CN103057693A - Fixed wing aircraft tail wheel steering apparatus - Google Patents
Fixed wing aircraft tail wheel steering apparatus Download PDFInfo
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- CN103057693A CN103057693A CN 201210576001 CN201210576001A CN103057693A CN 103057693 A CN103057693 A CN 103057693A CN 201210576001 CN201210576001 CN 201210576001 CN 201210576001 A CN201210576001 A CN 201210576001A CN 103057693 A CN103057693 A CN 103057693A
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- wing aircraft
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Abstract
The invention provides a fixed wing aircraft tail wheel steering apparatus, which belongs to the technical field of fixed wing aircrafts. The apparatus comprises a fuselage connecting piece, a support and airplane wheels and is characterized in that a servo steering engine is mounted on the fuselage connecting piece and drives a steering engine rocker arm to swing back and forth, the fuselage connecting piece is further provided with a steering rocker arm, the steering engine rocker arm and the steering rocker arm are connected and driven through a connecting rod and a ball, the support is in fixed connection with the steering rocker arm, and the bottom of the support is provided with the airplane wheels. With such a technical scheme, disadvantages and deficiencies of traditional apparatuses are overcome, a fixed wing aircraft is allowed to travel along a correct course during take-off running and landing running, it is avoided that the aircraft deviates from a take-off or landing course because of incorrect adjustment of tail wheels or inaccurate adjustment of a rudder, and the apparatus is safe and reliable.
Description
Technical field
The invention belongs to the fixed wing aircraft technical field, especially relate to a kind of fixed wing aircraft tail wheel steering hardware.
Background technology
Existing fixed wing aircraft generally adopts the yaw rudder of tail wheel steering hardware and aircraft to link together, and namely controls turning to of tail wheel by the swing of yaw rudder, then controls the sliding direction of running of aircraft.There is certain defective in this device, for example, when tail wheel adjustment wrong or yaw rudder being installed slightly has error will cause taking off slidingly to run or occur the driftage phenomenon during landing run, particularly when the arduouser highway section of condition or landform are taken off landing, can cause aircraft to a certain degree damage in addition serious in also aircraft accident can appear.
Summary of the invention
The problem to be solved in the present invention provides a kind of fixed wing aircraft tail wheel steering hardware, make fixed wing aircraft when starting heats and landing run, can keep correct course, guarantee aircraft can be because of the adjusting of tail wheel wrong or yaw rudder regulate inaccurate and departing from of causing takes off or the phenomenon in the course line of landing, the safety that has improved fixed wing aircraft.
For solving the problems of the technologies described above, the technical solution used in the present invention is: a kind of fixed wing aircraft tail wheel steering hardware, comprise fuselage attaching parts, support and wheel, it is characterized in that: on the described fuselage attaching parts Servo-controller is installed, described Servo-controller drives the swing of steering wheel rocking arm, on the described fuselage attaching parts pitman arm is installed also, described steering wheel rocking arm and pitman arm are by connecting rod and bulb connection for transmission; Described support and pitman arm are for captiveing joint, and the bottom of support is equipped with wheel.
Further, described pitman arm links to each other with the fuselage attaching parts by steering shaft.
Further, between described fuselage attaching parts and the support, shock absorption device is installed vertically.
Further, described shock absorption device is hydraulic damping device.
Further, between described support and the support, and be connected by jump ring between support and the wheel.
Advantage and good effect that the present invention has are: owing to adopt technique scheme, overcome the shortcoming and defect part of conventional apparatus, make fixed wing aircraft when starting heats and landing run, can keep correct course, guarantee aircraft can be because of the adjusting of tail wheel wrong or yaw rudder regulate inaccurate and departing from of causing takes off or the phenomenon in the course line of landing, safe and reliable, failure rate is low etc.
Description of drawings
Fig. 1 is structural representation of the present invention
Among the figure:
1, fuselage attaching parts 2, support 21, jump ring
3, wheel 4, Servo-controller 41, steering wheel rocking arm
5, steering shaft 51, pitman arm 6, connecting rod
61, bulb 7, liquid damper
The specific embodiment
As shown in Figure 1, fixed wing aircraft tail wheel steering hardware provided by the invention, comprise fuselage attaching parts 1, support 2 and wheel 3, wherein, on the described fuselage attaching parts 1 Servo-controller 4 is installed, described Servo-controller 4 drives 1 swing of steering wheel Rocker arm 4, on the described fuselage attaching parts 1 pitman arm 51 is installed also, and described steering wheel Rocker arm 41 and pitman arm 51 are by connecting rod 6 and bulb 61 connection for transmissions; Described support 2 and pitman arm 51 are for captiveing joint, and the bottom of support 2 is equipped with wheel 3.Described pitman arm 51 links to each other with fuselage attaching parts 1 by steering shaft 5.Between described fuselage attaching parts 1 and the support 2, shock absorption device vertically is installed, described shock absorption device is hydraulic damping device 7, adopt the hydraulic shock-absorption mode, than before the spring vibration damper that generally adopts have clearly damping effect, the safety when also further having guaranteed aircraft landing on the other hand.Between support 2 and the support 2, and be connected by jump ring 21 between support 2 and the wheel 3.
Turning to by Servo-controller of fixed wing aircraft tail wheel steering hardware provided by the invention controlled separately, not affected by yaw rudder, and the line Self-adjustment can run away according to the cunning of oneself.When remote manipulation Servo-controller 4, steering wheel Rocker arm 41 meeting swing on the Servo-controller 4, because the effect of connecting rod 6 can drive the swing of pitman arm 51, owing to be captive joint between pitman arm 51 and the tail wheel bracket 2, then can drive the deflection of wheel 3.Thereby can realize the real-time adjustment of the sliding line that runs away.
More than one embodiment of the present of invention are had been described in detail, but described content only is preferred embodiment of the present invention, can not be considered to be used to limiting practical range of the present invention.All equalizations of doing according to the present patent application scope change and improve etc., all should still belong within the patent covering scope of the present invention.
Claims (5)
1. fixed wing aircraft tail wheel steering hardware, comprise fuselage attaching parts, support and wheel, it is characterized in that: on the described fuselage attaching parts Servo-controller is installed, described Servo-controller drives the swing of steering wheel rocking arm, on the described fuselage attaching parts pitman arm is installed also, described steering wheel rocking arm and pitman arm are by connecting rod and bulb connection for transmission; Described support and pitman arm are for captiveing joint, and the bottom of support is equipped with wheel.
2. fixed wing aircraft tail wheel steering hardware according to claim 1, it is characterized in that: described pitman arm links to each other with the fuselage attaching parts by steering shaft.
3. fixed wing aircraft tail wheel steering hardware according to claim 1 is characterized in that: between described fuselage attaching parts and the support, shock absorption device is installed vertically.
4. fixed wing aircraft tail wheel steering hardware according to claim 3, it is characterized in that: described shock absorption device is hydraulic damping device.
5. according to claim 1 to the described fixed wing aircraft tail wheel of 4 arbitrary claims steering hardware, it is characterized in that: between described support and the support, and be connected by jump ring between support and the wheel.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201210576001 CN103057693A (en) | 2012-12-25 | 2012-12-25 | Fixed wing aircraft tail wheel steering apparatus |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201210576001 CN103057693A (en) | 2012-12-25 | 2012-12-25 | Fixed wing aircraft tail wheel steering apparatus |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN103057693A true CN103057693A (en) | 2013-04-24 |
Family
ID=48100657
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201210576001 Pending CN103057693A (en) | 2012-12-25 | 2012-12-25 | Fixed wing aircraft tail wheel steering apparatus |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103057693A (en) |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105197229A (en) * | 2015-10-16 | 2015-12-30 | 河南翱翔航空科技有限公司 | Front landing gear of unmanned aerial vehicle |
| CN105217019A (en) * | 2015-10-16 | 2016-01-06 | 河南翱翔航空科技有限公司 | Unmanned plane horizontal tail wing control mechanism |
| CN106428535A (en) * | 2016-12-02 | 2017-02-22 | 北京尖翼科技有限公司 | Nose landing gear of unmanned aerial vehicle |
| CN106628130A (en) * | 2016-12-26 | 2017-05-10 | 中国航空工业集团公司西安飞机设计研究所 | Unmanned aerial vehicle nose landing gear shock absorption and steering mechanism |
| CN108839791A (en) * | 2018-08-29 | 2018-11-20 | 西安航远数字技术有限公司 | A kind of damping wheel mechanism |
| CN111824365A (en) * | 2020-07-15 | 2020-10-27 | 中船重工（海南）飞船发展有限公司 | Ground effect wing ship landing wheel device |
| CN113022844A (en) * | 2019-12-25 | 2021-06-25 | 海鹰航空通用装备有限责任公司 | Linkage mechanism for tail wheel steering and rudder |
| CN115094760A (en) * | 2022-06-20 | 2022-09-23 | 中国十九冶集团有限公司 | Stay cable hanging device and method for cable-stayed bridge |
-
2012
- 2012-12-25 CN CN 201210576001 patent/CN103057693A/en active Pending
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105197229A (en) * | 2015-10-16 | 2015-12-30 | 河南翱翔航空科技有限公司 | Front landing gear of unmanned aerial vehicle |
| CN105217019A (en) * | 2015-10-16 | 2016-01-06 | 河南翱翔航空科技有限公司 | Unmanned plane horizontal tail wing control mechanism |
| CN106428535A (en) * | 2016-12-02 | 2017-02-22 | 北京尖翼科技有限公司 | Nose landing gear of unmanned aerial vehicle |
| CN106628130A (en) * | 2016-12-26 | 2017-05-10 | 中国航空工业集团公司西安飞机设计研究所 | Unmanned aerial vehicle nose landing gear shock absorption and steering mechanism |
| CN108839791A (en) * | 2018-08-29 | 2018-11-20 | 西安航远数字技术有限公司 | A kind of damping wheel mechanism |
| CN113022844A (en) * | 2019-12-25 | 2021-06-25 | 海鹰航空通用装备有限责任公司 | Linkage mechanism for tail wheel steering and rudder |
| CN111824365A (en) * | 2020-07-15 | 2020-10-27 | 中船重工（海南）飞船发展有限公司 | Ground effect wing ship landing wheel device |
| CN115094760A (en) * | 2022-06-20 | 2022-09-23 | 中国十九冶集团有限公司 | Stay cable hanging device and method for cable-stayed bridge |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20130424 |