CN102390526B - Rocker-arm-type bearable lock connecting rod emergency disengagement mechanism, system and method - Google Patents
Rocker-arm-type bearable lock connecting rod emergency disengagement mechanism, system and method Download PDFInfo
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- CN102390526B CN102390526B CN 201110317667 CN201110317667A CN102390526B CN 102390526 B CN102390526 B CN 102390526B CN 201110317667 CN201110317667 CN 201110317667 CN 201110317667 A CN201110317667 A CN 201110317667A CN 102390526 B CN102390526 B CN 102390526B
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Abstract
The invention relates to a rocker-arm-type bearable lock connecting rod emergency disengagement mechanism, system and method and belongs to the technical field of landing gears. The rocker-arm-type bearable lock connecting rod emergency disengagement mechanism mainly comprises a main force-bearing member of a lock connecting rod, a rotating part of the disengagement mechanism, a safety device after disengagement of the mechanism and a blocking device of the rocker arm, wherein the main force-bearing member is composed of an upper lock connecting rod (1), a lower lock connecting rod (2), a pull rod (3), thrust cylindrical rollers (6, 9) and an upper platform (4) and a lower platform (7) of the pull rod; the rotating part of the disengagement mechanism is composed of a spur gear (10), a mixed gear (11), a bevel gear (12), a torsional spring (15) and a rocker arm (13); the safety device after disengagement of the mechanism is composed of a tension spring (14); and the blocking device of the rocker arm is composed of a head-end pulley (16), transitional pulley blocks (17, 18), a tail-end pulley (19), a steel cable (20), a blocking rod (21) and an emergency release system (22). According to the invention, the problem that the emergency release of the landing gear can not be realized under the situation of having no auxiliary power source.
Description
Technical field
The invention belongs to a kind of releasing mechanism, particularly a kind ofly realize that the lock connecting rod breaks away from the technical field of function when being applicable to that alighting gear is emergent and putting
Technical background
Alighting gear is the vitals of aircraft, because Landing Gear System working environment complexity, present generation aircraft vacant lot repetition period is short, so operational failure is more.And in whole Landing Gear System, extension and retraction system is owing to himself mechanism kinematic and control system complexity, and extension and retraction system proportion in whole Landing Gear System operational failure compares higher.In order to improve landing safety, air worthiness regulation stipulates for airplane in transportation category, landing-gear system occur any rationally may lose efficacy or situation that single hydraulic power source, power supply or the equivalent energy lost efficacy under, aircraft should have emergent playing function.
The normal folding and unfolding of undercarriage is that engine installation carries out folding and unfolding by hydraulic pressure folding and unfolding pressurized strut j, the configuration that emergent place system is that cable wire transmission, machinery are unblanked, alighting gear freely puts down and locks by self gravitation and pillar aerodynamic drag behind bypass disc (or blow off valve) release of pressure.Concrete mode is: the aviator hinders gear down in order to avoid produce excessive hydraulic damping mechanical resistance earlier with the pressurized strut release of pressure; Spur the emergent handle of letting go then, cable wire upwards draws i, drives to separate the emergent rocking arm h rotation of uplock, and rocking arm turns to unties uplock, and alighting gear puts down by self gravity and pillar aerodynamic loading, thereby realizes the emergency extension of alighting gear, and principle such as Fig. 4 are shown in 5,6.Modern a lot of type is for simplified control system, and the folding and unfolding of hatch door is not provided with propulsion source separately, the mode of big more options hatch door and alighting gear link gear.As shown in Figure 6, hatch door is connected on the strut p of alighting gear by preceding lock connecting rod l, crossbeam r, back lock connecting rod k, realizes alighting gear and hatch door mechanical linkage.But the suffered aerodynamic loading m of this mechanism's hatch door hinders gear down, and different flight operating mode is very big to the emergent influence of putting of alighting gear, crosses conference when the hatch door aerodynamic drag and causes the alighting gear emergency extension not in place.
In actual engineering, similar models more both domestic and external just occurred because the hatch door aerodynamic drag is excessive, and alighting gear is emergent puts situation not in place, and alighting gear is emergent puts inefficacy.Meet an urgent need and put the landing safety that inefficacy can have a strong impact on aircraft, influence the seaworthiness evidence obtaining of aircraft.Put Problem of Failure for solving to meet an urgent need, military secret often adopts dual mode:
⑴ auxiliary power source: when the active force hydraulic power source lost efficacy, adopt and hold hydraulic power source, driving folding and unfolding pressurized strut is put down alighting gear smoothly and is put in place;
⑵ non-productive operation: under special flight operating mode, alighting gear is met an urgent need when failing to lay down, and aircraft is established an emergent handle in addition, and the aviator spurs handle drop by force.
All do not meet the civil aircraft airworthiness requirement but increase auxiliary hydraulic pressure source and increase pilot operator, so said method and be not suitable for civilian transport plane and airliner etc.The adoptable mode of civilian type is connection mode or the connection location of hatch door for a change, but is subject to the structure space Layout Problem, and aforesaid way often can not be realized.Also have a kind of mode to break away from for bindiny mechanism and the alighting gear that will hinder gear down, but according to airworthiness requirement, the aviator can not have unnecessary additional operations and excessive operating effort, there is not simultaneously auxiliary power source again, therefore realize that with mechanical type mechanism breaks away from relatively difficulty, also do not have concrete type to adopt the mechanical type releasing mechanism to solve emergent problem of putting inefficacy at present.
Summary of the invention
Purpose of the present invention: at some special type, when satisfying normal folding and unfolding, under the prerequisite of the interlock of mechanism and load delivery request, design a lock set connecting rod releasing mechanism and detachment system and method, solve the problem that the emergent playing function of alighting gear lost efficacy effectively.
The lock connecting rod emergency escape mechanism that a kind of rocker-arm can carry, it is characterized in that: comprise the following lock connecting rod of locking connecting rod and linking with alighting gear with the hatch door interlock, the connecting rod of locking has the pull bar installation cavity with the junction of locking connecting rod down, and pull bar is installed in the pull bar installation cavity; Above-mentioned pull bar has upper mounting plate, the above-mentioned connecting rod bottom of locking has the upper mounting plate chamber that cooperates with upper mounting plate, above-mentioned upper mounting plate is embedded in the upper mounting plate chamber, and there is cylindrical roller thrust on the upper and lower surface of this upper mounting plate along circumferential arrangement, makes the company of locking bottom and pull bar top form the thrust roller bearing connection mode; Above-mentioned upper mounting plate is star-like dentalation, and the lower wall surface in upper mounting plate chamber has the star-like groove shape structure that cooperates with this star-like dentalation; Above-mentioned pull bar has lower platform, the above-mentioned connecting rod of lock down top has the lower platform chamber that cooperates with lower platform, above-mentioned lower platform is embedded in the lower platform chamber, and there is cylindrical roller thrust on the upper and lower surface of this lower platform along circumferential arrangement, makes down lock connect portion and pull bar bottom formation thrust roller bearing connection mode; Straight gear also is installed in the above-mentioned pull bar installation cavity, mixes gear, finishing bevel gear cuter, rocking arm and extension spring; Wherein straight gear is coaxial with pull bar and captive joint, mix gear and coaxial connection of an anchor shaft of lock connecting rod down; rocking arm is installed on the connecting rod of locking; and rocking arm one end is coaxial with finishing bevel gear cuter and captive joint; and the other end stretches out the pull bar installation cavity; straight gear partly is meshed with the straight gear of mixing gear, and finishing bevel gear cuter is meshed with the bevel gear part of mixing gear; Extension spring one end is connected with the connecting rod lower part of locking, and the other end is connected with following lock connecting rod top; This emergency escape mechanism comprises that also an end links to each other with above-mentioned pull bar, the torsion spring that the other end links to each other with the above-mentioned connecting rod of lock down.
Utilize the detachment system of the lock connecting rod emergency escape mechanism that described rocker-arm can carry, it is characterized in that: this detachment system is made up of the lock connecting rod emergency escape mechanism that emergent place system, rocking arm arresting system, rocker-arm can carry; The rocking arm arresting system by head end pulley, transition assembly pulley, block, cable wire, block bar and form; Wherein the head end pulley is installed on the rotating part of emergent place system, and rotates with rotating part; Transition assembly pulley and block are installed on the interior framing member of landing gear compartment; The above-mentioned bar that blocks is installed on the block, and blocks axis and the block axis normal of bar; Cable wire one end is connected in the head end pulley, the other end is walked around the transition assembly pulley and is connected with block.
The mode of operation of detachment system as described is characterized in that comprising following process:
(a), when the normal folding and unfolding of Landing Gear System, the lock connecting rod emergency escape mechanism that this rocker-arm can carry realizes the interlock of hatch door mechanism and the transmission of load as a lock connecting rod, concrete working process is as follows: lock connecting rod internal load transfer mode is passed to pull bar for the connecting rod of locking by the thrust roller bearing structure, pull bar is passed to down the lock connecting rod by the thrust roller bearing structure, thereby realizes the transmission of load; During normal folding and unfolding, block bar and pack up, the lock connecting rod is servo-actuated when blocking the bar position, can pass through smoothly, does not influence the normal folding and unfolding of alighting gear;
(b), when alighting gear is in emergent release position, the hatch door load unloading that hinders gear down need be about to lock connecting rod and break away from; The aviator spurs emergent handle, drive emergent laying mechanism rotation, thereby drive the rotation of head end pulley, correspondingly drive the block rotation by cable wire, block bar by the block driven rotary to down state, when the lock connecting rod servo-actuated when blocking the bar position; rocking arm collides and blocks bar and begin to rotate; rocking arm rotating band dynamic bevel gear, and the finishing bevel gear cuter rotation drives the combination tooth wheel, mixes the moving straight gear of gear rotating band; thus drive the pull bar rotation; pull bar with lock connecting rod and down the way of contact of lock connecting rod be the cylindrical roller bearing form, so friction force is less, it is also less to break away from required application force; When the groove of the star-like dentalation of the tooth of the star-like dentalation of pull bar upper mounting plate and upper mounting plate chamber lower wall aligned, the load transmission of the connecting rod of locking was less than pull bar, and the connecting rod of locking is then separated with lock connecting rod down, realizes that the lock connecting rod breaks away from; Locking up and down has extension spring dragging after connecting rod breaks away from, and limits its free motion;
(c) under the normal circumstances, the groove of the star-like dentalation of the tooth of the star-like dentalation of pull bar upper mounting plate and upper mounting plate chamber lower wall aligns, so that transmitted load, can not occur because the situation that the environmental perturbation pull bar freely rotates, therefore for safe and reliable, be connected torsion spring at pull bar with following the lock between connecting rod, be used for the restriction pull bar and do freely rotating of time spent at non-rocking arm, sleeve mechanism is in the state of being lockable.
Principle of the present invention: arresting system directly is connected with emergent laying mechanism, i.e. emergent laying mechanism motion, and arresting system is corresponding working also, so the aviator do not need to increase operation bidirectional, only needs the emergent handle of disposable pulling to get final product.Work and be when blocking bar; the rocking arm bump blocks bar and realizes the rocking arm rotation; rocking arm rotating band dynamic bevel gear; the finishing bevel gear cuter rotation drives combination tooth wheel (half cone tooth half straight-tooth), the combination tooth rotation drives straight gear, thereby drives the pull bar rotation; when pull bar rotates when aligning to the groove of the tooth of the star-like dentalation of upper mounting plate and the star-like dentalation of upper mounting plate chamber lower wall; the load transmission of the connecting rod of locking is less than pull bar, and the connecting rod of locking is then separated with lock connecting rod down, realizes the disengaging of lock connecting rod; Cylindrical roller thrust can bear axial load effectively, the roller force of rolling friction is less simultaneously, these two attributes have solved the lock connecting rod effectively can bear bigger axis load, and the suffered friction force of rotating rod is little simultaneously, namely breaks away from two problems of the little grade of required application force; Amplify transmission by the one-level of mixing gear and straight gear, increase the rocking arm force transmission effectively to the load of pull bar, the rocking arm corner is passed to the pull bar corner and also obtains amplification simultaneously, has increased the margin of safety of body function effectively, has improved mechanism reliability; Torsion spring is used for the restriction pull bar is done the time spent at non-rocking arm free motion; Extension spring is used for restriction lock connecting rod the first half and the free motion of lock connecting rod the latter half after disengaging;
Beneficial effect of the present invention:
(a) this cover releasing mechanism solves effectively there not being the emergent problem of putting inefficacy of alighting gear under the auxiliary power source situation, and restriction hatch door aerodynamic drag and alighting gear gear down broken away from.
(b) realization of this cover releasing mechanism function satisfy do not increase aviator's operation bidirectional, not obvious increase pilot operator power, dialysis after each mechanism can not cause instability or damage three basic design principle because of uncertain motion.
(c) the amplification transmission of this cover releasing mechanism has improved the margin of safety of body function effectively, has improved the reliability of mechanism effectively.
(d) this cover releasing mechanism can be widely used in having the emergent civilian type that discharges the alighting gear function, and the manned aerospace plane of some space industry is applicable to that also some is not provided with the military type of auxiliary folding and unfolding propulsion source
Description of drawings
The lock connecting rod releasing mechanism inner structure detail drawing that accompanying drawing 1 can carry;
The lock connecting rod releasing mechanism external structure scheme drawing that accompanying drawing 2 can carry;
Accompanying drawing 3 arresting system structural representations; A is the rocking arm stowed position; B is the rocking arm extended position;
Accompanying drawing 4 arresting system principle of work scheme drawings; C drives the cable wire travel direction for after the aviator spurs handle; D is for being used for separating the emergent rocking arm of uplock; E is the part of connecting rod and hatch door interlock of locking; F is rocking arm and blocks the bar impingement position; G is for locking the part of connecting rod and alighting gear interlock down;
The combination tooth wheel construction scheme drawing of accompanying drawing 5 half cone teeth half straight-tooth;
Accompanying drawing 6 pull bar assembly parts structural representations;
Accompanying drawing 7 gear up view; H is for separating the emergent rocking arm unlocked position of uplock; I drives the cable wire travel direction for after the aviator spurs handle; J is the folding and unfolding pressurized strut; K is back lock connecting rod; L is preceding lock connecting rod; M is hatch door aerodynamic loading direction; R is crossbeam;
Number in the figure title: 1, the connecting rod of locking, 2, lock connecting rod down, 3, pull bar, 4, upper mounting plate, 5, upper mounting plate chamber, 6, cylindrical roller thrust, 7, lower platform, 8, the lower platform chamber, 9, cylindrical roller thrust, 10, straight gear, 11, mix gear, 12, finishing bevel gear cuter, 13, rocking arm, 14, extension spring, 15, torsion spring, 16, the head end pulley, 17, second pulley, the 18, the 3rd pulley, 19, block, 20, cable wire, 21, block bar, 22, emergent place system, C, pull bar installation cavity.
The specific embodiment:
The lock connecting rod emergency escape mechanism structure detail drawing that rocker-arm can carry is shown in accompanying drawing 1,2, and arresting system mechanism detail drawing is shown in Fig. 3,4.Lock connecting rod emergency escape mechanism that this rocker-arm can carry and the specific embodiment of detachment system will be described here.
The specific embodiment of the lock connecting rod emergency escape mechanism that rocker-arm can carry is:
(a), when the normal folding and unfolding of Landing Gear System, the lock connecting rod emergency escape mechanism that this rocker-arm can carry realizes the interlock of hatch door mechanism and the transmission of load as a lock connecting rod, concrete working process is as follows: lock connecting rod internal load transfer mode is passed to pull bar 3 for the connecting rod 1 of locking by the thrust roller bearing structure, pull bar 3 is passed to lower link 2 by the thrust roller bearing structure, thereby realizes the transmission of load;
During normal folding and unfolding, block bar and be received in a position (as shown in Figure 3), the lock connecting rod is servo-actuated when blocking the bar position, can pass through smoothly, does not influence the normal folding and unfolding of alighting gear.
(b), when alighting gear is in emergent release position, the hatch door load unloading that hinders gear down need be about to lock connecting rod and break away from; The aviator spurs emergent handle, drive emergent laying mechanism rotation, thereby drive 16 rotations of head end pulley, correspondingly drive block 19 rotations by cable wire, block bar by block 19 driven rotary to b position (as shown in Figure 3), when the lock connecting rod servo-actuated when blocking the bar position; rocking arm 13 collides and blocks bar and begin to rotate; rocking arm 13 rotating band dynamic bevel gears 12, and finishing bevel gear cuter 12 rotations drive combination tooths wheel 11, mix gear 11 rotations and drive straight gears 10; thus drive pull bar 3 rotations; pull bar 3 with lock connecting rod 1 and down 2 ways of contact of lock connecting rod be the cylindrical roller bearing form, so friction force is less, it is also less to break away from required application force; When the groove of the star-like dentalation of the tooth of pull bar upper mounting plate 4 star-like dentalations and upper mounting plate chamber 5 lower walls aligned, the load transmission of the connecting rod 1 of locking was less than pull bar 3, and the connecting rod 1 of locking is separated with 2 on connecting rod of lock down, realizes that the lock connecting rod breaks away from; Locking up and down has extension spring 14 dragging after connecting rod breaks away from, and limits its free motion;
(c) under the normal circumstances, the tooth of the star-like dentalation of the tooth of pull bar upper mounting plate 4 star-like dentalations and upper mounting plate chamber 5 lower walls aligns, so that transmitted load, can not occur because the situation that the environmental perturbation pull bar freely rotates, therefore for safe and reliable, be connected torsion spring 15 at pull bar 3 with following 2 on connecting rod of lock, be used for the restriction pull bar and do freely rotating of time spent at non-rocking arm 13, sleeve mechanism is in the state of being lockable.
Claims (3)
1. lock connecting rod emergency escape mechanism that rocker-arm can carry is characterized in that:
Comprise and the connecting rod of locking (1) of hatch door interlock and the following lock connecting rod (2) that links with alighting gear that the connecting rod of locking has pull bar installation cavity (C) with the junction of locking connecting rod down, and pull bar (3) is installed in the pull bar installation cavity;
Above-mentioned pull bar (3) has upper mounting plate (4), the above-mentioned connecting rod bottom of locking has the upper mounting plate chamber (5) that cooperates with upper mounting plate, above-mentioned upper mounting plate (4) is embedded in the upper mounting plate chamber (5), and there is cylindrical roller thrust (6) on the upper and lower surface of this upper mounting plate (4) along circumferential arrangement, makes lock connecting rod bottom and pull bar top formation thrust roller bearing connection mode; Above-mentioned upper mounting plate (4) is star-like dentalation, and the lower wall surface of upper mounting plate chamber (5) has the star-like groove shape structure that cooperates with this star-like dentalation;
Above-mentioned pull bar has lower platform (7), the above-mentioned connecting rod of lock down top has the lower platform chamber (8) that cooperates with lower platform, above-mentioned lower platform (7) is embedded in the lower platform chamber (8), and there is cylindrical roller thrust (9) on the upper and lower surface of this lower platform (7) along circumferential arrangement, makes down lock connecting rod top and pull bar bottom form the thrust roller bearing connection mode;
Straight gear (10) also is installed in the above-mentioned pull bar installation cavity (C), mixes gear (11), finishing bevel gear cuter (12), rocking arm (13) and extension spring (14); Wherein straight gear (10) is coaxial with pull bar (3) and captive joint, mix gear (11) and coaxial connection of an anchor shaft of lock connecting rod (2) down; rocking arm (13) is installed on the connecting rod of locking; and rocking arm (13) one ends are coaxial with finishing bevel gear cuter (12) and captive joint; and the other end stretches out pull bar installation cavity (C); straight gear (10) partly is meshed with the straight gear of mixing gear (11), and finishing bevel gear cuter (12) is meshed with the bevel gear part of mixing gear (11); Extension spring (14) one ends are connected with the connecting rod of locking (1) lower part, and the other end is connected with following lock connecting rod (2) top;
This emergency escape mechanism comprises that also an end links to each other with above-mentioned pull bar (3), the torsion spring (15) that the other end links to each other with above-mentioned lock connecting rod (2) down.
2. utilize the detachment system of the lock connecting rod emergency escape mechanism that the described rocker-arm of claim 1 can carry, it is characterized in that: this detachment system is made up of the lock connecting rod emergency escape mechanism that emergent place system (22), rocking arm arresting system, rocker-arm can carry;
This rocking arm arresting system by head end pulley (16), transition assembly pulley (17,18), block (19), cable wire (20), block bar (21) and form; Wherein head end pulley (16) is installed on the rotating part of emergent place system (22), and rotates with rotating part; Transition assembly pulley and block (19) are installed on the interior framing member of landing gear compartment; The above-mentioned bar (21) that blocks is installed on the block (19), and blocks axis and the block axis normal of bar (21); Cable wire one end is connected in head end pulley (16), the other end is walked around the transition assembly pulley and is connected with block (19).
3. the method for work of detachment system as claimed in claim 2 is characterized in that comprising following process:
(a), when the normal folding and unfolding of Landing Gear System, the lock connecting rod emergency escape mechanism that this rocker-arm can carry realizes the interlock of hatch door mechanism and the transmission of load as a lock connecting rod, concrete working process is as follows: lock connecting rod internal load transfer mode is passed to pull bar (3) for the connecting rod of locking (1) by the thrust roller bearing structure, pull bar (3) is passed to down lock connecting rod (2) by the thrust roller bearing structure, thereby realizes the transmission of load;
During normal folding and unfolding, block bar and pack up, the lock connecting rod is servo-actuated when blocking the bar position, can pass through smoothly, does not influence the normal folding and unfolding of alighting gear;
(b), when alighting gear is in emergent release position, the hatch door load unloading that hinders gear down need be about to lock connecting rod and break away from; The aviator spurs emergent handle, drive emergent laying mechanism rotation, thereby drive head end pulley (16) rotation, correspondingly drive block (19) rotation by cable wire, block bar by block (19) driven rotary to down state, when the lock connecting rod servo-actuated when blocking the bar position; rocking arm (13) collides and blocks bar and begin to rotate; rocking arm (13) rotating band dynamic bevel gear (12); finishing bevel gear cuter (12) rotation drives combination tooth wheel (11); mix gear (11) rotation and drive straight gear (10); thus drive pull bar (3) rotation; pull bar (3) with lock connecting rod (1) and to lock connecting rod (2) way of contact down be the cylindrical roller bearing form, so friction force is less, it is also less to break away from required application force; When the groove of the star-like dentalation of the tooth of the star-like dentalation of pull bar upper mounting plate (4) and upper mounting plate chamber (5) lower wall aligns, lock the load transmission of connecting rod (1) less than pull bar (3), the connecting rod (1) of locking is then separated with locking connecting rod (2) down, realizes that the lock connecting rod breaks away from; Locking up and down has extension spring (14) dragging after connecting rod breaks away from, and limits its free motion;
(c) under the normal circumstances, the groove of the star-like dentalation of the tooth of the star-like dentalation of pull bar upper mounting plate (4) and upper mounting plate chamber (5) lower wall aligns, so that transmitted load, can not occur because the situation that the environmental perturbation pull bar freely rotates, therefore for safe and reliable, be connected torsion spring (15) at pull bar (3) with following the lock between connecting rod (2), be used for the restriction pull bar and do freely rotating of time spent at non-rocking arm (13), sleeve mechanism is in the state of being lockable.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201110317667 CN102390526B (en) | 2011-10-19 | 2011-10-19 | Rocker-arm-type bearable lock connecting rod emergency disengagement mechanism, system and method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201110317667 CN102390526B (en) | 2011-10-19 | 2011-10-19 | Rocker-arm-type bearable lock connecting rod emergency disengagement mechanism, system and method |
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| Publication Number | Publication Date |
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| CN102390526A CN102390526A (en) | 2012-03-28 |
| CN102390526B true CN102390526B (en) | 2013-10-02 |
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| CN 201110317667 Active CN102390526B (en) | 2011-10-19 | 2011-10-19 | Rocker-arm-type bearable lock connecting rod emergency disengagement mechanism, system and method |
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Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP3020632B1 (en) | 2014-11-13 | 2018-12-26 | Safran Landing Systems UK Limited | Aircraft landing gear assembly |
| CN109131846B (en) * | 2018-07-25 | 2022-05-10 | 苏州频聿精密机械有限公司 | Manual steering device of undercarriage |
| CN112572781B (en) * | 2020-12-04 | 2023-04-14 | 中国航空工业集团公司成都飞机设计研究所 | Front wheel turning speed reduction output mechanism |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4573649A (en) * | 1983-08-01 | 1986-03-04 | The Boeing Company | Integrated alternate gear extension and ground-crew door opening/closing system for an aircraft |
| EP0564772A1 (en) * | 1992-04-07 | 1993-10-13 | Deutsche Aerospace Airbus Gesellschaft mit beschränkter Haftung | Main landing gear for an aircraft with aft center of gravity |
| CN2369952Y (en) * | 1999-05-12 | 2000-03-22 | 袁立建 | Compensating device for out of order of areoplane landing gear |
| GB2373772A (en) * | 2001-03-24 | 2002-10-02 | Bae Systems Plc | Aircraft undercarriage system |
| CN102020014A (en) * | 2010-12-09 | 2011-04-20 | 南京航空航天大学 | Airplane landing gear with deflected airplane wheel retraction jack |
-
2011
- 2011-10-19 CN CN 201110317667 patent/CN102390526B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4573649A (en) * | 1983-08-01 | 1986-03-04 | The Boeing Company | Integrated alternate gear extension and ground-crew door opening/closing system for an aircraft |
| EP0564772A1 (en) * | 1992-04-07 | 1993-10-13 | Deutsche Aerospace Airbus Gesellschaft mit beschränkter Haftung | Main landing gear for an aircraft with aft center of gravity |
| CN2369952Y (en) * | 1999-05-12 | 2000-03-22 | 袁立建 | Compensating device for out of order of areoplane landing gear |
| GB2373772A (en) * | 2001-03-24 | 2002-10-02 | Bae Systems Plc | Aircraft undercarriage system |
| CN102020014A (en) * | 2010-12-09 | 2011-04-20 | 南京航空航天大学 | Airplane landing gear with deflected airplane wheel retraction jack |
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| CN102390526A (en) | 2012-03-28 |
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