CN207242064U - The guide tracked aircraft arrestment device of electromagnetism - Google Patents
The guide tracked aircraft arrestment device of electromagnetism Download PDFInfo
- Publication number
- CN207242064U CN207242064U CN201720874365.6U CN201720874365U CN207242064U CN 207242064 U CN207242064 U CN 207242064U CN 201720874365 U CN201720874365 U CN 201720874365U CN 207242064 U CN207242064 U CN 207242064U
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- deck
- aircraft
- fixed
- carrier
- deceleration
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Abstract
It the utility model is related to a kind of guide tracked aircraft arrestment device of electromagnetism, including carrier aircraft deck, deck fixed pulley is fixedly mounted with respectively in carrier aircraft deck rear end both sides, two top positioning pulleys and two lower part positioning pulleys are fixedly mounted with deck two side rear end is longitudinally asymmetric respectively, belowdecks square both sides are laterally fixedly mounted with two deceleration cylinders respectively, the uniform arranging conductors coil in deceleration cylinder, bottom in deceleration cylinder is fixedly mounted with horizontal slide rail, pillar-shaped permanent magnet is installed in horizontal slide rail, interception rope is connected between the left end of two pillar-shaped permanent magnets, the both sides for intercepting rope are pierced by after deceleration cylinder again respectively successively by lower part positioning pulley respectively, top positioning pulley and deck fixed pulley are oriented to after the upper surface middle part tandem of carrier aircraft deck.The utility model substantially reduces space hold, uniform to the active force of carrier-borne aircraft, easy to maintain, easy to adjust, saves the energy, is applicable in various types of carrier-borne aircraft landing.
Description
Technical field
The utility model belongs to that fixed-wing is carrier-borne or the landing arrester technical field of roadbed short distance landing aircraft, especially
It is to be related to a kind of guide tracked aircraft arrestment device of electromagnetism.
Background technology
Active service aircraft carrier using hydraulic machinery motion mode absorb carrier-borne aircraft warship kinetic energy, as the U.S. Mk7 types stop
Device, its specific mode are the hydraulic cylinders plunger push-in arresting engine, force the fluid in hydraulic cylinder to be flowed into by control valve
Fluid cylinder is stored, until carrier-borne aircraft completes steady and controllable warship recycling.Wherein, arresting engine is the energy absorbing component of arrester, bag
Water turbine, the conical drum with certain inertia, mechanical brake device, induction conductivity and a connection are included with upper member
Rotation axis, arrester wires is connected to pulley rope, winds conical drum by follower pulley, is finally fixed on conical drum.Should
System can accurately control aircraft arrestment the process of warship, and the distance that aircraft can be controlled to stop above deck, but use at present
Aircraft arrestment device there are following defect：(1) it is uneven to the active force of carrier-borne aircraft in removal process, cause carrier-borne aircraft knot
Structure loss is big, when carrier-borne aircraft pintle contact arrester wires moment, can produce the phenomenon slowed down suddenly, i.e., the so-called arrester wires that is subject to is " violent
The effect of drawing "；(2) upgrading potential is little, it is impossible to which recycling is heavier, and the faster aircraft of speed, and future will carry on aircraft carrier
Lightweight unmanned plane；(3) since the transmission process of machinery is complicated, cause the process of maintenance cumbersome, expend substantial amounts of manpower.(4)
Need to occupy the space of larger deck lower part, cause space availability ratio not high；(5) work expends a large amount of electric energy.
The content of the invention
The purpose of the utility model is to overcome the deficiencies in the prior art, there is provided a kind of guide tracked aircraft arrestment dress of electromagnetism
Put.
The utility model solves its technical problem and takes following technical scheme to realize：
A kind of guide tracked aircraft arrestment device of electromagnetism, including carrier aircraft deck, at the two corners of carrier aircraft deck upper surface rear portion, point
Other horizontal symmetrical is fixed with two deck fixed pulleys, in the two side rear end on carrier aircraft deck at the upper surface of carrier aircraft deck, point
It is not longitudinally asymmetric to be fixedly mounted with two top positioning pulleys, in the lower section of two top positioning pulleys at the lower surface of carrier aircraft deck,
It is longitudinally asymmetric respectively to be fixedly mounted with two lower part positioning pulleys, in the lower section on carrier aircraft deck, laterally it is fixed with respectively along warship body two side
Two deceleration cylinders, inside deceleration cylinder, are uniformly placed with conductor coils, conductor coils are by deceleration cylinder from left to right along medial wall of the tube
External power supply is powered, and the bottom in deceleration cylinder is fixed with horizontal slide rail, is provided with horizontal slide rail and transversely slides vertically
The pillar-shaped permanent magnet that rail slides, is provided with bridle port, on a left side for described two pillar-shaped permanent magnets in the middle part of the left end sealing plate of deceleration cylinder
Interception rope is connected between end, the both sides for intercepting rope are each passed through after bridle port to be positioned by lower part successively respectively again and slide
Wheel, top positioning pulley and deck fixed pulley are oriented to after the upper surface middle part tandem of carrier aircraft deck.
Moreover, the left end sealing plate inner annular in deceleration cylinder is fixed with a circle transverse direction compression spring, on the right side of the horizontal compression spring of a circle
Side head is fixed with decelerating barrier.
Moreover, the deceleration cylinder uses the positional structure at the left right bottom of height.
Moreover, reset fixed pulley is fixed with respectively on the outside of the right end of described two deceleration cylinders, in described two columns forever
The right end of magnet is respectively and fixedly connected with two isometric reset ropes, two reset after ropes are oriented to from reset fixed pulley vertically to
Under, the other end is connected with two contour reset pouring weights, and two are fixed with the lower section same level that two reset pouring weight
With the positioning table of Hull Welding.
Moreover, the external power supply is voltage controller power source.
Moreover, the pillar-shaped permanent magnet is equipped with battery by inside, the electromagnet of exterior wound around coil replaces.
The advantages of the utility model and good effect are：
1st, due to being influenced in whole guide rail by constant electromagnetic power in the utility model, to the work of carrier-borne aircraft in removal process
Firmly uniformly, carrier-borne aircraft structural failure is little, can be in guide rail for electromagnetism iron slider when carrier-borne aircraft pintle contact arrester wires moment
In move freely, the effect of arrester wires " wrench " will not be subject to.
2nd, the utility model upgrading potential is big, and the electromagnetic force of bigger can be obtained by way of high current, so as to return
Receive heavier, the faster aircraft of speed.
3rd, the mechanical transmission course of the utility model is simple, easy to maintain, and maintenance period length, will not expend substantial amounts of people
Power.
4th, the utility model will not occupy larger deck lower space, Ke Yiteng since guide rail is in aircraft carrier warship body both sides
Go out more spaces and park more carrier-borne aircrafts, so as to improve space availability ratio.
5th, produce electricl energy, can charge at the same time for external power supply during the utility model electromagnetism iron slider cutting magnetic line, from
And achieve the purpose that energy saving.
Brief description of the drawings
Fig. 1 is the dimensional structure diagram of the utility model；
Fig. 2 is the horizontal schematic cross-sectional view of deceleration cylinder in the utility model.
Embodiment
The utility model embodiment is further described below in conjunction with attached drawing, it is emphasized that, implementation below
It is illustrative, rather than limited, it is impossible in this embodiment as the restriction to the utility model.
A kind of guide tracked aircraft arrestment device of electromagnetism, as shown in the figures 1 and 2, including carrier aircraft deck 2, in carrier aircraft deck upper table
At the two corners of face rear portion, horizontal symmetrical is fixed with two deck fixed pulleys 1 respectively, and the both sides surface rear end on carrier aircraft deck is close to be carried
It is longitudinally asymmetric respectively to be fixedly mounted with two top positioning pulleys 4 at the upper surface of machine deck, it is close in the lower section of two top positioning pulleys
It is longitudinally asymmetric respectively to be fixedly mounted with two lower part positioning pulleys 9 at the lower surface of carrier aircraft deck, in the lower section on carrier aircraft deck, along warship body two
Side wall is laterally fixed with two deceleration cylinders 6 respectively, and inside deceleration cylinder, conductor lines are uniformly placed with from left to right along cylinder side inner wall
Circle 13, conductor coils are powered by deceleration cylinder external power supply 14, and the bottom in deceleration cylinder is fixed with horizontal slide rail 7 vertically,
The pillar-shaped permanent magnet 5 that transversely slide slides is installed in horizontal slide rail, it is equal at the middle part of the left end sealing plate 10 of two deceleration cylinders
Bridle port 8 is provided with, is connected between the left end of described two pillar-shaped permanent magnets and intercepts rope 3, affixed two pillar-shaped permanent magnets
Both sides intercept rope and be each passed through after bridle port and slided surely by lower part positioning pulley, top positioning pulley and deck successively respectively again
Wheel is oriented to after the upper surface middle part tandem of carrier aircraft deck.
In the specific implementation of the utility model, to prevent pillar-shaped permanent magnet from being hit with deceleration cylinder left end sealing plate hardness,
Side ring dress is fixed with a circle transverse direction compression spring 11 in the left end sealing plate of deceleration cylinder, is fixed with and subtracts in the right side termination of the horizontal compression spring of a circle
Speed gear plate 12.
In the specific implementation of the utility model, after interception rope is completed to block machine task, to make interception rope reply immediately soon
Position, described two deceleration cylinders use the positional structure at the left right bottom of height, and after interception rope is completed to block machine task, two columns are forever
Magnet slides into the right end of deceleration cylinder along respective horizontal slide rail respectively under gravity, completes deceleration task.
In the specific implementation of the utility model, it is fixed sliding to be fixed with reset respectively on the outside of the right end of described two deceleration cylinders
Wheel 16, two isometric reset ropes 15 are respectively and fixedly connected with the right end of described two pillar-shaped permanent magnets, two reset ropes by
Reset after fixed pulley is oriented to vertically downward, the other end is connected with two contour reset pouring weights 17, is resetted at two under pouring weight
Two positioning tables 18 with Hull Welding are fixed with square same level, when pillar-shaped permanent magnet in deceleration cylinder proper reset
Afterwards, the reset pouring weight is just contacted with positioning table, resets position when side pillar-shaped permanent magnet could not be reached correctly in deceleration cylinder
When putting, which resets rope and pulling force is produced under the action of pouring weight is resetted, and pulls pillar-shaped permanent magnet proper reset, meanwhile, adjust
The pulling force for intercepting rope can be adjusted by resetting the weight of pouring weight, adapt to the landing of different type aircraft.
In the specific implementation of the utility model, the external power supply is voltage controller power source, adjusts the voltage number of external power supply
Value, changes the size of current in conductor coils, so as to change the magnetic field intensity in deceleration cylinder, changes the pulling force for intercepting rope, fits
Answer the landing of different type aircraft.
In the specific implementation of the utility model, the pillar-shaped permanent magnet is equipped with battery by inside, exterior wound around coil
Electromagnet replaces.
Claims (6)
1. a kind of guide tracked aircraft arrestment device of electromagnetism, including carrier aircraft deck, it is characterised in that：At carrier aircraft deck upper surface rear portion
At two corners, horizontal symmetrical is fixed with two deck fixed pulleys respectively, in the two side rear end on carrier aircraft deck on carrier aircraft deck
It is longitudinally asymmetric respectively to be fixedly mounted with two top positioning pulleys at surface, in the lower section of two top positioning pulleys close to carrier aircraft deck
It is longitudinally asymmetric respectively to be fixedly mounted with two lower part positioning pulleys at lower surface, it is horizontal respectively along warship body two side in the lower section on carrier aircraft deck
To two deceleration cylinders are fixed with, inside deceleration cylinder, conductor coils, conductor coils are uniformly placed with from left to right along medial wall of the tube
Powered by deceleration cylinder external power supply, the bottom in deceleration cylinder is fixed with horizontal slide rail, is provided with horizontal slide rail vertically
The pillar-shaped permanent magnet that transversely slide slides, is provided with bridle port, in described two columns forever in the middle part of the left end sealing plate of deceleration cylinder
Interception rope is connected between the left end of magnet, the both sides for intercepting rope are each passed through after bridle port to be distinguished successively under again
Portion's positioning pulley, top positioning pulley and deck fixed pulley are oriented to after the upper surface middle part tandem of carrier aircraft deck.
2. the guide tracked aircraft arrestment device of electromagnetism according to claim 1, it is characterised in that：In the left end sealing plate of deceleration cylinder
Inner annular is fixed with a circle transverse direction compression spring, and decelerating barrier is fixed with the right side termination of the horizontal compression spring of a circle.
3. the guide tracked aircraft arrestment device of electromagnetism according to claim 1, it is characterised in that：The deceleration cylinder uses left height
The positional structure at right bottom.
4. the guide tracked aircraft arrestment device of electromagnetism according to claim 1 or 3, it is characterised in that：In described two decelerations
Cylinder right end on the outside of be fixed with reset fixed pulley respectively, the right end of described two pillar-shaped permanent magnets be respectively and fixedly connected with two it is isometric
Reset rope, two reset ropes by reset fixed pulley be oriented to after vertically downward, the other end and two contour reset pouring weights
Connection, two positioning tables with Hull Welding are fixed with the lower section same level that two reset pouring weight.
5. the guide tracked aircraft arrestment device of electromagnetism according to claim 1, it is characterised in that：The external power supply is pressure regulation
Power supply.
6. the guide tracked aircraft arrestment device of electromagnetism according to claim 1, it is characterised in that：The pillar-shaped permanent magnet is by interior
Portion is equipped with battery, and the electromagnet of exterior wound around coil replaces.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720874365.6U CN207242064U (en) | 2017-07-19 | 2017-07-19 | The guide tracked aircraft arrestment device of electromagnetism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720874365.6U CN207242064U (en) | 2017-07-19 | 2017-07-19 | The guide tracked aircraft arrestment device of electromagnetism |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207242064U true CN207242064U (en) | 2018-04-17 |
Family
ID=61878533
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720874365.6U Expired - Fee Related CN207242064U (en) | 2017-07-19 | 2017-07-19 | The guide tracked aircraft arrestment device of electromagnetism |
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| Country | Link |
|---|---|
| CN (1) | CN207242064U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107310743A (en) * | 2017-07-19 | 2017-11-03 | 张博放 | A kind of guide tracked aircraft arrestment device of electromagnetism |
-
2017
- 2017-07-19 CN CN201720874365.6U patent/CN207242064U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107310743A (en) * | 2017-07-19 | 2017-11-03 | 张博放 | A kind of guide tracked aircraft arrestment device of electromagnetism |
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| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20180417 Termination date: 20190719 |
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| CF01 | Termination of patent right due to non-payment of annual fee |