CN103863571B - Aircraft ejection kit and airplane catapult method - Google Patents
Aircraft ejection kit and airplane catapult method Download PDFInfo
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- CN103863571B CN103863571B CN201210536743.1A CN201210536743A CN103863571B CN 103863571 B CN103863571 B CN 103863571B CN 201210536743 A CN201210536743 A CN 201210536743A CN 103863571 B CN103863571 B CN 103863571B
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Abstract
The present invention relates to the equipment facility taken off in civil airport or aircraft carrier for second-mission aircraft, a kind of aircraft ejection kit is provided, it uses controllable electromagnetic to drive magnetic slider device to replace traditional steam driven piston device, the deformable sine curve utilizing multiple movable pulley to carry out drag rope is structured the formation and is realized launching aircraft, and it includes at least three fixed pulley, rope winch, multiple movable pulley, provides track, drive the magnetic slider of movable pulley and drive a plurality of slide rail of calutron of calutron.This device capacity usage ratio is high；Range of application can be expanded and can be used for the Assisted Take Off of civil aircraft；Improve the safety and comfortableness taken off；Complete equipment structure is the simplest, safety；Reduce device along the sliding length run on direction.The present invention also provides for a kind of airplane catapult method.
Description
Technical field
The equipment that the present invention relates to take off for second-mission aircraft in civil airport or aircraft carrier sets
Execute, particularly relate to a kind of aircraft ejection kit.
Background technology
Before the taking off of aircraft, need on very long runway, to be accelerated sliding race, until possessing
The speed enough taken off, just can leave ground.In this process, electromotor is all the time with maximum
Operating mode is in work, and oil consumption rate is the highest, and the sliding distance run is longer, can not meet short at all
The demand that distance is taken off.
In order to meet the short field take-off of aircraft, especially meet carrier-borne aircraft on aircraft carrier
Short field take-off, current aircraft carrier mainly uses the method that steam ejection takes off, i.e. utilizes height
The steam of temperature high pressure promotes the mode that piston driving aircraft accelerates.
But, the steam catapult of prior art exists following not enough:
One, structure is complicated, and cost is high.Nearly 500 tons of one steam power ejector gross weight,
It is segmented into 7 Major Systems: take-off system, vapour system, homing system, hydraulic pressure by function
System, pre-Force system, lubricating system, control system.These systems can be decomposed into again more
Mini system；
Two, the highest to material, technological requirement.Now in addition to individual countries, a lot of developed countries
The most all can not manufacture, rely primarily on purchase；
Three, efficiency is low, expends big.Once launch and to consume 800～1000 kg of vapor.Produce
The water of desalination first by desalinization, then to be heated into High Temperature High Pressure in boiler by these steam raw
Steam, and the ejection power that these steam change into piston only has 4-6%, and this 4% dynamic
Power is to convert in the stroke of front ten meters of piston, and the power of remaining 2% is that piston is remaining 90
The stroke of rice changing into inertia motion, if launched with minimum interval, needing to consume boat
The steam of female boiler 20%；
Four, system complex necessarily brings operator many, ejector need operator and
Reform personnel about 120 people.The Operation and maintenance personnel that four ejectors need are up to more than 500,
Accounting for about the 10% of the establishment of full warship, maintenance capacity is big, launches 400 to 500 times and is accomplished by the grounding,
By the maintenance carrying out 1-2 days with warship personnel；
Five, launching power big, power can not adjust, and flies the comfortableness perceptual difference of staff on board.
Six, current steam ejector technology uses the cylinder that cracks, and piston is direct and sliding by cracking
Shuttle links, and causes cylinder to be easily deformed, cracks and need particulate metal sealing strip to seal, gas
Close property reduces, and vapour losses amount is big, and metal sealing bar is easily damaged to directly affect and launches cylinder
Service life.
Summary of the invention
It is an object of the invention to provide a kind of novel aircraft ejection kit, it can solve the problem that above-mentioned
The following problem that prior art exists:
1) energy ecology solving current steam catapult-launching gear is low, and equipment is fragile, safeguards
The problem that cost is high；
2) solve that the power of current steam catapult-launching gear is too quickly and nonadjustable problem；And
3) after solving problem two, this device can apply to civil airport, assists civil aircraft
Taking off, the oil consumption that solves to take off is high, ground CO2, and DS NOx Est is high, ground run distance is very long etc. asks
Topic；
4) problem that current steam catapult-launching gear homing device is complicated is solved.
To this end, according to the first aspect of the invention, it is provided that a kind of aircraft ejection kit, use
Controllable electromagnetic drives magnetic slider device to replace traditional steam driven piston device, and utilization is many
Individual movable pulley carries out the deformable sine curve of drag rope and structures the formation and realize launching aircraft.
Specifically, the present invention provides a kind of aircraft ejection kit, including:
At least three fixed pulley, it includes the first fixed pulley arranged along runway interval the first distance
Threeth fixed pulley spaced apart with the second fixed pulley and the second fixed pulley；
Rope winch, its offer walks in the pull rope between described first fixed pulley and the 3rd fixed pulley
Rope；
Multiple movable pulleys, it is arranged between the second fixed pulley and the 3rd fixed pulley, described drag rope
Walk on many group movable pulleys and extend in sine curve；
A plurality of slide rail, every slide rail includes track, slidably and carries a movable pulley along track
Magnetic slider, it is positioned at track one end and is controlled the first calutron of magnetic pole by institute's galvanization；
Wherein, described a plurality of slide rail is arranged to: when aircraft is positioned at race start and is in and slides beginning shape
During state, magnetic slider is positioned at described one end of track, now described between the adjacent movable pulley of each two
Drag rope is the shortest, and the first calutron relative magnetism slide block produces electromagnetic repulsive force and promotes magnetic
Slide block is along slide to pull described drag rope for taking off the ejection force providing enough；When flying
Machine is positioned at runway takeoff point and is in when sliding done state, magnetic slider away from described one end of track,
Now the described drag rope between the adjacent movable pulley of each two is the longest, and the first calutron stops producing
Described electromagnetic repulsive force, or start to produce the electromagnetic attraction of relative magnetism slide block, so that magnetic is sliding
Block stopped forward slip before arriving at the other end of track；And
Wherein, the second distance between described race start and runway takeoff point is fixed sliding less than described first
Described first distance between wheel and the second fixed pulley.
Preferably, when described magnetic slider stops forward slip, described first calutron is borrowed
The electromagnetic attraction helping the control of described electric current starts or continues to produce relative magnetism slide block is straight
Described one end of slide rail is returned to magnetic slider.
Preferably, also include being positioned at the described track other end and controlling magnetic pole by institute's galvanization
The second calutron, the magnetic of the magnetic pole of described second calutron and described first calutron
Pole contrast.
It is further preferred that two adjacent slide rails from respective described one end to the respective described other end
The direction extended is the most contrary.
Preferably, described magnetic slider is permanent magnet or electromagnet.
Preferably, described fixed pulley and/or described movable pulley are taken turns equipped with anticreep.
Preferably, each described fixed pulley and/or described movable pulley are configured to assembly pulley, and described
The quantity of drag rope is corresponding to the quantity of described assembly pulley middle pulley.
Preferably, between two adjacent described movable pulleys, the 4th fixed pulley is also arranged.
Preferably, away from a movable pulley of described 3rd fixed pulley in the plurality of movable pulley
And also arrange at least one fixed pulley between described second fixed pulley.
Preferably, also include traction apparatus, when aircraft is in and slides original state, this traction apparatus
It is connected between rope and undercarriage at described first fixed pulley；It is at aircraft and slides
During done state, this traction apparatus is disconnected with undercarriage.
According to the second aspect of the invention, it is provided that a kind of utilize flying of above-mentioned aircraft ejection kit
Machine catapult technique, comprises the steps:
Traction apparatus is connected to the traction at the undercarriage that is on race start and the first fixed pulley
Between rope；
Control the magnetic pole that the first calutron makes it produce and with magnetic slider homopolar-repulsion thus promote magnetic
Slide block is slided away from the first calutron by track one end, and movable pulley moves with magnetic slider and drives
Drag rope moves to the 3rd fixed pulley from the first fixed pulley；
Traction apparatus moves with drag rope and drives aircraft to add ski-running along runway and runs, and runs until aircraft arrives
Obtain required speed at road takeoff point and depart from traction apparatus and take off；
Control the first calutron make its lose magnetic pole or change the first calutron described magnetic pole so that
Magnetic slider stopped sliding before arriving the track other end.
Preferably, also include by controlling the magnetic slider that the magnetic pole of the first calutron makes stopping slide
Step by one end described in the attraction of the first calutron and regression orbit.
Preferably, also include that controlling the second calutron makes it produce the magnetic pole phase with the first calutron
The step of anti-magnetic pole.
Preferably, also include controlling the first calutron and the second electromagnetism by the size controlling electric current
The size of electromagnetic force produced by device and then the step of the traveling of control drag rope.
The beneficial effect of the invention:
1) utilize galvanomagnetic-effect to increase substantially the utilization rate of energy, convert electrical energy into a greater extent
Kinetic energy；
2) by civil aircraft is launched power-assisted, can reduce the civil aircraft fuel oil consumption on ground can
Reach 70%, significantly less noise and the discharge of pollutant simultaneously, reduces runway length, reduces
Runway construction cost；
3) owing to can control calutron by controlling electric current, thus it drives power adjustable, carries
Safety that height takes off and comfortableness；
4) positive and negative adjustable by magnetic pole, former drive system can become brakes by Transient transformation, makes the whole series set
Standby structure is the simplest, safety；
5) structured the formation by the sinusoidal of pulley and drag rope, reduce device and run direction along sliding
On length.
By with reference to embodiment disclosed below, these and other aspects of the present invention
Will clearly be illustrated.
Accompanying drawing explanation
The structurally and operationally mode of the present invention and further purpose and advantage will be by following knots
The description closing accompanying drawing is better understood, wherein, and the unit that identical reference marker mark is identical
Part:
Fig. 1 shows a kind of airplane catapult dress of preferred implementation according to a first aspect of the present invention
The plane figure put, wherein this aircraft ejection kit is in state to be launched；
Fig. 2 shows the another kind of plane figure of aircraft ejection kit in Fig. 1, and wherein this flies
Machine catapult-launching gear is in the resting state after having launched；
Fig. 3 shows in Fig. 1 magnetic slider and the assembly of movable pulley in aircraft ejection kit；
Fig. 4 shows that the fixed pulley of aircraft ejection kit in Fig. 1 and/or movable pulley are taken turns with anticreep
Example；
Fig. 5 shows that fixed pulley and/or movable pulley are configured to the structure of assembly pulley；
Fig. 6 shows the airplane catapult method of preferred implementation according to a second aspect of the present invention
Flow chart.
Description of reference numerals
1 slideway 2 first calutron
3 second calutron 4 magnetic slider
5 movable pulley 61 first fixed pulleys
62 second fixed pulley 63 the 3rd fixed pulleys
64 the 4th fixed pulley 65 the 5th fixed pulleys
7 rope winch 8 drag ropes
9 traction apparatus 10 runways
11 aircraft 12 race start
13 takeoff point 14 anticreep wheels
15 assembly pulleys
Detailed description of the invention
Below in conjunction with accompanying drawing, the preferred embodiment of the present invention is described.
First some terms of the art are introduced, wherein:
Airplane catapult takes off: refer to the conventional fixed-wing carrier-borne aircraft function by catapult-launching gear, relatively
Short within discrete time, aircraft is accelerated to regulation from warship speed.
Traction apparatus: catapult-launching gear attachment means between undercarriage, for launch
Accelerate.
Seeing shown in Fig. 1 and Fig. 2, in a preferred embodiment of the invention, airplane catapult fills
Put and include five by track the 1, first calutron 2 and the second calutron 3, magnetic slider (example
Such as permanent magnet or electromagnet) 4 and the slide rail that constitutes of the movable pulley 5 that carried by magnetic slider 4,
Five fixed pulley 61-65, rope winch 7, through the first fixed pulley after rope winch 7 elder generation
61, on second fixed pulley the 62, the 5th fixed pulley the 65, the 4th 64, five articles of slide rails of fixed pulley
Five movable pulleys 5, finally arrive the drag rope 8 of the 3rd fixed pulley 63, traction apparatus 9, should
Traction apparatus is connected to the drag rope 8 between the first fixed pulley 61 and the second fixed pulley 62 and position
Between the undercarriage of the aircraft 11 on runway 10.When aircraft ejection kit starts, aircraft
11 start to accelerate to slide along runway 10 from race start 12 under the drive of traction apparatus 9, until
Arrive runway takeoff point 13 obtain takeoff speed and depart from traction apparatus 9 and complete to take off.
The most as depicted in figs. 1 and 2, the first fixed pulley 61 and the second fixed pulley 62 run along aircraft
Road 10 layout at a distance, this distance is more than between race start 12 and runway takeoff point 13
Distance, thereby may be ensured that aircraft completes accelerated slip and taking off on runway.3rd is fixed sliding
Between wheel 63 and the second fixed pulley 62 and between the 3rd fixed pulley 63 and the 4th fixed pulley 64
Layout will be spaced, in order to arrange a plurality of track 1.It is equiped with in one end of every track 1
One calutron 2, is preferably equiped with the second calutron 3, the two calutron at the other end
Can be controlled them have by controlling their startup or closedown and institute's galvanization direction and size
Nonmagnetic, magnetic pole and the size of produced electromagnetic force.Wherein, the magnetic of the second calutron 3
Pole and the magnetic pole contrast of the first calutron 2, to coordinate the first calutron 2 to improve magnetic
The slip effect of property slide block 4.Preferably, two adjacent orbits 1 from respective one end to the most another
The direction that one end extends is completely contrary, so that adjacent two movable pulleys 5 are along antipodal side
To slip, drag rope 8 length between them can be enlarged, and facilitates the first fixed pulley 61 He
The quick of drag rope 8 between second fixed pulley 62 is moved.
Fig. 1 shows the plane figure of the aircraft ejection kit of preferred implementation, wherein should
Aircraft ejection kit is in state to be launched.In this condition, aircraft 11 is positioned at race start
12 and be in and treat sliding state, magnetic slider 4 is positioned at track 1 and is equiped with the first calutron 2
One end, now, drag rope 8 length between the adjacent movable pulley of each two 5 is the shortest, this
Time, starting aircraft ejection kit, the first calutron 2 relative magnetism slide block 4 produces electromagnetism row
Repulsion, the second calutron 3 relative magnetism slide block 4 produces electromagnetic attraction simultaneously so that magnetic
Property slide block 4 slide to the other end along track 1 by one end, thus drag rope 8 is quickly pulled
And drive traction apparatus 9 and then drive aircraft 11 accelerated slip, make aircraft 11 arrive runway and take off
Obtain takeoff speed during point 13 and depart from traction apparatus 9.It will be seen from figure 1 that at airplane catapult
When device is in state to be launched, the drag rope 8 walking path between five movable pulleys 5
The sine curve less in amplitude extends.
Fig. 2 shows the another kind of plane figure of the aircraft ejection kit of preferred implementation,
Wherein this aircraft ejection kit is in the resting state after having launched.Runway is arrived at aircraft 11
Takeoff point 13 is also in when sliding done state, and magnetic slider 4 is equiped with away from track 1
One end of one calutron 2 the close other end being equiped with the second calutron 3, the most often
Drag rope 8 length between two adjacent movable pulleys 5 is the longest, and the first calutron 2 is closed
Close thus stop producing electromagnetic repulsive force, or the magnetic pole changing the first calutron 2 makes it start
Produce the electromagnetic attraction of relative magnetism slide block 4, so that magnetic slider 4 is arriving at track 1
This other end before stop forward slip collision free phenomenon generation.Certainly, the is being controlled
During one calutron 2, control the second calutron 3 the most simultaneously.Specifically, sliding at aircraft
At the end of row, the second calutron 3 is also turned off thus stops producing electromagnetic attraction, or changes
The magnetic pole becoming the second calutron 3 makes its electromagnetic repulsive force starting to produce relative magnetism slide block 4,
Thus more efficiently promote magnetic slider 4 stopped before arriving at this other end of track 1 to
The generation of front slide collision free phenomenon.When magnetic slider 4 stops sliding, whole device is i.e.
It is in the state of Fig. 2.
In order to meet the use next time of aircraft ejection kit, it is preferable that in described magnetic slider
During 4 stopping forward slip, the first calutron 2 is opened by means of to wherein alive control
Beginning or the electromagnetic attraction of continuation generation relative magnetism slide block 4, the second calutron 3 is borrowed simultaneously
Help to wherein alive control start or continue to produce relative magnetism slide block 4 electromagnetism row
Repulsion, until one end of installing first calutron 2 of magnetic slider 4 regression orbit 1.
As it is shown on figure 3, movable pulley 5 is carried in magnetic slider 4, thus when magnetic slider 4
Under the influence of a magnetic field along track 1 slide time, movable pulley 5 can be driven to move together.Although figure
In do not show magnetic slider 4 and the sliding matching structure of track 1, but it is to be understood that, track
Groove or protruding rail can be provided with on 1, protruding rail or recessed can be correspondingly provided with in magnetic slider 4 simultaneously
Groove, thus be bonded with each other.
In addition, it is to be understood that in order to avoid drag rope is slided from fixed pulley and movable pulley
De-, an anticreep wheel 14 can be equipped with on each fixed pulley and movable pulley.As shown in Figure 4, anti-
De-wheel 14 can be directly connected on fixed pulley or movable pulley by means of the connection between pulley spindle.
It should also be understood that each fixed pulley and/or movable pulley may be configured as single pulley or
The assembly pulley connected as one by several pulleys.As it is shown in figure 5, each assembly pulley includes 3
Pulley, so, drag rope 8 can arrange 3, thus improves the peace of aircraft ejection kit
Full reliability.
It should be noted that particular number described above is all the spy in this preferred implementation
Fixed setting, they can be changed as required.Such as, the number of the quantity of track, fixed pulley
Amount, the quantity of movable pulley, the quantity of assembly pulley middle pulley, they all can be made as required
Adjust and arrange.
Aircraft ejection kit construction and work process to this preferred implementation below is retouched
State.
First, as it is shown in figure 1, arrange 5 tracks 1, one end of track 1 arranges first
Calutron 2, the other end arranges the second calutron 3, and these calutrons can pass through circuit
Change magnetic pole.Arrange magnetic slider 4 on path 1, magnetic slider 4 is arranged and drives
Pulley 5.Meanwhile, there also is provided 5 fixed pulley 61-65,5 movable pulleys 5, rope winch 7,
Drag rope 8, traction apparatus 9.Traction apparatus 9 is fixed on drag rope.Drag rope 8 one end
Connecting the 3rd fixed pulley 63, the other end connects rope winch 7.Time to be launched, magnetic slider 5
Near at the first calutron 2, drag rope 8 is wound around in the mode such as Fig. 1 of movable pulley 5
Shown in, to structure the formation with the sine curve that amplitude is less, aircraft 11 and traction apparatus 9 connect, and rest on
At the starting point 12 of runway 10.
When aircraft to start to slide, the first calutron 2 and the second calutron 3 start to open
Dynamic, produce magnetic pole.Magnetic pole and the magnetic pole of magnetic slider 4 that first calutron 2 produces produce
The effect of " homopolar-repulsion ", meanwhile, the second calutron 3 and magnetic slider 4 produce " different
The most attracting " effect, then drive magnetic slider 4 to slide along track 1, drive dynamic simultaneously
Pulley 5 pulling traction rope rope 8, drag rope 8 pulls traction apparatus 9, makes aircraft 11 start
Add ski-running on runway 10 to run.
Aircraft 11 accelerates at the takeoff point 13 preset at race start 12, now aircraft speed
Degree has met required speed of taking off, and just departs from traction apparatus 9 and starts to take off.Simultaneously,
Magnetic slider 4 is accelerated to slide and close to the second calutron 3 in track 1, in order to prevent with
There is high velocity impact in the second calutron 3, then needs to change the first calutron 2 and the second electricity
The magnetic pole of magnetic device 3, makes the first calutron 2 and magnetic slider 4 produce " heteropole is attracting "
Effect, make magnetic pole that the second calutron 3 produces and the magnetic pole of magnetic slider 4 reach " with
Repel each other in pole " effect, make magnetic slider 4 slow down until slide stop, traction apparatus 9 is also simultaneously
Stopping sliding, now calutron 2,3 quit work, and whole aircraft ejection kit presents Fig. 2
State.
After aircraft safety takes off, rope winch 7 is started working, and regains drag rope 8, makes
After state to be launched is arrived in magnetic slider 4 playback, stop rope winch 7 and work, whole aircraft bullet
Injection device presents again the state to be launched of Fig. 1.
According to the second aspect of the invention, it is provided that a kind of utilize flying of above-mentioned aircraft ejection kit
The preferred implementation of machine catapult technique.As shown in Figure 6, the method comprises the steps:
Step S1 of traction apparatus is installed: be connected to be on race start 12 by traction apparatus 9
Between drag rope 8 at the undercarriage of aircraft 11 and the first fixed pulley 61；
Start step S2 of calutron: start the first calutron 2 and the second calutron 3,
Make magnetic pole and magnetic slider 4 homopolar-repulsion that the first calutron 2 produces and the second calutron
3 magnetic poles produced are attracting with magnetic slider 4 heteropole, thus promote magnetic slider 4 by track 1
One end to the other end slide, the movable pulley 5 moved with magnetic slider 4 drives pull rope
Rope 8 and then drive traction apparatus move to the second fixed pulley 62 from the first fixed pulley 61；
Aircraft departs from step S3 that traction apparatus takes off: under the effect of traction apparatus 9, aircraft 11
Add ski-running along runway 10 to run, until aircraft arrives obtains required speed at runway takeoff point 13 also
Depart from traction apparatus 9 to take off；
Stop step S4 of magnetic slider: close the first calutron 2 and the second calutron 3
Make its lose magnetic pole or change they magnetic pole so that magnetic slider 4 arrive track 1 another
Stop before end sliding.
Step S5 of magnetic slider playback: control the first calutron 2 and magnetic of the second calutron 3
Pole makes magnetic slider 4 that stopping slides by the attraction of the first calutron 2 and the second calutron
The repulsion of 3 and above-mentioned one end of regression orbit 1.
It should be understood that, above-mentioned embodiment can also include controlling the by the size controlling electric current
The size of electromagnetic force produced by one calutron and the second calutron and then the row of control drag rope
The step entered.So, different take off required speed and can obtain effective guarantee.
The aircraft ejection kit that the present invention provides utilizes galvanomagnetic-effect that the utilization of energy is greatly improved
Rate, converts electrical energy into kinetic energy to a greater extent；And may apply to civil aircraft aspect, pass through
Civil aircraft is launched power-assisted, the civil aircraft fuel oil consumption on ground can be reduced up to 70%, with
Time significantly less noise and the discharge of pollutant, reduce runway length, reduce runway cost of erection
With；Owing to can control calutron by controlling electric current, thus it drives power adjustable, it is possible to
Improve the safety and comfortableness taken off；Positive and negative adjustable by magnetic pole, former drive system can Transient transformation
Become brakes, make that complete equipment structure is the simplest, safety；It addition, by pulley and pull rope
The sinusoidal of rope is structured the formation, and reduces device along the sliding length run on direction.
The heretofore described case that is embodied as is only the preferable case study on implementation of the present invention, and
The non-practical range being used for limiting the present invention.The most all content institutes according to scope of the present invention patent
Equivalence change and the modification made, broadly falls into protection scope of the present invention.
Claims (14)
1. an aircraft ejection kit, it is characterised in that including:
At least three fixed pulley, it includes first arranged along runway (10) interval the first distance
Fixed pulley (61) and the second fixed pulley (62) and the second fixed pulley (62) the spaced apart 3rd
Fixed pulley (63)；
Rope winch (7), its offer walks in described first fixed pulley (61) and the 3rd fixed pulley (63)
Between drag rope (8)；
Multiple movable pulleys (5), its be arranged in the second fixed pulley (62) and the 3rd fixed pulley (63) it
Between, described drag rope walks in be organized on movable pulley (5) more and extends in sine curve；
A plurality of slide rail, every slide rail includes track (1), slidably and carries one along track (1)
The magnetic slider (4) of individual movable pulley (5), it is positioned at track (1) one end and is controlled by institute's galvanization
First calutron (2) of magnetic pole processed；
Wherein, described a plurality of slide rail is arranged to: when aircraft (11) is positioned at race start (12) and locates
In time sliding beginning state, magnetic slider (4) is positioned at described one end of track (1), and the most every two
Described drag rope between individual adjacent movable pulley (5) is the shortest, and the first calutron (2) phase
Magnetic slider (4) produces electromagnetic repulsive force promotes magnetic slider (4) to slide along track (1) to draw
Dynamic described drag rope is for taking off the ejection force providing enough；When aircraft is positioned at runway takeoff point
And be in when sliding done state (13), magnetic slider (4) away from described one end of track (1),
Now the described drag rope between the adjacent movable pulley of each two (5) is the longest, the first calutron (2)
Stop producing described electromagnetic repulsive force, or start to produce the electromagnetic attraction of relative magnetism slide block (4),
So that magnetic slider (4) stopped forward slip before arriving at the other end of track (1)；And
Wherein, the second distance between described race start and runway takeoff point is fixed sliding less than described first
Described first distance between wheel (61) and the second fixed pulley (62).
Aircraft ejection kit the most according to claim 1, it is characterised in that sliding in described magnetic
When block (4) stops forward slip, described first calutron (2) is by means of the control to described electric current
System starts or continues to produce the electromagnetic attraction of relative magnetism slide block (4) until magnetic slider (4) is returned
Return described one end of track (1).
Aircraft ejection kit the most according to claim 1, it is characterised in that also include being positioned at institute
State track (1) other end and controlled second calutron (3) of magnetic pole, institute by institute's galvanization
State the magnetic pole of the second calutron (3) and the magnetic pole contrast of described first calutron (2).
Aircraft ejection kit the most according to claim 3, it is characterised in that two adjacent orbits
The direction extended to the respective described other end from respective described one end is the most contrary.
Aircraft ejection kit the most according to claim 1, it is characterised in that described magnetic slider
(4) it is permanent magnet or electromagnet.
6. according to the aircraft ejection kit described in any one of claim 1 to 5, it is characterised in that institute
State and take turns (14) equipped with anticreep on fixed pulley and/or described movable pulley.
7. according to the aircraft ejection kit described in any one of claim 1 to 5, it is characterised in that every
Individual described fixed pulley and/or described movable pulley are configured to assembly pulley, and the quantity of described drag rope is corresponding
Quantity in described assembly pulley middle pulley.
8. according to the aircraft ejection kit described in any one of claim 1 to 5, it is characterised in that
The 4th fixed pulley is also arranged between two adjacent described movable pulleys (5).
9. according to the aircraft ejection kit described in any one of claim 1 to 5, it is characterised in that
Away from a movable pulley and described of described 3rd fixed pulley (63) in the plurality of movable pulley (5)
Two fixed pulleys also arrange at least one fixed pulley between (62).
Aircraft ejection kit the most according to claim 1, it is characterised in that also include traction
Device (9), when aircraft is in and slides original state, this traction apparatus (9) is at described first fixed pulley
(61) place is connected between rope and undercarriage；When aircraft is in and slides done state, should
Traction apparatus (9) is disconnected with undercarriage.
The airplane catapult of 11. 1 kinds of aircraft ejection kits utilized according to any one of claim 1 to 10
Method, it is characterised in that comprise the steps:
It is connected to traction apparatus (9) be in the undercarriage in runway (10) starting point (12) and
Between the drag rope (8) at one fixed pulley (61) place；
Control magnetic pole that the first calutron (2) makes it produce and magnetic slider (4) homopolar-repulsion thus
Magnetic slider (4) is promoted to be slided away from the first calutron (2) by track (1) one end, and dynamic sliding
Wheel (5) mobile with magnetic slider (4) and drive drag rope (8) from the first fixed pulley (61) to
3rd fixed pulley (63) is mobile；
Traction apparatus (9) is mobile with drag rope (8) and drives aircraft to add ski-running race along runway (10),
Until aircraft arrives runway takeoff point (13) place and obtains required speed and depart from traction apparatus and take off；
Controlling the first calutron (2) makes it lose magnetic pole or change the described of the first calutron (2)
Magnetic pole is so that magnetic slider (4) stopped sliding before arriving track (1) other end.
12. airplane catapult methods according to claim 11, it is characterised in that also include by control
The magnetic slider (4) that the magnetic pole making the first calutron (2) makes stopping slide is by the first electromagnetic installing
Put the attraction of (2) and the step of regression orbit (1) described one end.
13. airplane catapult methods according to claim 11, it is characterised in that also include controlling
Two calutrons (3) make it produce the step of the magnetic pole contrary with the magnetic pole of the first calutron (2).
14. airplane catapult methods according to claim 13, it is characterised in that also include by control
The size of electric current processed controls electricity produced by the first calutron (2) and the second calutron (3)
The size of magnetic force and then the step of the traveling of control drag rope (8).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210536743.1A CN103863571B (en) | 2012-12-12 | 2012-12-12 | Aircraft ejection kit and airplane catapult method |
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| CN104494841B (en) * | 2014-12-16 | 2016-10-12 | 董兰田 | Compound electric unit power turns strap towing aircraft ejector |
| CN104986350B (en) * | 2015-07-23 | 2017-08-25 | 漯河亚斯达科技有限公司 | Aircraft carrier ejector |
| CN105398580B (en) * | 2015-12-11 | 2017-11-24 | 南京涵曦月自动化科技有限公司 | Aircraft ejection kit |
| CN105973064A (en) * | 2016-06-24 | 2016-09-28 | 李少春 | Electromagnetic bow |
| CN106697318A (en) * | 2016-12-08 | 2017-05-24 | 国科天地科技有限公司 | Electromagnetic catapult for carrier aircraft |
| CN106904289A (en) * | 2017-03-21 | 2017-06-30 | 张宏 | Aircraft elevation angle ejector |
| CN107097968B (en) * | 2017-05-03 | 2019-06-11 | 西安伺动科技有限公司 | A kind of pneumatic unmanned plane emitter |
| CN107600447A (en) * | 2017-09-26 | 2018-01-19 | 甘肃省测绘工程院 | Air-mapping aircraft launching apparatus |
| CN110386261A (en) * | 2018-04-23 | 2019-10-29 | 韩培洲 | Aircraft carrier takes off catapult-launching gear |
| CN109131923A (en) * | 2018-10-29 | 2019-01-04 | 陈穗 | A kind of pull-type auxiliary taking-off system of airplane peculiar to vessel |
| CN112937900A (en) * | 2021-02-10 | 2021-06-11 | 张志刚 | Aircraft launching system, launching method and aircraft |
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| CN103863571A (en) | 2014-06-18 |
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