CN201385784Y - Aircraft carrier launching device - Google Patents
Aircraft carrier launching device Download PDFInfo
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- CN201385784Y CN201385784Y CN200920009443U CN200920009443U CN201385784Y CN 201385784 Y CN201385784 Y CN 201385784Y CN 200920009443 U CN200920009443 U CN 200920009443U CN 200920009443 U CN200920009443 U CN 200920009443U CN 201385784 Y CN201385784 Y CN 201385784Y
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Abstract
The utility model relates to an aircraft carrier launching device, which comprises a single-pendulum projectile mechanism. The single-pendulum projectile mechanism is arranged on one side edge of a carrier-borne aircraft and used for launching the carrier-borne aircraft an oscillating arm is arranged in the mechanism, the lower end of the oscillating arm is connected with a projectile, the projectile can be movably connected with the carrier-borne aircraft and can be provided with a boosting engine; the upper end of the oscillating arm has a single-pendulum suspension structure, which is a rotating shaft consisting of the external end of a suspension arm extending out of the outer side edge of the aircraft body and the upper end of the oscillating arm, the rotating shaft can be provided with a swing-assisting device with the vertical plane for swinging in parallel to an aircraft chord and vertical to the suspension arm, and one side of a pendulum is provided with a gantry at a certain height for arrangement of a carrier-borne aircraft to take off. Before the carrier-borne aircraft takes off, the projectile is stopped beside the gantry and movably connected with the carrier-borne aircraft. When the carrier-borne aircraft takes off, the projectile is not stopped any more but immediately performs the single-pendulum movement together with the carrier-borne aircraft, and the carrier-borne aircraft swings to the opposite side at an increasing speed and is launched to take off under the additional effect of the thrust force of the engine and / or the assisting pendulum.
Description
Technical field
The utility model relates to the structure of aircraft carrier, is specifically related to a kind of aircraft carrier launching apparatus.
Background technology
Aircraft carrier (abbreviation aircraft carrier) is as a kind of " super " main battle weapons, and power mainly is the ability in the tens of of its lift-launch even the extremely vast marine site of control that up to a hundred airplane carrier fighters had.Advance to attack the target that is in tens thousand of square kilometres of marine sites of circumference, keep the attack that to defend from the various weapons in the same vast marine site.The fighting capacity of weighing aircraft carrier mainly is to weigh the fighting capacity of the carrier-borne aircraft that can bring into play maximum horizontal that takes off on this aircraft carrier.
Now, the mode of taking off of world Navy aircraft carrier mainly contains catapult-assisted take-off, sliding jumping up flies (sliding perk flies) and vertical/short distance rolling start etc.Catapult-assisted take-off is to utilize the catapult-launching gear of arranging on the flight deck, to the carrier-borne aircraft applied thrust, it is reached from the warship takeoff speed in certain stroke.Cunning is jumped up and flown is the deck that upwarps that utilizes the aircraft carrier bow, realizes taking off under the high thrust of airborne driving engine.Vertically/the short distance rolling start then is to utilize the thrust vectoring of airborne driving engine to control to realize taking off, in view of the former Soviet Union " Ya Ke-38 " vertical/the short range attack plane is along with " Kiev " level aircraft carrier is retired together, and Britain vertical/discharging quantity and the voyage of short take-off and landing (STOL) formula " sea-gull " fighter plane be difficult to meet requirements, therefore this mode of taking off is used less at present.
The steam catapult-assisted take-off
After World War II, jet-propelled carrier-borne aircraft carries warship in succession.With the weight and the engine power calculating of carrier-borne aircraft at that time, need sliding distance of running more than 1000 meter." Nimitz " even of current tonnage maximum level aircraft carrier, the deck runway is rice surplus in the of 300 only.If there is not the help-fly of high-power ejector, the carrier-borne aircraft of full carry will be difficult to lift-off.Therefore world's military project circle is all being paid close attention to the more powerful novel ejector of development.
Steam catapult was come out August nineteen fifty, and prototype is the commandant Mitchell of British Naval Air Service reserve force development, and United States Navy has bought patent and it is full-fledged.On principle of work, steam catapult is with the slide block on the high pressure steam promotion piston drive ejection orbit, and the carrier-borne aircraft that is attached thereto is launched away.Even to this day, have only the U.S. to grasp the steam catapult technology, what medium-sized " gaullist " of connection state number nuclear aircraft carrier adopted also is U.S.'s steam catapult technique comprehensively.C-13-1 type steam catapult stroke on the large-scale aircraft carrier of the U.S. reaches 94.6 meters, 36.3 tons of heavy carrier-borne aircrafts can be launched away with the high speed of 185 joints (i.e. 339 kms/hour), can satisfy the requirement of taking off of F-14 fighter plane and E-2 early warning plane.
Sliding jumping up flies
Cunning is jumped up and flown principle is that slope, deck upper uplifting angle is considered as vibrating deflection.Carrier-borne aircraft rushes at oblique upper along the slope that upwarps, and forms inclined throw movements.States such as Russia, Britain, Italy, Spain and India are because technical limitation, can't develop technically with technology on the steam catapult that reaches a standard, so aircraft carrier warship bow is installed the platform that jumps (10 °～15 ° of deck, slope upper uplifting angles) and is helped to take off home.Carrier-borne aircraft power with oneself when taking off rushes to via the assistance of the platform that jumps in the air.The sliding take-off weight that flies and the efficient of taking off of jumping up is not as catapult-assisted take-off.Its Operational Effectiveness Rat can not show a candle to steam catapult.Be better than the F-14 opportunity of combat as Soviet Union's-33 opportunity of combat fighting capacity, be meant when both all can give full play to separately fighting capacity.But after they took off from separately aircraft carrier, situation had been not so just.On U.S. army's aircraft carrier, F-14 utilizes steam catapult to take off, even full carry also can go up to the air smoothly; And on Russia " storehouse is the Huangshui River assistant husband now " aircraft carrier, Soviet Union's-33 sliding jumping up can only be carried the effective carry that is equivalent to actual carry ability 50% when flying, and this has just dropped sharply the air battle ability and the combat radius of this heavy air superiority fighter.So generally believe that " storehouse is the Huangshui River assistant husband now " is not the adversary of U.S.'s aircraft carrier.
Electromagnetic launch in the research and development
Certainly steam catapult also has many shortcomings:
1, ejector not only occupies big between deck space, and also the side establishes facilities such as ejector steam storage tank, ejector pipeline storehouse belowdecks.
2, need be from preparing fresh water.Steam catapult also need be reserved the position and give huge tanks, to deposit fresh water except reserve the equipment of itself position in the cabin.Launch 1 medium-sized fighter plane, approximately will consume 1 fresh water.
3, energy consumption height for fresh water is burnt till steam, must expend a large amount of energy, therefore will reserve exceptional space again for storing fuel.
4, ejector building technology difficulty is big, seal request height, component processing precision height, cost height.
5, wartime is easily impaired and be difficult to repair.
6, safeguard that operating needs is very high, whenever launching needs marine grounding maintenance for 3000-3200 time or returns the port maintenance.
United States Navy carries out the technical study of electromagnetic launch system since nineteen eighty-two for this reason.Up to autumn in 2004 the electromagnetic launch device enter the finished product test stage.The electromagnetic launch device is the inheritance system of a complexity, and its core is the straight line ejection motor.Ejection motor has roller, is being with a reciprocal car to slide along catapult track.During work, electrical motor obtains power supply, and back and forth car hauls carrier-borne aircraft and accelerates to takeoff speed along launching stroke under the effect of electromagnetic force." Bush " number aircraft carrier of the approaching completion of the U.S. at present, cost reaches 8,000,000,000 dollars, is same in the past more than a times of aircraft carrier cost, will adopt later-model electromagnetic launch device, uses steam catapult for many years to step down from the stage of history when the time comes on U.S.'s aircraft carrier.
The efficient of electromagnetic launch device is about 60%, and the efficient of steam catapult 4%-6% only, its efficient improves greatly.Though the consumption of electric energy is lower than 120,000,000 Jiao but electromagnetic launch takes off, and is still a sizable energy consumption.The electromagnetic launch system has not had those as fine as a spider's web high temperature and high pressure steam pipelines of steam ejection system, but needs more than 100 meter long linear induction motor, and the large power, electrically force control apparatus forces closed-center system, and structure is still rather complicated.The maintainer of electromagnetic launch system has reduced 30% than steam ejection system, but only operating personal still needs 90 people.In a word, though the electromagnetic launch device has had very big improvement than steam catapult, it remains a kind of complex structure, and research and development are built expensive, and energy consumption is big, at ordinary times attended operation require high, wartime the easily impaired and system that is difficult to repair.
The utility model content
The purpose of this utility model is to overcome above-mentioned defective of the prior art, designs a kind of simple and direct aircraft carrier work-saving device that takes off, and makes carrier-borne aircraft in take-off process:
1, a kind of consumes energy that need not of stack is by the acceleration/accel of single pendulum generation;
2, alleviate of the influence of carrier-borne aircraft take-off weight to takeoff speed;
3, avoid carrier-borne aircraft sliding friction drag that runs on runway;
4, can conveniently add the outer booster engine of machine and use mechanical thrust, thereby improve takeoff speed.
This device has significantly reduced the carrier-borne aircraft take-off system to be built and use cost, carrier-borne aircraft is taken off fast, and be applicable to various aircraft carriers.
For realizing above-mentioned utility model purpose, the technical solution of the utility model is to adopt a kind of aircraft carrier launching apparatus, and this device comprises the single pendulum impelling mechanism that is arranged on the aircraft carrier side, and described single pendulum impelling mechanism is used for the carrier-borne aircraft impelling is gone out;
The single pendulum suspended structure that described single pendulum impelling mechanism is made up of swing arm, cantilever, flinger, the upper end of described swing arm is suspended on the outer end of cantilever, activity articulates between described swing arm lower end and the flinger, the inner of described cantilever is installed on the bracing frame or building on the described aircraft carrier side, described swing arm is around the swing of the outer end of described cantilever, or states swing arm and described cantilever and be fixed as one and swing around cantilever is inner;
Cantilever is connected by rotating shaft and swing arm are vertical in the described single pendulum suspended structure;
Described cantilever is parallel with the water surface, vertical with warship side string, and an end of described cantilever stretches out outside the string of warship side, and described swing arm swinging plane is vertical with described cantilever, and intersects with the cantilever outer end;
Vertical side along aircraft carrier, side in described single pendulum impelling mechanism is provided with the stand that the carrier-borne aircraft standby for takeoff is used, described stand also stretches out the side of described aircraft carrier, described stand longitudinal middle part is a certain to coincide perpendicular to the plane of the water surface and the swinging plane of described swing arm, do not having under the carrier-borne aircraft takeoff condition, described swing arm is stuck in described stand one side, and the stagnation position of described swing arm is corresponding with the end position of described stand.
Wherein,
Right side and/or left side that described aircraft carrier side is the aircraft carrier deck.
Its length of stretching out limit, warship side part of described cantilever is greater than 1/2 of carrier-borne aircraft width.
Described swing arm is the rigidity fork, or is flexible rope; The length of described swing arm adds that the height of carrier-borne aircraft is less than the distance of described cantilever to the water surface.
Described rotating shaft matches with axle sleeve by bearing, and described bearing is ball bearing of main shaft or magnetic suspension bearing;
Described cantilever is rotating shaft with the inner, the driving and/or the stop mechanism of the described swing arm swing of boosting are housed in described rotating shaft, described swing arm fixedly is articulated in the cantilever outer end of stretching out limit, warship side, described rotating shaft can or be braked around support sleeve swing, and described supporting sleeve is fixed on the bracing frame or building on the described aircraft carrier side;
Or described cantilever is rotating shaft with the outer end, and the driving and/or the stop mechanism of the described swing arm swing of boosting is housed in described rotating shaft, and described swing arm can be around described shaft swing, and the inner of described cantilever is fixed on the bracing frame or building on the described aircraft carrier side.
Described swing arm can be equipped with booster engine at the end that flinger is housed.
In described flinger, be provided with and articulate and break away from the mechanism that articulates carrier-borne aircraft, in described flinger or control system, also be provided with the control flinger and articulate or break away from the control mechanism that articulates carrier-borne aircraft.
The end of described stand exceeds the aircraft carrier deck, described stand is the lifting mode stand, or for making the stand of carrier-borne aircraft along the ramp ascending manner, near described stand, be provided with the stop mechanism that stops the swing arm swing, the swing arm and the angle of swing arm between the upright position that are stuck in described stand upper end are θ, and this angle is called as the carrier-borne aircraft ready position drift angle of taking off.
The side string of described aircraft carrier be positioned at swing arm below be provided with the wallboard of shielding wave, described wallboard is scalable or folding plate.
Theoretical foundation of the present utility model
In mechanism is taken off in the single pendulum impelling, when " flinger " together with carrier-borne aircraft from " ready position takes off " beginning when the central balancing position of pendulum is made simple harmonic motion pendulum and is gone, be subjected to a power along swaying direction.Be made as G
1, G
1=mgsin θ, θ are the drift angle of swing arm in reference position.The generation of this power and can be with certain form and other catabiotic thrust superpositions, architecture basics is a mono-pendulum type impelling mechanism.
According to Huygens's theorem:
The period T that single pendulum is done shm is directly proportional with the square root of pendulum length l, is inversely proportional to the square root of gravity acceleration g, and is irrelevant with the quality of amplitude, swing ball.G is regarded as constant on the sea level, and unique here variable is pendulum length l, and in the mono-pendulum type impelling was taken off, carrier-borne aircraft take-off weight size can't directly influence the cycle of simple harmonic motion itself.
Carrier-borne aircraft is flapped toward the central balancing position from " standby for takeoff position " motion is as desirable simple harmonic motion analysis, and establishing " ready position takes off " is h for the relative height of central balancing position, and the momentary velocity that the terminal of pendulum was put the central balancing position is V, then
As seen carrier-borne aircraft obtains the speed of the speed that can produce with other thrust that consumes energy with certain form superposition in single pendulum impelling take-off process, and its architecture basics is a single pendulum impelling mechanism.
No matter sliding jumps up flies still catapult-assisted take-off, all exists carrier-borne aircraft or carrier-borne aircraft to haul body (slide block or reciprocal car) together with it in the starting heats, and certain friction force F between deck runway or the slide rail.The size of F is directly proportional with the positive pressure N of carrier-borne aircraft take-off weight (or adding its haul body) to deck runway (or slide rail): F=fN, f are friction coefficient.This friction force for single pendulum impelling take off, do not exist.
Advantage of the present utility model and beneficial effect are: the mode that this aircraft carrier launching apparatus adopts the mono-pendulum type impelling to take off, the various negative effects of carrier-borne aircraft take-off weight are reduced to some extent or do not exist, carrier-borne aircraft can obtain the thrust and the speed of superposition in the same way, can also add booster engine at the flinger end of swing arm and/or install additional and help pendulum device, thereby the takeoff thrust that obtains to strengthen does not but increase the carrier-borne aircraft deadweight in rotating shaft.
So the mono-pendulum type impelling is taken off more simple in structure than the catapult-assisted take-off, cost reduces, and saves the energy.And fly to compare with sliding jumping up, sliding jump up fly in because of take-off weight restriction institute to problems such as the fighter plane fixed-wing early warning plane that only 50% carry takes off and thrust-weight ratio is not high, antisubmarine plane can't take off, the mono-pendulum type impelling is taken off and can be solved.
Single pendulum impelling mechanism can build the warship side in the utility model, warship around in addition the warship body on suitable position.The continental rise rare on smooth ground also can be used.
Description of drawings
Fig. 1 is the schematic top plan view of the utility model aircraft carrier launching apparatus;
Fig. 2 is the schematic side view of the utility model aircraft carrier launching apparatus;
Fig. 3 is the single pendulum impelling structural scheme of mechanism of the utility model aircraft carrier launching apparatus;
Fig. 4 is that the part of stand 9 ends among Fig. 2 sends out figure big.
Among the figure: 1, aircraft carrier; 2, carrier-borne aircraft; 3, single pendulum impelling mechanism; 4, swing arm; 5, cantilever; 6, flinger; 7, rotating shaft; 8, bracing frame or building; 9, stand; 10, the water surface; 11, driver train; 12, wallboard; 13, central balancing position; 14, buffer-braking district; 15, only put the position; 16, the position of dishing out; 17, stop mechanism.
The specific embodiment
Below in conjunction with drawings and Examples, the specific embodiment of the present utility model is further described.Following examples only are used for the technical solution of the utility model more clearly is described, and can not limit protection domain of the present utility model with this.
Shown in accompanying drawing 1 to 3, the concrete technical scheme of implementing of the utility model is:
A kind of aircraft carrier launching apparatus, this device comprise the single pendulum impelling mechanism 3 that is arranged on aircraft carrier 1 side, and described single pendulum impelling mechanism 3 is used for carrier-borne aircraft 2 impellings are gone out;
The single pendulum suspended structure that described single pendulum impelling mechanism 3 is made up of swing arm 4, cantilever 5, flinger 6, the upper end of described swing arm 4 is suspended on the outer end of cantilever 5, activity articulates between described swing arm 4 lower ends and the flinger 6, the inner of described cantilever 5 is installed on the bracing frame or building 8 on described aircraft carrier 1 side, described swing arm 4 is around the swing of the outer end of described cantilever 5, or states swing arm 4 and be fixed as one around cantilever 5 inner swings with described cantilever 5;
Described cantilever 5 is parallel, vertical with warship side string with the water surface 10, and stretch out outside the string of warship side the outer end of described cantilever 5, and described swing arm 4 swinging planes are vertical with described cantilever 5, and intersects with cantilever 5 outer ends;
Vertical side along aircraft carrier 1, side in described single pendulum impelling mechanism is provided with the stand 9 that carrier-borne aircraft 2 standby for takeoffs are used, described stand 9 also stretches out the side of described aircraft carrier 1, described stand 9 longitudinal middle parts are a certain to coincide perpendicular to the plane of the water surface and the swinging plane of described swing arm 4, do not having under the carrier-borne aircraft takeoff condition, described swing arm 4 is stuck in described stand 9 one sides, and the stagnation position of described swing arm 4 is corresponding with the end position of described stand 9.
On the basis of embodiment 1, described aircraft carrier 1 side generally is meant the right side on aircraft carrier deck, single pendulum impelling of the present utility model mechanism 3 also can be arranged on the limit, left side of aircraft carrier 1, or is separately positioned on two sides of aircraft carrier 1, and a cover single pendulum impelling mechanism 3 wherein can be used as standby.
On the basis of embodiment 2, described cantilever 5 its length of stretching out limit, warship side part should be greater than 1/2 of carrier-borne fuselage width, because the carrier-borne aircraft that is draped 2 is in swing process, its fuselage is positioned at the space outside the aircraft carrier warship body, so as long as a side of fuselage does not bump all passable with the warship string.
On the basis of embodiment 3, described swing arm 4 can be designed to the rigidity fork, also can be designed to flexible rope; The length of described swing arm 4 adds that the height of carrier-borne aircraft 2 should be swinging in the water to avoid carrier-borne aircraft 2 less than the distance of described cantilever 5 to the water surface 10.
On the basis of embodiment 4, described rotating shaft 7 matches with axle sleeve by bearing, and described bearing is ball bearing of main shaft or magnetic suspension bearing;
Described cantilever 5 is rotating shaft 7 with the inner, the driver train 11 and/or the stop mechanism 17 of described swing arm 4 swings of boosting are housed in described rotating shaft 7, described swing arm 4 fixedly is articulated in cantilever 5 outer ends of stretching out limit, warship side, described rotating shaft 7 can or be braked around support sleeve swing, and described supporting sleeve is fixed on the bracing frame or building 8 on the described aircraft carrier side;
Or described cantilever 5 is rotating shaft 7 with the outer end, the driver train 11 and/or the stop mechanism 17 of the described swing arm swing of boosting are housed in described rotating shaft 7, described swing arm 4 can be around described rotating shaft 7 swings, and the inner of described cantilever 5 is fixed on the bracing frame or building 8 on the described aircraft carrier side.
On the basis of embodiment 4 or 5, described swing arm 4 can be equipped with booster engine in the lower end that flinger 6 is housed.That is to say on described flinger 6 and install the boosting transmitting set again additional that this booster engine is the effect of the swing naturally of swing arm 4 being played boosting equally.
On the basis of embodiment 6, in described flinger 6, be provided with and articulate and break away from the mechanism that articulates carrier-borne aircraft, also be provided with control flinger 6 and articulate or break away from the control mechanism that articulates carrier-borne aircraft 2 in described flinger 6 or control system, said mechanism can be used for making between carrier-borne aircraft 2 and the flinger 6 realization to articulate easily and breaks away from the process that articulates.
On the basis of embodiment 7, the end of described stand 9 exceeds the aircraft carrier deck, described stand 9 can be a lifting mode stand 9, or for making the stand 9 of carrier-borne aircraft 2 along the ramp ascending manner, near described stand 9, be provided with the stop mechanism 17 that stops the swing arm swing, the swing arm 4 and the angle of swing arm 4 between the upright position that are stuck in described stand 9 upper ends are θ, and this angle also can be called as the carrier-borne aircraft ready position drift angle of taking off.
On the basis of embodiment 8, the side string of described aircraft carrier 1 be positioned at swing arm 4 below be provided with the wallboard 12 of shielding wave, described wallboard is scalable or folding plate, this wallboard also can be replaced by pontoon, this pontoon is by having the side string that rests in aircraft carrier when taking off, in the aircraft carrier of this pontoon can being packed into when not taking off.
So that single pendulum impelling mechanism 3 to be installed on U.S.'s Nimitz aircraft carrier is example, 11 meters of U.S.'s Nimitz aircraft carrier lower aprons, 30 meters to the deck of the waters surface, the water surface about 75 pacts in superstructure top to the warship.Now suppose 4 three kinds of length of swing arm of single pendulum impelling mechanism: 57 meters, 60 meters and 65 meters; Take off 75 ° of ready position drift angles, drift angle-15, impelling position ° (on lift up promptly 15 ° at angle); The ready position that takes off then is respectively 40.3 meters, 42.4 and 45.9 meters to the height of impelling position.
Because simple harmonic motion becomes kinetic energy, the speed that produces when arriving the impelling position is respectively 101 kilometers/hour, 103 kilometers/hour and 108 kilometers/hour when potential energy.
And the speed that produces by engine thrust, carrier-borne aircraft is an example with Soviet Union's-33 fighter planes and E-2C " hawkeye " early warning plane, establishes the booster engine that is installed on " flinger " and is respectively 3 and 4 F120, does a budgetary estimate.Soviet Union-33 is by 33 tons of higher continental rise take-off weights, airborne driving engine AL-31F thrust 125.4KN; E-2C weighs 23.5 tons, two thrust 102KN of airborne T56-A-417 driving engine; F120 engine thrust 155.7KN, heavily about 1.5 tons; " flinger " is reset to 2 tons.
To the impelling position, arc length is respectively 89.5 meters from the ready position that takes off, 94.2 meters and 102 meters.
Momentary velocity during arrival impelling position that Soviet Union-33 produces under AL-31F and 3 F120 thrust is respectively 191 kilometers/hour, 196 kilometers/hour and 204 kilometers/hour; At AL-31F with 4 F120 thrust is next is respectively 210 kilometers/hour, 216 kilometers/hour and 225 kilometers/hour.Momentary velocity during arrival impelling position that E-2C produces under 2 T56-A-417 and 3 F120 thrust is respectively 217 kilometers/hour, 222 kilometers/hour and 231 kilometers/hour; At 2 T56-A-417 with 4 F120 thrust is next is respectively 238 kilometers/hour; 244.9 kilometer/hour and 254.8 kilometers/hour.
These speed not only can certain form and above-mentioned simple harmonic motion produce the speed superposition, also can with aircraft carrier warship speed 20-30 joint (36 kilometers/hour-54 kilometers/hour) superposition, finish and take off.
The utility model is simple in structure, builds, use cost is very low, very saves the energy, is applicable to that various aircraft carriers take off, and do not take the deck runway substantially, and operation, maintenance technology is simple and clear, safe and reliable, expense is low.
The above only is a preferred implementation of the present utility model; should be understood that; for those skilled in the art; under the prerequisite that does not break away from the utility model know-why; can also make some improvements and modifications, these improvements and modifications also should be considered as protection domain of the present utility model.
Claims (9)
1, a kind of aircraft carrier launching apparatus is characterized in that, this device comprises the single pendulum impelling mechanism that is arranged on the aircraft carrier side, and described single pendulum impelling mechanism is used for the carrier-borne aircraft impelling is gone out;
The single pendulum suspended structure that described single pendulum impelling mechanism is made up of swing arm, cantilever, flinger, the upper end of described swing arm is suspended on the outer end of cantilever, activity articulates between described swing arm lower end and the flinger, the inner of described cantilever is installed on the bracing frame or building on the described aircraft carrier side, described swing arm is around the swing of the outer end of described cantilever, or described swing arm and described cantilever are fixed as one and swing around cantilever is inner;
Cantilever is connected by rotating shaft and swing arm are vertical in the described single pendulum suspended structure;
Described cantilever is parallel with the water surface, vertical with warship side string, and an end of described cantilever stretches out outside the string of warship side, and described swing arm swinging plane is vertical with described cantilever, and intersects with the cantilever outer end;
Vertical side along aircraft carrier, side in described single pendulum impelling mechanism is provided with the stand that the carrier-borne aircraft standby for takeoff is used, described stand also stretches out the side of described aircraft carrier, described stand longitudinal middle part is a certain to coincide perpendicular to the plane of the water surface and the swinging plane of described swing arm, do not having under the carrier-borne aircraft takeoff condition, described swing arm is stuck in described stand one side, and the stagnation position of described swing arm is corresponding with the end position of described stand.
2, aircraft carrier launching apparatus according to claim 1 is characterized in that right side and/or left side that described aircraft carrier side is the aircraft carrier deck.
3, as aircraft carrier launching apparatus as described in the claim 2, it is characterized in that its length of stretching out limit, warship side part of described cantilever is greater than 1/2 of carrier-borne aircraft width.
4, as aircraft carrier launching apparatus as described in the claim 3, it is characterized in that described swing arm is the rigidity fork, or be flexible rope; The length of described swing arm adds that the height of carrier-borne aircraft is less than the distance of described cantilever to the water surface.
5, as aircraft carrier launching apparatus as described in the claim 3, it is characterized in that described rotating shaft matches with axle sleeve by bearing, described bearing is ball bearing of main shaft or magnetic suspension bearing;
Described cantilever is rotating shaft with the inner, the driving and/or the stop mechanism of the described swing arm swing of boosting are housed in described rotating shaft, described swing arm fixedly is articulated in the cantilever outer end of stretching out limit, warship side, described rotating shaft can or be braked around support sleeve swing, and described supporting sleeve is fixed on the bracing frame or building on the described aircraft carrier side;
Or described cantilever is rotating shaft with the outer end, and the driving and/or the stop mechanism of the described swing arm swing of boosting is housed in described rotating shaft, and described swing arm can be around described shaft swing, and the inner of described cantilever is fixed on the bracing frame or building on the described aircraft carrier side.
6, as aircraft carrier launching apparatus as described in claim 4 or 5, it is characterized in that described swing arm can be equipped with booster engine at the end that flinger is housed.
7, as aircraft carrier launching apparatus as described in the claim 6, it is characterized in that, in described flinger, be provided with and articulate and break away from the mechanism that articulates carrier-borne aircraft, in described flinger or control system, also be provided with the control flinger and articulate or break away from the control mechanism that articulates carrier-borne aircraft.
8, aircraft carrier launching apparatus according to claim 1, it is characterized in that, the end of described stand exceeds the aircraft carrier deck, described stand is the lifting mode stand, or for making the stand of carrier-borne aircraft along the ramp ascending manner, be provided with the stop mechanism that stops swing arm swing near described stand, the swing arm and the angle of swing arm between the upright position that are stuck in described stand upper end are θ, and this angle is called as the carrier-borne aircraft ready position drift angle of taking off.
9, aircraft carrier launching apparatus according to claim 1 is characterized in that, the side string of described aircraft carrier be positioned at swing arm below be provided with the wallboard of shielding wave, described wallboard is scalable or folding plate.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200920009443U CN201385784Y (en) | 2009-03-31 | 2009-03-31 | Aircraft carrier launching device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200920009443U CN201385784Y (en) | 2009-03-31 | 2009-03-31 | Aircraft carrier launching device |
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| Publication Number | Publication Date |
|---|---|
| CN201385784Y true CN201385784Y (en) | 2010-01-20 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN200920009443U Expired - Fee Related CN201385784Y (en) | 2009-03-31 | 2009-03-31 | Aircraft carrier launching device |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113415434A (en) * | 2021-07-20 | 2021-09-21 | 胡国明 | Deck layout structure of aircraft carrier |
-
2009
- 2009-03-31 CN CN200920009443U patent/CN201385784Y/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113415434A (en) * | 2021-07-20 | 2021-09-21 | 胡国明 | Deck layout structure of aircraft carrier |
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Granted publication date: 20100120 Termination date: 20120331 |