CN204210730U - Landing gear uplock mechanism - Google Patents
Landing gear uplock mechanism Download PDFInfo
- Publication number
- CN204210730U CN204210730U CN201420538328.4U CN201420538328U CN204210730U CN 204210730 U CN204210730 U CN 204210730U CN 201420538328 U CN201420538328 U CN 201420538328U CN 204210730 U CN204210730 U CN 204210730U
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- Prior art keywords
- rocking arm
- unblanking
- latch hook
- unblank
- landing gear
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- Expired - Lifetime
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Abstract
The utility model discloses an undercarriage uplock mechanism, including the latch hook, with holding spring that the latch hook links to each other, can promote the rocking arm and the drive of unblanking of latch hook unblanking the actuating cylinder of unblanking the rocking arm, wherein, the rocking arm of unblanking includes integrative coaxial pivoted rocking arm, mechanical rocker arm and the latch key of unblanking, the tip of latch key is equipped with the gyro wheel in order to promote the latch hook. The landing gear upper lock mechanism of the utility model has simple and compact structure, high utilization rate, larger acting moment of the mechanical unlocking rocker arm, more labor-saving unlocking and improved operability; the addition of the roller can effectively avoid the impact of the locking key and the locking hook, obviously reduce the frictional resistance of the locking key and the locking hook, protect the locking key from being damaged, and improve the maintainability of the mechanism.
Description
Technical field
The utility model relates generally to aeronautical engineering technical field, particularly relates to a kind of civil aircraft landing gear uplock mechanism.
Background technology
Uplock is that gear up is in the anchor fitting of end position, the functional reliability of reliability on Landing Gear System of latch mechanism has very important impact, according to made, once there is multiple aircraft model that uplock occurred and normally can not open the serious aviation accident caused.Usually, uplock mechanism mainly contains hook ring type and block type two kinds, wherein hook ring type refers to that the lock ring on alighting gear moving member hooks by the latch hook be arranged on uplock mechanism, thus moving member is fixed on desired position, and this is the form that civil aircraft uplock is conventional.Must open uplock in advance during drop, therefore the unlocking function of uplock first needs to ensure.Fig. 1 and Fig. 2 shows existing a kind of hook ring type landing gear uplock mechanism.In the lockout condition, as shown in Figure 1, pressurized strut 21 of unblanking is failure to actuate, and latch hook 26 keeps the locking of the lock ring to alighting gear under the action of the spring 28.When implementing when adopting hydraulic actuation to unblank, there is the pressurized strut 21 of unblanking of oil inlet 22 and return opening 23 by operating bar 24 pairs of locking key 25 applied thrusts, and then promotion latch hook 26 deflection disengaging lock ring realizes unblanking.When adopting mechanical, hand-driven to unblank, mechanical force can be applied to machinery rocking arm 27 of unblanking, and then drive locking key 25 to realize unblanking by drive spindle 29.Although this kind of uplock mechanism can realize the unlocking function to alighting gear lock ring, but complex structure, parts are various, layout and operation are all comparatively complicated, on the other hand, locking key by clash into and the mode of cliding friction is implemented, requires higher to the intensity of locking key and latch hook and surface treatment to the effect of latch hook.Therefore, the efficient cooperation and reliable use that how to realize each parts in uplock mechanism become those skilled in the art's problem demanding prompt solution.
Utility model content
The purpose of this utility model is to be improved existing landing gear uplock mechanism, a kind of novel hook ring type landing gear uplock mechanism is proposed, it comprises latch hook, the keep-spring be connected with described latch hook, can promote the pressurized strut of unblanking of unblank rocking arm and the rocking arm of unblanking described in driving of described latch hook, wherein, described rocking arm of unblanking comprises the rocking arm of normally unblanking of coaxial rotation of one, machinery unblanks rocking arm and locking key, and the end of described locking key is provided with roller to promote described latch hook.
According to a kind of preferred implementation, the unblank length of rocking arm of described machinery is three times of the length of described rocking arm of normally unblanking, thus increases machinery and to unblank the applied moment of rocking arm.
According to a kind of embodiment, described in unblank to be provided with in pressurized strut normally unblank piston and the emergent unlocking piston of linkage, and rocking arm of unblanking described in being promoted by the piston rod of described emergent unlocking piston.Can realize respectively according to actual needs normally unblanking and emergent unlocking thus.
According to a kind of embodiment, described in unblank pressurized strut by hydraulic actuation, be provided with normal oil inlet, emergent oil inlet and return opening.But those skilled in the art also can recognize that employing pneumatic mode realizes start.
Advantageously, unblank rocking arm and described latch hook of described rocking arm of normally unblanking, described machinery limits range of deflection by stop ledge.According to a kind of embodiment, the maximum actuating travel of pressurized strut of unblanking described in described stop ledge is provided so that is 35mm, and the maximum deflection angle of described latch hook is 22.6 °.
According to a kind of embodiment, described keep-spring one end connects described latch hook, and the other end connects the stop ledge of described rocking arm of normally unblanking.
As can be seen from above-mentioned general introduction, the advantage according to landing gear uplock mechanism of the present utility model is:
1, rocking arm actv. of normally unblank rocking arm and machinery for subsequent use being unblanked is molded as one and coaxial rotation, and structure is simple, easy to assembly, space availability ratio is high;
2, the unblank length of rocking arm of machinery is longer, and thus applied moment is comparatively large, unblanks more laborsaving, improves operability;
3, in locking key, increase roller, connect latch hook by roller, actv. avoids locking key and latch hook clashes into, and changes the cliding friction of locking key and latch hook into friction of rolling, and friction drag significantly reduces; On the other hand, roller is changed convenient, and maintainability and economy are significantly improved.
Accompanying drawing explanation
More multiple features of the present utility model and advantage are by by understanding better below in conjunction with the further description of accompanying drawing to preferred implementation.In accompanying drawing:
Fig. 1 is the schematic diagram of the hook ring type landing gear uplock mechanism of prior art, and uplock mechanism is now in locking state;
Fig. 2 is in the schematic diagram of unlocking condition for landing gear uplock mechanism existing shown in Fig. 1;
Fig. 3 is the schematic diagram of the hook ring type landing gear uplock mechanism according to a kind of embodiment of the utility model, and uplock mechanism is now in locking state;
The schematic diagram that Fig. 4 is unblanked by hydraulic efficiency pressure system for the landing gear uplock mechanism of hook ring type shown in Fig. 3;
The schematic diagram that Fig. 5 is unblanked by mechanical rocking arm of unblanking for the landing gear uplock mechanism of hook ring type shown in Fig. 3.
Detailed description of the invention
Discuss enforcement and the use of embodiment below in detail.But, should be appreciated that discussed specific embodiment only exemplarily illustrates and implement and use ad hoc fashion of the present utility model, and unrestricted scope of the present utility model.
Fig. 3 shows the hook ring type landing gear uplock mechanism according to a kind of embodiment of the utility model.In this uplock mechanism, latch hook 11 can be clamped by coupled keep-spring 12 and the lock ring (not shown) of alighting gear and lock realization and lock.When implementing to unblank, the rocking arm of unblanking driven by pressurized strut 1 of unblanking can promote latch hook 11 and deflects disengaging lock ring thus realize unblanking.In this embodiment, rocking arm of unblanking comprises and is fabricated to one and can the rocking arm 15 of normally unblanking of coaxial rotation, machinery unblanks rocking arm 7 and locking key 13, and the end of wherein locking key 13 is provided with roller 9 to promote latch hook 11.Normally unblank piston 3 and the emergent unlocking piston 2 of linkage is provided with in described pressurized strut 1 of unblanking.When adopting hydraulic actuation, normal oil inlet 4, emergent oil inlet 5 and return opening 6 can be provided with, promote to unblank rocking arm by the piston rod of emergent unlocking piston 2, be specially promotion and normally to unblank rocking arm 15, normal fluid pressure can be realized respectively and to unblank and hydraulic pressure of meeting an urgent need is unblanked.
According to a favourable aspect of the present utility model, the unblank length of rocking arm 7 of machinery can be set to normally to unblank three times of length of rocking arm 15, as shown in Figure 3.In this way, when the mechanical rocking arm 7 of unblanking of use carries out unblanking, because moment is comparatively large, the required power applied of operator is relatively little, and it is more light easy to operate.
Also can find out from Fig. 3, be respectively equipped with stop ledge 14 and stop ledge 8 to limit range of deflection for normally unblank rocking arm 15 and machinery rocking arm 7 of unblanking.Equally, latch hook 11 is also provided with stop ledge 10.The position of each stop ledge can set according to range of deflection angles needed for each parts, such as, makes the maximum deflection angle of latch hook 11 be 22.6 °.Be understandable that, the position of the stop ledge 14 coordinated with rocking arm 15 of normally unblanking sets the start scope also determining pressurized strut 1 of unblanking, and such as, in the pressurized strut 1 that makes to unblank, the maximum actuating travel of piston rod is 35mm.Consider the rational deployment of each parts, also one end of keep-spring 12 can be connected latch hook 11, the other end is connected to the stop ledge 14 of rocking arm 15 of normally unblanking.Like this, when comprise normally unblank rocking arm 15 and locking key 13 unblank rocking arm yaw motion time, can not interfere with keep-spring 12.
Below the operating principle of landing gear uplock mechanism of the present utility model is described below:
When gear up is about to put in place, as shown in Figure 3, the piston rod of pressurized strut 1 rocking arm 15 that promotes normally to unblank of unblanking deflects and drives locking key 13 deflection to make the roller 9 of its end promote latch hook 11 to turn an angle, the lock ring of alighting gear is entered in latch hook 11 thereupon.Unblank the immediately piston rod of pressurized strut 1 is packed up, and now under the elastic force effect of the keep-spring 12 be connected with latch hook 11, latch hook 11 is to counter-rotation, and the lock ring of alighting gear is firmly locked in stowed position, realizes locking.
When normal fluid pressure is unblanked, as shown in Figure 4, normal oil inlet 4 passes into high pressure oil and promotes piston 3 of normally unblanking and move, and promotes emergent unlocking piston 2, and the piston rod rocking arm 15 that promotes normally to unblank is deflected.When emergency hydraulic system is unblanked, emergent oil inlet 5 passes into high pressure oil and directly promotes emergent unlocking piston 2 and move.Rocking arm 15 of normally unblanking drives locking key 13 to deflect and makes roller 9 pairs of latch hooks 11 of its end produce a thrust, and latch hook 11 deflects and departs from lock ring, realizes unblanking.
When mechanical system is unblanked, as shown in Figure 5, cable wire can be adopted to pull machinery to unblank rocking arm 7, make machinery unblank rocking arm 7 along rotating counterclockwise in figure, thus make roller 9 pairs of latch hooks 11 produce a thrust, latch hook 11 deflects and departs from lock ring, realizes unblanking.
Be not difficult to draw by foregoing description, simple, compact according to the structure of the hook ring type landing gear uplock mechanism for civil aircraft of the present utility model, degree of utilization is high, and machinery is unblanked, the applied moment of rocking arm is comparatively large, unblanks more laborsaving, improves operability; Roller add the shock effectively can avoiding locking key and latch hook, significantly reduce the friction drag of locking key and latch hook, guard latch is not damaged, and can improve the maintainability of mechanism.
Technology contents of the present utility model and technical characterstic have disclosed as above.Should be understood that, what also described shown in accompanying drawing is only principle of the present utility model, and above-mentioned embodiment exists many alter modes, and these modes are clearly concerning various equivalent modifications.Such as; the planform of each parts shown in figure is only example; conduct is not to restriction of the present utility model; every above embodiment is done according to technical spirit of the present utility model any simple modification, equivalent variations and modification, all fall in the protection domain of technical solutions of the utility model.
Claims (6)
1. landing gear uplock mechanism, comprise latch hook, the keep-spring be connected with described latch hook, the pressurized strut of unblanking of unblank rocking arm and the rocking arm of unblanking described in driving of described latch hook can be promoted, it is characterized in that, described rocking arm of unblanking comprises the rocking arm of normally unblanking of coaxial rotation of one, machinery unblanks rocking arm and locking key, and the end of described locking key is provided with roller to promote described latch hook.
2. landing gear uplock mechanism according to claim 1, is characterized in that, the unblank length of rocking arm of described machinery is three times of the length of described rocking arm of normally unblanking.
3. landing gear uplock mechanism according to claim 1, is characterized in that, described in unblank to be provided with in pressurized strut normally unblank piston and the emergent unlocking piston of linkage, and rocking arm of unblanking described in being promoted by the piston rod of described emergent unlocking piston.
4. landing gear uplock mechanism according to claim 3, is characterized in that, described in unblank pressurized strut by hydraulic actuation, be provided with normal oil inlet, emergent oil inlet and return opening.
5. landing gear uplock mechanism according to claim 1, is characterized in that, unblank rocking arm and described latch hook of described rocking arm of normally unblanking, described machinery limits range of deflection by stop ledge.
6. landing gear uplock mechanism according to claim 5, is characterized in that, described keep-spring one end connects described latch hook, and the other end connects the stop ledge of described rocking arm of normally unblanking.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420538328.4U CN204210730U (en) | 2014-09-18 | 2014-09-18 | Landing gear uplock mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420538328.4U CN204210730U (en) | 2014-09-18 | 2014-09-18 | Landing gear uplock mechanism |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204210730U true CN204210730U (en) | 2015-03-18 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420538328.4U Expired - Lifetime CN204210730U (en) | 2014-09-18 | 2014-09-18 | Landing gear uplock mechanism |
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| CN (1) | CN204210730U (en) |
Cited By (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106081071A (en) * | 2016-06-02 | 2016-11-09 | 江西洪都航空工业集团有限责任公司 | A kind of Novel electric door trip cam trigger mechanism |
| CN106428518A (en) * | 2016-11-29 | 2017-02-22 | 四川凌峰航空液压机械有限公司 | Upper lock turnover device of cabin door |
| CN107036745A (en) * | 2017-04-24 | 2017-08-11 | 西北工业大学 | Latch hook staring torque measurement apparatus and method for uplock reliability test |
| CN107380406A (en) * | 2017-07-13 | 2017-11-24 | 江西洪都航空工业集团有限责任公司 | A kind of aircraft backplate joins breaking mechanism |
| CN107600394A (en) * | 2017-09-08 | 2018-01-19 | 中航飞机起落架有限责任公司 | A kind of electronic upper locking device of undercarriage |
| CN107719647A (en) * | 2017-09-22 | 2018-02-23 | 北京航空航天大学 | High reliability unmanned plane undercarriage control system |
| CN107757945A (en) * | 2017-09-12 | 2018-03-06 | 陕西飞机工业（集团）有限公司 | A kind of measurement apparatus for aircraft nose landing gear uplock emergent unlocking |
| CN108100237A (en) * | 2017-11-30 | 2018-06-01 | 江西洪都航空工业集团有限责任公司 | A kind of type aircraft backplate joins breaking mechanism |
| CN111169624A (en) * | 2020-03-11 | 2020-05-19 | 中国民用航空飞行学院 | Undercarriage uplock structure for aviation emergency |
| CN112572779A (en) * | 2020-12-04 | 2021-03-30 | 中国航空工业集团公司成都飞机设计研究所 | Electrically driven passive pillar upper lock |
| CN112623198A (en) * | 2020-12-29 | 2021-04-09 | 中国航空工业集团公司西安飞机设计研究所 | Lifting type undercarriage lower lock |
| CN113955090A (en) * | 2021-12-17 | 2022-01-21 | 江西洪都航空工业集团有限责任公司 | Integral landing gear uplock |
| CN114313229A (en) * | 2021-12-15 | 2022-04-12 | 中国航空工业集团公司成都飞机设计研究所 | Upper lock of full electric aircraft |
| CN114599586A (en) * | 2019-10-17 | 2022-06-07 | 赛峰起落架系统公司 | Equipped with upper lock for holding detection device |
| CN115111235A (en) * | 2022-06-27 | 2022-09-27 | 北京航天发射技术研究所 | Manual and pneumatic dual-purpose connector locking and dropping mechanism |
| US12187417B2 (en) | 2023-05-01 | 2025-01-07 | Safran Landing Systems Canada Inc. | Retractable landing gear system with magnetic uplocks |
-
2014
- 2014-09-18 CN CN201420538328.4U patent/CN204210730U/en not_active Expired - Lifetime
Cited By (24)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106081071A (en) * | 2016-06-02 | 2016-11-09 | 江西洪都航空工业集团有限责任公司 | A kind of Novel electric door trip cam trigger mechanism |
| CN106428518B (en) * | 2016-11-29 | 2018-08-07 | 四川凌峰航空液压机械有限公司 | Hatch door uplock turnover device |
| CN106428518A (en) * | 2016-11-29 | 2017-02-22 | 四川凌峰航空液压机械有限公司 | Upper lock turnover device of cabin door |
| CN107036745A (en) * | 2017-04-24 | 2017-08-11 | 西北工业大学 | Latch hook staring torque measurement apparatus and method for uplock reliability test |
| CN107036745B (en) * | 2017-04-24 | 2019-05-17 | 西北工业大学 | Latch hook staring torque measuring device and method for uplock reliability test |
| CN107380406A (en) * | 2017-07-13 | 2017-11-24 | 江西洪都航空工业集团有限责任公司 | A kind of aircraft backplate joins breaking mechanism |
| CN107380406B (en) * | 2017-07-13 | 2020-04-28 | 江西洪都航空工业集团有限责任公司 | Aircraft backplate allies oneself with disconnected mechanism |
| CN107600394A (en) * | 2017-09-08 | 2018-01-19 | 中航飞机起落架有限责任公司 | A kind of electronic upper locking device of undercarriage |
| CN107757945A (en) * | 2017-09-12 | 2018-03-06 | 陕西飞机工业（集团）有限公司 | A kind of measurement apparatus for aircraft nose landing gear uplock emergent unlocking |
| CN107757945B (en) * | 2017-09-12 | 2020-01-10 | 陕西飞机工业（集团）有限公司 | Measuring device for emergency unlocking of uplock of nose landing gear of airplane |
| CN107719647A (en) * | 2017-09-22 | 2018-02-23 | 北京航空航天大学 | High reliability unmanned plane undercarriage control system |
| CN108100237A (en) * | 2017-11-30 | 2018-06-01 | 江西洪都航空工业集团有限责任公司 | A kind of type aircraft backplate joins breaking mechanism |
| CN108100237B (en) * | 2017-11-30 | 2021-01-05 | 江西洪都航空工业集团有限责任公司 | Novel aircraft backplate allies oneself with disconnected mechanism |
| CN114599586A (en) * | 2019-10-17 | 2022-06-07 | 赛峰起落架系统公司 | Equipped with upper lock for holding detection device |
| CN111169624A (en) * | 2020-03-11 | 2020-05-19 | 中国民用航空飞行学院 | Undercarriage uplock structure for aviation emergency |
| CN111169624B (en) * | 2020-03-11 | 2024-05-28 | 中国民用航空飞行学院 | Landing gear upper lock structure for aviation emergency |
| CN112572779A (en) * | 2020-12-04 | 2021-03-30 | 中国航空工业集团公司成都飞机设计研究所 | Electrically driven passive pillar upper lock |
| CN112623198A (en) * | 2020-12-29 | 2021-04-09 | 中国航空工业集团公司西安飞机设计研究所 | Lifting type undercarriage lower lock |
| CN114313229A (en) * | 2021-12-15 | 2022-04-12 | 中国航空工业集团公司成都飞机设计研究所 | Upper lock of full electric aircraft |
| CN113955090A (en) * | 2021-12-17 | 2022-01-21 | 江西洪都航空工业集团有限责任公司 | Integral landing gear uplock |
| CN113955090B (en) * | 2021-12-17 | 2024-01-30 | 江西洪都航空工业集团有限责任公司 | Integrated landing gear upper lock |
| CN115111235A (en) * | 2022-06-27 | 2022-09-27 | 北京航天发射技术研究所 | Manual and pneumatic dual-purpose connector locking and dropping mechanism |
| CN115111235B (en) * | 2022-06-27 | 2024-03-05 | 北京航天发射技术研究所 | Manual and pneumatic connector locking and falling mechanism |
| US12187417B2 (en) | 2023-05-01 | 2025-01-07 | Safran Landing Systems Canada Inc. | Retractable landing gear system with magnetic uplocks |
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| Date | Code | Title | Description |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term | ||
| CX01 | Expiry of patent term |
Granted publication date: 20150318 |