CN205087135U - Light fixed -wing aircraft's tail damping device - Google Patents

Light fixed -wing aircraft's tail damping device Download PDF

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Publication number
CN205087135U
CN205087135U CN201520885928.2U CN201520885928U CN205087135U CN 205087135 U CN205087135 U CN 205087135U CN 201520885928 U CN201520885928 U CN 201520885928U CN 205087135 U CN205087135 U CN 205087135U
Authority
CN
China
Prior art keywords
tail
compressed gas
gas spring
fly leaf
wing aircraft
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
Application number
CN201520885928.2U
Other languages
Chinese (zh)
Inventor
陈加华
陈墨
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
GUANGDONG CHENGXING UNMANNED AERIAL VEHICLE COMPANY LIMITED
Original Assignee
GUANGDONG CHENGXING MODELAIRPLANE SCIENCE Co Ltd
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 GUANGDONG CHENGXING MODELAIRPLANE SCIENCE Co Ltd filed Critical GUANGDONG CHENGXING MODELAIRPLANE SCIENCE Co Ltd
Priority to CN201520885928.2U priority Critical patent/CN205087135U/en
Application granted granted Critical
Publication of CN205087135U publication Critical patent/CN205087135U/en
Expired - Fee Related legal-status Critical Current
Anticipated expiration legal-status Critical

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Abstract

The utility model provides a light fixed -wing aircraft's tail damping device, its characterized in that includes rear wheel housing support, damper, damper comprises fly leaf and compressed gas spring, the below at the fly leaf is rotationally installed to the rear wheel housing support, but fly leaf and tail swing joint, the top at the fly leaf is rotationally installed to compressed gas spring one end, the compressed gas spring other end is fixed on the tail. The utility model discloses a cooperateing between rear wheel housing support, compressed gas spring, the fly leaf forms the good shock -absorbing structure of damping performance, its better consumption with absorb the aircraft and at the striking that descends with slide the in -process, improve tailwheel life, the greatly reduced accident risk incidence, its simple structure moreover, it is convenient to maintain, low in manufacturing cost.

Description

A kind of tail shock absorption device of light fixed-wing aircraft
Technical field
The utility model relates to aircraft technology field, more particularly, relates to a kind of tail shock absorption device of light fixed-wing aircraft.
Background technology
Light fixed-wing aircraft has been widely used in the every field such as military affairs in modern society and agricultural, existing light fixed-wing aircraft tail is equipped with tail wheel, tail wheel is air-inflation tyre, namely use pressurized air to carry out support tire and bear certain load, and can consume and absorb aircraft to a certain extent in problems such as the shocks declined and in taxiing procedures, but the tail wheel only by inflation carries out tail damping, its damping performance is poor, landing is easily bounced, even there is the accident potential that blows out, and is absolutely unsafe.
Utility model content
The technical problems to be solved in the utility model is to provide the tail shock absorption device that a kind of structure is simple, have the light fixed-wing aircraft of good damping performance.
In order to solve the problems of the technologies described above, the technical solution adopted in the utility model is as follows:
A kind of tail shock absorption device of light fixed-wing aircraft, it is characterized in that, comprise tail wheel mounting bracket, damping, described damping is made up of portable plate and compressed gas spring, described tail wheel mounting bracket is installed in rotation on the below of portable plate, described portable plate is connected with tail is movable, and described compressed gas spring one end is installed in rotation on the top of portable plate, and the described compressed gas spring other end is fixed on tail.
Further, described portable plate is connected with tail by piano hinge.
Further, described compressed gas spring is provided with two.
Further, described tail wheel mounting bracket is provided with direction controlling bar, and direction controlling bar, for linking with the directional controller on fuselage, can control the line of travel after the landing of tail wheel.
The utility model beneficial effect is against existing technologies: adopt matching between tail wheel mounting bracket, compressed gas spring, portable plate to form the good shock-damping structure of damping performance, it better consumes and absorbs aircraft at the shock declined and in taxiing procedures, improve tail wheel service life, greatly reduce accident risk incidence, and its structure is simple, easy to maintenance, low cost of manufacture.
Below in conjunction with the drawings and specific embodiments, the utility model is described further.
Accompanying drawing explanation
Fig. 1 is the structural representation of the utility model preferred embodiment;
Fig. 2 is the schematic diagram that preferred embodiment shown in Fig. 1 installs tail wheel.
Detailed description of the invention
As shown in Figure 1-2, the tail shock absorption device of light fixed-wing aircraft in the utility model preferred embodiment, comprise tail wheel mounting bracket 1, damping 2, described damping 2 is made up of portable plate 21 and two compressed gas springs 22, described tail wheel mounting bracket 1 is installed in rotation on the below of portable plate 21, described portable plate 21 is connected with tail by piano hinge 3, described compressed gas spring 22 one end 221 is installed in rotation on the top of portable plate 21, described compressed gas spring 22 other end 222 is fixed on tail, described tail wheel mounting bracket 1 is provided with direction controlling bar 4.
The foregoing is only preferred embodiment of the present utility model, be not used for limiting practical range of the present utility model; Namely all equivalents done according to right of the present utility model, are right of the present utility model and cover.

Claims (4)

1. the tail shock absorption device of a light fixed-wing aircraft, it is characterized in that, comprise tail wheel mounting bracket, damping, described damping is made up of portable plate and compressed gas spring, described tail wheel mounting bracket is installed in rotation on the below of portable plate, described portable plate is connected with tail is movable, and described compressed gas spring one end is installed in rotation on the top of portable plate, and the described compressed gas spring other end is fixed on tail.
2. the tail shock absorption device of light fixed-wing aircraft as claimed in claim 1, is characterized in that: described portable plate is connected with tail by piano hinge.
3. the tail shock absorption device of light fixed-wing aircraft as claimed in claim 1, is characterized in that: described compressed gas spring is provided with two.
4. the tail shock absorption device of light fixed-wing aircraft as claimed in claim 1, is characterized in that: described tail wheel mounting bracket is provided with direction controlling bar.
CN201520885928.2U 2015-11-03 2015-11-03 Light fixed -wing aircraft's tail damping device Expired - Fee Related CN205087135U (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201520885928.2U CN205087135U (en) 2015-11-03 2015-11-03 Light fixed -wing aircraft's tail damping device

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201520885928.2U CN205087135U (en) 2015-11-03 2015-11-03 Light fixed -wing aircraft's tail damping device

Publications (1)

Publication Number Publication Date
CN205087135U true CN205087135U (en) 2016-03-16

Family

ID=55477845

Family Applications (1)

Application Number Title Priority Date Filing Date
CN201520885928.2U Expired - Fee Related CN205087135U (en) 2015-11-03 2015-11-03 Light fixed -wing aircraft's tail damping device

Country Status (1)

Country Link
CN (1) CN205087135U (en)

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Legal Events

Date Code Title Description
C14 Grant of patent or utility model
GR01 Patent grant
C56 Change in the name or address of the patentee
CP01 Change in the name or title of a patent holder

Address after: 515800 Xifeng Industrial Zone, Chenghai District, Guangdong, Shantou

Patentee after: GUANGDONG CHENGXING UNMANNED AERIAL VEHICLE COMPANY LIMITED

Address before: 515800 Xifeng Industrial Zone, Chenghai District, Guangdong, Shantou

Patentee before: Guangdong Chengxing Modelairplane Science Company Limted

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: 20160316

Termination date: 20181103