CN103029846B - Notch sealing device for steam catapult of aircraft carrier - Google Patents
Notch sealing device for steam catapult of aircraft carrier Download PDFInfo
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- CN103029846B CN103029846B CN201210554451.0A CN201210554451A CN103029846B CN 103029846 B CN103029846 B CN 103029846B CN 201210554451 A CN201210554451 A CN 201210554451A CN 103029846 B CN103029846 B CN 103029846B
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Abstract
The invention discloses a notch sealing device for a steam catapult of an aircraft carrier. The notch sealing device comprises lower strip-shaped supporting plates positioned on both sides of a notch, and an upright push rod which is positioned in the middle of the notch and is vertical to the lower supporting plates, wherein upper cover plates of which the lengths and widths are the same as those of the lower supporting plates are covered on the lower supporting plates; the lower supporting plates are connected with the upper cover plates through a row of screw rods, so that fixed gaps are reserved between the lower supporting plates and the upper cover plates; a plurality of sealing plates are arranged in the gaps between the lower supporting plates and the upper cover plates; the front ends of the sealing plates are smaller while the back ends of the sealing plates are slightly larger; one side of two side faces of each sealing plate is a V-shaped concave surface, and the other side is a V-shaped convex surface; the concave surfaces and the convex surfaces of adjacent sealing plates are matched, i.e., the concave surfaces and the convex surfaces of adjacent sealing plates can be clamped together for sealing; the sealing plates extend inwards from gaps on both sides at intervals; one shaft is arranged at the back end of each sealing plate; large springs are sleeved on the outer sides of the shafts; the other ends of the shafts are connected with large permanent magnetic columns; and parts of the large permanent magnetic columns are sleeved in the inner cavities of large electromagnetic coils.
Description
Technical field
The present invention relates to aircraft carrier steam catapult notch sealing arrangement, be applicable to the notch sealing of aircraft carrier-based aircraft steam catapult, belong to science and techniques of defence field.
Background technology
The steam catapult that aircraft carrier-based aircraft takes off is the proprietary technology of the U.S., this is mainly the notch sealing problem of steam catapult, because make rear portion that notch moves at push rod fast, sealing closely, and be sealed under high-temperature steam condition and can only seal with metal or soft metal, so the most key of the Application and Development of restriction other countries steam catapult is exactly the sealing of notch, the present invention is just to provide the method for the satisfied above fast sealing notch requiring of a kind of energy.
Summary of the invention
The object of this invention is to provide a kind of aircraft carrier steam catapult notch sealing arrangement of energy fast sealing notch.
Steam catapult notch sealing arrangement for aircraft carrier, comprise that respectively there are the bottom plate of a block length bar shaped and notch intermediate vertical in notch both sides in the upright push rod of bottom plate, push rod can move forward fast promotion aircraft carrier along horizontal direction at notch and advance, also can be in notch travelling backwards the initiating terminal to notch, cover and on bottom plate, have the upper cover plate the same with width with bottom plate length, between bottom plate and upper cover plate, be connected by row's screw rod, the spiro rod section periphery cover of the screw rod of connection bottom plate and upper cover plate between bottom plate and upper cover plate has nut, make to leave between bottom plate and upper cover plate fixing gap, gap between bottom plate and upper cover plate is provided with polylith closing plate, the little rear end of closing plate front end is slightly large, one side of closing plate two sides is V-arrangement concave surfaces, opposite side is V-arrangement convex surface, and the concave surface of adjacent seals plate and convex surface match and can just be stuck and seal, closing plate compartment of terrain is stretched into from the space of both sides, first closing plate stretches into notch and covers notch between the bottom plate in push rod working direction left side and upper cover plate, and its front end enters the gap between bottom plate and the upper cover plate that opposite side is push rod working direction right side, second closing plate stretches into notch and covers notch between the bottom plate on push rod working direction right side and upper cover plate, and its front end enters the gap between bottom plate and the upper cover plate on the left of push rod working direction, simultaneously second closing plate is squeezed in first closing plate near the V-arrangement concave surface of a side of first closing plate and contacts with it on the V-arrangement convex surface of a side, and the formation power that is squeezed seals with it, the 3rd closing plate stretches into notch and covers notch between the bottom plate in push rod working direction left side and upper cover plate, and its front end enters the gap between bottom plate and the upper cover plate on push rod working direction right side, simultaneously the 3rd closing plate is squeezed in second closing plate near the V-arrangement concave surface of a side of second closing plate and contacts with it on the V-arrangement convex surface of a side, and the formation power that is squeezed seals with it, the 4th closing plate stretches into notch and covers notch between the bottom plate on push rod working direction right side and upper cover plate, and its front end enters the gap between bottom plate and the upper cover plate on the left of push rod working direction, simultaneously the 4th closing plate is squeezed in the 3rd closing plate near the V-arrangement concave surface of a side of the 3rd closing plate and contacts with it on the V-arrangement convex surface of a side, and the formation power that is squeezed seals with it, can cover rectangular notch and make its sealing and the difficult high pressure steam of revealing by polylith closing plate like this, closing plate rear end is provided with an axle, and axle outside cover has a big spring, and the other end of axle connects a large permanent magnetism post, and large permanent magnetism post part is placed on a large magnet coil inner chamber, it is characterized in that:
1, closing plate both sides of the edge one side is V-arrangement convex surface, opposite side is V-arrangement concave surface, and the V-arrangement convex surface of all closing plates is all in the same side of closing plate, be that to be positioned at the side that push rod promotes carrier-borne aircraft working direction be V-arrangement convex surface to closing plate, the V-arrangement concave surface of all closing plates is all at opposite side, be that push rod travelling backwards a to side of notch initiating terminal direction is V-arrangement concave surface, all so adjacent closing plates can be realized V-arrangement convex surface and the crush seal of V-arrangement concave surface, thereby make the high pressure steam in notch be difficult for releasing from seal clearance.
2, closing plate be positioned at a rear flank end that push rod promotes carrier-borne aircraft working direction a larger end side surface have a bayonet socket, and there is a fixture block matching with it on its big spring side, fixture block is connected with a little permanent magnetism post away from one end of big spring, little permanent magnetism post is connected with an axle away from one end of fixture block, this axle outside cover has a little spring, and the little spring in this axle and outside thereof is all enclosed within a little magnet coil inner chamber, the axle that fixture block of every closing plate correspondence is connected with a little permanent magnetism post and with little permanent magnetism post and the little spring in axle outside, the little spring in the fixture block that every closing plate is corresponding and little permanent magnetism post and axle and axle outside is arranged on sealing plate and is positioned on the upper cover plate that push rod promotes carrier-borne aircraft working direction one side, and its fixture block is in bayonet socket one side of sealing plate, when being produced magnetic field by large magnet coil energising, inhales after notch closing plate, the fixture block that sealing plate is corresponding can just snap in the bayonet socket of sealing plate and pin sealing plate.
3, the corresponding rebanking that can be advanced by push rod or push away to hit when travelling backwards of each closing plate, it is notch one side that push rod is passed carrier-borne aircraft working direction that every rebanking corresponding to closing plate is arranged on sealing plate front, and with the large magnet coil of the sealing plate upper cover plate upside in the same side, and there are 2/5ths length horizontal directions to stretch at notch, can just be advanced or the push rod of travelling backwards pushes away and hits, another 3/5ths length of rebanking are at upper cover plate upside, there is a vertically arranged little rotating shaft in rebanking central authorities, the position of upper cover plate upside near notch is fixed in little rotating shaft, rebanking can be done around little rotating shaft the rotation of horizontal direction, in little rotating shaft, cover has a little convolution spring, can make little rotating shaft hit occurred level direction rotation by pushing away and separate with push rod after immediate recovery to perpendicular to the position of notch, rebanking respectively has a contact block away from the horizontal both sides, one end of notch, the contact block that push rod is passed aircraft carrier working direction one side is front contact block, opposite side is that the contact block of travelling backwards direction one side is rear contact block, front contact block is connected with one end of the large magnet coil of corresponding closing plate by electric wire, another of the large magnet coil other end of corresponding closing plate and power lead is extremely connected, rear contact block is connected by one end of electric wire and the little magnet coil of corresponding fixture block, and another of the little magnet coil other end of corresponding fixture block and power lead is extremely connected, the little rotating shaft of rebanking is connected with power lead, when process is advanced in rebanking by push rod in, push away and hit and make rebanking in the time that little rotating shaft horizontally rotates, rebanking just touches rear contact block away from notch one end, and the little magnet coil that is connected with rear contact block electric wire of connection, little magnet coil generates an electromagnetic field immediately and little permanent magnetism post is sucked to little magnet coil inner chamber, thereby fixture block is pulled away to bayonet socket, and then make closing plate under the thrust of big spring, stretch into the gap between bottom plate and upper cover plate and cover and seal notch, advance and push away and hit the adjacent rebanking in front along with push rod continues pushing away carrier-borne aircraft, make equally the more closing plate fast sealing notch of this correspondence, when push rod promotes after carrier-borne aircraft takes off to be moved back in the process of notch initiating terminal, push rod travelling backwards pushes away rebanking, make rebanking touch the power supply of the front contact block large magnet coil that also connection is attached thereto around little rotating shaft rotation, this large magnet coil is generated an electromagnetic field, near large permanent magnetism post this large magnet coil one end of electromagnetic fields attract also makes large permanent magnetism post overcome big spring power and extend into large magnet coil inner chamber, thereby make sealing plate move apart notch, and then make push rod be moved back into notch initiating terminal by notch smoothly, when large permanent magnetism post sucks large magnet coil, also the bayonet socket that makes sealing plate is blocked by fixture block and is locked, equally, along with push rod continues the initiating terminal travelling backwards to notch, more closing plate is inhaled from notch by its large magnet coil, until push rod is moved back into the initiating terminal of notch completely, all closing plates also all move apart notch makes notch be full open position, thereby for launching next time ready.
4, near the closing plate front end while connecting screw rod between bottom plate and upper cover plate and be arranged on closing plate and stretch into notch and cover notch, and make closing plate and not make the high pressure steam leakage of notch with the space sealing of bottom plate and upper cover plate composition as far as possible.
The present invention compared with prior art has the following advantages:
1, the steam catapult notch sealing arrangement of this Purely mechanical, good seal performance, simple in structure, stable performance.
2,this closing plate stretches into the sealing between bottom plate and upper cover plate, can bear preferably the pressure of high pressure steam maintenance sealing significantly in notch.
Brief description of the drawings
Fig. 1 is the schematic side view that the embodiment of the present invention is removed upper cover plate;
Fig. 2 is M enlarged diagram embodiment illustrated in fig. 1;
Fig. 3 is middle A-A generalized section embodiment illustrated in fig. 1.
In Fig. 1-3: 1, power lead 2, notch 3, little magnet coil 4, fixture block 5, large permanent magnetism post 6, push rod 7, large magnet coil 8, big spring 9, axle sleeve 10, closing plate 11, screw rod 12, bottom plate 13, bayonet socket 14, rebanking 15, front contact block 16, rear contact block 17, little spring 18, little permanent magnetism post 19, upper recess surface 20, concave surface 21, upper convex surface 22, lower convex surface.
Detailed description of the invention
In the embodiment shown in Fig. 1-3: steam catapult notch sealing arrangement for aircraft carrier, comprise that respectively there are the bottom plate 12 of a block length bar shaped and notch 2 intermediate vertical in notch 2 both sides in the upright push rod 6 of bottom plate 12, push rod 6 can move forward fast promotion aircraft carrier along horizontal direction at notch 2 and advance, also can be in notch 2 travelling backwards the initiating terminal to notch 2, cover and on bottom plate 12, have the upper cover plate the same with width with bottom plate 12 length, between bottom plate 12 and upper cover plate, be connected by row's screw rod 11, the screw rod 11 of connection bottom plate 12 and upper cover plate 11 sections of periphery covers of screw rod between bottom plate 12 and upper cover plate have nut, make to leave between bottom plate 12 and upper cover plate fixing gap, gap between bottom plate 12 and upper cover plate is provided with polylith closing plate 10, the closing plate 10 little rear ends of front end are slightly large, one side of closing plate 10 two sides is V-arrangement concave surfaces, opposite side is V-arrangement convex surface, and the concave surface of adjacent seals plate 10 and convex surface match and can just be stuck and seal, closing plate 10 compartment of terrains are stretched into from the space of both sides, first closing plate 10 stretches into notch 2 and covers notch 2 between the bottom plate 12 in push rod 6 working direction left sides and upper cover plate, and its front end enters the gap between bottom plate 12 and the upper cover plate that opposite side is push rod 6 working direction right sides, second closing plate 10 stretches into notch 2 and covers notch 2 between the bottom plate 12 on push rod 6 working direction right sides and upper cover plate, and its front end enters the gap between bottom plate 12 and the upper cover plate on the left of push rod 6 working direction, simultaneously second closing plate 10 is squeezed in first closing plate 10 near the V-arrangement concave surface of a side of first closing plate 10 and contacts with it on the V-arrangement convex surface of a side, and the formation power that is squeezed seals with it, the 3rd closing plate 10 stretches into notch 2 and covers notch 2 between the bottom plate 12 in push rod 6 working direction left sides and upper cover plate, and its front end enters the gap between bottom plate 12 and the upper cover plate on push rod 6 working direction right sides, simultaneously the 3rd closing plate 10 is squeezed in second closing plate 10 near the V-arrangement concave surface of a side of second closing plate 10 and contacts with it on the V-arrangement convex surface of a side, and the formation power that is squeezed seals with it, the 4th closing plate 10 stretches into notch 2 and covers notch 2 between the bottom plate 12 on push rod 6 working direction right sides and upper cover plate, and its front end enters the gap between bottom plate 12 and the upper cover plate on the left of push rod 6 working direction, simultaneously the 4th closing plate 10 is squeezed in the 3rd closing plate 10 near the V-arrangement concave surface of a side of the 3rd closing plate 10 and contacts with it on the V-arrangement convex surface of a side, and the formation power that is squeezed seals with it, can cover rectangular notch 2 and make its sealing and the difficult high pressure steam of revealing by polylith closing plate 10 like this, closing plate 10 rear ends are provided with an axle, and axle outside cover has a big spring 8, and the other end of axle connects a large permanent magnetism post 5, and large permanent magnetism post 5 parts are placed on large magnet coil 7 inner chambers, it is characterized in that: closing plate 10 both sides of the edge one sides are V-arrangement convex surface, opposite side is V-arrangement concave surface, and the V-arrangement convex surface of all closing plates 10 is all in the same side of closing plate 10, be that to be positioned at the side that push rod 6 promotes carrier-borne aircraft working direction be V-arrangement convex surface to closing plate 10, the V-arrangement concave surface of all closing plates 10 is all at opposite side, be that push rod 6 travelling backwards a to side of notch 2 initiating terminal directions is V-arrangement concave surface, all so adjacent closing plates 10 can be realized V-arrangement convex surface and the crush seal of V-arrangement concave surface, thereby make the high pressure steam in notch 2 be difficult for releasing from seal clearance.
Closing plate 10 be positioned at a rear flank end that push rod 6 promotes carrier-borne aircraft working direction a larger end side surface have a bayonet socket 13, and there is a fixture block matching with it 4 on its big spring 8 sides, fixture block 4 is connected with a little permanent magnetism post 18 away from one end of big spring 8, little permanent magnetism post 18 is connected with an axle away from one end of fixture block 4, this axle outside cover has a little spring 17, and the little spring 17 in this axle and outside thereof is all enclosed within little magnet coil 3 inner chambers, the axle that fixture block 4 of every closing plate 10 correspondences is connected with a little permanent magnetism post 18 and with little permanent magnetism post and the little spring 17 in axle outside, the little spring 17 in the fixture block 4 of every closing plate 10 correspondences and little permanent magnetism post 18 and axle and axle outside is arranged on sealing plate 10 and is positioned on the upper cover plate that push rod 6 promotes carrier-borne aircraft working direction one side, and its fixture block 4 is in bayonet socket 13 1 sides of sealing plate 10, when closing plate 10 is switched on and produced magnetic field and inhale after notch 2 by large magnet coil 7, the fixture block 4 of sealing plate 10 correspondences can just snap in the bayonet socket 13 of sealing plate 10 and pin sealing plate 10.
The corresponding rebanking 14 that can be advanced by push rod 6 or push away to hit when travelling backwards of each closing plate 10, it is notch 2 one sides that push rod 6 is passed carrier-borne aircraft working direction that the rebanking 14 of every closing plate 10 correspondences is arranged on sealing plate 10 fronts, and with the large magnet coil 7 of the sealing plate 10 upper cover plate upside in the same side, and there are 2/5ths length horizontal directions to stretch at notch 2, can just be advanced or the push rod 6 of travelling backwards pushes away and hits, another 3/5ths length of rebanking 14 are at upper cover plate upside, there is a vertically arranged little rotating shaft in rebanking 14 central authorities, the position of upper cover plate upside near notch 2 is fixed in little rotating shaft, rebanking 14 can be done around little rotating shaft the rotation of horizontal direction, in little rotating shaft, cover has a little convolution spring, can make little rotating shaft hit occurred level direction rotation by pushing away and separate with push rod 6 after immediate recovery to perpendicular to the position of notch 2, rebanking 14 respectively has a contact block away from the horizontal both sides, one end of notch 2, the contact block that push rod 6 is passed aircraft carrier working direction one side is front contact block 15, opposite side is that the contact block of travelling backwards direction one side is rear contact block 16, front contact block 15 is connected with one end of the large magnet coil 7 of corresponding closing plate 10 by electric wire, another of large magnet coil 7 other ends of corresponding closing plate 10 and power lead 1 is extremely connected, rear contact block 16 is connected by one end of electric wire and the little magnet coil 3 of corresponding fixture block 4, and another of little magnet coil 3 other ends of corresponding fixture block 4 and power lead 1 is extremely connected, the little rotating shaft of rebanking 14 is connected with power lead 1, when process is advanced in rebanking 14 by push rod 6 in, push away and hit and make rebanking 14 in the time that little rotating shaft horizontally rotates, rebanking 14 just touches rear contact block 16 away from notch 2 one end, and the little magnet coil 3 that is connected with rear contact block 16 electric wires of connection, little magnet coil 3 generates an electromagnetic field immediately and little permanent magnetism post 18 is sucked to little magnet coil 3 inner chambers, thereby fixture block 4 is pulled away to bayonet socket 13, and then make closing plate 10 under the thrust of big spring 8, stretch into the gap between bottom plate 12 and upper cover plate and cover and seal notch 2, advance and push away and hit the adjacent rebanking in front 14 along with push rod 6 continues pushing away carrier-borne aircraft, make equally the more closing plate 10 fast sealing notches 2 of this correspondence, when push rod 6 promotes to be moved back in the process of notch 2 initiating terminals after carrier-borne aircraft takes off, push rod 6 travelling backwards push away rebanking 14, make rebanking 14 touch the power supply of the front contact block 15 large magnet coil 7 that also connection is attached thereto around little rotating shaft rotation, this large magnet coil 7 is generated an electromagnetic field, near large permanent magnetism post 5 these large magnet coil 7 one end of electromagnetic fields attract also makes large permanent magnetism post 5 overcome big spring 8 power and extend into large magnet coil 7 inner chambers, thereby make sealing plate 10 move apart notch 2, and then make push rod 6 be moved back into notch 2 initiating terminals by notch 2 smoothly, when large permanent magnetism post 5 sucks large magnet coil 7, also the bayonet socket 13 that makes sealing plate 10 is blocked by fixture block 4 and is locked, equally, along with push rod 6 continues the initiating terminal travelling backwards to notch 2, more closing plate 10 is inhaled from notch 2 by its large magnet coil 7, until push rod 6 is moved back into the initiating terminal of notch 2 completely, all closing plates 10 also all move apart notch 2 and make 2 one-tenth full open position of notch, thereby for launching next time ready.
Near closing plate 10 front ends when connecting screw rod 11 between bottom plate 12 and upper cover plate and being arranged on closing plate 10 and stretching into notch 2 and cover notch 2, and make closing plate 10 and not make the high pressure steam leakage of notch 2 with the space sealing of bottom plate 12 and upper cover plate composition as far as possible.
Claims (3)
1. steam catapult notch sealing arrangement for aircraft carrier, comprise that respectively there are the bottom plate (12) of a block length bar shaped and notch (2) intermediate vertical in notch (2) both sides in the upright push rod (6) of bottom plate (12), push rod (6) can move forward fast promotion aircraft carrier along horizontal direction at notch (2) and advance, also can be in notch (2) travelling backwards the initiating terminal to notch (2), cover and on bottom plate (12), have the upper cover plate the same with width with bottom plate (12) length, between bottom plate (12) and upper cover plate, be connected by row's screw rod (11), screw rod (11) the section periphery cover of the screw rod (11) of connection bottom plate (12) and upper cover plate between bottom plate (12) and upper cover plate has nut, make to leave fixing gap between bottom plate (12) and upper cover plate, gap between bottom plate (12) and upper cover plate is provided with polylith closing plate (10), the little rear end of closing plate (10) front end is slightly large, one side of closing plate (10) two sides is V-arrangement concave surfaces, opposite side is V-arrangement convex surface, and the concave surface of adjacent seals plate (10) and convex surface match and can just be stuck and seal, closing plate (10) compartment of terrain is stretched into from the space of both sides, first closing plate (10) stretches into notch (2) and covers notch (2) between the bottom plate (12) in push rod (6) working direction left side and upper cover plate, and its front end enters the gap between bottom plate (12) and the upper cover plate that opposite side is push rod (6) working direction right side, second closing plate (10) stretches into notch (2) and covers notch (2) between the bottom plate (12) on push rod (6) working direction right side and upper cover plate, and its front end enters the gap between bottom plate (12) and the upper cover plate on the left of push rod (6) working direction, simultaneously second closing plate (10) is squeezed in first closing plate (10) near the V-arrangement concave surface of a side of first closing plate (10) and contacts with it on the V-arrangement convex surface of a side, and the formation power that is squeezed seals with it, the 3rd closing plate (10) stretches into notch (2) and covers notch (2) between the bottom plate (12) in push rod (6) working direction left side and upper cover plate, and its front end enters the gap between bottom plate (12) and the upper cover plate on push rod (6) working direction right side, simultaneously the 3rd closing plate (10) is squeezed in second closing plate (10) near the V-arrangement concave surface of a side of second closing plate (10) and contacts with it on the V-arrangement convex surface of a side, and the formation power that is squeezed seals with it, the 4th closing plate (10) stretches into notch (2) and covers notch (2) between the bottom plate (12) on push rod (6) working direction right side and upper cover plate, and its front end enters the gap between bottom plate (12) and the upper cover plate on the left of push rod (6) working direction, simultaneously the 4th closing plate (10) is squeezed in the 3rd closing plate (10) near the V-arrangement concave surface of a side of the 3rd closing plate (10) and contacts with it on the V-arrangement convex surface of a side, and the formation power that is squeezed seals with it, can cover rectangular notch (2) and make its sealing and the difficult high pressure steam of revealing by polylith closing plate (10) like this, closing plate (10) rear end is provided with an axle, and axle outside cover has a big spring (8), and the other end of axle connects a large permanent magnetism post (5), and large permanent magnetism post (5) part is placed on a large magnet coil (7) inner chamber,
it is characterized in that:closing plate (10) both sides of the edge one side is V-arrangement convex surface, opposite side is V-arrangement concave surface, and the V-arrangement convex surface of all closing plates (10) is all in the same sides of closing plate (10), be that to be positioned at the side that push rod (6) promotes carrier-borne aircraft working direction be V-arrangement convex surface to closing plate (10), the V-arrangement concave surface of all closing plates (10) is all at opposite side, be that push rod (6) travelling backwards a to side of notch (2) initiating terminal direction is V-arrangement concave surface, all so adjacent closing plates (10) can be realized V-arrangement convex surface and the crush seal of V-arrangement concave surface, thereby make the high pressure steam in notch (2) be difficult for releasing from seal clearance, the corresponding rebanking (14) that can be advanced by push rod (6) or push away to hit when travelling backwards of each closing plate (10), it is notch (2) one sides that push rod (6) is passed carrier-borne aircraft working direction that the rebanking (14) that every closing plate (10) is corresponding is arranged on sealing plate (10) front, and with the large magnet coil (7) of sealing plate (10) the upper cover plate upside in the same side, and there are 2/5ths length horizontal directions to stretch in notch (2), can just be advanced or the push rod (6) of travelling backwards pushes away and hits, another 3/5ths length of rebanking (14) are at upper cover plate upside, there is a vertically arranged little rotating shaft in rebanking (14) central authorities, the position of upper cover plate upside near notch (2) is fixed in little rotating shaft, rebanking (14) can be done around little rotating shaft the rotation of horizontal direction, in little rotating shaft, cover has a little convolution spring, can make little rotating shaft be hit occurred level direction rotation by pushing away and separate rear immediate recovery with push rod (6) to the position perpendicular to notch (2), rebanking (14) respectively has a contact block away from the horizontal both sides, one end of notch (2), the contact block that push rod (6) is passed aircraft carrier working direction one side is front contact block (15), opposite side is that the contact block of travelling backwards direction one side is rear contact block (16), front contact block (15) is connected with one end of the large magnet coil (7) of corresponding closing plate (10) by electric wire, another of large magnet coil (7) other end of corresponding closing plate (10) and power lead (1) is extremely connected, rear contact block (16) is connected with one end of the little magnet coil (3) of corresponding fixture block (4) by electric wire, another of little magnet coil (3) other end of corresponding fixture block (4) and power lead (1) is extremely connected, the little rotating shaft of rebanking (14) is connected with power lead (1), when process is advanced in rebanking (14) by push rod (6) in, push away and hit and make rebanking (14) in the time that little rotating shaft horizontally rotates, rebanking (14) just touches rear contact block (16) away from notch (2) one end, and the little magnet coil (3) that is connected with rear contact block (16) electric wire of connection, little magnet coil (3) generates an electromagnetic field immediately and little permanent magnetism post (18) is sucked to little magnet coil (3) inner chamber, thereby fixture block (4) is pulled away to bayonet socket (13), and then make closing plate (10) under the thrust of big spring (8), stretch into the gap between bottom plate (12) and upper cover plate and cover and seal notch (2), advance and push away and hit the adjacent rebanking in front (14) along with push rod (6) continues pushing away carrier-borne aircraft, make equally more closing plate (10) the fast sealing notch (2) of this correspondence, when push rod (6) promotes after carrier-borne aircraft takes off to be moved back in the process of notch (2) initiating terminal, push rod (6) travelling backwards pushes away rebanking (14), make rebanking (14) touch the power supply of front contact block (15) the large magnet coil (7) that also connection is attached thereto around little rotating shaft rotation, this large magnet coil (7) is generated an electromagnetic field, near large permanent magnetism post (5) this large magnet coil (7) one end of electromagnetic fields attract also makes large permanent magnetism post (5) overcome big spring (8) power and extend into large magnet coil (7) inner chamber, thereby make sealing plate (10) move apart notch (2), and then make push rod (6) be moved back into notch (2) initiating terminal by notch (2) smoothly, when large permanent magnetism post (5) sucks large magnet coil (7), also the bayonet socket (13) that makes sealing plate (10) is blocked by fixture block (4) and is locked, equally, along with push rod (6) continues the initiating terminal travelling backwards to notch (2), more closing plate (10) is inhaled from notch (2) by its large magnet coil (7), until push rod (6) is moved back into the initiating terminal of notch (2) completely, all closing plates (10) also all move apart notch (2) makes notch (2) be full open position, thereby for launching next time ready.
2. steam catapult notch sealing arrangement for aircraft carrier as claimed in claim 1, it is characterized in that: closing plate (10) be positioned at a rear flank end that push rod (6) promotes carrier-borne aircraft working direction a larger end side surface have a bayonet socket (13), and there is a fixture block matching with it (4) on its big spring (8) side, fixture block (4) is connected with a little permanent magnetism post (18) away from one end of big spring (8), little permanent magnetism post (18) is connected with an axle away from one end of fixture block (4), this axle outside cover has a little spring (17), and the little spring in this axle and outside thereof (17) is all enclosed within a little magnet coil (3) inner chamber, the little spring (17) in the axle that the corresponding fixture block of every closing plate (10) (4) is connected with a little permanent magnetism post (18) and with little permanent magnetism post and axle outside, the little spring (17) in the fixture block (4) that every closing plate (10) is corresponding and little permanent magnetism post (18) and axle and axle outside is arranged on the upper cover plate that sealing plate (10) is positioned at push rod (6) promotion carrier-borne aircraft working direction one side, and its fixture block (4) is in bayonet socket (13) one sides of sealing plate (10), when being produced magnetic field by large magnet coil (7) energising, inhales after notch (2) closing plate (10), the fixture block (4) that sealing plate (10) is corresponding can just snap in the bayonet socket (13) of sealing plate (10) and pin sealing plate (10).
3. steam catapult notch sealing arrangement for aircraft carrier as claimed in claim 1, it is characterized in that: near closing plate (10) front end when connecting screw rod (11) between bottom plate (12) and upper cover plate and being arranged on closing plate (10) and stretching into notch (2) and cover notch (2), and make closing plate (10) and not make the high pressure steam leakage of notch (2) with the space sealing of bottom plate (12) and upper cover plate composition as far as possible.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210554451.0A CN103029846B (en) | 2012-12-20 | 2012-12-20 | Notch sealing device for steam catapult of aircraft carrier |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210554451.0A CN103029846B (en) | 2012-12-20 | 2012-12-20 | Notch sealing device for steam catapult of aircraft carrier |
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| Publication Number | Publication Date |
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| CN103029846A CN103029846A (en) | 2013-04-10 |
| CN103029846B true CN103029846B (en) | 2014-12-10 |
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| CN201210554451.0A Active CN103029846B (en) | 2012-12-20 | 2012-12-20 | Notch sealing device for steam catapult of aircraft carrier |
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|---|---|---|---|---|
| CN107187610B (en) * | 2017-05-26 | 2019-08-09 | 中国航天空气动力技术研究院 | Bomb radiolysis locking device |
| CN115523753A (en) * | 2022-09-17 | 2022-12-27 | 江苏晨朗电子集团有限公司 | Preparation facilities of abundant tombarthite permanent magnet material |
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| US4252285A (en) * | 1979-04-30 | 1981-02-24 | The United States Of America As Represented By The Secretary Of The Navy | Dynamic seal for slotted cylinder |
| CN101311072B (en) * | 2007-05-21 | 2010-04-21 | 赵家瑞 | Steam power aircraft catapult vertical elongated slot sealed system |
| CN102040007B (en) * | 2009-10-19 | 2014-05-14 | 李家春 | Bypass cylinder honeycomb dynamically sealed steam ejector with pneumatically closed zipper |
| CN102343981A (en) * | 2010-07-30 | 2012-02-08 | 杨建东 | Steam power catapult of aircraft carrier plane |
| CN203005755U (en) * | 2012-12-20 | 2013-06-19 | 魏伯卿 | Notch sealing system used for steam ejector of aircraft carrier shipboard aircraft |
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