CN207550513U - Unmanned plane - Google Patents
Unmanned plane Download PDFInfo
- Publication number
- CN207550513U CN207550513U CN201721574194.1U CN201721574194U CN207550513U CN 207550513 U CN207550513 U CN 207550513U CN 201721574194 U CN201721574194 U CN 201721574194U CN 207550513 U CN207550513 U CN 207550513U
- Authority
- CN
- China
- Prior art keywords
- undercarriage
- fuselage
- stabilizer blade
- unmanned plane
- connection sheet
- 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
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Abstract
The utility model discloses a kind of unmanned planes, and including fuselage, wing and undercarriage, the undercarriage includes nose-gear and rear undercarriage, and the nose-gear includes two stabilizer blades positioned at fuselage both sides, and the feet bottom is equipped with wheel；Each stabilizer blade is correspondingly arranged a gas spring connecting rod, and one end of the gas spring connecting rod is connected on stabilizer blade, and the other end is connected on fuselage, and forms acute triangle region between gas spring connecting rod corresponding to stabilizer blade, stabilizer blade and fuselage.The application increases the height of undercarriage, and there is provided the gas spring connecting rod being adapted with undercarriage, it is good to unload power effect.
Description
Technical field
The utility model is related to unmanned plane fields, and in particular to unmanned plane.
Background technology
Unmanned plane is with its advantage such as flexible, fast and convenient, it has also become land mapping, emergency disaster relief, economic construction etc.
The important way of aspect data acquisition.Traditional unmanned plane, which measures, is generally optical photography, and optics boat takes the photograph system climate, time
Limit it is larger, airborne synthetic aperture radar it is emergent still not extensively.SAR is mainly mounted in satellite, has on the equipments such as man-machine, application
In space flight, ocean, military detection and monitoring, feature is high resolution, and energy all weather operations can efficiently identify camouflage and penetrate
Cloak.Obtained high azimuth resolution is equivalent to the azimuth resolution that a wide aperture antenna can be provided.The application master
It is the needs for meeting SAR system, the structure of unmanned plane is improved.
Utility model content
The purpose of this utility model is to provide a kind of unmanned plane, after solving existing unmanned plane loading SAR system, due to rising
The problem of height of frame is fallen than relatively low, can not work normally after antenna is mounted below wing.
To solve the technical issues of above-mentioned, the utility model uses following technical scheme：
A kind of unmanned plane, including fuselage, wing and undercarriage, the undercarriage includes nose-gear and rear undercarriage, institute
It states nose-gear and includes two stabilizer blades for being located at fuselage both sides, the feet bottom is equipped with wheel；Each stabilizer blade is right
One gas spring connecting rod should be set, one end of the gas spring connecting rod is connected on stabilizer blade, and the other end is connected on fuselage,
And acute triangle region is formed between gas spring connecting rod corresponding to stabilizer blade, stabilizer blade and fuselage.
After SAR system is loaded on unmanned plane, it to be just correspondingly arranged reception antenna and transmitting antenna under the wings of an airplane, it is original
Unmanned plane undercarriage height it is relatively low, so wing below do not leave the enough spaces of antenna for, for ensure antenna safety, should
Liftoff more than the 10CM of antenna is ensured, so needing the height of increase undercarriage.But improved unmanned aerial vehicle body weight increases,
The strength bigger that undercarriage is born during landing, along with can be inherently easily damaged after the height increase of undercarriage, so need pair
Undercarriage is reinforced.
Undercarriage in the application is tail wheel type landing gear, and wherein nose-gear is main landing gear, using aluminium alloy plus
Composite material is reinforced；Damping device is installed on undercarriage, damping device connects undercarriage using gas spring connecting rod
It is good to unload power effect for lower part and fuselage.
As preference, undercarriage is slide-type after described.
Undercarriage is changed to slide-type by wheeled afterwards, shortens the landing distance of unmanned plane.
As preference, the fuselage is equipped with connection sheet with stabilizer blade junction, the connection sheet rear end is turned under curved
Into at an acute angle between fixed part and the connection sheet and fixed part, the stabilizer blade and fixed part integrated molding.
Fuselage and nose-gear junction are reinforced, increase the contact area of undercarriage and fuselage using connection sheet,
Disperse stress.In addition, at an acute angle between connection sheet and fixed part and have certain toughness, during landing, cushioning effect can be played,
Have no effect on the pneumatic property of unmanned plane.
As preference, buffer bar is provided between the connection sheet and fixed part, the buffer bar, connection sheet and fixation
Delta-shaped region is formed between portion.
When unmanned plane break down can not stable landing when, undercarriage can be anti-by bigger impact force during landing
Only connection sheet and fixinig plate are broken by greater impact, set buffer bar.
As preference, the buffer bar both ends are both provided with spherical parts, and connection sheet and fixed part are connect with buffer bar
Place is both provided with cavity, and the size and shape of the cavity is adapted with the size and shape of spherical parts.
After fixinig plate and connection sheet are by impact force, angle therebetween can change, and buffer bar can also be generated
Certain torque, so being connected between buffer bar and connection sheet, fixed part by spherical parts with cavity, spherical parts can be in cavity
Inside it is freely rotated.
As preference, the buffer bar is one kind in hydraulic cushion bar or spring buffer bar.
Compared with prior art, the beneficial effects of the utility model are at least one of following：
The application increases the height of undercarriage, and there is provided the gas spring connecting rods being adapted with undercarriage, unload power effect
Fruit is good.
There is provided connection sheets, increase undercarriage and the area of fuselage junction, can play the role of disperseing stress.
Buffer bar both ends are connected by spherical parts and cavity with fixinig plate, connection sheet, and spherical parts can be in cavity freely
Rotation.
Description of the drawings
Fig. 1 is the structure diagram of the utility model unmanned plane.
Fig. 2 is the sectional view of the utility model unmanned plane.
Fig. 3 is the connection diagram of the utility model nose-gear and fuselage.
Specific embodiment
In order to make the purpose of the utility model, technical solutions and advantages more clearly understood, below in conjunction with attached drawing and implementation
Example, the present invention is further described in detail.It should be appreciated that specific embodiment described herein is only used to explain
The utility model is not used to limit the utility model.
Embodiment 1：
A kind of unmanned plane is present embodiments provided, as shown in Figs. 1-2, including fuselage 1, wing 2 and undercarriage 3, the machine
Antenna is provided on the wing 2, the undercarriage 3 includes nose-gear and rear undercarriage 33, and the nose-gear includes being located at fuselage 1
Two stabilizer blades 31 of both sides, 31 bottom end of stabilizer blade are equipped with wheel；Each stabilizer blade 31 is correspondingly arranged a gas spring
Connecting rod 32, one end of the gas spring connecting rod 32 are connected on stabilizer blade 31, and the other end connects on the fuselage 1, and stabilizer blade 31,
Acute triangle region is formed between gas spring connecting rod 32 and fuselage 1 corresponding to stabilizer blade 31.
After SAR system is loaded on unmanned plane, reception antenna and transmitting antenna are correspondingly arranged below wing 2, it is former
3 height of undercarriage of some unmanned planes is relatively low, so 2 lower section of wing does not leave the enough spaces of antenna for, to ensure antenna peace
Entirely, it should be ensured that antenna is liftoff more than 10CM, so needing to increase the height of undercarriage 3.But improved 1 weight of unmanned aerial vehicle body
Amount increases, the strength bigger that undercarriage 3 is born during landing, along with can be inherently easily damaged after the height increase of undercarriage 3,
So undercarriage 3 need to be reinforced.
Undercarriage 3 in the application is tail wheel type landing gear 3, and wherein nose-gear is main landing gear 3, using aluminium alloy
Composite material is added to be reinforced；Damping device is installed on undercarriage 3, damping device is connected using gas spring connecting rod 32
3 lower part of frame and fuselage 1 are fallen, it is good to unload power effect.
Embodiment 2：
The present embodiment further defines on the basis of embodiment 1：Undercarriage 33 is slide-type after described.
Undercarriage 33 is changed to slide-type by wheeled afterwards, shortens the landing distance of unmanned plane.
Embodiment 3：
The present embodiment further defines on the basis of embodiment 2：The fuselage 1 is equipped with 31 junction of stabilizer blade
Connection sheet 4,4 rear end of connection sheet are bent downwardly to form at an acute angle between fixed part 5 and the connection sheet 4 and fixed part 5, institute
It states stabilizer blade to be integrally formed with fixed part 5, as shown in Figure 3.
Fuselage 1 and nose-gear junction are reinforced, increase the contact surface of undercarriage 3 and fuselage 1 using connection sheet 4
Product disperses stress.In addition, at an acute angle between connection sheet 4 and fixed part 5 and have certain toughness, during landing, buffering can be played
Effect, has no effect on the pneumatic property of unmanned plane
Embodiment 4：
The present embodiment further defines on the basis of embodiment 3：It is provided between the connection sheet 4 and fixed part 5
Buffer bar 6 forms delta-shaped region between the buffer bar 6, connection sheet 4 and fixed part 5.
When unmanned plane break down can not stable landing when, undercarriage 3 can be anti-by bigger impact force during landing
Only connection sheet 4 and fixinig plate are broken by greater impact, set buffer bar 6.
Embodiment 5：
The present embodiment further defines on the basis of embodiment 4：6 both ends of buffer bar are both provided with spherical parts
61, and connection sheet 4 and fixed part 5 are both provided with cavity, the size and shape and spherical parts of the cavity with 6 junction of buffer bar
61 size and shape is adapted.
After fixinig plate and connection sheet 4 are by impact force, angle therebetween can change, and buffer bar 6 can also be produced
Raw certain torque, so being connected between buffer bar 6 and connection sheet 4, fixed part 5 by spherical parts 61 with cavity, spherical parts 61
It can be freely rotated in cavity.
Embodiment 6：
The present embodiment further defines on the basis of embodiment 4：The buffer bar 6 is hydraulic cushion bar 6 or spring
One kind in buffer bar 6.
Although reference be made herein to the utility model is described in multiple explanatory embodiments of the utility model, still,
It should be understood that those skilled in the art can be designed that a lot of other modifications and embodiment, these modifications and embodiment
It will fall within spirit disclosed in the present application and spirit.More specifically, it discloses in the application, drawings and claims
In the range of, a variety of variations and modifications can be carried out to the building block and/or layout of theme combination layout.In addition to building block
And/or outside the modification and improvement of layout progress, to those skilled in the art, other purposes also will be apparent.
Claims (6)
1. a kind of unmanned plane, including fuselage（1）, wing（2）And undercarriage（3）, it is characterised in that：The undercarriage（3）Including
Nose-gear and rear undercarriage（33）, the nose-gear is including being located at fuselage（1）Two stabilizer blades of both sides（31）, the stabilizer blade
（31）Bottom end is equipped with wheel；Each stabilizer blade（31）It is correspondingly arranged a gas spring connecting rod（32）, the gas spring
Connecting rod（32）One end be connected to stabilizer blade（31）On, the other end is connected to fuselage（1）On, and stabilizer blade（31）, stabilizer blade（31）Institute
Corresponding gas spring connecting rod（32）And fuselage（1）Between form acute triangle region.
2. unmanned plane according to claim 1, which is characterized in that undercarriage after described（33）For slide-type.
3. unmanned plane according to claim 2, which is characterized in that the fuselage（1）With stabilizer blade（31）Junction is equipped with
Connection sheet（4）, the connection sheet（4）Rear end is bent downwardly to form fixed part（5）And the connection sheet（4）With fixed part（5）It
Between at an acute angle, the stabilizer blade and fixed part（5）It is integrally formed.
4. unmanned plane according to claim 3, which is characterized in that the connection sheet（4）With fixed part（5）Between be provided with
Buffer bar（6）, the buffer bar（6）, connection sheet（4）And fixed part（5）Between form delta-shaped region.
5. unmanned plane according to claim 4, which is characterized in that the buffer bar（6）Both ends are both provided with spherical parts
（61）, and connection sheet（4）And fixed part（5）With buffer bar（6）Junction is both provided with cavity, the size and shape of the cavity
With spherical parts（61）Size and shape be adapted.
6. unmanned plane according to claim 4, which is characterized in that the buffer bar（6）For hydraulic cushion bar（6）Or spring
Buffer bar（6）In one kind.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721574194.1U CN207550513U (en) | 2017-11-22 | 2017-11-22 | Unmanned plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721574194.1U CN207550513U (en) | 2017-11-22 | 2017-11-22 | Unmanned plane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207550513U true CN207550513U (en) | 2018-06-29 |
Family
ID=62679671
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201721574194.1U Expired - Fee Related CN207550513U (en) | 2017-11-22 | 2017-11-22 | Unmanned plane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN207550513U (en) |
-
2017
- 2017-11-22 CN CN201721574194.1U patent/CN207550513U/en not_active Expired - Fee Related
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| 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: 20180629 Termination date: 20211122 |