CN203681866U - Side lock mechanism of unmanned aircraft landing gear - Google Patents
Side lock mechanism of unmanned aircraft landing gear Download PDFInfo
- Publication number
- CN203681866U CN203681866U CN201320212580.1U CN201320212580U CN203681866U CN 203681866 U CN203681866 U CN 203681866U CN 201320212580 U CN201320212580 U CN 201320212580U CN 203681866 U CN203681866 U CN 203681866U
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- lock
- uplock
- locking
- ring bar
- lock ring
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- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
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Abstract
The utility model belongs to the technique of an aircraft takeoff and landing system, relates to specialties of locks and lock mechanism designs and structure designs of the takeoff and landing system, and particularly relates to a side lock mechanism of an unmanned aircraft landing gear. The side lock mechanism comprises an upper lock, a lock ring bar, a docking conversion connector and fastening nuts. The side lock mechanism is characterized in that the docking conversion connector is of a dual-fork lug structure on a landing gear support column; the lock ring bar passes through double fork lugs of the docking conversion connector and is locked by the fastening nuts; the lock ring bar is parallel to the landing gear support column; a lock track plane is vertical to the mounting direction of the upper lock on the machine body.
Description
Technical field
The invention belongs to the aviation landing system technology of taking off, relate to the specialty such as lock and lock mechanism design and structure design of the landing system that takes off, relate in particular to a kind of unmanned plane alighting gear side mechanism for locking up.
Background technology
Alighting gear lock has uplock, down lock, cabin door lock etc.Their normal work is very important, if uplock or cabin door lock block, hinders gear down; Or the down lock inefficacy of locking, alighting gear can not put down and put in place, all can make aircraft damage.
The normal work of alighting gear indicating system is equally quite important, it tell aviator's alighting gear whether in safety put down, locking state.But sometimes have false instruction situation, as undercarriage down and lock, due to indication fault, chaufeur but do not know, or originally gear down unlocked, and improper owing to adjusting, but instruction is locked, and this is all breakneck.
1. down lock
The function of down lock is that undercarriage leg is fixed on to extended position.Therefore not, primary guarantee because interference gets loose after how making it lock smoothly and lock when design.
A) internal lock of retractable actuating cylinder or sleeve-type strut
In undercarriage control pressurized strut or sleeve-type strut, be often with a kind of internal lock: steel ball lock, finger-type lock, retaining ring lock.After locking, make its bar long definite, thereby realize, alighting gear is fixed on to extended position, play down lock effect.Multiplex down lock or the hatch door open position lock of making alighting gear of this lock.
In existing undercarriage design, steel ball is locked, retaining ring lock is comparatively common.
B) shackle lock
The latch hook being arranged on housing construction hooks the lock ring on alighting gear moving member, thereby moving member is fixed on to desired location.The form that this is alighting gear down lock and uplock, cabin door lock is conventional.
C) can holding lever lock
In strut burst, mechanical lock (or shackle lock, link lock) is housed, after locking, its strut can not fold, and can bear Tensile or Compressive Loading.
D) block type down lock
Block type down lock has different version on different aircrafts.Destroying 7 III nose-gear block type down locks is that compact conformation, reliability are a kind of preferably.
2. uplock
The function of uplock is that undercarriage leg is fixed on to retracted position, bears the alighting gear quality load in the each flight situation of aircraft.When blow the gear down, must first open uplock, it is unblanked to be first and will ensure, therefore, uplock should be provided with emergent unlocking system, should be preferably mechanical.
A) hook ring type uplock
BAe.146 Aircraft Main landing gear uplock.Artificial unlocking handle is connected with mechanical emergency unlocking system.
Certain destroys Hong owner's landing gear uplock.The urceolus of aluminum lock housing and the pressurized strut of unblanking is integrated, and guiding clamping plate are housed on it, can ensure that lock ring accurately puts in place and locks when gear up.The pressurized strut of unblanking has three pressure inlets, i.e. oil-feed ozzle, fuel-displaced ozzle, oil return ozzle.When blow the gear down, fluid enters the chamber of unblanking of the pressurized strut of unblanking from oil-feed ozzle, promotes piston rod and unblanks.The oil outlet of inner chamber is opened immediately, has led retractable actuating cylinder, drop so fluid flows into.Folding and unfolding switch returns all logical oil returns of two chambeies of the pressurized strut of unblanking after " neutrality ", can ensure that uplock is locked in retracted position by alighting gear securely, not because the variation of pressure is unblanked.
The lock ring of uplock should be contained in the constant position of relative pillar shaft length, on pillar urceolus; Should not be contained on piston rod (or lower shake-changing arm).Be provided with guiding clamping plate and do not have the hook ring type uplock of guiding clamping plate, its lock ring should be respectively hinged be fixed on pillar.
B) block type uplock
Destroy 7 III aircraft nose-gears and be not only block type down lock, or block type uplock.The locking pin of upper and lower lock and the indentation propulsion source while unblanking thereof are same systems.
While receiving nose-gear, the locking pin 12 on alighting gear angle-shaped piece 11 turns to support arm 4, and slides along its inclined-plane.In the time that alighting gear forwards retracted position to, locking pin, under spring-force driven dual, inserts support arm lower end.Stop nose-gear oppositely to rotate counterclockwise, alighting gear is locked in to retracted position securely.When landing gear switch is placed in retracted position, pressurized strut while entirely stretching, the gap between locking pin and support arm should be 0.2～0.5mm.Landing gear switch is in the time of center position, and this gap is conducted oneself with dignity and disappeared because of alighting gear.The contact rocking arm 7 of micro-switch is also depressed on bridle 9 tops, unclamps micro-switch, and red eye is bright.
When drop, along with pressurized strut is shunk, locking pin 12 is pulled in angle-shaped piece hole, and alighting gear can be freely from propping up
Holding rocking arm produces.Now support arm, because of projection 2 stop, can not be rotated; Uplock rocking arm 7, because bridle 9 leaves and unclamps with alighting gear, rotates under spring-force driven dual, compression micro-switch, and red eye goes out.If during with cable wire landing-gear emergency extension, rocking arm 1 and projection 2 rotate simultaneously, unclamp support arm 4.Under alighting gear Gravitative Loads, rotating support rocking arm, puts down nose-gear.At this moment due to hydraulic system fault, in locking pin not retraction angle-shaped piece hole.
C) hatch door docking lock
Hatch door has off position lock and open position lock, and most typical is hatch door docking lock.
Certain destroys Hong owner's undercarriage door docking lock.Lead side hatch door and lower hatch door in the time of off position, pinned by the retaining ring lock of hatch door pressurized strut.Hatch door docking lock is the support stiffness in order to improve hatch door, is loaded on the front end of two hatch door apposition positions, also hatch door is pinned.This lock adopts a locking key, the pressurized strut control two of unblanking to fan opening and cutting out of hatch door.
Whether synchronously all should ensure to lock for adapting to two hatch door closing movements, the form that has adopted two latch hooks to lock respectively.The constraint direction of latch hook to lock ring after locking, in lock ring path of motion.
D) alighting gear and hatch door UNICOM uplock
Landing gear uplock and backplate interlock are unblanked, and are to connect two rocking arms of unblanking of locking by cable wire to realize.
This is the more easy half mechanical unlocking system of one, and the power that the power of unblanking is provided by hydraulic pressure and cold gas system is respectively realized.Simple in structure, unblank for the uplock of destroying 7 III main landing gears and wheel backplate.But, if wherein certain part goes wrong, by not only affecting putting down of backplate, also affect putting down of alighting gear.From the angle analysis of reliability redundancy design, backplate and alighting gear can increase system reliability with uplock separately respectively.
Summary of the invention
The object of the invention is: invent a kind of side mechanism for locking up that middle-size and small-size unmanned plane uses that is suitable for, can avoid, because installing space is limited, the problem of landing gear uplock being installed, there is the advantages such as design processing is simple, working service is convenient, safe and reliable.
Technical scheme of the present invention is: a kind of unmanned plane alighting gear side mechanism for locking up, this side mechanism for locking up is made up of uplock, lock ring bar, docking adapter substitute and clamp nut, docking adapter substitute is the two fork ear structures that are arranged on undercarriage leg, lock ring bar is through two fork ears of docking adapter substitute, and lock with clamp nut, described lock ring bar is parallel with undercarriage leg, and the trajectory plane of locking is the installation direction on fuselage perpendicular to uplock.
Advantage of the present invention is: a kind of side mechanism for locking up that is suitable for middle-size and small-size unmanned plane use of the present invention.Its outstanding advantages is:
The one, solve uplock installing space problem:
Due to middle-size and small-size unmanned plane landing gear compartment limited space, and the requirement of Landing Gear Design is as far as possible simple, can not as large-scale have people's aircraft can design complicated mechanism.
Middle-size and small-size unmanned plane is generally monowheel chassis, and mechanism for locking up can not be too complicated.Traditional aircraft mechanism for locking up is locked by front, as shown in Figure 1, it is the lock ring bar parallel uplock placement direction of trajectory plane of locking, the plane of movement of wheel and tire and uplock are in a plane, lock ring bar is not also suspended on uplock so, and wheel and tire have just knocked uplock.
There is not this problem in the large-scale people's of having aircraft, because the large-scale people's of having undercarriage is generally two-wheel, after lock ring bar is suspended on uplock, the position of uplock is just in the middle of two wheels.
The 2nd, design processing is simple
Hang the problem of uplock for solving middle-size and small-size unmanned plane monowheel chassis, the lock ring bar only designing by the present invention and docking adapter substitute, directly be connected on the lock ring of existing alighting gear, by uplock side, and be 90 ° with original position, and by the spring lock position of well-designed uplock, just can realize middle-size and small-size unmanned plane monowheel chassis side and lock, as shown in Figures 2 and 3.After padlock, because uplock is at side, will can not interfere with alighting gear wheel and tire.
The 3rd, reliability is high
Due to by the spring lock position of well-designed uplock, ensure that lock and unlock is safe and reliable.After nose-gear is locked, front-wheel is handled electricity under steering wheel, and in quick condition, because the state after locking is with the mechanism for locking up state of conventional airplane, has also ensured the reliability after locking on principle of design.
Prove through large number of ground test and flight test examination, this side mechanism for locking up can meet actual operation requirements, has larger using value.
Brief description of the drawings
Fig. 1 is the conventional airplane lock ring bar direction schematic diagram of locking;
Fig. 2 is the lock ring bar of the present invention direction schematic side view of locking;
Fig. 3 is the lock ring bar of the present invention direction front elevational schematic of locking;
Fig. 4 side mechanism for locking up is installed and work front elevational schematic;
Fig. 5 side mechanism for locking up is installed and work schematic side view;
Wherein, 1 be uplock, 2 for docking adapter substitute, 3 for lock ring bar, 4 for clamp nut, 5 for undercarriage leg, 6 for docking adapter substitute and alighting gear point of connection one, 7 for docking adapter substitute and alighting gear point of connection two, be 8. uplock installing floor board.
Detailed description of the invention
Below in conjunction with accompanying drawing, the present invention is elaborated.Side mechanism for locking up comprises uplock 1, docking adapter substitute 2, lock ring bar 3, clamp nut 4, as shown in Figure 1, Figure 2 and Figure 3.Adapter substitute 2 is connected with alighting gear 5 with alighting gear point of connection two with docking adapter substitute with alighting gear point of connection one by docking adapter substitute, and side mechanism for locking up is installed and worked schematic diagram as shown in Figure 4 and Figure 5.
Embodiment
The first step:
Press Fig. 2 and Fig. 3, manufacture and prepare docking adapter substitute 2, lock ring bar 3, and uplock 1 and clamp nut 4.Wherein, the dimensional data of docking adapter substitute 2 will be coordinated with 7 data mutually with the point of connection of alighting gear 56.The hook mouth size of the diameter of lock ring bar 3 and uplock 1 match (diameters of the corresponding corresponding lock ring bar 3 of different hook mouth size).
Second step:
The 3rd step:
By docking adapter substitute and alighting gear point of connection one and docking adapter substitute and alighting gear point of connection two, the assembly set that connects adapter substitute 2, lock ring bar 3 and clamp nut 4 of state is as shown in Figures 2 and 3 arranged on alighting gear 5.
The 4th step:
Claims (1)
1. a unmanned plane alighting gear side mechanism for locking up, this side mechanism for locking up is made up of uplock, lock ring bar, docking adapter substitute and clamp nut, it is characterized in that, docking adapter substitute is the two fork ear structures that are arranged on undercarriage leg, lock ring bar is through two fork ears of docking adapter substitute, and lock with clamp nut, described lock ring bar is parallel with undercarriage leg, and the trajectory plane of locking is the installation direction on fuselage perpendicular to uplock.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320212580.1U CN203681866U (en) | 2013-04-24 | 2013-04-24 | Side lock mechanism of unmanned aircraft landing gear |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320212580.1U CN203681866U (en) | 2013-04-24 | 2013-04-24 | Side lock mechanism of unmanned aircraft landing gear |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203681866U true CN203681866U (en) | 2014-07-02 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201320212580.1U Expired - Lifetime CN203681866U (en) | 2013-04-24 | 2013-04-24 | Side lock mechanism of unmanned aircraft landing gear |
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| Country | Link |
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| CN (1) | CN203681866U (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104443367A (en) * | 2014-11-06 | 2015-03-25 | 江西洪都航空工业集团有限责任公司 | Undercarriage mechanical lock and locking ring structure thereof |
| CN105502026A (en) * | 2015-11-26 | 2016-04-20 | 庆安集团有限公司 | Slipping-off prevention and restriction device of aircraft containerized system |
| WO2018077299A1 (en) * | 2016-10-31 | 2018-05-03 | 比亚迪股份有限公司 | Landing gear for unmanned aerial vehicle, and unmanned aerial vehicle |
| CN111605700A (en) * | 2019-02-25 | 2020-09-01 | 空中客车营运有限公司 | Aircraft Landing Gear Upper Lock System |
| CN114383934A (en) * | 2022-01-10 | 2022-04-22 | 中航飞机起落架有限责任公司 | Loading device and method for hook-and-loop lock ring test of landing gear |
| CN114802720A (en) * | 2022-02-18 | 2022-07-29 | 成都飞机工业（集团）有限责任公司 | Undercarriage guard plate linkage mechanism and machining method thereof |
-
2013
- 2013-04-24 CN CN201320212580.1U patent/CN203681866U/en not_active Expired - Lifetime
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104443367A (en) * | 2014-11-06 | 2015-03-25 | 江西洪都航空工业集团有限责任公司 | Undercarriage mechanical lock and locking ring structure thereof |
| WO2016070479A1 (en) * | 2014-11-06 | 2016-05-12 | 江西洪都航空工业集团有限责任公司 | Mechanical lock for landing gear and lock ring mechanism thereof |
| CN105502026A (en) * | 2015-11-26 | 2016-04-20 | 庆安集团有限公司 | Slipping-off prevention and restriction device of aircraft containerized system |
| CN105502026B (en) * | 2015-11-26 | 2017-09-12 | 庆安集团有限公司 | A kind of anti-skidding restraint device of aircraft staging system |
| WO2018077299A1 (en) * | 2016-10-31 | 2018-05-03 | 比亚迪股份有限公司 | Landing gear for unmanned aerial vehicle, and unmanned aerial vehicle |
| CN111605700A (en) * | 2019-02-25 | 2020-09-01 | 空中客车营运有限公司 | Aircraft Landing Gear Upper Lock System |
| CN114383934A (en) * | 2022-01-10 | 2022-04-22 | 中航飞机起落架有限责任公司 | Loading device and method for hook-and-loop lock ring test of landing gear |
| CN114383934B (en) * | 2022-01-10 | 2023-11-21 | 中航飞机起落架有限责任公司 | Landing gear hook ring lock ring test loading device and method |
| CN114802720A (en) * | 2022-02-18 | 2022-07-29 | 成都飞机工业（集团）有限责任公司 | Undercarriage guard plate linkage mechanism and machining method thereof |
| CN114802720B (en) * | 2022-02-18 | 2024-06-11 | 成都飞机工业（集团）有限责任公司 | Landing gear guard plate linkage mechanism and processing method thereof |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CP01 | Change in the name or title of a patent holder | ||
| CP01 | Change in the name or title of a patent holder |
Address after: 610091 planning and Development Department of Chengdu aircraft design and Research Institute, 1610 Riyue Avenue, Qingyang District, Chengdu City, Sichuan Province Patentee after: AVIC CHENGDU AIRCRAFT DESIGN & Research Institute Address before: 610091 planning and Development Department of Chengdu aircraft design and Research Institute, 1610 Riyue Avenue, Qingyang District, Chengdu City, Sichuan Province Patentee before: AVIC CHENGDU AIRCRAFT DESIGN & Research Institute |
|
| CX01 | Expiry of patent term | ||
| CX01 | Expiry of patent term |
Granted publication date: 20140702 |