CN103640704A - Rotary extending-retracting mechanism of exposed device of aircraft - Google Patents
Rotary extending-retracting mechanism of exposed device of aircraft Download PDFInfo
- Publication number
- CN103640704A CN103640704A CN201310612207.XA CN201310612207A CN103640704A CN 103640704 A CN103640704 A CN 103640704A CN 201310612207 A CN201310612207 A CN 201310612207A CN 103640704 A CN103640704 A CN 103640704A
- Authority
- CN
- China
- Prior art keywords
- equipment
- aircraft
- rocking arm
- exposed
- retracting mechanism
- 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
Links
Images
Abstract
The invention relates to a rotary extending-retracting mechanism of an exposed device of an aircraft and belongs to the technical field of aircraft manufacturing. The rotary extending-retracting mechanism comprises a device cabin doorway frame, a rocker arm, a doorway frame connecting structure, an adjustable connecting rod, a contact switch, a driving rocker arm, a device cabin structure wall board, a connecting bolt, a driving rotation shaft, a following-up base, a device base, the exposed device, a device rotation shaft and a limiting structure. The rotary extending-retracting mechanism can achieve a rotary extending-retracting function of the device on the aircraft, has the advantages of being stable in transmission, reliable in fixing, light in weight and the like, is a novel rotary extending-retracting mechanism for the extending device required to be shortened by the aircraft and effectively utilizes a limited installing space of the aircraft.
Description
Technical field
The present invention relates to a kind of aircraft exposed equipment rotation jack, belong to aircraft manufacturing technical field.
Background technology
Conventionally, aircraft is in order to complete specific task, need to load the equipment of some outstanding aircraft surfaces, as photoelectric platform equipment, large-scale antenna etc., wherein only of short duration use within some specific time period of some equipment, if be directly installed on aircraft surfaces, can affect pneumatic, the Stealth Fighter of aircraft.This kind equipment adopts folding and unfolding design can actv. to improve the pneumatic and Stealth Fighter of aircraft.
Conventional jack is vertical folding and unfolding form, and the longitudinal space of aircraft is had relatively high expectations, and affects the structural arrangement of aircraft.
Summary of the invention
In order to overcome above-mentioned defect, the object of the present invention is to provide a kind of steadily, registration effectively utilize the aircraft exposed equipment rotation jack in space.
To achieve these goals, the present invention adopts following technical scheme:
An aircraft exposed equipment rotation jack, this mechanism comprises equipment compartment doorway frame, rocking arm, mouthful frame connecting structure, adjustable connecting-rod, contact switch, driving rocking arm, equipment compartment construction panels, tie bolt, drive shaft, servo-actuated pedestal, equipment base, exposed equipment, equipment S. A., position limiting structure;
Equipment compartment construction panels, equipment compartment doorway frame are connected mutually by mouth frame connecting structure, form the equipment compartment of erecting equipment, by tie bolt, on construction panels, are connected with Flight Vehicle Structure; Drive shaft is fixed on equipment compartment construction panels, drive rocking arm be connected with drive shaft on, along with identical rotation is done in rotating shaft, adjustable connecting-rod one end is connected in and is driven on rocking arm by bearing, when driving rocking arm rotation, regulating connecting rod is done translation and is added rotation, and the adjustable connecting-rod other end is connected on rocking arm by bearing; Exposed equipment is fixed on servo-actuated pedestal by equipment base, and servo-actuated pedestal and rocking arm are connected.Thereby the equipment of realization rotates out of my cabin.When turning to when contact switch touches position limiting structure, close rotary power, equipment is stabilized in design point position.
When drive shaft is along arrow counter-rotation, optoelectronic device is done the motion contrary with emitting hatch door, in income hatch door
The present invention has the following advantages:
Mechanism of the present invention can realize vehicle-borne equipment rotation draw-in and draw-off function, has stable drive, the fixing advantage such as reliable, lightweight, for needing overhanging equipment in short-term that a kind of rotation jack of novelty is provided on aircraft.This mechanism's actv. has utilized the limited installing space of aircraft.
Accompanying drawing explanation
Fig. 1 is state of kinematic motion 1 structural representation of the present invention.
Fig. 2 is state of kinematic motion 2 structural representations of the present invention.
Fig. 3 is state of kinematic motion 3 structural representations of the present invention.
Fig. 4 is state of kinematic motion 4 structural representations of the present invention.
Fig. 5 receives status architecture schematic diagram in exposed equipment of the present invention.
Fig. 6 is exposed equipment working state structure schematic diagram of the present invention.
The specific embodiment
Below in conjunction with accompanying drawing 1,2,3,4,5,6, describe the present invention:
An aircraft exposed equipment rotation jack, this mechanism comprises equipment compartment doorway frame 1, rocking arm 2, mouthful frame connecting structure 3, adjustable connecting-rod 4, contact switch 5, drives rocking arm 6, equipment compartment construction panels 7, tie bolt 8, drive shaft 9, servo-actuated pedestal 10, equipment base 11, exposed equipment 12, equipment S. A. 13, position limiting structure 14;
Equipment compartment construction panels 7, equipment compartment doorway frame 1 are connected mutually by mouth frame connecting structure 3, form the equipment compartment of erecting equipment, by tie bolt 8, on construction panels, are connected with Flight Vehicle Structure.In order to realize exposed equipment 12, emit out of my cabin, the function of assigned address in income cabin, as Fig. 1-4, drive shaft 9 is fixed on equipment compartment construction panels 7, first be that power fluid potential source promotes drive shaft, drive rocking arm 6 be connected with drive shaft on, along with identical rotation is done in rotating shaft, adjustable connecting-rod 4 one end are connected in and are driven on rocking arm by bearing, when driving rocking arm rotation, adjustable connecting-rod is done translation and is added rotation, the adjustable connecting-rod other end is connected on rocking arm 2 by bearing, regulating connecting rod can be done the fine setting of length direction, guarantee the initial of connecting rod setting accuracy and equipment, end position.Connecting rod pulls rocking arm 2 winding apparatus S. A.s 13 to do the rotation contrary with drive shaft, and rocking arm 2 is connected with servo-actuated pedestal, and when rocking arm 2 rotates, servo-actuated pedestal is done therewith around driver S. A. and rotated.Exposed equipment 12 is fixed on servo-actuated pedestal by equipment base 11.During servo-actuated pedestal rotation, can from equipment compartment doorway frame 1, put down and regain with equipment.Turn to when contact switch 5 touches position limiting structure 14 and close the locked kinematic link of hydraulic efficiency power unit, equipment is stabilized in design point position.
When drive shaft 9 is along arrow counter-rotation, equipment is done the motion contrary with emitting hatch door, in income hatch door, (presses motion shown in Fig. 1-4).
Described exposed equipment 12 can be optoelectronic device.
Claims (1)
1. aircraft exposed equipment rotates a jack, and this mechanism comprises equipment compartment doorway frame (1), rocking arm (2), mouthful frame connecting structure (3), adjustable connecting-rod (4), contact switch (5), drives rocking arm (6), equipment compartment construction panels (7), tie bolt (8), drive shaft (9), servo-actuated pedestal (10), equipment base (11), exposed equipment (12), equipment S. A. (13), position limiting structure (14);
It is characterized in that: equipment compartment construction panels (7), equipment compartment doorway frame (1) are connected mutually by a mouthful frame connecting structure (3), form the equipment compartment of erecting equipment, by tie bolt (8), on construction panels, are connected with Flight Vehicle Structure; Drive shaft (9) is fixed on equipment compartment construction panels (7), drive rocking arm (6) be connected with drive shaft (9) on, along with identical rotation is done in rotating shaft, adjustable connecting-rod (4) one end is connected in and is driven on rocking arm by bearing, when driving rocking arm rotation, regulating connecting rod is done translation and is added rotation, and adjustable connecting-rod (4) other end is connected on rocking arm (2) by bearing; It is upper that exposed equipment (12) is fixed on servo-actuated pedestal (10) by equipment base (11), and servo-actuated pedestal (10) is connected with rocking arm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310612207.XA CN103640704B (en) | 2013-11-28 | 2013-11-28 | A kind of aircraft exposed equipment rotates jack |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310612207.XA CN103640704B (en) | 2013-11-28 | 2013-11-28 | A kind of aircraft exposed equipment rotates jack |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103640704A true CN103640704A (en) | 2014-03-19 |
| CN103640704B CN103640704B (en) | 2016-01-06 |
Family
ID=50246044
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310612207.XA Active CN103640704B (en) | 2013-11-28 | 2013-11-28 | A kind of aircraft exposed equipment rotates jack |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103640704B (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109573034A (en) * | 2018-12-30 | 2019-04-05 | 成都纵横大鹏无人机科技有限公司 | Jack and unmanned plane |
| CN109606618A (en) * | 2018-12-14 | 2019-04-12 | 中航沈飞民用飞机有限责任公司 | A kind of hatch door timesharing driving mechanism and its application |
| CN112208770A (en) * | 2020-10-10 | 2021-01-12 | 江西洪都航空工业集团有限责任公司 | Linkage retraction device for cabin door of exposed equipment of airplane |
| CN115783330A (en) * | 2023-02-08 | 2023-03-14 | 成都纵横大鹏无人机科技有限公司 | Unmanned aerial vehicle nacelle rotary retraction mechanism and unmanned aerial vehicle |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20050211844A1 (en) * | 2004-02-13 | 2005-09-29 | Airbus France | Seat rail for aircraft cabin and method of manufacturing such a rail |
| RU2268765C1 (en) * | 2004-11-10 | 2006-01-27 | Открытое акционерное общество Таганрогский авиационный научно-технический комплекс им. Г.М. Бериева | Water intake device for fire-fighting seaplane |
| DE102005034975A1 (en) * | 2005-07-22 | 2007-01-25 | Hce Consulting + Engineering Horst Herrmann | Drive for e.g. power glider, has carrier, where jet engine is extended and retracted over carrier by single hand movement, carrier is arranged over central point and hand lever is supported on base plate |
| CN200951833Y (en) * | 2006-07-11 | 2007-09-26 | 青岛天骄无人机遥感技术有限公司 | Photographic rotating platform |
| CN102849219A (en) * | 2012-09-27 | 2013-01-02 | 中国科学院长春光学精密机械与物理研究所 | Omni-directional damping single-freedom-degree photoelectric reconnaissance platform device |
-
2013
- 2013-11-28 CN CN201310612207.XA patent/CN103640704B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20050211844A1 (en) * | 2004-02-13 | 2005-09-29 | Airbus France | Seat rail for aircraft cabin and method of manufacturing such a rail |
| RU2268765C1 (en) * | 2004-11-10 | 2006-01-27 | Открытое акционерное общество Таганрогский авиационный научно-технический комплекс им. Г.М. Бериева | Water intake device for fire-fighting seaplane |
| DE102005034975A1 (en) * | 2005-07-22 | 2007-01-25 | Hce Consulting + Engineering Horst Herrmann | Drive for e.g. power glider, has carrier, where jet engine is extended and retracted over carrier by single hand movement, carrier is arranged over central point and hand lever is supported on base plate |
| CN200951833Y (en) * | 2006-07-11 | 2007-09-26 | 青岛天骄无人机遥感技术有限公司 | Photographic rotating platform |
| CN102849219A (en) * | 2012-09-27 | 2013-01-02 | 中国科学院长春光学精密机械与物理研究所 | Omni-directional damping single-freedom-degree photoelectric reconnaissance platform device |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109606618A (en) * | 2018-12-14 | 2019-04-12 | 中航沈飞民用飞机有限责任公司 | A kind of hatch door timesharing driving mechanism and its application |
| CN109573034A (en) * | 2018-12-30 | 2019-04-05 | 成都纵横大鹏无人机科技有限公司 | Jack and unmanned plane |
| CN112208770A (en) * | 2020-10-10 | 2021-01-12 | 江西洪都航空工业集团有限责任公司 | Linkage retraction device for cabin door of exposed equipment of airplane |
| CN112208770B (en) * | 2020-10-10 | 2022-08-26 | 江西洪都航空工业集团有限责任公司 | Cabin door linkage retracting and releasing device for exposed equipment of airplane |
| CN115783330A (en) * | 2023-02-08 | 2023-03-14 | 成都纵横大鹏无人机科技有限公司 | Unmanned aerial vehicle nacelle rotary retraction mechanism and unmanned aerial vehicle |
| CN115783330B (en) * | 2023-02-08 | 2023-04-18 | 成都纵横大鹏无人机科技有限公司 | Unmanned aerial vehicle nacelle rotary retraction mechanism and unmanned aerial vehicle |
Also Published As
| Publication number | Publication date |
|---|---|
| CN103640704B (en) | 2016-01-06 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103640704A (en) | Rotary extending-retracting mechanism of exposed device of aircraft | |
| CN206277401U (en) | A kind of automatic climbing pole machine people | |
| CN103737588A (en) | Multi-freedom-degree controllable spray painting robot | |
| CN201518321U (en) | Reversing-board type solar double-shaft tracking mechanism | |
| CN202765291U (en) | Insect aircraft imitating flapping wing mechanism | |
| CN105064841A (en) | Cabin door opening drive mechanism for torsion bar type airliner | |
| CN204928722U (en) | Can fascinate, turn around, folding solar cell panel bears device | |
| CN209593364U (en) | A kind of folding solar battery board mounting stand | |
| CN103495976B (en) | Box-type goods stacking manipulator | |
| CN203229719U (en) | Actuating mechanism of loom edge folding device | |
| CN202986306U (en) | High-speed rotating plane silk-screen machine | |
| CN101489730A (en) | Power hand tool with a percussion unit | |
| CN201980908U (en) | Hydraulic cylinder type swing mechanism | |
| CN102092632B (en) | Powerless automatic container hoist | |
| CN105656415A (en) | Sun linkage tracking device | |
| CN203383707U (en) | Electric vertical curtain | |
| KR200413647Y1 (en) | Device for tracking sunlight | |
| CN204160476U (en) | Servo four axle stamping mechanical arm | |
| CN108033004B (en) | Tilting system of tilting wing machine | |
| CN204197274U (en) | Civilian depopulated helicopter empennage control setup | |
| CN111181306A (en) | Multi-section worm cylinder | |
| CN102788532A (en) | High-precision combined photoelectric mast set system | |
| CN105227084A (en) | A kind of solar panel bogey of rotatable, twofold | |
| CN105626803A (en) | Cam driving mechanism | |
| CN206885066U (en) | A kind of stopping means of railcar |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |