CN102336273A - Rolling type universal joint movement mechanism - Google Patents
Rolling type universal joint movement mechanism Download PDFInfo
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- CN102336273A CN102336273A CN2011102727500A CN201110272750A CN102336273A CN 102336273 A CN102336273 A CN 102336273A CN 2011102727500 A CN2011102727500 A CN 2011102727500A CN 201110272750 A CN201110272750 A CN 201110272750A CN 102336273 A CN102336273 A CN 102336273A
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- sidewinder
- side rolling
- sleeve
- rolling shaft
- shaft sleeve
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Abstract
The invention belongs to the field of mechanical structure design, and particularly relates to an improvement of a universal joint movement mechanism. The rolling type universal joint movement mechanism is characterized by comprising seven parts including a fixed support seat, an actuator cylinder, a rocker arm connecting rod mechanism, a side rolling shaft, a sleeve of the side rolling shaft, a side rolling fork lug and an oil filling pipe connecting support seat, and the like, wherein the sleeve of the side rolling shaft comprises a front end cover, a cylinder body and a rear end cover; the connection relationship of the components is as follows: the fixed support seat is connected with the actuator cylinder, a rocker arm and the sleeve of the side rolling shaft in a way of hinge joint; the actuator cylinder is connected with the rocker arm in a way of hinge joint; a connecting rod is connected with the sleeve of the side rolling shaft in a way of hinge joint; the side rolling shaft is arranged in the sleeve of the side rolling shaft and is supported by a bearing and a bushing; the side rolling shaft passes through the rear end cover of the sleeve of the side rolling shaft and is closely fixed with the side rolling fork lug by a bolt; and the side rolling fork lug is connected with the oil filling pipe connecting support seat in a way of hinge joint. The rolling type universal joint movement mechanism is simple in the fundamental principle, fast in installation and debugging and convenient to maintain, and is capable of meeting the use requirement of an oil filling pipe which flexibly moves in a control envelope curve of an airplane.
Description
Technical field
The invention belongs to the Design of Mechanical Structure field, be specifically related to improvement a kind of Hooke's coupling kinematic mechanism.
Background technology
The present invention is different from traditional universal-joint, forked element or X conn, need utilize the rolling characteristics of this mechanism to keep the direction and the air-flow performance of installation shaft to be complementary domestic this kind rolling type Hooke's coupling kinematic mechanism that never designed before this.Applicant not discovery feature, the similar Hooke's coupling kinematic mechanism of principle in the patent documentation that has retrieved.
In European patent GB586271, disclosed a kind of device that in process is dropped a bomb in underriding, is used to improve the aircraft ken, be the cam link rocker arm body, its function and principle all have very big difference with the present invention.
In Chinese patent CN02823572.X, disclosed a kind of tunable arrangement, utilized two lockable ball pivots to realize universal movement, be used for realizing firmly fixing putting in place temporarily with Hooke's coupling.
Domestic more Hooke's coupling mechanism patent is used for vehicle transmission.In Chinese patent CN200480017182.8, disclosed a kind of Hooke's coupling; It is maximum and along with from then on leaving the resistance applying mechanism that diminishes gradually when pivot angle is 0 ° that this Hooke's coupling is provided with drag loading for the oscillating motion of spider arm; To suppress the change of the transmitting torque between the input and output shaft; This Hooke's coupling is used on the auto steerer, can improves and handle sense.
The swing fuel filler pipe of KC-135A is through waving the realization side travel around vertical axis, the section of fuel filler pipe can not can be complementary by gentle fluidity.This Hooke's coupling kinematic mechanism and KC-10A aircraft universal joint mechanism are similar; Rotate the side travel of realizing the fuel filler pipe end around major axis through making the fuel filler pipe installation shaft; The direction of installation shaft keeps the section of fuel filler pipe and its air-flow performance to be complementary; By comparison, this programme anufacturability and maintainability are better, also have many places to improve on the local detail.
Summary of the invention
The object of the invention: task of the present invention is to make the direction of fuel filler pipe installation shaft keep the section of fuel filler pipe and its air-flow performance to be complementary, and in work envelope curve limit range, all can realize control.Its objective is to make fuel filler pipe flexible motion in the control envelope curve of aircraft that assurance aircraft refuelling pipe docks and disengagement with the refueled aircraft socket.
Technical scheme of the present invention is:
A kind of rolling type Hooke's coupling kinematic mechanism; It is characterized in that, by fixed bearing, pressurized strut, rocker-arm link mechanism, sidewinder axle, sidewinder shaft sleeve, sidewinder fork ear, fuel filler pipe and connect bearing seven parts and form, wherein; Sidewindering shaft sleeve is made up of three parts; Comprise front end cover, cylindrical shell and rear side housing, the annexation of said modules is: fixed bearing is with pressurized strut, rocking arm and sidewinder shaft sleeve and be connected through articulated manner, and pressurized strut adopts articulated manner to be connected with rocking arm; Connecting rod with sidewinder shaft sleeve and be connected through articulated manner; Sidewinder axle and in sidewindering shaft sleeve, support, sidewinder axle and pass and sidewinder the shaft sleeve rear side housing and sidewinder the fork ear, sidewinder the fork ear and be connected bearing with fuel filler pipe and pass through the articulated manner connection through bolt tightening through bearing and lining.
Said fixed bearing is made up of pressurized strut fixed bearing, rocking arm fixed bearing, sleeve fixed bearing three parts.
Said length of connecting rod is adjustable.
Said cylindrical shell adopts bolt tightening with sidewindering a front and rear cover, and front end cover is an enclosed construction, and rear side housing leaves and sidewinders shaft through-hole.
Said connecting rod is connected through articulated manner with the front end cover that sidewinders shaft sleeve.
Said sleeve fixed bearing with sidewinder the shaft sleeve rear side housing and be connected through articulated manner.
Beneficial effect of the present invention is: it is blank that the present invention has filled up domestic prior art.Its advantage is that groundwork is simple, and Installation and Debugging are quick, and maintenance and repair is convenient, can satisfy the operating needs of fuel filler pipe flexible motion in the control envelope curve of aircraft.This Hooke's coupling kinematic mechanism uses general aeronautical material commonly used to process, and the installation adjustment is simple, has practiced thrift manufacturing cost greatly.
Description of drawings
Fig. 1: mechanism's level attitude lateral plan
Fig. 2: mechanism's level attitude birds-eye view
Fig. 3: sidewinder the shaft sleeve cutaway view
Fig. 4: mechanism's favorite places
Fig. 5: mechanism's extended position
Fig. 6: the side direction lift-over of mechanism
Wherein, the 1-fixed bearing, the 2-pressurized strut, 3-rocker-arm link mechanism, 4-sidewinders axle; 5-sidewinders shaft sleeve, and 6-sidewinders the fork ear, and the 7-fuel filler pipe connects bearing, 8-fuel filler pipe, 9-pressurized strut fixed bearing; 10-rocking arm fixed bearing, 11-sleeve fixed bearing, 12-barrel forward end lid, 13-sleeve cylindrical shell, 14-sleeve rear end lid; The 15-bearing, 16-lining, 17-rocking arm, 18-pull bar.
The specific embodiment
Through the specific embodiment the present invention is further described below:
During favorite places, sidewinder the axle bigger with the angle of airframe horizontal reference line, make fuel filler pipe be close to airframe and be covered up.When putting down fuel filler pipe, pressurized strut is rotated around hinge A through rocker-arm link mechanism urges sleeve, sidewinders axle and reduces with aircraft horizontal reference line angle; Hinge B position moves down; Apart from becoming far away, fuel filler pipe serves as axle luffing up and down with hinge B from airframe, and sidewindering axle can rotate in sleeve; Through the side direction lift-over that the fork ear is realized fuel filler pipe of sidewindering that is connected with it; Under the aerodynamic force effect, keep the section of fuel filler pipe to be complementary, the action radius of fuel filler pipe increased with its air-flow performance, realize making fuel filler pipe in the control envelope curve of aircraft flexible motion, guarantee docking and the purpose of disengagement of aircraft refuelling pipe and refueled aircraft socket.
This Hooke's coupling kinematic mechanism is used in certain aircraft breadboard part, and the direction of installation shaft keeps the section of fuel filler pipe and its air-flow performance to be complementary, and fuel filler pipe is flexible motion in the control envelope curve of aircraft, in work envelope curve limit range, all can realize control.
Claims (6)
1. rolling type Hooke's coupling kinematic mechanism; It is characterized in that; By fixed bearing (1), pressurized strut (2), rocker-arm link mechanism (3), sidewinder axle (4), sidewinder shaft sleeve (5), sidewinder fork ear (6), fuel filler pipe and connect bearing (7) seven parts and form; Wherein, Sidewinder shaft sleeve and comprise front end cover (12), cylindrical shell (13) and rear side housing (14), the annexation of said modules is: fixed bearing (1) is with pressurized strut (2), rocking arm (11) and sidewinder shaft sleeve (5) and be connected through articulated manner, and pressurized strut (2) adopts articulated manner to be connected with rocking arm (17); Connecting rod (18) with sidewinder shaft sleeve (5) and be connected through articulated manner; Sidewinder axle (4) and during sidewindering shaft sleeve (5), support, sidewinder axle (4) and pass and sidewinder shaft sleeve rear side housing (10) and sidewinder fork ear (6), sidewinder fork ear (6) and be connected bearing (7) with fuel filler pipe and pass through the articulated manner connection through bolt tightening through bearing (15) and lining (16).
2. rolling type Hooke's coupling kinematic mechanism according to claim 1 is characterized in that, said fixed bearing is made up of pressurized strut fixed bearing (9), rocking arm fixed bearing (10), sleeve fixed bearing (11) three parts.
3. rolling type Hooke's coupling kinematic mechanism according to claim 1 is characterized in that, said connecting rod (18) adjustable length.
4. rolling type Hooke's coupling kinematic mechanism according to claim 1 is characterized in that, said cylindrical shell (13) adopts bolt tightening with sidewindering a front and rear cover, and front end cover (12) is an enclosed construction, and rear side housing (14) leaves and sidewinders shaft through-hole.
5. rolling type Hooke's coupling kinematic mechanism according to claim 1 is characterized in that, said connecting rod (18) is connected through articulated manner with the front end cover that sidewinders shaft sleeve (12).
6. rolling type Hooke's coupling kinematic mechanism according to claim 1 is characterized in that, said sleeve fixed bearing (11) with sidewinder shaft sleeve rear side housing (14) and be connected through articulated manner.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201110272750.0A CN102336273B (en) | 2011-09-14 | 2011-09-14 | Rolling type universal joint movement mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201110272750.0A CN102336273B (en) | 2011-09-14 | 2011-09-14 | Rolling type universal joint movement mechanism |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102336273A true CN102336273A (en) | 2012-02-01 |
| CN102336273B CN102336273B (en) | 2014-08-06 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201110272750.0A Active CN102336273B (en) | 2011-09-14 | 2011-09-14 | Rolling type universal joint movement mechanism |
Country Status (1)
| Country | Link |
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| CN (1) | CN102336273B (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103423028A (en) * | 2013-08-09 | 2013-12-04 | 中国航空工业集团公司沈阳发动机设计研究所 | Two-dimensional nozzle throat area control mechanism |
| CN109625299A (en) * | 2018-12-11 | 2019-04-16 | 四川航空工业川西机器有限责任公司 | A kind of adjustable air refueling pipe |
| CN115424496A (en) * | 2022-08-31 | 2022-12-02 | 北京蓝天航空科技股份有限公司 | Air refueling training simulation system |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB586271A (en) * | 1940-08-01 | 1947-03-13 | James Blacklock Henderson | Improvements in aircraft sights for use in aiming bombs during a dive |
| US4129270A (en) * | 1977-06-13 | 1978-12-12 | The Boeing Company | Air refueling boom pivot gimbal arrangements |
| CN1596356A (en) * | 2001-11-27 | 2005-03-16 | 瑞尼斯豪公司 | Adjustable device with universal joints |
| CN1809705A (en) * | 2003-06-20 | 2006-07-26 | 日本精工株式会社 | Universal joint |
| CN101898641A (en) * | 2010-03-15 | 2010-12-01 | 王雪松 | Air oil-receiving device |
-
2011
- 2011-09-14 CN CN201110272750.0A patent/CN102336273B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB586271A (en) * | 1940-08-01 | 1947-03-13 | James Blacklock Henderson | Improvements in aircraft sights for use in aiming bombs during a dive |
| US4129270A (en) * | 1977-06-13 | 1978-12-12 | The Boeing Company | Air refueling boom pivot gimbal arrangements |
| CN1596356A (en) * | 2001-11-27 | 2005-03-16 | 瑞尼斯豪公司 | Adjustable device with universal joints |
| CN1809705A (en) * | 2003-06-20 | 2006-07-26 | 日本精工株式会社 | Universal joint |
| CN101898641A (en) * | 2010-03-15 | 2010-12-01 | 王雪松 | Air oil-receiving device |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103423028A (en) * | 2013-08-09 | 2013-12-04 | 中国航空工业集团公司沈阳发动机设计研究所 | Two-dimensional nozzle throat area control mechanism |
| CN103423028B (en) * | 2013-08-09 | 2015-08-12 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of two-dimensional nozzle throat area control mechanism |
| CN109625299A (en) * | 2018-12-11 | 2019-04-16 | 四川航空工业川西机器有限责任公司 | A kind of adjustable air refueling pipe |
| CN115424496A (en) * | 2022-08-31 | 2022-12-02 | 北京蓝天航空科技股份有限公司 | Air refueling training simulation system |
| CN115424496B (en) * | 2022-08-31 | 2023-09-26 | 北京蓝天航空科技股份有限公司 | Aerial refueling training simulation system |
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| Publication number | Publication date |
|---|---|
| CN102336273B (en) | 2014-08-06 |
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