CN203666974U - Remote sensing remote metering fixed wing unmanned air vehicle - Google Patents
Remote sensing remote metering fixed wing unmanned air vehicle Download PDFInfo
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- CN203666974U CN203666974U CN201320736318.7U CN201320736318U CN203666974U CN 203666974 U CN203666974 U CN 203666974U CN 201320736318 U CN201320736318 U CN 201320736318U CN 203666974 U CN203666974 U CN 203666974U
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- fuselage
- wheel
- air vehicle
- tailplane
- remote sensing
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Abstract
The utility model provides a remote sensing remote metering fixed wing unmanned air vehicle. The unmanned air vehicle comprises a fuselage, wings and horizontal empennages, wherein propellers are arranged at the front end of the head part of the fuselage; the wings are arranged at the front part of the upper end of the fuselage; the horizontal empennages are arranged at the tail part of the fuselage; undercarriages are arranged on the bottom surface of the fuselage below the wings of the fuselage and the horizontal empennages respectively; a front wheel damper and front wheels are arranged on the undercarriage at the front part; a back wheel damper and a back wheel are arranged on the undercarriage at the back part, and the back wheel can swerve; vertical empennages perpendicular to the horizontal empennages are arranged at the two ends of the horizontal empennages respectively. According to the utility model, the unmanned air vehicle has the following benefits: double vertical empennage structure can enable the air vehicle to keep the accuracy of air lines during the operation process and play a key role in remote sensing remote metering topographic reconnaissance; the tail wheel of the air vehicle adopts a spring for shock absorption, so that the safety factor is increased when the air vehicle lands on the ground; in addition, the tail wheel is controlled alone, so that the skating direction of the air vehicle on the ground can be better regulated; a pneumatic bumper that is better in damping effect is adopted by the undercarriage at the front part, so that the cabin volume is increased, therefore, the placing space of equipment is increased and oil is increased to prolong the aircraft range.
Description
Technical field
The utility model belongs to aerospace flight vehicle field, relates to a kind of remote sensing remote measurement fixed-wing unmanned aerial vehicle.
Background technology
The structure of existing a kind of remote sensing remote measurement fixed-wing unmanned aerial vehicle adopts the design of a vertical tail, has greatly limited the track stability of aircraft in operation.In extraneous large wind, easy aircraft drifts off the course.And in landing, because burst air-flow is prone to the strong shock on aircraft and ground, can cause like this device damage of aircraft bottom or lift-launch to affect safety performance.And due to the runway situation difference of landing site, when aircraft landing contacts with ground, can not effectively control the stability of aircraft directivity in sliding race process.
Summary of the invention
Problem to be solved in the utility model is to provide a kind of remote sensing remote measurement fixed-wing unmanned aerial vehicle, is especially applicable to long working in remote sensing remote measurement, a kind of remote sensing remote measurement fixed-wing unmanned aerial vehicle of topographic(al) reconnaissance task.
For solving the problems of the technologies described above, the technical solution adopted in the utility model is:
A kind of remote sensing remote measurement fixed-wing unmanned aerial vehicle, comprises fuselage, wing, tailplane;
The front end face of described fuselage head is provided with screw propeller, and front portion is provided with wing, and afterbody is provided with tailplane;
On the body bottom surface of described fuselage wing and tailplane below, be respectively equipped with alighting gear, be provided with front-wheel damping and front-wheel on anterior alighting gear, be provided with rear wheel shock-absorbing and tail wheel on the alighting gear of rear portion, described tail wheel can turn to;
Described tailplane two ends are provided with respectively the vertical tail perpendicular to tailplane.
Further, described front-wheel damping adopts pneumatic spring damping, and described rear wheel shock-absorbing adopts common spring shock absorption.
Further, also comprise cabin, described cabin is arranged on fuselage interior wing below.
Further, described fuselage and wing adopt multi-segment structure, and the junction of every section is provided with reinforced rib, and described fuselage cross section is cylindric.
Further, described vertical tail middle part is affixed with described tailplane, and in the middle of vertical tail, forward end is outstanding, and upper/lower terminal is provided with sweepback angle.
Further, described fuselage, vertical tail, tailplane all use glass-reinforced plastic material.
Advantage and the good effect that the utlity model has are: twin vertical fin wing structure form makes aircraft can guarantee course line accuracy in operation, the powerful guarantee of the operation in both to fix the courses that is aircraft.Operation, in remote sensing remote measurement, is played to crucial effect in topographic(al) reconnaissance task.Aircraft tail wheel adopts spring shock absorption to strengthen the safety factor of aircraft in the time landing, and has avoided the body injury occurring while landing.Tail wheel is controlled separately simultaneously, can better adjust aircraft sliding directivity of running on the ground.Nose-gear adopts pneumatic damping, and damping effect is better.Cabin volumes strengthens, and the equipment that guaranteed is laid enough spaces, can increase oil plant, has increased aircraft range.
Accompanying drawing explanation
Fig. 1 is the overall schematic of this utility model.
In figure:
1, screw propeller 2, fuselage 3, wing
4, alighting gear 5, tailplane 6, vertical tail
7, front-wheel damping 8, rear wheel shock-absorbing 9, cabin
The specific embodiment
As shown in Figure 1, a kind of remote sensing remote measurement fixed-wing unmanned aerial vehicle comprises fuselage 2, wing 3, tailplane 5; The head front end face of described fuselage 2 is provided with screw propeller 1, and upper-end front is provided with wing 3, and afterbody is provided with tailplane 5; On fuselage 2 bottom surfaces of described fuselage wing 3 and tailplane 5 belows, be respectively equipped with alighting gear 4, on anterior alighting gear 4, be provided with front-wheel damping 7 and front-wheel, on rear portion alighting gear 4, be provided with rear wheel shock-absorbing 8 and tail wheel, described tail wheel can turn to, and when the tail wheel that can turn to contributes to help aircraft landing, rational adjusting circuit is avoided risk.Described tailplane 5 two ends are provided with respectively the vertical tail 6 perpendicular to tailplane 5.The design of two vertical tails 6 can make aircraft in operation, have good course line rectilinearity, does not drift off the course.
Front-wheel damping 7 adopts pneumatic spring damping, and described rear wheel shock-absorbing 8 adopts common spring shock absorption.Adopting pneumatic spring damping and common spring Aseismatic Design is all in order to make aircraft reduce excessive impulsive force with ground, bulk strength and the service life of assurance aircraft the landing time.Also comprise cabin 9, described cabin 9 is arranged on fuselage 2 inner airfoil 3 belows.Be used for arranging instrument of surveying and mapping or increase oil storage space.
Fuselage 2 and wing 3 adopt multi-segment structure, and the junction of every section is provided with reinforced rib, and described fuselage 2 cross sections are cylindric.Junction is provided with the reinforced rib that meets cross sectional shape for one week, the structure of fuselage 2 is played to the effect of gaining in strength.Fuselage 2 in the present embodiment is 5 segmentation structures, and wing 3 is 6 segmentation structures.Fuselage 2 is inserted sledge with wing 3 by carbon pipe and is connected with screw, in guaranteeing location, has very high intensity, and the fuselage 2 of glass-felt plastic and wing 3 also play very large intensity in addition.Fuselage 2 is made the shape of approximate cylinder in addition, has reduced the impact of crosswind, and some flat fuselage 2 has also played and has been subject to crosswind to affect little effect.
Above an embodiment of the present utility model is had been described in detail, but described content is only preferred embodiment of the present utility model, can not be considered to for limiting practical range of the present utility model.All equalization variation and improvement etc. of doing according to the utility model application range, within all should still belonging to patent covering scope of the present utility model.
Claims (6)
1. a remote sensing remote measurement fixed-wing unmanned aerial vehicle, is characterized in that: comprise fuselage (2), wing (3), tailplane (5);
The front end face of described fuselage (2) head is provided with screw propeller (1), and front portion is provided with wing (3), and afterbody is provided with tailplane (5);
On fuselage (2) bottom surface of described fuselage wing (3) and tailplane (5) below, be respectively equipped with alighting gear (4), on anterior alighting gear (4), be provided with front-wheel damping (7) and front-wheel, on rear portion alighting gear (4), be provided with rear wheel shock-absorbing (8) and tail wheel, described tail wheel can turn to;
Described tailplane (5) two ends are provided with respectively the vertical tail (6) perpendicular to tailplane (5).
2. a kind of remote sensing remote measurement fixed-wing unmanned aerial vehicle according to claim 1, is characterized in that: described front-wheel damping (7) adopts pneumatic spring damping, and described rear wheel shock-absorbing (8) adopts common spring shock absorption.
3. a kind of remote sensing remote measurement fixed-wing unmanned aerial vehicle according to claim 1, is characterized in that: also comprise cabin (9), described cabin (9) are arranged on fuselage (2) inner airfoil (3) below.
4. a kind of remote sensing remote measurement fixed-wing unmanned aerial vehicle according to claim 1, is characterized in that: described fuselage (2) and wing (3) adopt multi-segment structure, and the junction of every section is provided with reinforced rib, and described fuselage (2) cross section is cylindric.
5. a kind of remote sensing remote measurement fixed-wing unmanned aerial vehicle according to claim 1, is characterized in that: described vertical tail (6) middle part is affixed with described tailplane (5), and in the middle of vertical tail (6), forward end is outstanding, and upper/lower terminal is provided with sweepback angle.
6. a kind of remote sensing remote measurement fixed-wing unmanned aerial vehicle according to claim 1, is characterized in that: described fuselage (2), vertical tail (6), tailplane (5) all use glass-reinforced plastic material.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320736318.7U CN203666974U (en) | 2013-11-20 | 2013-11-20 | Remote sensing remote metering fixed wing unmanned air vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320736318.7U CN203666974U (en) | 2013-11-20 | 2013-11-20 | Remote sensing remote metering fixed wing unmanned air vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203666974U true CN203666974U (en) | 2014-06-25 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201320736318.7U Expired - Fee Related CN203666974U (en) | 2013-11-20 | 2013-11-20 | Remote sensing remote metering fixed wing unmanned air vehicle |
Country Status (1)
| Country | Link |
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| CN (1) | CN203666974U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104443353A (en) * | 2014-12-15 | 2015-03-25 | 佛山市神风航空科技有限公司 | Wing-changeable airplane |
| CN113734428A (en) * | 2021-08-30 | 2021-12-03 | 北京航空航天大学 | A simple and easy skid formula rear landing gear for solar energy unmanned aerial vehicle |
-
2013
- 2013-11-20 CN CN201320736318.7U patent/CN203666974U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104443353A (en) * | 2014-12-15 | 2015-03-25 | 佛山市神风航空科技有限公司 | Wing-changeable airplane |
| CN113734428A (en) * | 2021-08-30 | 2021-12-03 | 北京航空航天大学 | A simple and easy skid formula rear landing gear for solar energy unmanned aerial vehicle |
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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 | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20140625 Termination date: 20181120 |