CN102001445B - Electromagnetic torque lock for undercarriage and control system thereof - Google Patents
Electromagnetic torque lock for undercarriage and control system thereof Download PDFInfo
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- CN102001445B CN102001445B CN 201010557060 CN201010557060A CN102001445B CN 102001445 B CN102001445 B CN 102001445B CN 201010557060 CN201010557060 CN 201010557060 CN 201010557060 A CN201010557060 A CN 201010557060A CN 102001445 B CN102001445 B CN 102001445B
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Abstract
The invention relates to an electromagnetic torque lock for an undercarriage and a control system thereof, and belongs to the field of an airplane undercarriage locking device. The torque lock comprises a shaft sleeve (5) and a first shaft (1) arranged inside the shaft sleeve, wherein a shaft shoulder (6) and a second shaft (403) are fixedly connected at one end of the first shaft (1); a stopper (101) is fixedly connected on an outer surface of the first shaft (1); when the first shaft (1) rotates relative to the shaft sleeve (5), the stopper (101) can rotate in an angle range of a stopping groove; a locking frame (503) is also fixedly arranged on the shaft sleeve (5); an electromagnet (504) is arranged on the locking frame (503); a locking cavity (502) is arranged inside the locking frame (503); a locking pin (507) and a spring (509) are arranged inside the locking cavity (502); and one end of the locking pin (507) serves as an armature end matched with an electromagnet (506), and the other end of the locking pin (507) extends out or retracts into the locking cavity to serve as a bolt end matched with the stopper (101). The invention is simple in structure and high in reliability.
Description
Technical field
The invention belongs to undercarriage locking device field.
Technical background
The present invention obtains the postgraduate of Nanjing Aero-Space University Innovation Base (laboratory) open fund (201001001) and subsidizes.
Amphibious aircraft has the characteristics that are better than vehicle and boats and ships in land and landing waterborne, speed.So in today of 21 century, along with the World Airways industrial expansion, countries in the world just progressively start the development climax of hydroairplane, amphibious aircraft and ground (sea) face effect aircraft of a new round.
China there is no practical large-scale amphibious aircraft at present in labour, and unique is " water bangs 5 " at the labour large water aircraft.
So, carry out at present the research of amphibious aircraft Landing Gear System aspect, the meaning of " work is in the contemporary generation, profit is in the future thousands of years " is arranged for the development that promotes China's modernization national defense construction and General Aviation cause.
As one of important references type of Chinese large-sized amphibious aircraft, what Muscovite not-200 aircrafts adopted is two jet engines, and China does not also grasp this technology at present, will still adopt airscrew engine; See again Canadian CL-215 aircraft, because maximum take-off weight only has 19890 kilograms; And the maximum take-off weight of U.S. PBY-5A aircraft also only has 16066 kilograms, greatly differs from each other with 45000 kilograms of water Hong-5 maximum take-off weights.So the main landing gear placement scheme of above three kinds of aircrafts all is not suitable for the actual conditions of the large-scale amphibious aircraft of the current research and development of China.
And the US-1 aircraft maximum take-off weight of Japan is 45000 kilograms, with water Hong-5 identical; Therefore, the reference value of US-1 aircraft is the highest.Yet the water of China Hong-5 aircrafts just once in a while can be at the hydroairplane of land landing, and US-1 but is genuine amphibious aircraft.So this paper has following guess to the large-scale amphibious aircraft of China:
From principle of design, consider the factor of design cycle and design cost, only need on water Hong-5 basis emphatically with reference to the US-1 aircraft, redesign its Landing Gear System, employing adds the narrow wheelspan scheme of bulge in the fuselage both sides, just can reach and in the purpose of land and water landing, to develop real amphibious aircraft.Afterwards, as basical traditional model, according to requirement and the user of air worthiness regulation, comprise the various requirement of military secret user, civil aircraft user and Foreign User, update, optimize and the various aspects of performance of the aircraft of upgrading, thereby derive a series of products, take part in international competition.
The design of amphibious aircraft Landing Gear System, key are the layout of main landing gear and the design of jack.
The applicant is called " a kind of undercarriage " in the name of in May, 2010 application, and application number is the patent of " 201010180497.1 ", and this undercarriage is applicable to the above-mentioned narrow wheelspan scheme that adds bulge in the fuselage both sides; This electromagnetic torque lock for undercarriage and control system thereof are based on this kind undercarriage and design, and both combine closely; This electromagnetic torque lock for undercarriage and control system thereof can not break away from this undercarriage and work independently.
This undercarriage integral structure explanation:
As shown in the figure, a kind of undercarriage comprises rotating shaft 1, pressurized strut 2, energy disperser 4, sleeve 5, the shaft shoulder 6 and two hinged auricles 202 of criss-cross, 302.Sleeve 5 is fixedly connected on the fuselage.Rotating shaft 1 is arranged in sleeve 5, and it is connected with lock control devices.The lock control mode of this lock control devices can be lock control mode common in the landing gear of aircraft, for example uplock and down lock in the alighting gear.When this lock control devices countershaft 1 locking, rotating shaft 1 just cannot be rotated in this sleeve 5; When this lock control devices countershaft 1 release, rotating shaft 1 just can be rotated in this sleeve 5.The top of energy disperser 4 is provided with the first auricle 401, and the middle part is provided with the second auricle 402.Rotating shaft 1 is embedded in the first auricle 4, and leaves the space between the first auricle 4 and the rotating shaft 1.Rotating shaft 1 be connected auricle 4 and connect by pin.Like this, energy disperser 4 can rotate around this pin.The through hole that matches with rotating shaft 1 on the shaft shoulder 6 arrives the distance of the shaft shoulder 6 end faces to the distance of the shaft shoulder 6 sides less than it, and when fitting with the assurance shaft shoulder 6 and the first auricle 401, contact surface has good stressed effect.
The shaft shoulder 6 is arranged in the rotating shaft 1 between the first auricle 401 and the sleeve 5.The shape of the shaft shoulder 6 can have various ways, and still, the shaft shoulder 6 is all inclined towards a side of the first auricle 401.Like this can be so that alighting gear can be controlled to be certain angle in first process of packing up.The shaft shoulder 6 can be the ring that arranges along rotating shaft 1 surface.As another kind of shape, as shown in Figure 3, the vertical section of the shaft shoulder 6 is trapezoidal, and is provided with the through hole that matches with rotating shaft 1.The shaft shoulder 6 is single piece as good no matter adopt which kind of shape take itself and rotating shaft 1.Can guarantee that like this shaft shoulder 6 can be not mobile in rotating shaft 1, can save between the shaft shoulder 6 and rotating shaft 1 simultaneously and set up securing device.Pressurized strut 2 one ends are provided with an auricle 201.Piston rod 3 of pressurized strut 2 interior suits.Piston rod 3 one ends stretch out pressurized strut 2, and are provided with an auricle 301 at this end.Auricle 201 in the pressurized strut 2 is connected with auricle 203 on the fuselage by the hinged auricle 202 of criss-cross.Auricle 301 on the piston rod 3 is connected with the second auricle 402 on the energy disperser 4 by the hinged auricle 302 of criss-cross.The mode of motion of pressurized strut 2 is hydraulic driving modes common in the aircraft field.
This undercarriage is packed up procedure declaration:
The first step: 1 locking of lock control devices countershaft, simultaneously, piston rod 3 is protruding.Shown in Figure 5 is the view of alighting gear when normal operation.At this moment, the axis of the axis of energy disperser 4 and rotating shaft 1 is vertical relation.As shown in Figure 6, piston rod 3 is protruding in pressurized strut 2.In this process, 1 locking of lock control devices countershaft.Like this, rotating shaft 1 maintains static, and energy disperser 4 also just can not rotate in sleeve 5 with rotating shaft 1 together.Along with piston rod 3 is protruding, by the second auricle 402, the pin-and-hole rotation of energy disperser 4 on the first auricle 401 is until the side of the first auricle 401 and the shaft shoulder 6 fit.In this process, the path of motion of energy disperser 4 axis is plane sectors.By this step, energy disperser 4 can be walked around the bulge on the fuselage.
Second step: 1 release of lock control devices countershaft, simultaneously, piston rod 3 continues protruding, until energy disperser 4 axis rotate up to being in same level with rotating shaft 1 axis.As shown in Figure 7, lock control devices countershaft 1 is separated and is decided.Like this, rotating shaft 1 can be rotated in sleeve 5, and energy disperser 4 also can rotate in sleeve 5 together with rotating shaft 1.When piston rod 3 continuation were protruding, energy disperser 4 rotated to the position of Fig. 7 from the position of Fig. 6, and namely energy disperser 4 axis rotate up to being in same level with rotating shaft 1 axis.In this rotary course, the first auricle 401 on the energy disperser 4 is fitted with the inclined side of the shaft shoulder 6 all the time.Energy disperser 4 moves in three dimensional space, and the path of motion of its axis is that a space is fan-shaped.
The 3rd step: again countershaft 1 locking of lock control devices, simultaneously, piston rod 3 inwardly reclaims, until the axis of the axis of energy disperser 4 and rotating shaft 1 is perpendicular.As shown in Figure 8, lock control devices countershaft 1 locking.Like this, rotating shaft 1 maintains static, and energy disperser 4 also just can not rotate in sleeve 5 with rotating shaft 1 together.When piston rod 3 inwardly reclaims, the pin rotation of energy disperser 4 on the first auricle 401, perpendicular from the fit axis of the axis that moves to energy disperser 4 and rotating shaft 1 of the first auricle 401 and the shaft shoulder 6.In this process, the path of motion of energy disperser 4 axis is plane sectors.The angular dimension of the plane sector that energy disperser 4 axis are walked around in this fan-shaped angle and the first step is identical.By this step, alighting gear can be recovered in the landing gear compartment in the fuselage bulge.
The folding and unfolding step of the alighting gear of this structure, namely over the step of the state of use in the landing gear compartment from its fuselage bulge, with pack up the step contrary, be that its first step is above-mentioned the 3rd step of packing up step, second step is the above-mentioned second step of packing up step, and the 3rd step was the above-mentioned first step of packing up step.
Summary of the invention
The object of the present invention is to provide a kind of simple in structurely, reliability is high, with the matching used electromagnetism torsion lock of foregoing undercarriage and control system thereof.
A kind of undercarriage electromagnetism torsion lock is characterized in that: comprise axle sleeve, be installed on an axle in the axle sleeve, No. one axle one end is fixed with the shaft shoulder and No. two axles successively; Wherein No. two axles are vertical with an axle, and the shaft shoulder is the inclined-plane form near the surface of No. two axle one sides, and this inclined-plane tilts to a direction of principal axis, with an axle axes intersect, parallel with No. two axle axis; Two end faces of above-mentioned axle sleeve are 90 ° along circumferentially all having angle a
a
95 ° locking groove; Above-mentioned locking groove all has limes superiors end face and smallest limit end face separately, and the smallest limit end face of two locking grooves is mutually vertical, and the limes superiors end face of two locking grooves is also mutually vertical.
Be fixed with locking plate on the above-mentioned axle outside face, when a relative axle sleeve rotation of axle, locking plate can rotate in the locking groove angular range, the up and down slewing area of two limit end face restriction locking plates of locking groove; Also be installed with the lock frame on the above-mentioned axle sleeve, on the lock frame electromagnet is installed, also has the lock chamber in the lock frame, lock is equipped with lock pin and spring in the chamber, the armature end that the conduct of lock pin one end cooperates with above-mentioned electromagnet, the dead bolt that the extended or retracted lock of other end chamber, conduct cooperate with above-mentioned locking plate.
About above-mentioned locking plate, locking groove, lock frame, electromagnet, lock pin, spring are divided into two groups; Above-mentioned two locking plates are assemblied in respectively two lock frame arranged on left and right sides; Lock pin in the left side lock frame is that the dead bolt end is positioned at the mounting means that left side, armature end are positioned at the right side; Lock pin in the right lock frame is that the dead bolt end is positioned at the mounting means that right side, armature end are positioned at the left side; The electromagnet that cooperates with lock pin armature end in the lock frame of the left side is installed on the lock frame of the right, and the electromagnet that cooperates with lock pin armature end in the lock frame of the right is installed on the lock frame of the left side; Angle between above-mentioned two locking plates is 90 degree, and the angle between up and down two limit end faces of above-mentioned locking groove is 90 °
a
95 °; Wherein, limit section refers in the process of an axle rotation, that face in the locking groove that its locking plate touches at last.
Said structure is the wheel-retracting gear work in the matching background technology effectively, makes whole landing-gear system more succinct, effectively.Wherein, " angle is 90 degree between two locking plates " is the second step for gear up in the matching background technology; " two locking grooves circumferentially differ the 90-95 degree " is the angle surplus that a 0-5 degree is provided for the second step of gear up in the background technology, in order at the limit end face of left locking groove the second trigger switch is installed.
The control system of above-mentioned electromagnetic torque lock for undercarriage is characterized in that: this control system comprises the ball bearing made using that is comprised of the first trigger switch, the second trigger switch, electromagnet, power supply; And the whole electromagnet in this electromagnetism torsion lock are connected in the same control circuit, and wherein the first trigger switch is installed on the inclined-plane of the shaft shoulder, the left locking groove limes superiors end when the second trigger switch is installed in gear up.
Beneficial effect of the present invention: for the hydraulically actuated lock on being widely used in aircraft, the present invention is simple in structure, and weight is little, controls simply, and reliability is high, can cooperate well the folding and unfolding campaign in the alighting gear background technology.
Description of drawings
Fig. 1 undercarriage integral structure schematic diagram;
Fig. 2 is the view that alighting gear puts down fully;
Fig. 3 is the last current state schematic diagram of the gear up first step;
Fig. 4 is the last current state schematic diagram of gear up second step;
Fig. 5 is the view that alighting gear is packed up fully;
Fig. 6 is the alighting gear rotating axis component schematic diagram that is equipped with bottom stopper moving plate and the trapezoidal shaft shoulder;
Fig. 7 is the lock pin schematic diagram;
Fig. 8 is the alighting gear rotating shaft sleeve part schematic diagram that is equipped with electromagnet and lock frame;
Fig. 9 is whole locking device schematic diagram;
Figure 10 is the locking state schematic diagram of locking device;
Figure 11 is the control circuit figure corresponding to Fig. 2 alighting gear state;
Figure 12 is the control circuit figure corresponding to Fig. 3 alighting gear state;
Figure 13 is the control circuit figure corresponding to Fig. 4 alighting gear state;
Figure 14 is the control circuit figure corresponding to Fig. 5 alighting gear state;
Number in the figure title: 1, an axle, 2, pressurized strut, 3, piston rod, 4, energy disperser, 5, sleeve, 6, the shaft shoulder, 201, auricle, 202, the hinged auricle of criss-cross, 203, auricle, 301, auricle, 302, the hinged auricle of criss-cross, 401, the first auricle, 402, the second auricle, 403, No. two axles, 701, matrix, 702, the first boss, 703, the second boss, 704, the 3rd boss, 705, minor axis, 706, circular hole, 101, left locking plate, 102, right locking plate, 501, left locking groove, 502, the lock chamber, 503, left lock frame, 504, left electromagnet, 505, right lock frame, 506, right electromagnet, 507, left lock pin, 508, right lock pin, 509, left spring, 510, right spring, 511, right locking groove, 701, the first trigger switch, 702, the second trigger switch.
The specific embodiment
(1), the co-ordination principle of rotating shaft lock and undercarriage control process is as follows:
When locking, No. one axle is locked, can not rotate; When unblanking, No. one axle unlocks, and can rotate.No. two axles all can rotate when locking and unblank.
Such as Fig. 2, alighting gear puts down fully; At this moment, the first trigger switch 701 is not stressed, the control circuit state as shown in figure 11: the first trigger switch 701 disconnects, and the second trigger switch 702 closures are locked;
From Fig. 2 to Fig. 3, the first trigger switch 701 pressurizeds are in closure state; At this moment, the control circuit state as shown in figure 12: the first trigger switch 701 closures, the second trigger switch 702 closures are unblanked;
From Fig. 3 to Fig. 4, the control circuit state is shown in Figure 12: the first trigger switch 701 closures, and the second trigger switch 702 closures are unblanked;
Continue up to rotate a very little angle (being less than or equal to 5 °) from Fig. 4, the second trigger switch 702 pressurizeds disconnect.At this moment, the control circuit state as shown in figure 13: the first trigger switch 701 closures, the second trigger switch 702 disconnects, and locks;
Then, alighting gear down turns round a very little angle (being less than or equal to 5 °), gets back to state shown in Figure 4, the control circuit state as shown in figure 13: the first trigger switch 701 closures, the second trigger switch 702 disconnects, and locks;
From Fig. 4 to Fig. 5, alighting gear is packed up fully, and the first trigger switch 701 is not stressed, and is in off-state.The control circuit state as shown in figure 14 at this moment: the first trigger switch 701 disconnects, and the second trigger switch 702 disconnects, and locks.
Gear down process and the above-mentioned process contrary of packing up.
(2), the parts of rotating shaft lock are composed as follows:
As shown in Figure 6, for being equipped with axle 1 parts of the trapezoidal shaft shoulder 6, No. two axles 403 and locking plate 101;
As shown in Figure 7, be lock pin 507 schematic diagrams, the inclined-plane on the lock pin 507 can reduce the resistance that lock pin is subject in the contractile motion process.
As shown in Figure 8, for being equipped with lock frame 503, rotating shaft axle sleeve 5 parts of electromagnet 504 comprising locking groove 501, are locked chamber 502, lock frame 503, electromagnet 504; Angle between up and down two limit end faces of locking groove 501 is a, and 90 °
a
95 °.
(3) rotating shaft lock itself is locked as follows with the principle of work of unblanking:
As shown in Figure 9, when putting down fully for alighting gear, the state of locking device; Left locking plate is by the restriction of the smallest limit end face of left lock pin and left locked groove, so that an axle 1 can not rotate; The first trigger switch 701 disconnects in the circuit, and the second trigger switch 702 closures are locked; At this moment, alighting gear state and control circuit state such as Fig. 2 and shown in Figure 11.
Move to Fig. 3 position to alighting gear by Fig. 2, the first trigger switch 701 closures in the circuit, second triggers 702 closures, and electromagnet is started working, and the attractive force of electromagnet makes lock pin shrink, and unblanks; At this moment, the control circuit state of lock system as shown in figure 12.
Move to Fig. 4 position from Fig. 3, electromagnet is worked always, and lock pin is attracted by electromagnet always and shrinks, and unblanks; At this moment, the control circuit state of lock system as shown in figure 12.
When pressurized strut 2 continuation elongations, No. one axle 1 continues to turn over a minute angle (being less than or equal to 5 °) from Fig. 4 position, and at this moment, left locking plate and right locking plate are respectively by the limes superiors end face stop of the limes superiors end face of left locking groove and right locking groove; The first trigger switch 701 is pressurized still, and the first trigger switch 701 is in closure state; The second trigger switch 702 is pressed, and the second trigger switch 702 is in off-state; So the electromagnet outage quits work; Left lock pin and right lock pin are stretched under the effect of contained spring, lock; At this moment, the control circuit state of lock system as shown in figure 13.
Then, pressurized strut 2 is shunk, and alighting gear is got back to the position of Fig. 4, the first trigger switch 701 closures, and the second trigger switch 702 disconnects, and locks; At this moment, the control circuit state of lock system as shown in figure 13.
From Fig. 4 to Fig. 5 position, the first trigger switch 701 pressure relieves disconnect; The second trigger switch 702 disconnects, and locks; Shrink in pressurized strut 2, when alighting gear was taken in to fuselage is inboard, axle 1 of alighting gear had the back trend of motion, thereby locking plate 102 also has the back trend of motion; But locking plate 102, is taken in the landing gear compartment so that alighting gear can be drawn close toward fuselage under the contractile motion of pressurized strut 2 smoothly fully by lock pin 508 stop at this moment; At this moment, the control circuit state of lock system as shown in figure 14.
Gear down process is packed up the process contrary therewith.
(4), unblanking and the principle of locking of lock:
Be locking state such as Figure 10, control circuit is off state, and no current passes through in the electromagnet, lock pin under the effect of contained spring, elongation, thus lock;
When the first trigger switch 701 and the second trigger switch 702 while closure, control circuit is open-circuit condition, has electric current to pass through in the electromagnet, and lock pin is attracted by electromagnet, unblanks; Compressed and the storage potential energy of spring is when locking.
Claims (3)
1. electromagnetic torque lock for undercarriage is characterized in that:
Comprise axle sleeve (5), be installed on the axle (1) in the axle sleeve, No. one axle (1) one end is fixed with the shaft shoulder (6) and No. two axles (403) successively;
Wherein No. two axles (403) are vertical with an axle (1), and the shaft shoulder (6) is the inclined-plane form near the surface of No. two axle (403) one sides, and this inclined-plane tilts to a direction of principal axis, with an axle axes intersect, parallel with No. two axle axis;
Above-mentioned axle sleeve (5) is along circumferentially having angular range at the locking groove (501) of 90-95 degree; Be fixed with locking plate (101) on an above-mentioned axle (1) outside face, when relative axle sleeve (5) rotation of an axle (1), locking plate (101) can rotate in the locking groove angular range;
Also be installed with lock frame (503) on the above-mentioned axle sleeve (5), on the lock frame (503) electromagnet (504) is installed, also has lock chamber (502) in the lock frame (503), in the lock chamber (502) lock pin (507) and spring (509) are installed, lock pin (507) one ends are as the armature end that cooperates with electromagnet (506), and the extended or retracted lock of other end chamber is as the dead bolt end that cooperates with above-mentioned locking plate (101).
2. electromagnetic torque lock for undercarriage according to claim 1 is characterized in that:
Above-mentioned locking plate, locking groove, lock frame, electromagnet, lock pin, spring be altogether about two groups;
Above-mentioned two locking plates lay respectively in left and right two locking grooves of two lock frame arranged on left and right sides; Lock pin in the lock frame of the left side is that the dead bolt end is positioned at the left side, and armature end is positioned at the mounting means on right side; Lock pin in the lock frame of the right is that the dead bolt end is positioned at the right side, and armature end is positioned at the mounting means in left side; The electromagnet that cooperates with lock pin armature end in the lock frame of the left side is installed on the lock frame of the right, and the electromagnet that cooperates with lock pin armature end in the lock frame of the right is installed on the lock frame of the left side;
Above-mentioned two locking plates are circumferentially differing 90 degree, and above-mentioned two locking grooves circumferentially differ the 90-95 degree.
3. the control system of electromagnetic torque lock for undercarriage according to claim 2 is characterized in that:
This control system comprises the loop that is comprised of the first trigger switch (701), the second trigger switch (702), electromagnet, power supply; Wherein the first trigger switch is installed on the inclined-plane of the shaft shoulder, the left locking groove limes superiors end when the second trigger switch is installed in gear up; Whole electromagnet in this control system are connected in the same control circuit, and it is closed simultaneously that the first trigger switch and the second trigger switch are wanted, and electromagnet just has magnetic; As long as one of them switch disconnects, electromagnet just loses magnetism.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201010557060 CN102001445B (en) | 2010-11-24 | 2010-11-24 | Electromagnetic torque lock for undercarriage and control system thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201010557060 CN102001445B (en) | 2010-11-24 | 2010-11-24 | Electromagnetic torque lock for undercarriage and control system thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102001445A CN102001445A (en) | 2011-04-06 |
| CN102001445B true CN102001445B (en) | 2013-01-30 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201010557060 Active CN102001445B (en) | 2010-11-24 | 2010-11-24 | Electromagnetic torque lock for undercarriage and control system thereof |
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| CN (1) | CN102001445B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104787307B (en) * | 2015-03-31 | 2017-09-26 | 深圳一电航空技术有限公司 | The control method of UAS, unmanned plane and the UAS |
| CN105160961B (en) * | 2015-09-29 | 2017-12-26 | 哈尔滨莱特兄弟科技开发有限公司 | Emulate undercarriage analogue means |
Family Cites Families (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU1775985C (en) * | 1989-03-20 | 1995-04-20 | Авиационный комплекс им.С.В.Ильюшина | Device for measuring number of revolution of undercarriage leg wheels |
| CN2073457U (en) * | 1990-08-21 | 1991-03-20 | 葛德华 | Electromagnetic lock |
| FR2836668B1 (en) * | 2002-03-04 | 2004-12-03 | Messier Bugatti | ATTACHMENT DEVICE, IN PARTICULAR FOR ATTACHING AN AIRCRAFT LANDING GEAR OR AN AIRCRAFT LANDING GEAR HATCH, AND METHOD FOR OPERATING THE SAID DEVICE |
| CN2704658Y (en) * | 2004-06-28 | 2005-06-15 | 北京超辰经济发展有限责任公司 | Electromagnetic locks |
| FR2901242B1 (en) * | 2006-05-17 | 2009-02-20 | Airbus Sas | DEVICE FOR LOCKING A MOBILE ELEMENT OF AN AIRCRAFT |
| WO2009079785A1 (en) * | 2007-12-21 | 2009-07-02 | Messier-Dowty Inc. | Landing gear uplock mechanism employing thermal phase-change actuation |
| GB2460088B (en) * | 2008-05-16 | 2012-05-09 | Ge Aviat Systems Ltd | Locking assembly |
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2010
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