CN102673797A - Device employed to assist shipboard aircraft in takeoff - Google Patents
Device employed to assist shipboard aircraft in takeoff Download PDFInfo
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- CN102673797A CN102673797A CN2011104353047A CN201110435304A CN102673797A CN 102673797 A CN102673797 A CN 102673797A CN 2011104353047 A CN2011104353047 A CN 2011104353047A CN 201110435304 A CN201110435304 A CN 201110435304A CN 102673797 A CN102673797 A CN 102673797A
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Abstract
The invention relates to a device employed to assist shipboard aircraft in takeoff. The device comprises a steam generator provided with a steam outlet and a steam return port, and a transmission chamber communicated with the steam outlet and the steam return port of the steam generator respectively; the wall of the transmission chamber is rotationally provided with a transmission shaft in form of hermetic seal; one end of the transmission shaft is configured to be a power input end extending into the transmission chamber, the other end of the transmission shaft is configured to be a power output end extending out of the transmission chamber; a steam impeller is coaxially fixed on the transmission shaft in the transmission chamber; a driver gear is coaxially fixed on the power output end of the transmission shaft; the device employed to assist shipboard aircraft in takeoff further comprises a takeoff-assisting track tipsily arranged in the transmission direction and engaged with the driver gear; both ends of the takeoff-assisting track are provided with a main tensioning wheel respectively; the middle part of the takeoff-assisting track is provided with a loading wheel; and the periphery of the takeoff-assisting track is provided with a limiting structure used for limiting the airplane wheels of corresponding shipboard aircraft. By using the track with high bearing property in the invention, the invention provides the device employed to assist shipboard aircraft in takeoff, which is suitable for large and middle shipboard aircrafts.
Description
Technical field
The present invention relates to a kind of jato unit that is used for large and medium-sized carrier-borne aircraft at carrier-based.
Background technology
Jato unit is the accessory appliances that aircraft is realized ultra-short takeoff, according to quality, profile, the performance of aircraft, gives its huge energy at short notice, makes it obtain bigger initial velocity and realizes taking off purpose, thereby realize carrier-borneization of various aircrafts.Aircraft carrier generally uses steam catapult now, but its power consumption is big, can only quicken blimp, can not realize taking off of large and medium-sized aircraft, has seriously limited the development of naval's cause.Owing to receive the influence of technological fund etc., the carrier-borne jato unit of large and medium-sized aircraft worldwide still belongs to blank.
Present ejector in the world mainly contains following 3 kinds:
1, steam catapult
Steam catapult is the aircraft launching apparatus on the aircraft carrier, is used for the catapult-assisted take-off of carrier-borne aircraft steam, uses a flush deck as airstrip.A steam-powered catapult-launching gear drive aircraft reaches takeoff speed when taking off in two seconds.
Heavy airplane wants from carrier-based, and steam catapult must be arranged.Before taking off, be buckled in afterbody on the firm point by the holdback steel ring, near the draw bar the aircraft nose wheel hangs in the shuttle, and shuttle hooks aircraft with hook.Shuttle is the unique part that is exposed on the flight deck of steam catapult.Under the aircraft fwd deck, two parallel cylinders are arranged, each is to 45 meters of the youthful and the elderlys, and the piston in the tube links to each other with all shuttles.Steam is imported shuttle by the output of the boiler on the mother ship carrier after the supercharging.Put into high gear when taking off, but fastened by holdback.Steam catapult one starts, and the power of aeroengine adds steam pressure, and steel ring is broken off, the aircraft preshoot, in 45 meters distances, reach speed per hour 250 kms/hour.After airplane catapult took off and breaks away from shuttle, the notes pipe of piston nose just fell into the pond, in several meters distance, pauses, and shuttle is retracted original position, promotes another airplane and takes off.Each steam catapult per minute can promote two airplanes and takes off on the aircraft carrier.Usually aircraft carrier is installed 4 steam catapults at most.
Steam has launched two kinds of ejection modes, and a kind of is that front-wheel launches, and, is directly hauled aircraft nose wheel by slide block when launching and takes off in success of the test in 1964 by United States Navy.Come to hang tow rope and subtracted tow rope for aircraft without 8-10 people like this, the time of launching shortens, and aircraft safety is good.U.S.'s active service aircraft carrier all adopts this mode.Have only the U.S. to possess the mature technology of producing this steam catapult at present.
But steam catapult has its intrinsic weak point:
(1) maintenance cost is big, and U type sealing band is changed frequent and very bothered, and material is required high;
(2) use the steam catapult cost big, efficient is low, and auxiliary facility is many, and system is loaded down with trivial details, and each link requires high;
(3) need to consume a large amount of fresh water, the U.S. once considered vapour-condensing equipment for recovering for this reason, and efficient is low to be cancelled because of volume reaches greatly eventually.
2, combustion vapour ejector
Combustion vapour ejector is structurally similar with steam catapult, and only the two ends admission port of steam has become combustion chamber, and wherein deoxidation compound and oxidizer inject through high pressure, but are controlled, and is to continue to inject.When work; Deoxidation compound and oxidizer inject to high combustion chamber pressures; Ignition device makes deoxidation compound and oxidizer at the combustion chamber internal reaction and produce a large amount of heat, and gas promotes the piston acting, because deoxidation compound and oxidizer continue to inject; Piston will be under the continuous thrust of gas high-speed cruising, take off thereby make.Deoxidation compound and oxidizer stop to inject after taking off, and open the combustion chamber air port, and the combustion chamber air port of return terminal is closed simultaneously, and piston can stop immediately.Return identical with said process, little than work of combustion chamber and high pressure injection device only.This ejector injects deoxidation compound by control and oxidizer controls, and advantage is not need fresh water, and work and time of return are short.But shortcoming is many especially, at first is that the condition such as high temperature resistant and anti-oxidation of combustion chamber is high, and barrel intensity and high temperature resistant requirement are high.The control requirement of injection deoxidation compound and oxidizer is accurate, the data reaction is fast, and certain danger is arranged, and consumes expensive liquid reducer and oxidizer, and the fault rate height is got rid of many unfavorable factors such as a large amount of gases pollutions and infrared radiation.Therefore this ejector is in fact just discussed in theory and was analyzed, and the record of large-scale practice is not arranged.
3, the multiple power ejector of spring
The multiple power ejector of spring is to utilize linear electric motors or stored energy mechanism to arrive the energy storage position to springs; Utilize stop mechanism to keep energy not discharge; Then utilize control system to break off stop mechanism during work; The moving aircraft of spring pulling under multiple power quickens, aircraft self driving engine and ejector make a concerted effort quicken down, the initialization stroke generally has only 60 meters.But regrettably this ejector can not directly take off airplane catapult, and aircraft must slide one section and just can take off under the thrust of driving engine.And this ejector is to be placed on spring in the slideway of opening (internal orifice band lubricating oil) in practical study; Purpose be do not allow ejector when work to around exert an influence; And this large power spring is strict to material requirements, just imagines that so high-performance spring do not change at aircraft carrier during one's term of military service, to material require be how to carve severe; Even slideway, its precision also requires very high.This ejector cataplane number of times is not high, because it accomplishes energy storage by stored energy mechanism.More kill be this ejector when initial pulling force very big, the phenomenon of fainting in short-term can take place in the aviator, also requires quite high to the structural strength of aircraft.And the working distal tip pulling force is very little, and crucial moment can not accelerated take-off.
Summary of the invention
The object of the present invention is to provide a kind of carrier-borne aircraft jato unit that is applicable to large and medium-sized carrier-borne aircraft.
In order to address the above problem, technical scheme of the present invention is:
A kind of carrier-borne aircraft jato unit; Comprise have, the steam generator of return-air mouth and respectively through the going out of outlet passageway and return gas channel and said steam generator, Transmission Room that the return-air mouth is communicated with; Describedly go out, be respectively equipped with in the return gas channel flow switch of steam flow in the control respective channel; Vapor seal is rotatably equipped with transmission shaft on the locular wall of said Transmission Room, and an end of said transmission shaft is the power intake that extends in the said Transmission Room; The other end is to extend to the outer clutch end of said Transmission Room, the coaxial steam impeller that is fixed with on the transmission shaft in the said Transmission Room; The coaxial driving gear that is fixed with on the clutch end of said transmission shaft; Described jato unit also comprises and said driving gear engaged transmission and the help-fly crawler belt that is inclined upwardly and is provided with along transmission direction; The two ends of said help-fly crawler belt are respectively equipped with said help-fly crawler belt interlock transmission and are used for the main brace bearing up pulley of the said help-fly crawler belt of stretching; The middle part of said help-fly crawler belt is provided with said help-fly crawler belt interlock transmission and is used to support the bearing wheed of said help-fly crawler belt, and the periphery of said help-fly crawler belt is provided with and is used for when taking off, cooperating so that carrier-borne aircraft moves spacing position limiting structure backward on the throughput direction of help-fly crawler belt with the wheel of corresponding carrier-borne aircraft is spacing.
Described help-fly crawler belt comprises that upper strata crawler belt, lower floor's crawler belt and folder establish the middle level crawler belt that is fixed between the said upper and lower layer crawler belt; Described lower floor crawler belt and described main brace bearing up pulley and bearing wheed are through ratchet interlock transmission; Described lower floor crawler belt and described driving gear engaged transmission; Described position limiting structure comprises the protruding position limiting structure that is arranged at said upper strata crawler belt periphery; Have through hole on the crawler belt of described middle level, be installed with the last interlock driving cog that extends in the said through hole on the crawler belt of described upper strata, be installed with on the described lower floor crawler belt and extend in the said through hole and go up the following interlock driving cog that the interlock of interlock driving cog is in transmission connection with said.
Described each main brace bearing up pulley all rotates and is assemblied on the cooresponding main brace bearing up pulley axle; Be fixed with connecting rod on said each main brace bearing up pulley axle; Each connecting rod all is rotatably equipped with auxilliary stretching wheel away from an end of said corresponding main brace bearing up pulley; All be connected with on described each connecting rod to respective link and apply pulling force so that corresponding auxilliary stretching wheel and of the extension spring of said help-fly crawler belt through ratchet interlock transmission and the said help-fly crawler belt of stretching; Each extension spring all is connected with stay cord away from an end of respective link, the other end of each stay cord through corresponding angle pulley group switching-over back on the output shaft of corresponding stay cord motor extremely.
Described jato unit also comprise with the spacing cooperation of the output shaft of said each stay cord motor to control the brake of said corresponding tension spring tension.
Described each bearing wheed rotates and is assemblied on the cooresponding heavy burden wheel shaft, and said two ends of respectively bearing a heavy burden wheel shaft are equipped with the bearing wheed assembling end on the warship body that is used to be assemblied in corresponding naval vessels.
Describedly go out, return gas channel is rectangular channel; Described flow switch is the gradual change type switch; Described gradual change type switch comprises that at least two rotation directions are all with the length of said rectangular channel or Width is consistent and the rotating shaft that is in transmission connection with corresponding change speed motor; Be equipped with the interlock that each other coincide on the adjacent shafts controlling the convex and concave teeth of corresponding steam flow when the corresponding rotating shaft different rotating speeds, describedly go out, the conduit wall of return gas channel is provided with corresponding rotating shaft on the coincide passage parietal tooth of snap fit of convex and concave teeth.
Be equipped with the FL/MTR that is used to detect steam flow in the respective channel behind described each flow switch.
Be equipped with steam outlet on the respective channel before described each flow switch.
Be provided with between the going out of said steam generator, the return-air mouth and be used for the steam circuit that corresponding steam cooled via return air mouth flow to air extractor duct, the circulation trend along steam in the described steam circuit is provided with surge chamber and at least one pressurized compartment successively.
Beneficial effect of the present invention is: in the specific implementation; Earlier corresponding carrier-borne aircraft is sailed on the help-fly crawler belt; Open the flow switch in the corresponding outlet passageway then, the steam impeller drives transmission shaft and rotates under the driving of steam, and transmission shaft drives the help-fly caterpillar drive through driving gear; The wheel of carrier-borne aircraft is synchronized with the movement with the help-fly crawler belt under the position-limiting action of position limiting structure; Control the kinematic velocity that steam flow in the corresponding outlet passageway increases the help-fly crawler belt through flow switch, in accelerator, the speed of carrier-borne aircraft is accelerated to a little more than before the takeoff speed gradually; The forward and backward wheel of carrier-borne aircraft remains with the help-fly crawler belt and contacts; When the speed gentle acceleration of carrier-borne aircraft reached takeoff speed, the steam flow of controlling in the corresponding outlet passageway through flow switch reduced the help-fly track speed, and carrier-borne aircraft relies on velocity inertial to break away from the help-fly crawler belt greater than help-fly crawler belt speed and takes off.Crawler belt has bigger load-carrying capacity, so this carrier-borne aircraft jato unit can be applicable to large and medium-sized carrier-borne aircraft.
Description of drawings
Fig. 1 is the structural representation of the embodiment of the invention 1;
Fig. 2 is the structural representation of gradual change type switch among Fig. 1;
Fig. 3 is the local structure scheme drawing of help-fly crawler belt among Fig. 1;
Fig. 4 is that the A of Fig. 3 is to cutaway view;
Fig. 5 is the scheme drawing that cooperates of driving gear and lower floor crawler belt among Fig. 1;
Fig. 6 is the structural representation of steam generator in the embodiment of the invention 2.
The specific embodiment
A kind of embodiment 1 of carrier-borne aircraft jato unit is shown in Fig. 1 ~ 5: comprise that two nucleon steam generators 22 that have air extractor duct 20-1, return-air mouth 20-2 respectively and two are respectively through cooresponding outlet passageway 5 and return gas channel 6 and the Transmission Room 25 that correspondingly goes out, the return-air mouth is communicated with.Respectively go out, return gas channel is rectangular channel, each rectangular channel is that the rectangular cavity of offering in the middle of the columniform connection pipe constitutes by periphery.Respectively go out, be equipped with gradual change type switch 4 in the return gas channel; Gradual change type switch 4 comprises three rotating shaft 4-1 that rotation direction is consistent with the length direction of rectangular channel; Be equipped with the convex and concave teeth of interlock that each other coincide on the adjacent shafts 4-1 with the steam flow in the control respective channel when the corresponding rotating shaft 4-1 different rotating speeds; Respectively go out, the conduit wall of return gas channel is provided with corresponding rotating shaft on the coincide passage parietal tooth of snap fit of convex and concave teeth; Identical interlock through each between cog realizes higher trapping effect, and the power intake of each rotating shaft 4-1 all is with the motor 4-3 of change speed gear box 4-2 to be in transmission connection with one.Motor 4-3, change speed gear box 4-2 all link to each other with central processing system 18 through the feedback regulation sensor.On the flow direction of corresponding steam; Be equipped with the FL/MTR (not shown) that is used to detect steam flow in the respective channel at each gradual change type switch 4 rear portion; Be equipped with the steam outlet (not shown) in the anterior respective channel of each gradual change type switch 4, the steam short time in respective channel assembles too much, or other reason causes intraductal pressure to cross conference when equipment is threatened; Open steam outlet, discharge the safety of an amount of steam with preventive device.All sealing gland is rotatably equipped with cooresponding transmission shaft 26 on the locular wall of each Transmission Room 25, and an end of transmission shaft 26 is for extending to corresponding Transmission Room 25 in-to-in power intakes; The other end is for extending to corresponding Transmission Room 25 exterior clutch ends; The coaxial steam impeller 11 that is fixed with on the transmission shaft 26 in the Transmission Room 25; When steam flows to Transmission Room by the channel outlet of cooresponding outlet passageway, can drive steam impeller 11 and drive cooresponding transmission shaft 26 and rotate.Coaxial being fixed with and driving gear 17 on the clutch end of transmission shaft 26; Jato unit also comprises and driving gear 17 engaged transmission and the help-fly crawler belt 13 that is inclined upwardly and is provided with along transmission direction; The help-fly crawler belt comprises that upper strata crawler belt 13-1, the crawler belt 13-3 of lower floor and folder establish the middle level crawler belt 13-2 that is fixed between the said upper and lower layer crawler belt, and crawler belt 13-3 of lower floor and driving gear 17 engaged transmission have through hole on the crawler belt 13-2 of middle level; The both sides of through hole are provided with tightening screw; Be installed with the last interlock driving cog 13-1-1 that extends in the through hole on the crawler belt 13-1 of upper strata, be installed with the following interlock driving cog 13-3-1 that extends in the through hole and be in transmission connection with last interlock driving cog 13-1-1 interlock on the crawler belt 13-3 of lower floor, upper and lower interlock driving cog is ratchet; Upper and lower layer crawler belt makes whole help-fly crawler belt 13 form an integral body through interlock; Middle level crawler belt 13-2 plays safety effect, when carrier-borne aircraft in accelerator, if the former thereby careless fracture of upper and lower layer crawler belt because of other; Middle level crawler belt 13-2 can guarantee that upper and lower layer crawler belt can not disintegrate immediately and continue to keep original state, to guarantee the accelerator of carrier-borne aircraft.Cooperate so that carrier-borne aircraft moves the protruding position limiting structure of spacing regular shape backward on the throughput direction of help-fly crawler belt 13 with the wheel of corresponding carrier-borne aircraft is spacing when the periphery of crawler belt 13-1 is provided with and is used for taking off on the upper strata.The two ends of help-fly crawler belt 13 be respectively equipped with the crawler belt 13-3 of lower floor through ratchet interlock transmission and be used for the main brace bearing up pulley 1 of stretching help-fly crawler belt 13; Each main brace bearing up pulley 1 all rotates and is assemblied on the cooresponding main brace bearing up pulley axle; Be fixed with connecting rod 2 on each main brace bearing up pulley axle; Each connecting rod 2 all is rotatably equipped with auxilliary stretching wheel 3 away from an end of corresponding main brace bearing up pulley 1; All be connected with on each connecting rod 2 to respective link 2 and apply pulling force so that corresponding auxilliary stretching wheel 3 and the extension spring 16 of help-fly crawler belt 13 through ratchet interlock transmission and stretching help-fly crawler belt 13; Each extension spring 16 all is connected with stay cord 10 away from an end of respective link 2; The other end of each stay cord 10 through corresponding angle pulley group 17 switching-over backs on the output shaft of corresponding stay cord motor 9 extremely, jato unit also comprise with the spacing cooperation of the output shaft of said each stay cord motor 9 to control the brake (not shown) of said corresponding extension spring 16 pulling force.The middle part of help-fly crawler belt be provided with one with the crawler belt 13-3 of lower floor through ratchet interlock transmission and be used to support the bearing wheed 8 of said help-fly crawler belt 13; Bearing wheed 8 is the entity wheel; The main support help-fly crawler belt 13 that plays a part; Bearing wheed 8 rotates and is assemblied on the cooresponding heavy burden wheel shaft 8-1, and the two ends of each wheel shaft 8-1 that bears a heavy burden are equipped with the bearing wheed assembling end on the warship body that is used to be assemblied in corresponding naval vessels.
Between each nucleon steam generator 22 cooresponding return-air mouth 20-2 and air extractor duct 20-1, be provided with and be used for the steam circuit 20 that corresponding steam cooled via return air mouth 20-2 flow to air extractor duct 20-1; In steam circuit 20, be provided with the surge chamber 24 that is communicated with two nucleon producers, 22 cooresponding return-air mouth 20-2; Surge chamber 24 is accepted in the corresponding return gas channel 6 high pressure steam and their pressure is suitably reduced, to reduce the requirement of next circulating system to equipment intensity.In the steam circuit 20 below the steam flow direction, be provided with the preliminary pressurized compartment 23 that is communicated with surge chamber 24; Be equipped with second pressurized compartment 19 between preliminary pressurized compartment 23 and corresponding nucleon steam generator 22 cooresponding air extractor duct 20-1; In each pressurized compartment respectively correspondence be provided with press, the steam that preliminary 23 pairs of circulations in pressurized compartment are returned tentatively pressurizes, and tentatively improves the steam pressure of vapour cycle in returning; Steam in the 19 pairs of steam circuits in second pressurized compartment further pressurizes; Behind second pressurized compartment 19, heating zone is set, is used to improve the temperature of pressurization back steam, further improve the pressure in the pipeline.Part 21 expressions are used to stop the one way switch of opposing steam flow among the figure.
In other embodiments of the invention, nucleon steam generator 22 can also be replaced by common steam generator; Gradual change type switch 4 can also be replaced by other flow switch; Certainly the number of bearing wheed 8 can also be two, three, four or more.
When carrying out corresponding carrier-borne aircraft help-fly; Above help-fly crawler belt 13, install and help-fly crawler belt 13 unconnected guide plates 12 earlier, be used for the guiding of carrier-borne aircraft, adjust the amount of contraction of corresponding extension spring 16 through cooresponding stretching motor 9 along help-fly crawler belt throughput direction; And then adjustment makes whole help-fly crawler belt 13 reach suitable degree of tension; Open cooresponding gradual change type switch 4, begin to feed steam, measure the speed of the carrier-borne aircraft of help-fly crawler belt 13; Feed back to master control system 18, system makes ventilation efficiency reach appropriate value through analyzing each gradual change type switch 4 corresponding change speed gear box 4-2 of adjusting.When carrier-borne aircraft accelerated to takeoff speed with help- fly crawler belt 13,4 beginnings of gradual change type switch were slowly closed, and the speed of help-fly this moment crawler belt 13 is less than the speed of carrier-borne aircraft, and carrier-borne aircraft breaks away from the help-fly crawler belt and takes off.
A kind of embodiment 2 of carrier-borne aircraft jato unit is as shown in Figure 6: different with embodiment 1 is; Nucleon steam generator 30 has only one; Between the air extractor duct of nucleon steam generator, increased a steam diversion chamber 31, let steam get into respectively in the cooresponding outlet passageway.
Claims (9)
1. carrier-borne aircraft jato unit; It is characterized in that: comprise have, the steam generator of return-air mouth and respectively through the going out of outlet passageway and return gas channel and said steam generator, Transmission Room that the return-air mouth is communicated with; Describedly go out, be respectively equipped with in the return gas channel flow switch of steam flow in the control respective channel; Vapor seal is rotatably equipped with transmission shaft on the locular wall of said Transmission Room, and an end of said transmission shaft is the power intake that extends in the said Transmission Room; The other end is to extend to the outer clutch end of said Transmission Room, the coaxial steam impeller that is fixed with on the transmission shaft in the said Transmission Room; The coaxial driving gear that is fixed with on the clutch end of said transmission shaft; Described jato unit also comprises and said driving gear engaged transmission and the help-fly crawler belt that is inclined upwardly and is provided with along transmission direction; The two ends of said help-fly crawler belt are respectively equipped with said help-fly crawler belt interlock transmission and are used for the main brace bearing up pulley of the said help-fly crawler belt of stretching; The middle part of said help-fly crawler belt is provided with said help-fly crawler belt interlock transmission and is used to support the bearing wheed of said help-fly crawler belt, and the periphery of said help-fly crawler belt is provided with and is used for when taking off, cooperating so that carrier-borne aircraft moves spacing position limiting structure backward on the throughput direction of help-fly crawler belt with the wheel of corresponding carrier-borne aircraft is spacing.
2. jato unit according to claim 1; It is characterized in that: described help-fly crawler belt comprises that upper strata crawler belt, lower floor's crawler belt and folder establish the middle level crawler belt that is fixed between the said upper and lower layer crawler belt; Described lower floor crawler belt and described main brace bearing up pulley and bearing wheed are through ratchet interlock transmission; Described lower floor crawler belt and described driving gear engaged transmission; Described position limiting structure comprises the protruding position limiting structure that is arranged at said upper strata crawler belt periphery; Have through hole on the crawler belt of described middle level, be installed with the last interlock driving cog that extends in the said through hole on the crawler belt of described upper strata, be installed with on the described lower floor crawler belt and extend in the said through hole and go up the following interlock driving cog that the interlock of interlock driving cog is in transmission connection with said.
3. jato unit according to claim 1; It is characterized in that: described each main brace bearing up pulley all rotates and is assemblied on the cooresponding main brace bearing up pulley axle; Be fixed with connecting rod on said each main brace bearing up pulley axle; Each connecting rod all is rotatably equipped with auxilliary stretching wheel away from an end of said corresponding main brace bearing up pulley; All be connected with on described each connecting rod to respective link and apply pulling force so that corresponding auxilliary stretching wheel and the extension spring of said help-fly crawler belt through ratchet interlock transmission and the said help-fly crawler belt of stretching, each extension spring all is connected with stay cord away from an end of respective link, the other end of each stay cord through corresponding angle pulley group switching-over back on the output shaft of corresponding stay cord motor extremely.
4. jato unit according to claim 3 is characterized in that: described jato unit also comprise with the spacing cooperation of the output shaft of said each stay cord motor to control the brake of said corresponding tension spring tension.
5. jato unit according to claim 1 is characterized in that: described each bearing wheed rotates and is assemblied on the cooresponding heavy burden wheel shaft, and said two ends of respectively bearing a heavy burden wheel shaft are equipped with the bearing wheed assembling end on the warship body that is used to be assemblied in corresponding naval vessels.
6. jato unit according to claim 1; It is characterized in that: describedly go out, return gas channel is rectangular channel; Described flow switch is the gradual change type switch; Described gradual change type switch comprises that at least two rotation directions are all with the length of said rectangular channel or Width is consistent and the rotating shaft that is in transmission connection with corresponding change speed motor; Be equipped with the interlock that each other coincide on the adjacent shafts controlling the convex and concave teeth of corresponding steam flow when the corresponding rotating shaft different rotating speeds, describedly go out, the conduit wall of return gas channel is provided with corresponding rotating shaft on the coincide passage parietal tooth of snap fit of convex and concave teeth.
7. jato unit according to claim 1 is characterized in that: be equipped with the FL/MTR that is used to detect steam flow in the respective channel behind described each flow switch.
8. jato unit according to claim 1 is characterized in that: be equipped with steam outlet on the respective channel before described each flow switch.
9. according to any described jato unit of claim 1 ~ 8; It is characterized in that: be provided with between the going out of said steam generator, the return-air mouth and be used for the steam circuit that corresponding steam cooled via return air mouth flow to air extractor duct, the circulation trend along steam in the described steam circuit is provided with surge chamber and at least one pressurized compartment successively.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201110435304.7A CN102673797B (en) | 2011-12-22 | 2011-12-22 | Device employed to assist shipboard aircraft in takeoff |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201110435304.7A CN102673797B (en) | 2011-12-22 | 2011-12-22 | Device employed to assist shipboard aircraft in takeoff |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102673797A true CN102673797A (en) | 2012-09-19 |
| CN102673797B CN102673797B (en) | 2014-06-11 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201110435304.7A Expired - Fee Related CN102673797B (en) | 2011-12-22 | 2011-12-22 | Device employed to assist shipboard aircraft in takeoff |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102923312A (en) * | 2012-10-18 | 2013-02-13 | 桂林鑫鹰电子科技有限公司 | Small take-off launch frame for unmanned aerial vehicle |
| CN107933945A (en) * | 2017-12-12 | 2018-04-20 | 杨富云 | Aircraft carrier rises and falls method and its device |
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| US4014246A (en) * | 1975-07-02 | 1977-03-29 | All American Industries, Inc. | Rocket-powered apparatus for launching a flying device |
| US6007022A (en) * | 1996-11-08 | 1999-12-28 | Newport News Shipbuilding | Internal combustion catapult |
| CN101758930A (en) * | 2009-12-28 | 2010-06-30 | 刘国忠 | Dynamic acceleration runway for take-off of carrier aircraft |
| CN202429359U (en) * | 2011-12-22 | 2012-09-12 | 河南科技大学 | Assistant flying device of shipboard aircraft |
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2011
- 2011-12-22 CN CN201110435304.7A patent/CN102673797B/en not_active Expired - Fee Related
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3178132A (en) * | 1962-12-06 | 1965-04-13 | Dowty Rotol Ltd | Aircraft and devices for launching same |
| US3474989A (en) * | 1967-09-11 | 1969-10-28 | Bliss Co | Programmed control for aircraft launching and arresting gear |
| US4014246A (en) * | 1975-07-02 | 1977-03-29 | All American Industries, Inc. | Rocket-powered apparatus for launching a flying device |
| US6007022A (en) * | 1996-11-08 | 1999-12-28 | Newport News Shipbuilding | Internal combustion catapult |
| CN101758930A (en) * | 2009-12-28 | 2010-06-30 | 刘国忠 | Dynamic acceleration runway for take-off of carrier aircraft |
| CN202429359U (en) * | 2011-12-22 | 2012-09-12 | 河南科技大学 | Assistant flying device of shipboard aircraft |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102923312A (en) * | 2012-10-18 | 2013-02-13 | 桂林鑫鹰电子科技有限公司 | Small take-off launch frame for unmanned aerial vehicle |
| CN107933945A (en) * | 2017-12-12 | 2018-04-20 | 杨富云 | Aircraft carrier rises and falls method and its device |
Also Published As
| Publication number | Publication date |
|---|---|
| CN102673797B (en) | 2014-06-11 |
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