CN205098463U - Full topography helicopter undercarriage - Google Patents

Full topography helicopter undercarriage Download PDF

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Publication number
CN205098463U
CN205098463U CN201520818620.6U CN201520818620U CN205098463U CN 205098463 U CN205098463 U CN 205098463U CN 201520818620 U CN201520818620 U CN 201520818620U CN 205098463 U CN205098463 U CN 205098463U
Authority
CN
China
Prior art keywords
rotating
support frame
support
leg
telescoping
Prior art date
Application number
CN201520818620.6U
Other languages
Chinese (zh)
Inventor
孟祥睿
盛遵荣
薛冰
张东伟
魏新利
Original Assignee
郑州大学
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by 郑州大学 filed Critical 郑州大学
Priority to CN201520818620.6U priority Critical patent/CN205098463U/en
Application granted granted Critical
Publication of CN205098463U publication Critical patent/CN205098463U/en

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Abstract

The utility model provides a full topography helicopter undercarriage, it includes controller, braced frame and at least three supporting leg, the top of supporting leg is connected braced frame is last, the last horizon sensor that is provided with of braced frame, be provided with rotary mechanism, telescopic machanism and pressure sensor on the supporting leg. The controller is connected respectively rotary mechanism telescopic machanism horizon sensor with pressure sensor, and according to horizon sensor pressure sensor's parameter adjustment the rotation angle and the flexible length of supporting leg. This full topography helicopter undercarriage has the advantage that the full topography of simple structure, safe and reliable and adaptation was taken off and land.

Description

Full landform helicopter landing gear
Technical field
The utility model relates to helicopter landing gear, specifically, relate to a kind of full landform helicopter landing gear.
Background technology
Present helicopter uses at multiple civil area such as medium, logistics, the regional feature complexity of its process is various, there is level land, also high mountain, hills is had, and at present conventional helicopter landing gear is mainly adapted at smooth ground and carries out landing, landing is easily toppled on the slope, causes damage to helicopter machine body or carrying equipment, can not meet in uneven local rising and falling and stop, greatly reduce the applicable ability of helicopter.
In order to solve the problem, it is simple and be suitable for the helicopter landing gear that carries out rising and falling and stopping under full topographic condition to seek a kind of structure, and people are seeking a kind of desirable technical solution always.
Summary of the invention
The purpose of this utility model is for the deficiencies in the prior art, thus the full landform helicopter landing gear providing a kind of structure simple, safe and reliable.
To achieve these goals, the technical scheme that the utility model adopts is: a kind of full landform helicopter landing gear, comprise controller, support frame and at least three supporting legs, the top of described supporting leg is connected on described support frame, and described support frame is provided with horizon sensor;
Described supporting leg comprises supporting leg and lower support leg, described upper supporting leg is connected by the first rotating mechanism with described lower support leg, described upper supporting leg is connected by the second rotating mechanism with described support frame, the S. A. of described first rotating mechanism and the S. A. of described second rotating mechanism are parallel to described support frame respectively, described lower support leg includes telescoping mechanism, described telescoping mechanism is arranged on described lower support midleg, the expansion link of described telescoping mechanism is arranged so that described lower support leg is along its axial stretching along the axis along described lower support leg, the bottom of described lower support leg is provided with pressure sensor,
Described controller connects described first rotating mechanism, described second rotating mechanism, described telescoping mechanism, described horizon sensor and described pressure sensor respectively, and according to the parameter adjustment of described horizon sensor, described pressure sensor the first rotating mechanism and the anglec of rotation of described second rotating mechanism and the collapsing length of described telescoping mechanism.
Based on above-mentioned, described supporting leg is symmetrical arranged along the left and right sides of described support frame.
Based on above-mentioned, described telescoping mechanism is hydraulic telescopic machanism.
Based on above-mentioned, described support frame is provided with the perforation of multiple drag reduction, axially arranging along the fore-and-aft direction in described support frame of described drag reduction perforation.
The utility model hinge structure has substantive distinguishing features and progress, and specifically, the utility model is provided with horizon sensor, can detect the inclined degree of fuselage, to adjust the upper angle of supporting leg and the length of described lower support leg described in each.Furtherly, the lower end of lower support leg described in each of the present utility model is respectively arranged with described pressure sensor, even if when described support frame maintenance level, described lower support leg is also possible unsettled and do not reach preset pressure, and the utility model can adjust the length of described lower support leg according to the situation of described pressure sensor in that case.The utility model structure is simple, safe and reliable and be adapted to the advantage of full landform landing.
Accompanying drawing explanation
Fig. 1 is structural representation of the present utility model.
Fig. 2 is control principle drawing of the present utility model.
In figure, 1. support frame, 11. drag reduction perforation, supporting leg on 21., 22. lower support leg, 3. horizon sensors, 4. the first rotating mechanism, 5. the second rotating mechanism, 6. telescoping mechanism, 7. pressure sensor.
Detailed description of the invention
Below by detailed description of the invention, the technical solution of the utility model is described in further detail.
As depicted in figs. 1 and 2, a kind of full landform helicopter landing gear, comprise controller, support frame 1 and four supporting legs, the top of described supporting leg is connected on described support frame 1, described support frame 1 is provided with horizon sensor 3, to measure described support frame 1 whether level.The number of described supporting leg also can be set according to the weight of the support strength of described supporting leg and helicopter in other embodiments.
Described supporting leg comprises supporting leg 21 and lower support leg 22, described upper supporting leg 21 is connected by the first rotating mechanism 4 with described lower support leg 22, described upper supporting leg 21 is connected by the second rotating mechanism 5 with described support frame 1, the S. A. of described first rotating mechanism 4 and the S. A. of described second rotating mechanism 5 are parallel to described support frame 1 respectively, described lower support leg 22 includes telescoping mechanism 6, described telescoping mechanism 6 is arranged on described lower support midleg, the expansion link of described telescoping mechanism 6 is arranged so that described lower support leg 22 is along its axial stretching along the axis along described lower support leg 22, described in concrete enforcement, telescoping mechanism can be arranged on the middle part of described lower support leg 22, the expansion link of described telescoping mechanism and described lower support leg 22 coaxial line, also described telescoping mechanism can be arranged on the part of one end as described lower support leg 22 for described lower support leg 22, described lower support leg 22 also can be made along the object of its axial stretching.
The bottom of described lower support leg 22 is provided with the pressure sensor 7 that connects described controller for the contact of lower support leg described in perception 22 with ground.
Described controller connects described first rotating mechanism 4, described second rotating mechanism 5, described telescoping mechanism 6, described horizon sensor 3 and described pressure sensor 7 respectively, when described horizon sensor 3 senses horizontal signal, described sensor also adjusts described first rotating mechanism 4, the described anglec of rotation of the second rotating mechanism 5 and the collapsing length of described telescoping mechanism 6 according to the horizontal signal of described horizon sensor 3, makes described support frame 1 maintain horizontality.When described pressure sensor 7 senses that contact does not reach preset pressure, even if when described support frame 1 is level, described first rotating mechanism 4 of described controller adjustment respective support leg, described second rotating mechanism 5 and described telescoping mechanism 6, when contact reaches preset value, respective support leg is fixed.This set can prevent described support frame 1 level and the unsettled situation of one or more supporting leg, keeps the level of described support frame 1 and stable, thus realizes the level of helicopter and stable, is adapted to full landform landing.
Described supporting leg is symmetrical arranged along the left and right sides of described support frame 1, agrees with the constructional feature of helicopter, enhances steadiness of the present utility model.
Described in concrete enforcement, telescoping mechanism 6 is set to hydraulic telescopic machanism, also can be arranged to the telescoping mechanisms such as electric expansion bar, cylinder to reach the object that can stretch.
Described support frame 1 is provided with multiple drag reduction perforation 11, axially arranging along the fore-and-aft direction in described support frame 1 of described drag reduction perforation 11.First described drag reduction perforation 11 can reduce the windage of this helicopter landing frame, and next alleviates the weight of this helicopter landing frame.
Finally should be noted that: above embodiment is only in order to illustrate that the technical solution of the utility model is not intended to limit; Although be described in detail the utility model with reference to preferred embodiment, those of ordinary skill in the field have been to be understood that: still can modify to detailed description of the invention of the present utility model or carry out equivalent replacement to portion of techniques feature; And not departing from the spirit of technical solutions of the utility model, it all should be encompassed in the middle of the technical scheme scope of the utility model request protection.

Claims (4)

1. a full landform helicopter landing gear, is characterized in that: it comprises controller, support frame and at least three supporting legs, and the top of described supporting leg is connected on described support frame, and described support frame is provided with horizon sensor;
Described supporting leg comprises supporting leg and lower support leg, described upper supporting leg is connected by the first rotating mechanism with described lower support leg, described upper supporting leg is connected by the second rotating mechanism with described support frame, the S. A. of described first rotating mechanism and the S. A. of described second rotating mechanism are parallel to described support frame respectively, described lower support leg includes telescoping mechanism, described telescoping mechanism is arranged on described lower support midleg, the expansion link of described telescoping mechanism is arranged so that described lower support leg is along its axial stretching along the axis along described lower support leg, the bottom of described lower support leg is provided with pressure sensor,
Described controller connects described first rotating mechanism, described second rotating mechanism, described telescoping mechanism, described horizon sensor and described pressure sensor respectively, and according to the parameter adjustment of described horizon sensor, described pressure sensor the first rotating mechanism and the anglec of rotation of described second rotating mechanism and the collapsing length of described telescoping mechanism.
2. full landform helicopter landing gear according to claim 1, is characterized in that: described supporting leg is symmetrical arranged along the left and right sides of described support frame.
3. full landform helicopter landing gear according to claim 1 and 2, is characterized in that: described telescoping mechanism is hydraulic telescopic machanism.
4. full landform helicopter landing gear according to claim 3, is characterized in that: described support frame is provided with the perforation of multiple drag reduction, axially arranging along the fore-and-aft direction in described support frame of described drag reduction perforation.
CN201520818620.6U 2015-10-22 2015-10-22 Full topography helicopter undercarriage CN205098463U (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201520818620.6U CN205098463U (en) 2015-10-22 2015-10-22 Full topography helicopter undercarriage

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201520818620.6U CN205098463U (en) 2015-10-22 2015-10-22 Full topography helicopter undercarriage

Publications (1)

Publication Number Publication Date
CN205098463U true CN205098463U (en) 2016-03-23

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Family Applications (1)

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CN201520818620.6U CN205098463U (en) 2015-10-22 2015-10-22 Full topography helicopter undercarriage

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CN (1) CN205098463U (en)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN105667772A (en) * 2016-03-29 2016-06-15 京东方科技集团股份有限公司 Aircraft landing gear, aircraft and aircraft landing method
CN105966602A (en) * 2016-05-19 2016-09-28 郑琳琳 Novel unmanned aerial vehicle
CN106218908A (en) * 2016-09-30 2016-12-14 安徽翼讯飞行安全技术有限公司 A kind of retractable support lever structure of UAV Landing device
CN106379517A (en) * 2016-11-11 2017-02-08 四川省科拓梦无人机科技有限公司 Unmanned plane undercarriage suitable for rough roads
CN107745753A (en) * 2017-10-24 2018-03-02 浙江海洋大学 A kind of transport vehicle of climbing stairs
CN107776691A (en) * 2017-10-24 2018-03-09 浙江海洋大学 A kind of movable bearing chassis and application method
CN108502146A (en) * 2018-03-27 2018-09-07 上海交通大学 Sufficient leg formula helicopter

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN105667772A (en) * 2016-03-29 2016-06-15 京东方科技集团股份有限公司 Aircraft landing gear, aircraft and aircraft landing method
US10124885B2 (en) 2016-03-29 2018-11-13 Boe Technology Group Co., Ltd. Undercarriage for aircraft, aircraft and aircraft landing method
CN105667772B (en) * 2016-03-29 2018-01-26 京东方科技集团股份有限公司 Undercarriage and aircraft, aircraft landing method
CN105966602A (en) * 2016-05-19 2016-09-28 郑琳琳 Novel unmanned aerial vehicle
CN107933897B (en) * 2016-05-19 2020-12-04 江苏锦程航空科技有限公司 Unmanned aerial vehicle based on infrared ray sensor
CN107933897A (en) * 2016-05-19 2018-04-20 蔡留凤 A kind of unmanned plane based on infrared ray sensor
CN106218908A (en) * 2016-09-30 2016-12-14 安徽翼讯飞行安全技术有限公司 A kind of retractable support lever structure of UAV Landing device
CN106379517A (en) * 2016-11-11 2017-02-08 四川省科拓梦无人机科技有限公司 Unmanned plane undercarriage suitable for rough roads
CN107776691A (en) * 2017-10-24 2018-03-09 浙江海洋大学 A kind of movable bearing chassis and application method
CN107776691B (en) * 2017-10-24 2020-05-26 浙江海洋大学 Mobile bearing chassis and use method
CN107745753A (en) * 2017-10-24 2018-03-02 浙江海洋大学 A kind of transport vehicle of climbing stairs
CN108502146A (en) * 2018-03-27 2018-09-07 上海交通大学 Sufficient leg formula helicopter

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Date Code Title Description
GR01 Patent grant
C14 Grant of patent or utility model
CF01 Termination of patent right due to non-payment of annual fee

Granted publication date: 20160323

Termination date: 20171022

CF01 Termination of patent right due to non-payment of annual fee