CN106628130A - Unmanned aerial vehicle nose landing gear shock absorption and steering mechanism - Google Patents
Unmanned aerial vehicle nose landing gear shock absorption and steering mechanism Download PDFInfo
- Publication number
- CN106628130A CN106628130A CN201611216931.0A CN201611216931A CN106628130A CN 106628130 A CN106628130 A CN 106628130A CN 201611216931 A CN201611216931 A CN 201611216931A CN 106628130 A CN106628130 A CN 106628130A
- Authority
- CN
- China
- Prior art keywords
- undercarriage
- landing gear
- steering
- unmanned aerial
- mounting seat
- 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.)
- Granted
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/50—Steerable undercarriages; Shimmy-damping
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/58—Arrangements or adaptations of shock-absorbers or springs
- B64C25/62—Spring shock-absorbers; Springs
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Steering-Linkage Mechanisms And Four-Wheel Steering (AREA)
Abstract
The invention belongs to the field of unmanned aerial vehicle nose landing gear structure/mechanism design, and relates to a nose landing gear suitable for small and medium-sized unmanned aerial vehicles. A landing gear steering rocker arm (1), a pin shaft (2), an installation base (3), a landing gear bumper post (4) and a compression spring (5) are included. The purposes are to improve steering of existing unmanned aerial vehicle nose landing gears and the force transmission characteristic of shock absorption mechanisms and decrease the number and the weight of structural parts. According to the nose landing gear, steering and buffering by two degrees of freedom are simultaneously achieved through an annular groove, an axial groove and the pin shaft, the number of parts is greatly decreased, the structure complexity and the manufacturing cost of the landing gear are reduced, and the reliability is improved; and as the landing gear post and an installation sleeve always have the maximum length of fit at any moment, the lateral rigidity is good, and the force bearing capacity of the parts is good.
Description
Technical field
The invention belongs to unmanned plane nose-gear structure/mechanism design field, is related to a kind of suitable small and medium size unmanned aerial vehicles
Nose-gear.
Background technology
The nose-gear requirement of unmanned plane is lightweight, and the rigidity of structure is good, and with turning function and good damping performance.
General unmanned plane nose-gear has independent steering mechanism and damping, and both series connection form practical structures, have led
Frame fall in elongation state, the fit dimension between undercarriage leg and sleeve is short, and transmission force property is poor, weight and size is big, laterally
Rigidity is low.The easily lateral bending deformation in the presence of lateral load in landing, or cause fuselage to roll in sliding race.
The content of the invention
It is an object of the invention to provide a kind of unmanned plane nose-gear damping steering mechanism, is risen and fallen with meeting all kinds of unmanned planes
The needs that frame is developed.
The technical scheme is that：
A kind of unmanned plane nose-gear damping steering mechanism, it is characterised in that including undercarriage pitman arm (1), bearing pin
(2), mounting seat (3), undercarriage damper leg (4), compression spring (5), wherein, undercarriage pitman arm (1), mounting seat (3),
Undercarriage damper leg (4) three is installed together by bearing pin (2), and bearing pin (2) sequentially passes through from outside to inside undercarriage steering
The circumferential slot on circular hole, mounting seat (3) on rocking arm (1), the axial groove on undercarriage damper leg (4), bearing pin (2) can pass through
Installing shaft block ring at two ends prevents abjection, and compression spring (5) is housed between mounting seat (3) and undercarriage damper leg (4),
Buffering is provided when undercarriage is impacted, mounting seat (3) is fixedly mounted on housing construction, undercarriage pitman arm by flange
(1) it is connected with steering-engine, transmits steering moment.
When steering-engine drives undercarriage pitman arm (1) to rotate, undercarriage pitman arm (1) is moved by bearing pin (2)
Undercarriage damper leg (4) is driven to rotate around pillar axes.Divertical motion does not interfere with each other with kicking motion.
Circumferential slot terminal position in mounting seat (3) provides the limit spacing of front-wheel steer.Undercarriage damper leg (4)
On axial groove terminal position determine state and maximum cushioning stroke that undercarriage freely extends.
It is an advantage of the invention that：
The present invention permeates steering mechanism and damping mechanism, greatly reduces number of parts and construction weight.
It is in-house without any securing member.Contact distance between undercarriage leg and sleeve so that transmission force property is good.Have concurrently simultaneously
Turn to the function with damping.Because number of parts is few, low cost of manufacture, reliability is high.Simultaneously because mechanism's non-bolt, the rivet
It is easy for installation Deng securing member and bearing.
Description of the drawings
Fig. 1 is structural representation after assembling of the invention.
Fig. 2 is the structural blast schematic diagram of the present invention.
Wherein, undercarriage pitman arm (1), bearing pin (2), mounting seat (3), undercarriage damper leg (4), compression spring
(5)。
Specific embodiment
The present invention is elaborated below.
Undercarriage in the present invention (contains machine by undercarriage pitman arm (1), mounting seat (3), undercarriage damper leg (4)
Wheel), bearing pin (2), compression spring (5) be assembled together.Bearing pin (2) is sequentially passed through from outside to inside on undercarriage pitman arm (1)
Circular hole, circumferential slot, the axial groove on undercarriage damper leg (4) in mounting seat (3).Bearing pin (2) can be by pacifying at two ends
Dress shaft block ring prevents abjection.Compression spring (5) is housed between mounting seat (3) and undercarriage damper leg (4), in undercarriage
Buffering is provided when being impacted.
When undercarriage stress is compressed, undercarriage damper leg (4) is moved upwards, and bearing pin (2) is in undercarriage buffering
Move relatively downward in axial groove in post (4), but because the restriction of undercarriage pitman arm (1) and bearing pin (2) can't be produced
It is raw to rotate.When the length of the axial groove is designed, it is defined by undercarriage buffer distance, while in the ginseng of design compression spring (5)
To ensure that maximum compression stroke lower spring is not compacted during number.
When spring parameter is designed, to should ensure that and there are enough pretightning forces after installation.The pretightning force should be at least above during shutdown
The dead load of nose-gear, to prevent undesirable negative ground angle.
When steering-engine drives undercarriage pitman arm (1) to rotate, undercarriage pitman arm (1) is moved by bearing pin (2)
Undercarriage damper leg (4) is driven to rotate around pillar axes.Bearing pin (2) slides in the circumferential slot of mounting seat (3).Should in design
During the center of circle angle range of circumferential slot, the scope and mounting seat (3) of Nose Wheel Steering angle residual intensity in this place should be considered.
The circumferential well width of axial groove and mounting seat (3) in undercarriage damper leg (4) should be with the diameter shape of bearing pin (2)
Coordinate into small―gap suture, and groove edge should as far as possible ensure linearity and flatness, to ensure to rotate flexible.Can apply in sliding position
Smear grease to reduce force of sliding friction.
Claims (1)
1. a kind of unmanned plane nose-gear damping steering mechanism, it is characterised in that including undercarriage pitman arm (1), bearing pin
(2), mounting seat (3), undercarriage damper leg (4), compression spring (5), wherein, undercarriage pitman arm (1), mounting seat (3),
Undercarriage damper leg (4) three is installed together by bearing pin (2), and bearing pin (2) sequentially passes through from outside to inside undercarriage steering
The circumferential slot on circular hole, mounting seat (3) on rocking arm (1), the axial groove on undercarriage damper leg (4), bearing pin (2) can pass through
Installing shaft block ring at two ends prevents abjection, and compression spring (5) is housed between mounting seat (3) and undercarriage damper leg (4),
Buffering is provided when undercarriage is impacted, mounting seat (3) is fixedly mounted on housing construction, undercarriage pitman arm by flange
(1) it is connected with steering-engine, transmits steering moment.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611216931.0A CN106628130B (en) | 2016-12-26 | 2016-12-26 | A kind of unmanned plane nose-gear damping steering mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611216931.0A CN106628130B (en) | 2016-12-26 | 2016-12-26 | A kind of unmanned plane nose-gear damping steering mechanism |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106628130A true CN106628130A (en) | 2017-05-10 |
| CN106628130B CN106628130B (en) | 2019-03-19 |
Family
ID=58827960
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611216931.0A Active CN106628130B (en) | 2016-12-26 | 2016-12-26 | A kind of unmanned plane nose-gear damping steering mechanism |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106628130B (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109835472A (en) * | 2019-03-22 | 2019-06-04 | 西北工业大学 | A kind of small drone column support type spring nose-gear |
| CN112722324A (en) * | 2021-01-19 | 2021-04-30 | 浙江吉利控股集团有限公司 | Vertical take-off and landing electric aircraft test platform |
| 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 |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB421223A (en) * | 1933-06-20 | 1934-12-17 | George Herbert Dowty | Improvements relating to tail wheels for aircraft |
| GB533111A (en) * | 1939-10-09 | 1941-02-06 | Gen Aircraft Ltd | Improvements in aircraft landing gear |
| CN103057693A (en) * | 2012-12-25 | 2013-04-24 | 天津三爻航空航天科技发展有限公司 | Fixed wing aircraft tail wheel steering apparatus |
| CN103523212A (en) * | 2012-07-06 | 2014-01-22 | 哈尔滨飞机工业集团有限责任公司 | Nose landing gear of aircraft |
| CN104192303A (en) * | 2014-09-15 | 2014-12-10 | 沈阳飞机工业（集团）有限公司 | Small nose landing gear for unmanned aerial vehicle |
| CN204399469U (en) * | 2014-12-04 | 2015-06-17 | 天津全华时代航天科技发展有限公司 | A kind of unmanned plane alighting gear |
| CN205076034U (en) * | 2015-10-16 | 2016-03-09 | 河南翱翔航空科技有限公司 | Unmanned aerial vehicle nose -gear |
-
2016
- 2016-12-26 CN CN201611216931.0A patent/CN106628130B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB421223A (en) * | 1933-06-20 | 1934-12-17 | George Herbert Dowty | Improvements relating to tail wheels for aircraft |
| GB533111A (en) * | 1939-10-09 | 1941-02-06 | Gen Aircraft Ltd | Improvements in aircraft landing gear |
| CN103523212A (en) * | 2012-07-06 | 2014-01-22 | 哈尔滨飞机工业集团有限责任公司 | Nose landing gear of aircraft |
| CN103057693A (en) * | 2012-12-25 | 2013-04-24 | 天津三爻航空航天科技发展有限公司 | Fixed wing aircraft tail wheel steering apparatus |
| CN104192303A (en) * | 2014-09-15 | 2014-12-10 | 沈阳飞机工业（集团）有限公司 | Small nose landing gear for unmanned aerial vehicle |
| CN204399469U (en) * | 2014-12-04 | 2015-06-17 | 天津全华时代航天科技发展有限公司 | A kind of unmanned plane alighting gear |
| CN205076034U (en) * | 2015-10-16 | 2016-03-09 | 河南翱翔航空科技有限公司 | Unmanned aerial vehicle nose -gear |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109835472A (en) * | 2019-03-22 | 2019-06-04 | 西北工业大学 | A kind of small drone column support type spring nose-gear |
| CN112722324A (en) * | 2021-01-19 | 2021-04-30 | 浙江吉利控股集团有限公司 | Vertical take-off and landing electric aircraft test platform |
| CN112722324B (en) * | 2021-01-19 | 2022-12-20 | 浙江吉利控股集团有限公司 | Vertical take-off and landing electric aircraft test platform |
| 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 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106628130B (en) | 2019-03-19 |
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