CN102001445A - 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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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 and innovates base (laboratory) open fund (201001001) subsidy.
Amphibious aircraft has the characteristics that are better than vehicle and boats and ships on 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 does not still have practical large-scale amphibious aircraft at present in labour, and unique is " water bangs 5 " at the labour large water aircraft.
So, carry out the research of amphibious aircraft Landing Gear System aspect at present, 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 Canadian CL-215 aircraft again, because maximum take-off weight has only 19890 kilograms; And the maximum take-off weight of U.S. PBY-5A aircraft also has only 16066 kilograms, greatly differs from each other for 45000 kilograms with water Hong-5 maximum take-off weight.So, more than the main landing gear placement scheme of three kinds of aircrafts all be 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 to develop real amphibious aircraft in the purpose of land and water landing.Afterwards,,, comprise military secret user, civil aircraft user and external user's various requirement, update, optimize and the various aspects of performance of the aircraft of upgrading, thereby derive a series of products, take part in international competition according to the requirement and the user of air worthiness regulation as basical traditional model.
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 alighting gear electromagnetism torsion lock and control system thereof are based on this kind undercarriage and design, and both combine closely; This alighting gear electromagnetism torsion lock 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 202,302 of criss-cross.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 a 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 first auricle 401, and the middle part is provided with second auricle 402.Rotating shaft 1 is embedded in first auricle 4, and leaves the space between first auricle 4 and the rotating shaft 1.Rotating shaft 1 is connected by pin with first auricle 4.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 first auricle 401, contact surface has good stressed effect.
The shaft shoulder 6 is arranged in the rotating shaft 1 between 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 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 is provided with 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.Which kind of shape the shaft shoulder 6 no matter adopt, and it is good being single piece with itself and rotating shaft 1.Can guarantee that like this shaft shoulder 6 can not move 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 suit in the pressurized strut 2.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 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 second auricle 402, the pin-and-hole rotation of energy disperser 4 on first auricle 401 fits until the side and the shaft shoulder 6 of first auricle 401.In this process, the path of motion of energy disperser 4 axis is that a plane is fan-shaped.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, rotates up to being in same horizontal surface with rotating shaft 1 axis until energy disperser 4 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 promptly energy disperser 4 axis rotate up to being in same horizontal surface with rotating shaft 1 axis.In this rotary course, 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: lock control devices countershaft 1 locking once more, simultaneously, piston rod 3 inwardly reclaims, and is perpendicular until the axis of the axis of energy disperser 4 and rotating shaft 1.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 first auricle 401, perpendicular from the fit axis of the axis that moves to energy disperser 4 and rotating shaft 1 of first auricle 401 and the shaft shoulder 6.In this process, the path of motion of energy disperser 4 axis is that a plane is fan-shaped.The fan-shaped angular dimension in the plane 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, promptly over the step of running condition 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 was 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, the reliability height is with the matching used electromagnetism torsion of foregoing undercarriage lock 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, and are crossing, parallel with No. two axis with an 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 vertical mutually, and the limes superiors end face of two locking grooves is also vertical mutually.
Be fixed with locking plate on the above-mentioned axle outside face, when the relative axle sleeve of axle rotated, locking plate can rotate in the locking groove angular range, the slewing area of two limit end face restriction locking plates up and down 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, lock pin one end is as the armature end that cooperates with above-mentioned electromagnet, the dead bolt that the other end stretches out or indentation lock 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 two lock frame and arranged on left and right sides respectively; 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 two limit end faces up and down 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 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 second step of gear up in the background technology, so that second trigger switch is installed on the limit end face of left locking groove.
The control system of above-mentioned alighting gear electromagnetism torsion lock, it is characterized in that: this control system comprises the ball bearing made using of being made up of first trigger switch, second trigger switch, electromagnet, power supply; And the whole electromagnet in this electromagnetism torsion lock are connected in the same control circuit, and wherein first trigger switch is installed on the inclined-plane of the shaft shoulder, the left locking groove limes superiors end when 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 the reliability height can cooperate the folding and unfolding campaign in the alighting gear background technology well.
Description of drawings
Fig. 1 undercarriage integral structure scheme drawing;
Fig. 2 is the view that alighting gear puts down fully;
Fig. 3 is the last current state scheme drawing of the gear up first step;
Fig. 4 is the gear up last current state scheme drawing in second step;
Fig. 5 is the view that alighting gear is packed up fully;
Fig. 6 is equipped with the up and down alighting gear rotating axis component scheme drawing of locking plate and the trapezoidal shaft shoulder;
Fig. 7 is the lock pin scheme drawing;
Fig. 8 is the alighting gear rotating shaft sleeve part scheme drawing that is equipped with electromagnet and lock frame;
Fig. 9 is whole locking device scheme drawing;
Figure 10 is the locking state scheme drawing 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, first auricle, 402, second auricle, 403, No. two axles, 701, matrix, 702, first boss, 703, second boss, 704, the 3rd boss, 705, minor axis, 706, circular hole, 101, left side locking plate, 102, right locking plate, 501, left side locking groove, 502, the lock chamber, 503, left side lock frame, 504, left side electromagnet, 505, right lock frame, 506, right electromagnet, 507, left side lock pin, 508, right lock pin, 509, left spring, 510, right spring, 511, right locking groove, 701, first trigger switch, 702, 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.
As Fig. 2, alighting gear puts down fully; At this moment, first trigger switch 701 is not stressed, the control circuit state as shown in figure 11: first trigger switch 701 disconnects, and second trigger switch, 702 closures are locked;
From Fig. 2 to Fig. 3, first trigger switch, 701 pressurizeds are in closure state; At this moment, the control circuit state as shown in figure 12: first trigger switch, 701 closures, second trigger switch, 702 closures are unblanked;
From Fig. 3 to Fig. 4, the control circuit state is shown in Figure 12: first trigger switch, 701 closures, and 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, second trigger switch, 702 pressurizeds disconnect.At this moment, the control circuit state as shown in figure 13: first trigger switch, 701 closures, second trigger switch 702 disconnects, and locks;
Then, alighting gear is got back to state shown in Figure 4 toward very little angle of turning down (being less than or equal to 5 °), the control circuit state as shown in figure 13: first trigger switch, 701 closures, second trigger switch 702 disconnects, and locks;
From Fig. 4 to Fig. 5, alighting gear is packed up fully, and first trigger switch 701 is not stressed, and is in off-state.The control circuit state as shown in figure 14 at this moment: first trigger switch 701 disconnects, and 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 scheme drawings, the inclined-plane on the lock pin 507 can reduce the resistance that lock pin is subjected 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 two limit end faces up and down of locking groove 501 is a, and 90 °
a
95 °.
(3) the rotating shaft lock principle of work of locking and unblanking itself is as follows:
As shown in Figure 9, when putting down fully for alighting gear, the state of locking device; Left side locking plate is made an axle 1 not rotate by the restriction of the smallest limit end face of left lock pin and left locked groove; First trigger switch 701 disconnects in the circuit, and 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, 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; First trigger switch 701 is pressurized still, and first trigger switch 701 is in closure state; Second trigger switch 702 is pressed, and second trigger switch 702 is in off-state; So the electromagnet outage quits work; Left side 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, first trigger switch, 701 closures, and second trigger switch 702 disconnects, and locks; At this moment, the control circuit state of lock system as shown in figure 13.
To Fig. 5 position, first trigger switch, 701 pressure relieves disconnect from Fig. 4; Second trigger switch 702 disconnects, and locks; Shrink in pressurized strut 2, alighting gear is when the inboard income of fuselage, and axle of alighting gear 1 has the trend of past swivel motion, thereby locking plate 102 also has the trend of past swivel motion; But locking plate 102 is made alighting gear can draw close toward fuselage smoothly under the contractile motion of pressurized strut 2 by lock pin 508 stop at this moment, takes in fully in the landing gear compartment; 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), the unblanking and lock principle of lock:
As Figure 10 is locking state, and control circuit is an off state, and no current passes through in the electromagnet, and lock pin extends, thereby locks under the effect of contained spring;
When first trigger switch 701 and second trigger switch, 702 while closure, control circuit is an open-circuit condition, has electric current to pass through in the electromagnet, and lock pin is attracted by electromagnet, unblanks; Spring is compressed and stores potential energy, uses when keeping supplying lock.
Claims (4)
1. an alighting gear electromagnetism torsion is locked, and it 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, and are crossing, parallel with No. two axis with an axis;
Above-mentioned axle sleeve (5) is along circumferentially having the locking groove (501) of angular range at the 90-95 degree; Be fixed with locking plate (101) on an above-mentioned axle (1) outside face, when the relative axle sleeve (5) of an axle (1) rotated, 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 other end stretches out or indentation is locked the chamber as the dead bolt end that cooperates with above-mentioned locking plate (101).
2. alighting gear electromagnetism torsion lock 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 and arranged on left and right sides; Lock pin in the lock frame of the left side is positioned at the left side for the dead bolt end, and armature end is positioned at the mounting means on right side; Lock pin in the lock frame of the right is positioned at the right side for the dead bolt end, 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 alighting gear electromagnetism torsion lock according to claim 1 is characterized in that:
This control system comprises the loop of being made up of first trigger switch (701), second trigger switch (702), electromagnet, power supply; Wherein first trigger switch is installed on the inclined-plane of the shaft shoulder, and second trigger switch is installed in the limit endface position of locking groove.
4. the control system of alighting gear electromagnetism torsion lock according to claim 1 is characterized in that:
Whole electromagnet in the above-mentioned electromagnetism torsion lock are connected in the same control circuit, and it is closed simultaneously that first trigger switch and 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 true CN102001445A (en) | 2011-04-06 |
| CN102001445B CN102001445B (en) | 2013-01-30 |
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| 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) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN105160961A (en) * | 2015-09-29 | 2015-12-16 | 哈尔滨莱特兄弟科技开发有限公司 | Simulation aircraft undercarriage analogue device |
| WO2016155250A1 (en) * | 2015-03-31 | 2016-10-06 | 深圳一电科技有限公司 | Unmanned aerial vehicle system, unmanned aerial vehicle and control method of unmanned aerial vehicle |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2016155250A1 (en) * | 2015-03-31 | 2016-10-06 | 深圳一电科技有限公司 | Unmanned aerial vehicle system, unmanned aerial vehicle and control method of unmanned aerial vehicle |
| CN105160961A (en) * | 2015-09-29 | 2015-12-16 | 哈尔滨莱特兄弟科技开发有限公司 | Simulation aircraft undercarriage analogue device |
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| CN102001445B (en) | 2013-01-30 |
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