CN204979212U - Remote sensing fixed wing uavs - Google Patents
Remote sensing fixed wing uavs Download PDFInfo
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- CN204979212U CN204979212U CN201520771802.2U CN201520771802U CN204979212U CN 204979212 U CN204979212 U CN 204979212U CN 201520771802 U CN201520771802 U CN 201520771802U CN 204979212 U CN204979212 U CN 204979212U
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- fuselage
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- 239000002828 fuel tank Substances 0.000 claims description 13
- 238000013461 design Methods 0.000 claims description 6
- 230000005540 biological transmission Effects 0.000 claims description 3
- 230000008602 contraction Effects 0.000 claims description 3
- 230000003028 elevating effect Effects 0.000 claims description 3
- 238000004519 manufacturing process Methods 0.000 abstract description 2
- 230000002349 favourable effect Effects 0.000 abstract 1
- 238000013507 mapping Methods 0.000 description 5
- 238000011161 development Methods 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 4
- 238000010586 diagram Methods 0.000 description 2
- 239000000446 fuel Substances 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 229910000838 Al alloy Inorganic materials 0.000 description 1
- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical group [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000004568 cement Substances 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000003384 imaging method Methods 0.000 description 1
- 238000011835 investigation Methods 0.000 description 1
- 229910052744 lithium Inorganic materials 0.000 description 1
- 230000008520 organization Effects 0.000 description 1
- 230000001737 promoting effect Effects 0.000 description 1
- 239000002699 waste material Substances 0.000 description 1
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Abstract
The utility model provides a remote sensing fixed wing uavs, includes the fuselage, connect in wing, the vertical tail of fuselage, connect in tailplane, engine and the automatic pilot of vertical tail both sides, its characterized in that, vertical tail is even as an organic whole with the fuselage, and vertical tail and tailplane's trailing edge is equipped with rudder and elevator respectively, and the wing trailing edge is equipped with movable aileron, the front end of fuselage is located to the engine, and the engine driven screw provides flight required pulling force for unmanned aerial vehicle. The utility model discloses an it is better that unmanned aerial vehicle flies to control the performance, can carry out long period and the more remote survey and drawing task of taking photo by plane flight, and it is great to carry the oil mass, and current unmanned aerial vehicle is compared to effective task load has great improvement, simultaneously unmanned aerial vehicle's manufacturing cost is lower, is favorable to being widely used.
Description
Technical field
The utility model belongs to unmanned air vehicle technique field, particularly relate to a kind of for taking photo by plane, the multiduty remote sensing fixed-wing unmanned plane such as mapping.
Background technology
State Development Planning Commission in 2009 and national geography spatial information coordinating council have organized NSII Symposium On Development Strategy in concert, discuss with regard to problems such as China's NSII construction and application, geospatialinformation sharing, " digital provinces and regions " development strategies, propose the plan of jointly sketching the contours " Digital CHINA " blueprint.Since 2010, " Digital CHINA " land resources of extensively carrying out in whole nation generaI investigation project, has been up to 1:500 to the drafting accuracy requirement of real-time map, but such imaging precision of current landsat also out of reach far away.
Along with the development of Aerial Surveying Technology, because unmanned plane is less by the image on weather and airport, the application of aerial survey of unmanned aerial vehicle technology in aerial mapping field gets more and more, especially cost-efficiently light-duty remote sensing fixed-wing unmanned plane taking photo by plane, mapping etc. is used widely in field.
At present, existing remote sensing unmanned plane is not too reasonable by structure design, causes the waste of most of flying windows, causes unmanned plane to absorb orthogonal projection phase inefficiency.Meanwhile, in use due to a series of reasons such as strength of aircraft design are not enough and modular layout's mode is unreasonable, cause aircraft dismounting inconvenient, service life is lower.In addition, shorter when current unmanned plane also exists boat, mission payload loads the shortcomings such as less, is not well positioned to meet long-time, takes photo by plane at a distance, the mission requirements such as mapping.
Utility model content
For solving the problems of the technologies described above, the utility model will provide that a kind of duration of voyage is long, mission payload carrying capacity is large and lower-cost for taking photo by plane, the multiduty remote sensing fixed-wing unmanned plane such as mapping.
Technical solution of the present utility model is such: a kind of remote sensing fixed-wing unmanned plane, comprise fuselage, be connected to the wing of fuselage, vertical tail, the tailplane being connected to vertical tail both sides, driving engine and autopilot, it is characterized in that, described vertical tail and fuselage are connected as a single entity, the trailing edge of vertical tail and tailplane is respectively equipped with yaw rudder and elevating rudder, and trailing edge is provided with movable aileron; The front end of fuselage is located at by described driving engine, and engine drive screw propeller provides the pulling force needed for flight for unmanned plane.
Further, also comprise the tail wheel type landing gear being located at fuselage bottom, tail wheel type landing gear comprises the main landing gear being located at fuselage bottom leading portion and the auxiliary landing gear be located at below empennage, main landing gear comprises two main wheels be connected with fuselage bottom by gas spring, and auxiliary landing gear comprises one by gas spring and the tail wheel be connected below empennage.
Further, described fuselage appearance adopts by the head of waist respectively to two ends and the structure design of tail gradual change contraction, and the arbitrary curve on fuselage curved surface is in accordance with at least second differential is continuous.
Further, described fuselage surrounds a cabin body, and body inside in cabin is placed with to tail successively by head: driving engine, main oil tank, task device, additional fuel tank and parachute, wherein main oil tank and additional fuel tank top placement machine carry electromechanical appliance.
Further, described driving engine is connected with main oil tank and additional fuel tank respectively by oil pipe.
Further, described tailplane is detachable is connected to vertical tail.
Further, described task device comprises photographic camera, pick up camera and search equipment.
Further, described dynamo-electric cabin is for placing autopilot and on-board data transmission equipment.
Further, described parachute compartment is for the pilot-parachute placing parachute and be connected with parachute, and parachute compartment top is provided with hatchcover.
Further, be placed with in described dynamo-electric cabin for the power supply to all airborne electromechanical appliance centrally connected power supplies.
The beneficial effects of the utility model are embodied in: compared with existing unmanned plane, unmanned plane of the present utility model is by rational aircraft configuration structure design and the rational assembly mounting arrangement of engine room inside, make aircraft can carry the fuel tank of larger capacity, the increase of fuel load makes the duration of voyage of aircraft increase, remote operation flight for a long time can be realized, meanwhile, the mission payload amount of described unmanned plane compares existing unmanned plane larger lifting; The manufacturing cost of described unmanned plane is lower, flies to control better performances, is conducive to promoting the use.
Accompanying drawing explanation
Fig. 1 is the cabin inner component mounting structure schematic diagram of the utility model unmanned plane.
Detailed description of the invention
Below in conjunction with the drawings and specific embodiments, the utility model is further elaborated.
A kind of remote sensing fixed-wing unmanned plane, comprise fuselage, be connected to the wing of fuselage, vertical tail, the tailplane being connected to vertical tail both sides, driving engine and autopilot, it is characterized in that, described vertical tail and fuselage are connected as a single entity, the trailing edge of vertical tail and tailplane is respectively equipped with yaw rudder and elevating rudder, and trailing edge is provided with movable aileron; The front end of fuselage is located at by described driving engine, and engine drive screw propeller provides the pulling force needed for flight for unmanned plane.
Preferably, also comprise the tail wheel type landing gear being located at fuselage bottom, tail wheel type landing gear comprises the main landing gear being located at fuselage bottom leading portion and the auxiliary landing gear be located at below empennage, main landing gear comprises two main wheels be connected with fuselage bottom by gas spring, and auxiliary landing gear comprises one by gas spring and the tail wheel be connected below empennage.Adopt gas spring as the buffer unit of alighting gear, larger impact load can be cushioned, realize available protecting during aircraft landing.As preferred embodiment, for alleviating the weight of aircraft self, described main wheel adopts the plastic cement cover tire of aluminium alloy wheel hub and lightweight.
Preferably, described fuselage appearance adopts by the head of waist respectively to two ends and the structure design of tail gradual change contraction, and the arbitrary curve on fuselage curved surface is in accordance with at least second differential is continuous.Adopt described project organization to make interior of aircraft space comparatively compact, also meet the demand of the flight resistance farthest reduced simultaneously.
Preferably, described fuselage surrounds a cabin body, and body inside in cabin is placed with to tail successively by head: driving engine, main oil tank, task device, additional fuel tank and parachute, wherein main oil tank and additional fuel tank top placement machine carry electromechanical appliance.For better fixing the on-board components of engine room inside, realize simultaneously fast, dismounting easily, the space of body inside, described cabin can become machinery space, main oil tank cabin, the mission module placing mission payload, additional fuel tank cabin and parachute compartment by separator lined, for making full use of space, main oil tank cabin and top, additional fuel tank cabin arrange and are used for the dynamo-electric cabin that placement machine carries electromechanical appliance, are illustrated in figure 1 the cabin inner component mounting structure schematic diagram of this practicality unmanned plane.
Preferably, described driving engine is connected with main oil tank and additional fuel tank respectively by oil pipe, adopts two fuel tank, effectively can increase fuel load, extend the distance to go of aircraft.
Preferably, described tailplane is detachable is connected to vertical tail, and as embody rule, mode with bolts, fast and easy dismounting, is also easy to carry simultaneously more.
Preferably, described task device comprises photographic camera, pick up camera and search equipment.
Preferably, described dynamo-electric cabin is for placing autopilot and on-board data transmission equipment.
Preferably, described parachute compartment is for the pilot-parachute placing parachute and be connected with parachute, and parachute compartment top is provided with hatchcover.When aircraft will perform landing task, autopilot controls to release a parachute the hatchcover at top, cabin, and pilot-parachute outwards flies out under the drive of high velocity air, and pull out outside parachute compartment by parachute, parachute is opened simultaneously, realizes aircraft stable landing.
Preferably, be placed with in described dynamo-electric cabin for the power supply to all airborne electromechanical appliance centrally connected power supplies, described power supply is lithium cell.
It is last it is noted that the above embodiment is only preferred embodiment of the present utility model, be not limited to the utility model, although be described in detail the utility model with reference to previous embodiment, for a person skilled in the art, it still can be modified to the technical scheme described in foregoing embodiments, or carries out equivalent replacement to wherein portion of techniques feature.All within spirit of the present utility model and principle, any amendment done, equivalent replacement, improvement etc., all should be included within protection domain of the present utility model.
Claims (10)
1. a remote sensing fixed-wing unmanned plane, comprise fuselage, be connected to the wing of fuselage, vertical tail, the tailplane being connected to vertical tail both sides, driving engine and autopilot, it is characterized in that, described vertical tail and fuselage are connected as a single entity, the trailing edge of vertical tail and tailplane is respectively equipped with yaw rudder and elevating rudder, and trailing edge is provided with movable aileron; The front end of fuselage is located at by described driving engine, and engine drive screw propeller provides the pulling force needed for flight for unmanned plane.
2. unmanned plane according to claim 1, it is characterized in that, also comprise the tail wheel type landing gear being located at fuselage bottom, tail wheel type landing gear comprises the main landing gear being located at fuselage bottom leading portion and the auxiliary landing gear be located at below empennage, main landing gear comprises two main wheels be connected with fuselage bottom by gas spring, and auxiliary landing gear comprises one by gas spring and the tail wheel be connected below empennage.
3. unmanned plane according to claim 1, is characterized in that, described fuselage appearance adopts by the head of waist respectively to two ends and the structure design of tail gradual change contraction, and the arbitrary curve on fuselage curved surface is in accordance with at least second differential is continuous.
4. the unmanned plane according to the arbitrary claim of claim 1-3, it is characterized in that, described fuselage surrounds a cabin body, body inside, cabin is placed with to tail successively by head: driving engine, main oil tank, task device, additional fuel tank and parachute, wherein main oil tank and additional fuel tank top placement machine carry electromechanical appliance.
5. unmanned plane according to claim 4, is characterized in that, described driving engine is connected with main oil tank and additional fuel tank respectively by oil pipe.
6. unmanned plane according to claim 4, is characterized in that, described tailplane is detachable is connected to vertical tail.
7. unmanned plane according to claim 4, is characterized in that, is placed with photographic camera, pick up camera, search equipment in described mission module.
8. unmanned plane according to claim 4, is characterized in that, described dynamo-electric cabin is for placing autopilot and on-board data transmission equipment.
9. unmanned plane according to claim 4, is characterized in that, described parachute compartment is for the pilot-parachute placing parachute and be connected with parachute, and parachute compartment top is provided with hatchcover.
10. unmanned plane according to claim 4, is characterized in that, is placed with for the power supply to airborne electromechanical appliance centrally connected power supply in described dynamo-electric cabin.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520771802.2U CN204979212U (en) | 2015-09-30 | 2015-09-30 | Remote sensing fixed wing uavs |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520771802.2U CN204979212U (en) | 2015-09-30 | 2015-09-30 | Remote sensing fixed wing uavs |
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| Publication Number | Publication Date |
|---|---|
| CN204979212U true CN204979212U (en) | 2016-01-20 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520771802.2U Expired - Fee Related CN204979212U (en) | 2015-09-30 | 2015-09-30 | Remote sensing fixed wing uavs |
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| CN (1) | CN204979212U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106114813A (en) * | 2016-08-31 | 2016-11-16 | 河南翱翔航空科技有限公司 | Unmanned plane body skeleton |
-
2015
- 2015-09-30 CN CN201520771802.2U patent/CN204979212U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106114813A (en) * | 2016-08-31 | 2016-11-16 | 河南翱翔航空科技有限公司 | Unmanned plane body skeleton |
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| 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: 20160120 Termination date: 20200930 |
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| CF01 | Termination of patent right due to non-payment of annual fee |