CN204279926U - A kind of Brattice type multi-rotor aerocraft alighting gear with guide functions - Google Patents
A kind of Brattice type multi-rotor aerocraft alighting gear with guide functions Download PDFInfo
- Publication number
- CN204279926U CN204279926U CN201420612781.5U CN201420612781U CN204279926U CN 204279926 U CN204279926 U CN 204279926U CN 201420612781 U CN201420612781 U CN 201420612781U CN 204279926 U CN204279926 U CN 204279926U
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- China
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- alighting gear
- aircraft body
- fixedly connected
- type multi
- rotor
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Abstract
The utility model provides a kind of Brattice type multi-rotor aerocraft alighting gear with guide functions, and this alighting gear is fixedly connected with aircraft body bottom aircraft body; This alighting gear is the structure of the frustum of hollow, and the upper following table of this frustum structure is the identical and equilateral polygon of correspondence of limit number, and the upper table surface of this frustum structure alighting gear is provided with and the installation sheet be fixedly connected with bottom aircraft body; Described installation sheet is fixedly connected with the bottom of aircraft body by bolt of rear end plate; And this alighting gear and aircraft body to be fixedly connected with rear described each guide face mutually corresponding with the rotor in aircraft body.The utility model is by the setting of guide face, alighting gear and installation sheet, be conducive to preventing the motor drive shaft axis of aircraft body in flight course axis and rotor up and down from producing larger angle and cause that deviation of gravity center is excessive to be overturn, improve the stability of flight, and then reduction maintenance cost, increase the service life.
Description
Technical field
The utility model belongs to aircraft spare and accessory parts technical field, particularly relates to a kind of Brattice type multi-rotor aerocraft alighting gear with guide functions.
Background technology
At present, rotor craft is in the process of rising and falling, and aircraft landing gear is the important devices in takeoff and landing process, to its weight, buffer capacity, mounting means and reliability have strict technical requirements, otherwise can have a negative impact to whole landing process, even cause the damage of aircraft.In addition, because unmanned vehicle adopts battery-driven mode usually, voyage is very limited effectively, need to reduce the weight of unmanned vehicle to extend voyage to greatest extent as far as possible, this causes actuating unit wherein (motor and rotor assemblies) without any redundancy, as long as wherein any one actuating unit et out of order, faults-tolerant control will be difficult to carry out, free falling can only be let alone, cause mission failure thus, present stage, common aircraft landing gear was generally steel wire or carbon plate and/or aluminium sheet, be made by Laos's bending process, be screwed on fuselage, although this structure is simple, but poor-performing, alighting gear is easily caused to be out of shape, sideslip, the situations such as fracture, meanwhile, existing aircraft in flight course, when running into larger strong wind, the motor drive shaft axis of the axis that the fuselage of aircraft is upper and lower and rotor produces larger lateral deviation, easily cause deviation of gravity center excessive and overturn, thus often causing fuselage to damage, alighting gear is difficult to the phenomenons such as reparation, thus, affect aircraft overall appearance and service life, there is structure based on existing aircraft landing gear simple, easily cause deviation of gravity center excessive and overturn, poor safety performance, the problem that maintenance cost is high and service life is short.
Therefore, invent a kind of Brattice type multi-rotor aerocraft alighting gear with guide functions and seem very necessary.
Utility model content
In order to solve the problems of the technologies described above, the utility model provides a kind of Brattice type multi-rotor aerocraft alighting gear with guide functions, to solve existing aircraft landing gear, to there is structure simple, easily cause deviation of gravity center excessive and overturn, poor safety performance, the problem that maintenance cost is high and service life is short.With a Brattice type multi-rotor aerocraft alighting gear for guide functions, this alighting gear is fixedly connected with aircraft body bottom aircraft body; It is characterized in that, this alighting gear is the structure of the frustum of hollow, the upper following table of this frustum structure is the identical and equilateral polygon of correspondence of limit number, each side of this frustum structure inwardly concaves and forms circular arc guide face, central axis and the line of upper following table geometric centre of this guide face are positioned at that same plane is crossing and angle is A, and the upper table surface of this frustum structure alighting gear is provided with and the installation sheet be fixedly connected with bottom aircraft body; Described installation sheet is fixedly connected with the bottom of aircraft body by bolt of rear end plate; And this alighting gear and aircraft body to be fixedly connected with rear described each guide face mutually corresponding with the rotor in aircraft body.
The equilateral polygon corresponding up and down of described frustum structure is square, be conducive to keeping the alighting gear bottommost of aircraft body corresponding with rotor, thus be conducive to preventing the motor drive shaft axis of aircraft body in flight course axis and rotor up and down from producing larger angle causing that deviation of gravity center is excessive to be overturn, and then reduction maintenance cost, increase the service life.
Described alighting gear specifically adopts the shape of hollow Brattice type structure, and described alighting gear specifically adopts lightweight carbon fiber sheet structure to make, and is conducive to alleviating deadweight, reduces maintenance cost further, increase the service life.
Described installation sheet specifically adopts the oblong schistose texture of 2 Bi-metal Steel Aluminums, is conducive to strengthening Joint strenght, is conducive to the stability improving flight further, and then increases the service life.
The bolt that described bolt of rear end plate specifically adopts 4 PVC plastic materials to make, is conducive to expendable weight, reduces and manufactures and maintenance cost, increase the service life.
The beneficial effects of the utility model are: by the setting of guide face, alighting gear and installation sheet, be conducive to preventing the motor drive shaft axis of aircraft body in flight course axis and rotor up and down from producing larger angle and cause that deviation of gravity center is excessive to be overturn, improve the stability of flight, and then reduction maintenance cost, increase the service life.
Accompanying drawing explanation
Fig. 1 is birds-eye view of the present utility model.
Fig. 2 is structural representation of the present utility model.
Detailed description of the invention
As shown in Figures 1 and 2
The utility model provides a kind of Brattice type multi-rotor aerocraft alighting gear with guide functions, and this alighting gear is fixedly connected with aircraft body 4 bottom aircraft body; This alighting gear 6 is the structure of the frustum of hollow, the upper following table of this frustum structure is the identical and equilateral polygon of correspondence of limit number, each side of this frustum structure inwardly concaves and forms circular arc guide face 7, central axis and the line of upper following table geometric centre of this guide face 7 are positioned at that same plane is crossing and angle is A, and the upper table surface of this frustum structure alighting gear 6 is provided with and the installation sheet 2 be fixedly connected with bottom aircraft body 4; Described installation sheet 2 is fixedly connected with by the bottom of bolt of rear end plate 3 with aircraft body 4; And this alighting gear 6 and aircraft body 4 to be fixedly connected with rear described each guide face 7 mutually corresponding with the rotor in aircraft body 4.
The equilateral polygon corresponding up and down of described frustum structure is square, be conducive to keeping alighting gear 6 bottommost of aircraft body 4 corresponding with rotor, thus be conducive to preventing the motor drive shaft axis of aircraft body 4 in flight course axis and rotor up and down from producing larger angle causing that deviation of gravity center is excessive to be overturn, and then reduction maintenance cost, increase the service life.
Described alighting gear 6 specifically adopts the shape of hollow Brattice type structure, and described alighting gear 6 specifically adopts lightweight carbon fiber sheet structure to make, and is conducive to alleviating deadweight, reduces maintenance cost further, increase the service life.
Described installation sheet 2 specifically adopts the oblong schistose texture of 2 Bi-metal Steel Aluminums, is conducive to strengthening Joint strenght, is conducive to the stability improving flight further, and then increases the service life.
The bolt that described bolt of rear end plate 3 specifically adopts 4 PVC plastic materials to make, is conducive to expendable weight, reduces and manufacture and maintenance cost, increase the service life.
The beneficial effects of the utility model are: by the setting of guide face, alighting gear and installation sheet, be conducive to preventing the motor drive shaft axis of aircraft body in flight course axis and rotor up and down from producing larger angle and cause that deviation of gravity center is excessive to be overturn, improve the stability of flight, and then reduction maintenance cost, increase the service life.
Utilize technical scheme described in the utility model, or those skilled in the art being under the inspiration of technical solutions of the utility model, designing similar technical scheme, and reach above-mentioned technique effect, is all fall into protection domain of the present utility model.
Claims (5)
1., with a Brattice type multi-rotor aerocraft alighting gear for guide functions, this alighting gear is fixedly connected with aircraft body bottom aircraft body; It is characterized in that, this alighting gear is the structure of the frustum of hollow, the upper following table of this frustum structure is the identical and equilateral polygon of correspondence of limit number, each side of this frustum structure inwardly concaves and forms circular arc guide face, the central axis of this guide face and the line isoplanar of upper following table geometric centre and angle is acute angle A, the upper table surface of this frustum structure alighting gear is provided with and the installation sheet be fixedly connected with bottom aircraft body; Described installation sheet is fixedly connected with the bottom of aircraft body by bolt of rear end plate; And this alighting gear and aircraft body to be fixedly connected with rear described each guide face mutually corresponding with the rotor in aircraft body.
2. a kind of Brattice type multi-rotor aerocraft alighting gear with guide functions as claimed in claim 1, is characterized in that, the equilateral polygon corresponding up and down of described frustum structure is square.
3. a kind of Brattice type multi-rotor aerocraft alighting gear with guide functions as claimed in claim 1, it is characterized in that, described alighting gear specifically adopts the shape of hollow Brattice type structure, and described alighting gear specifically adopts lightweight carbon fiber sheet structure to make.
4. a kind of Brattice type multi-rotor aerocraft alighting gear with guide functions as claimed in claim 1, it is characterized in that, described installation sheet specifically adopts the oblong schistose texture of 2 Bi-metal Steel Aluminums, is conducive to strengthening Joint strenght.
5. a kind of Brattice type multi-rotor aerocraft alighting gear with guide functions as claimed in claim 1, is characterized in that, the bolt that described bolt of rear end plate specifically adopts 4 PVC plastic materials to make.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420612781.5U CN204279926U (en) | 2014-10-23 | 2014-10-23 | A kind of Brattice type multi-rotor aerocraft alighting gear with guide functions |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420612781.5U CN204279926U (en) | 2014-10-23 | 2014-10-23 | A kind of Brattice type multi-rotor aerocraft alighting gear with guide functions |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204279926U true CN204279926U (en) | 2015-04-22 |
Family
ID=52863113
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420612781.5U Expired - Fee Related CN204279926U (en) | 2014-10-23 | 2014-10-23 | A kind of Brattice type multi-rotor aerocraft alighting gear with guide functions |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204279926U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108248851A (en) * | 2018-02-02 | 2018-07-06 | 郑州轻工业学院 | Aircraft for the device for protecting aircraft rotor and with the device |
| CN108945402A (en) * | 2017-05-26 | 2018-12-07 | 深圳光启合众科技有限公司 | Undercarriage for vertically taking off and landing flyer |
| CN109383765A (en) * | 2017-08-07 | 2019-02-26 | 波音公司 | Damping device for exposed undercarriage chamber |
-
2014
- 2014-10-23 CN CN201420612781.5U patent/CN204279926U/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108945402A (en) * | 2017-05-26 | 2018-12-07 | 深圳光启合众科技有限公司 | Undercarriage for vertically taking off and landing flyer |
| CN109383765A (en) * | 2017-08-07 | 2019-02-26 | 波音公司 | Damping device for exposed undercarriage chamber |
| CN109383765B (en) * | 2017-08-07 | 2023-08-25 | 波音公司 | Drag reducer for exposed landing gear cavity |
| CN108248851A (en) * | 2018-02-02 | 2018-07-06 | 郑州轻工业学院 | Aircraft for the device for protecting aircraft rotor and with the device |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| 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: 20150422 Termination date: 20161023 |