with payload portion, and payload portion links to each other with data link portion, and data link portion links to each other with structural portion; Be provided with earth station system, realize unmanned plane is set the program control navigation in course line, accomplish the accurate control in course line; Earth station system comprises ground observing and controlling portion and ground safeguard portion, and ground observing and controlling portion links to each other with ground safeguard portion.
Described structural portion is that body adopts flying wing type aerodynamic arrangement, lifting body fuselage, control rudder face employing elevon.
Described power part comprises brushless electric machine, brushless speed regulator, the collapsible screw propeller of carbon fibre and electrokinetic cell, and brushless electric machine and brushless speed regulator are arranged on the inside of body, and electrokinetic cell is arranged on the body.
Described Navigation Control portion comprises telepilot and robot pilot; Telepilot is used for launching and adjustment and the intervention of removal process to attitude of flight vehicle; Aircraft climbs after the safe altitude; Telepilot switches to automatic driving condition with airborne robot pilot, when the recovery flight device, by telepilot airborne robot pilot is switched back remote state earlier.
Described data link portion comprises on-board data transmission radio station and land station data transmission radio station, and the on-board data transmission radio station is installed in the vertical tail.
Described payload portion adopts board-like video camera, and the camera installation site is for when aircraft carries out orbit with 60 ° pitch angle, and camera is aimed at a certain target in ground all the time.
Described ground observing and controlling portion is used to receive and transmit the related data of airborne data transmission radio station and payload portion, and the data that receive are handled and manifested.
Described ground safeguard portion comprises emission and recovery and land station's power supply of unmanned plane, for the safe take-off of aircraft provides safeguard with making a return voyage.
The utility model has the advantages of as follows:
The utility model is a small-sized electric unmanned plane to the demand development of aspects such as the condition of a disaster assessment, emergency monitoring, urgent scouting, anti-terrorism.Have characteristics such as easy to carry, that maintenance is used simply, cost is low, reusable, aspect emergency repair, have strong advantage, the vast market demand is arranged, be easy to apply.
Description of drawings
Below, in conjunction with accompanying drawing, the utility model is elaborated.
Fig. 1 is the structural principle schematic block diagram of the utility model.
Fig. 2 is the airborne schematic layout pattern of the utility model.
Fig. 3 is the utility model work synoptic diagram.
Among the figure, 1, fuselage, 2, wing, 3, figure passes antenna, 4, data transmission antenna, 5, robot pilot, 6, pitot, 7, the image radio station, 8, electrokinetic cell, 9, camera, 10, the on-board data transmission radio station.
Embodiment
Embodiment
Shown in Fig. 1-3, be provided with the flying platform system, guarantee the normal flight of aircraft; The flying platform system comprises structural portion, power part, Navigation Control portion, data link portion, payload portion and electrical part; Structural portion links to each other with power part, and power part links to each other with Navigation Control portion, and Navigation Control portion links to each other with electrical part, and electrical part links to each other with payload portion, and payload portion links to each other with data link portion, and data link portion links to each other with structural portion; Be provided with earth station system, realize unmanned plane is set the program control navigation in course line, accomplish the accurate control in course line; Earth station system comprises ground observing and controlling portion and ground safeguard portion, and ground observing and controlling portion links to each other with ground safeguard portion.
Described structural portion does, body adopts flying wing type aerodynamic arrangement, lifting body fuselage 1, and rectangular wing 2, the upper counterangle is 1.5 °.The control rudder face adopts elevon, two rudder face pitch attitudes of deflection control aircraft in the same way, the lateral attitude of reverse deflection control aircraft.Design flying speed 70km/h～90km/h, design flying height 100m～300m, Reynolds number about 200,000.The main wing aerofoil profile is EMX-07, and center of gravity is positioned at 60mm behind the leading edge of a wing.
Described power part comprises brushless electric machine, brushless speed regulator, the collapsible screw propeller of carbon fibre and electrokinetic cell 8, and brushless electric machine and brushless speed regulator are arranged on the inside of body, and electrokinetic cell 8 is arranged on the body.The efficient of brushless electric machine surpasses 85%, can not disturb because of mechanical commutator produces electric spark, also need not to change brush, has reduced maintenance difficulties, has improved reliability.The about 50A of peak point current during brushless electric machine work, in order to guarantee when fortuitous event occurring, not damage electron speed regulator, having selected maximum current for use is the brushless speed regulator of Czech's product ADVANCE 77PLUS electronics of 75A.Screw propeller adopts the collapsible screw propeller of 14 * 9.5 carbon fibres.Two blades lean on action of centrifugal force to open automatically during brushless electric machine work, two blade automatic drawing backs when the motor parking is slided.Adopt collapsible screw propeller can reduce the resistance that stops when gliding, the damage probability of screw propeller when reducing downhill race is to reduce use cost.
LipoBattery single-unit capacity is 8000 mAh, and single-unit voltage is 3.7V, adopts the method for attachment of 6 joint series connection.The electric battery total volume is 8000 mAh, and saturation voltage is 25.2V, and general assembly (TW) is 1.1kg, and be 60min cruising time.
Described Navigation Control portion comprises telepilot and robot pilot; Telepilot is used for launching and adjustment and the intervention of removal process to attitude of flight vehicle; Aircraft mainly by remote control equipment control, can switch to automatic driving condition with airborne robot pilot 5 by telepilot after aircraft climbs safe altitude when emission.When the recovery flight device, by telepilot airborne robot pilot is switched back remote state earlier, visual control aircraft landing then.After the debugging that completion is taken off automatically and automatic deployment reclaims, the emission of unmanned plane and recovery will break away from remote control equipment fully, and ground controlling personnel hand-thrown mode is launched unmanned plane and got final product.Controlling schemes adopts the height of angle of attack controlling aircraft, the angle of attack of elevating rudder controlling aircraft, the speed of Throttle Opening Control aircraft.Laterally elevon Combination Control mode is adopted in control, and after deviation appearred in the way point of the flight way point of aircraft and setting, aileron made aircraft keep the fixing gradient by control rate output rudder amount, the height of elevating rudder maintenance aircraft.
Described data link portion comprises on-board data transmission radio station and land station data transmission radio station, and on-board data transmission radio station 10 is installed in the vertical tail.The data transmission antenna 4 in data transmission radio station adopts Patcho antenna or column antenna; Land station can adopt in the data transmission radio station the high antenna of gain.
Described payload portion adopts board-like video camera, and camera 9 installation sites are for when aircraft carries out orbit with 60 ° pitch angle, and camera is aimed at a certain target in ground all the time.Way point for scouting point of interest can be set the standard course line, unmanned plane is arrived get into grade behind the predetermined point to spiral, and target is carried out 360 ° of orientation observe.
Image radio station 7 is arranged on the wing 2, and figure passes antenna 3 and is arranged on the fuselage 1, and pitot 6 is arranged on the wing 2.
Described ground observing and controlling portion is used to receive and transmit the related data of airborne data transmission radio station and payload portion, and the data that receive are handled and manifested.
Described ground safeguard portion comprises emission and recovery and land station's power supply of unmanned plane, for the safe take-off of aircraft provides safeguard with making a return voyage.
Radiation pattern adopts the hand-thrown emission or launches.In the moment of hand-thrown emission; According to formula
; Can draw when general assembly (TW) is 4.7kg; When the emission angle of attack is the 5 degree left and right sides; The lift coefficient of aircraft
, emission rate V=4.8m/s.Be easy to reach this requirement for the general operation personnel.
Accomplish and to carry out the hand-thrown debugging of taking off automatically after the debugging of course line, adopt the mode of fixing rudder face drift angle or maintenance air speed to control behind the hand-thrown, after aircraft altitude reaches safe altitude, get into cruising condition automatically.
Recovery can be adopted automatic deployment, adopts the way point incident of robot pilot to be provided with can be set to arrive the set point coordinate and promptly release a parachute and close motor simultaneously, because of this aircraft adopts the drawing-in type layout, does not have the problem of parachute and screw propeller winding.
The utility model is through the integrated normal flight that can guarantee aircraft of each subsystem of flying platform system, and earth station system can realize unmanned plane is set the program control navigation in course line, can accomplish the accurate control in specific (special) requirements course line.Make unmanned plane keep the flight original state through jettisoninging or launching dual mode, unmanned plane is mainly manually controlled by ground system when emission, after unmanned plane climbs the safety height, switches to automatic navigation mode.Accomplish the autonomous navigation control in the prefabricated task of unmanned plane course line through navigation control system, can after unmanned plane arrives assigned address, carry out the task action of spiraling.Can accomplish the application of different field through carrying the different effective loading device, carry out corresponding task.When the recovery flight device, unmanned plane is switched earlier and turn round and stretch out the hand moving state, downhill race of visual control unmanned plane or parachuting then by earth station system.
The utility model general technical index is as shown in table 1.
Table 1 general technical index
| Sequence number | Title | Technical indicator | Remarks |
| 1 | Maximum take-off weight | 4.7 | |
| 2 | Flying speed | 20m/s～38m/s | Cruise speed 28m/s |
| 3 | The span | 1.5m | |
| 4 | The captain | 1.06 | |
| 5 | Mission payload | 1kg | |
| 6 | Control Radius | >=15km | |
| 7 | Cruising time | >=1h | |
| 8 | Image resolution ratio | >=640 * 480 | |
| 9 | Power | Electronic | |
| 10 | The mode of taking off | Hand is thrown, is launched | |
| 11 | Way of recycling | Parachuting, downhill race |
Claims (8)
1. the unmanned plane reconnaissance system is characterized in that being provided with the flying platform system, guarantees the normal flight of aircraft; The flying platform system comprises structural portion, power part, Navigation Control portion, data link portion, payload portion and electrical part; Structural portion links to each other with power part, and power part links to each other with Navigation Control portion, and Navigation Control portion links to each other with electrical part, and electrical part links to each other with payload portion, and payload portion links to each other with data link portion, and data link portion links to each other with structural portion; Be provided with earth station system, realize unmanned plane is set the program control navigation in course line, accomplish the accurate control in course line; Earth station system comprises ground observing and controlling portion and ground safeguard portion, and ground observing and controlling portion links to each other with ground safeguard portion.
2. unmanned plane reconnaissance system according to claim 1 is characterized in that described structural portion does, body adopts flying wing type aerodynamic arrangement, the lifting body fuselage, and the control rudder face adopts elevon.
3. unmanned plane reconnaissance system according to claim 1; It is characterized in that described power part comprises brushless electric machine, brushless speed regulator, the collapsible screw propeller of carbon fibre and electrokinetic cell; Brushless electric machine and brushless speed regulator are arranged on the inside of body, and electrokinetic cell is arranged on the body.
4. unmanned plane reconnaissance system according to claim 1; It is characterized in that described Navigation Control portion comprises telepilot and robot pilot; Telepilot is used for launching and adjustment and the intervention of removal process to attitude of flight vehicle, and aircraft climbs after the safe altitude, and telepilot switches to automatic driving condition with airborne robot pilot; When the recovery flight device, by telepilot airborne robot pilot is switched back remote state earlier.
5. unmanned plane reconnaissance system according to claim 1 is characterized in that described data link portion comprises on-board data transmission radio station and land station data transmission radio station, and the on-board data transmission radio station is installed in the vertical tail.
6. unmanned plane reconnaissance system according to claim 1 is characterized in that described payload portion adopts board-like video camera, and the camera installation site is for when aircraft carries out orbit with 60 ° pitch angle, and camera is aimed at a certain target in ground all the time.
7. unmanned plane reconnaissance system according to claim 1 is characterized in that described ground observing and controlling portion is used to receive and transmit the related data of airborne data transmission radio station and payload portion, and the data that receive are handled and manifested.
8. unmanned plane reconnaissance system according to claim 1 is characterized in that described ground safeguard portion comprises emission and recovery and land station's power supply of unmanned plane, for the safe take-off of aircraft provides safeguard with making a return voyage.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011205701705U CN202453736U (en) | 2011-12-31 | 2011-12-31 | Unmanned aerial vehicle reconnaissance system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011205701705U CN202453736U (en) | 2011-12-31 | 2011-12-31 | Unmanned aerial vehicle reconnaissance system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202453736U true CN202453736U (en) | 2012-09-26 |
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ID=46869589
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2011205701705U Expired - Fee Related CN202453736U (en) | 2011-12-31 | 2011-12-31 | Unmanned aerial vehicle reconnaissance system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202453736U (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104700576A (en) * | 2015-03-27 | 2015-06-10 | 徐州飞梦电子科技有限公司 | Quick water rescuing system and method |
| CN105843254A (en) * | 2016-04-29 | 2016-08-10 | 乐视控股（北京）有限公司 | UAV flight control mode switching method and device and UAV |
| CN108001685A (en) * | 2017-12-15 | 2018-05-08 | 佛山市神风航空科技有限公司 | A kind of unmanned plane for aerophotogrammetry |
| CN109062244A (en) * | 2018-06-22 | 2018-12-21 | 西安特种飞行器工程研究院有限公司 | A kind of system and method based on marine eco-environment inspection |
| CN109835473A (en) * | 2017-11-24 | 2019-06-04 | 智飞智能装备科技东台有限公司 | A kind of micro-unmanned airborne real time monitoring reconnaissance system |
-
2011
- 2011-12-31 CN CN2011205701705U patent/CN202453736U/en not_active Expired - Fee Related
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104700576A (en) * | 2015-03-27 | 2015-06-10 | 徐州飞梦电子科技有限公司 | Quick water rescuing system and method |
| CN105843254A (en) * | 2016-04-29 | 2016-08-10 | 乐视控股（北京）有限公司 | UAV flight control mode switching method and device and UAV |
| CN109835473A (en) * | 2017-11-24 | 2019-06-04 | 智飞智能装备科技东台有限公司 | A kind of micro-unmanned airborne real time monitoring reconnaissance system |
| CN108001685A (en) * | 2017-12-15 | 2018-05-08 | 佛山市神风航空科技有限公司 | A kind of unmanned plane for aerophotogrammetry |
| CN109062244A (en) * | 2018-06-22 | 2018-12-21 | 西安特种飞行器工程研究院有限公司 | A kind of system and method based on marine eco-environment inspection |
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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: 20120926 Termination date: 20151231 |
|
| EXPY | Termination of patent right or utility model |