CN202219842U - Auxiliary taking-off system of airplane - Google Patents
Auxiliary taking-off system of airplane Download PDFInfo
- Publication number
- CN202219842U CN202219842U CN2011203351618U CN201120335161U CN202219842U CN 202219842 U CN202219842 U CN 202219842U CN 2011203351618 U CN2011203351618 U CN 2011203351618U CN 201120335161 U CN201120335161 U CN 201120335161U CN 202219842 U CN202219842 U CN 202219842U
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- Prior art keywords
- airplane
- aircraft
- coaster
- slideway
- pulley
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Abstract
The utility model discloses an auxiliary taking-off system of an airplane, which comprises a slope slide and a pulley. One end of the slide is smoothly connected with a horizontal runway, the other end of the slide is fixed with a ship island of an aircraft carrier, and the starting end of the slide located at the ship island is in a horizontal state. A fixing and unlocking device for avoiding bump between the airplane and the pulley are arranged on the pulley. When the system is used, the airplanes is arranged at the starting end of the slide located at the ship island end, the pulley and the airplane dive and accelerate, when the airplane arrives at the bottom end of the slope, a travel switch enables an electromagnetic motor to work, fixation is removed, and the airplane accelerates continuously and soars. The system uses gravitational potential energy of the airplane to assist taking-off of the airplane, avoids the defect that ski jump taking-off limits weight of the airplane and an ejector is difficult to manufacture, supplies required auxiliary augmentation to the airplane when the airplane takes off, enables the airplane to reach taking-off initial velocity, not only can be applied in auxiliary taking-off of the airplane on the aircraft carrier, but also can be applied in short-distance auxiliary taking-off of the airplane at islands.
Description
Technical field
The utility model relates to aircraft Assisted Take Off technical field, particularly a kind of aircraft carrier, the narrow and small island short range Assisted Take Off system of boarding a plane.
Background technology
Carrier-borne aircraft is owing to the limited length of warship now, and the not speed when needing usually to adopt the Assisted Take Off mode just can make aircraft leave warship is more than or equal to the flying speed of aircraft, otherwise aircraft can't normally take off.Usually adopt dual mode when for example aviation warship ship-board aircraft takes off, a kind of is to adopt the sliding formula of jumping to take off, and the weight that this mode is taken off when requiring to take off can not be too big, promptly can not be with more fuel and ammunition, so the scope of its operation receives very big restriction; Another kind is to adopt ejection type to take off, though this mode is little to the weight limits of aircraft, and the complex structure of ejector, accuracy of manufacture requires high, so cost is also higher, and difficulty is very big, is grasped monopolization by a handful of countries such as the U.S. basically.
The utility model content
The technical matters that the utility model mainly solves provides a kind of aircraft Assisted Take Off system; The difficulty of this aircraft Assisted Take Off system manufacturing that restriction and ejector complex structure accuracy requirement height to aircraft weight bring of can avoiding adopting the sliding formula of jumping to take off; Reduce the equipment cost of ship-board aircraft Assisted Take Off, also initial velocity required when taking off can be provided simultaneously.
In order to address the above problem; The utility model provides a kind of aircraft Assisted Take Off system; This aircraft Assisted Take Off system comprises: gravitional force is changed into the runway of kinetic energy and cooperates with this slideway and along its coaster that moves; This slideway one end and the smooth connection of aircraft carrier flight deck, the other end and aircraft carrier warship island are fixed, and the slideway initiating terminal that is positioned at the warship island is a horizontality.
Say that further the bottom of said coaster is provided with at least three slide blocks, this slide block cooperates with guide groove on the slideway, in the lower, transverse of said slide block with vertically be respectively equipped with the pulley that cooperates with guide groove; On this coaster, be provided with the aircraft anchor fitting fixed respectively of four direction all around; Wherein, Each anchor fitting comprises preventer and permanent seat, and this permanent seat is provided with set pin, and said preventer one end is set on the set pin; The other end and coaster are fixed, this set pin one side be provided with carry out to remove fixing electromagnetic machine be arranged on this way end and with electromagnetic machine control circuit bonded assembly travel switch.
Say that further said preventer comprises nylon.
Say that further said coaster is provided with linear electric motors, these linear electric motors are connected with the pulley drive of horizontally set.
Say further, do not hold at said slideway to be provided with coaster deceleration arrester.
The utility model discloses a kind of aircraft Assisted Take Off system; Comprise gravitional force is changed into the runway of kinetic energy and the coaster that moves along this slideway; One of which end and level runway smooth connection, the other end and aircraft carrier warship island are fixed, and the slideway initiating terminal that is positioned at the warship island is a horizontality.Aircraft that will be to be taken off during use is promoted to the slideway initiating terminal that is positioned at warship island end, and aircraft wheel and supratrochlear Locking Device are fixed; Dive together to gliding with coaster then and quicken, when aircraft will leave the help-fly slideway on slope, control electromagnetic machine work by travel switch when being about to reach takeoff speed, make that the preventer on the anchor fitting unclamps, remove and fix, aircraft soars.This system utilizes the gravitional force second-mission aircraft of aircraft self to take off; The difficulty of the help-fly slideway on the slope manufacturing that restriction and ejector complex structure accuracy requirement height to aircraft weight bring of can avoiding adopting the sliding formula of jumping to take off; Reliably, auxiliary reinforcing required when taking off is provided effectively, stably; Reach the initial velocity that takes off rapidly, it both can be used for aircraft at the aircraft carrier Assisted Take Off, also can be used for aircraft short range Assisted Take Offs such as island.
Description of drawings
Fig. 1 is the utility model aircraft Assisted Take Off system embodiment structural representation.
Fig. 2 is a B part-structure enlarged diagram among Fig. 1.
Fig. 3 is coaster and slideway fit structure scheme drawing.
Fig. 4 is aircraft anchor fitting and aircraft hook fit structure scheme drawing.
Fig. 5 is a C part-structure scheme drawing among Fig. 4.
Below in conjunction with embodiment, and with reference to accompanying drawing, realization, functional characteristics and the advantage of the utility model purpose is described further.
The specific embodiment
As depicted in figs. 1 and 2, the utility model provides a kind of aircraft Assisted Take Off system embodiment.
This aircraft Assisted Take Off system comprises: can gravitional force changed into the runway 3 of kinetic energy and cooperates with this slideway 3 and along its coaster that moves 4; These slideway 3 one ends and 1 smooth connection of aircraft carrier flight deck; The other end and aircraft carrier warship island 2 is fixing, and the slideway initiating terminal that is positioned at warship island end 2 is a horizontality.
Specifically; Initiating terminal at said slideway 3 is provided with coaster 4, and the bottom of said coaster 4 is provided with three slide blocks 40 that are hinged with it, guide groove 41 bearing fits on this slide block 40 and the slideway 3; Promptly the bottom of this slide block 40 is embedded in the guide groove 41 on the slideway 3, and the top of this slide block 40 and coaster 4 are hinged.
As shown in Figure 3; In the lower, transverse of said slide block 40 with vertically be respectively equipped with the pulley with guide groove 41 bearing fits; The bottom that is slide block 40 is respectively equipped with horizontal pulley 43 and vertical pulley 42, because the bottom of slide block 40 is embedded in the guide groove 41 on the slideway 3, this horizontal pulley 43 contacts with two sides about in the of 41 with guide groove respectively with vertical pulley 42; Friction force between minimizing and the guide groove 41 improves its speed.
The bottom of said coaster 4 is provided with at least three slide blocks 40, and this slide block 40 cooperates with guide groove 41 on the slideway 3, in the lower, transverse of said slide block 40 with vertically be respectively equipped with the pulley (42,43) that cooperates with guide groove 41; On this coaster 4, be provided with the aircraft anchor fitting 5 fixed respectively of four direction all around; Wherein, Each anchor fitting 5 comprises preventer 54 and permanent seat 52, and this permanent seat 52 is provided with set pin 50, and said preventer 54 1 ends are set on the set pin 50; The other end and coaster 4 is fixing, these set pin 50 1 sides be provided with carry out remove fixing electromagnetic machine 53 be arranged on this slideway 3 terminal and with electromagnetic machine 53 control circuit bonded assembly travel switches (accompanying drawing does not indicate).
Like Fig. 2, Fig. 4 and shown in Figure 5, on this coaster 4, be provided with anchor fitting 5 on the aircraft four, each anchor fitting 5 cooperates with aircraft hook A1, trailing wheel and front-wheel respectively through preventer 54 makes said aircraft A fix.
Aircraft A that will be to be taken off during use is promoted to slideway 3 initiating terminals that are positioned at warship island end, by four anchor fittings on the coaster 45 aircraft is fixed.
When aircraft A and coaster 4 synchronously to sliding into slideway 3 when terminal, under the effect of travel switch, the potential energy of aircraft is converted into kinetic energy, promptly aircraft A slides into slideway 3 and produces certain initial velocity when terminal; Leave the help-fly slideway on slope as aircraft A; When being slideway 3 ends; Under the effect of travel switch, start electromagnetic machine 53 set pin 50 is transferred to, the preventer that is set on this set pin 50 separates respectively with front-wheel with aircraft hook A1, trailing wheel rapidly, makes aircraft be in the releasing stationary state.
Speed in the time of under the suitable dynamic action of aircraft, can relatively easily making aircraft leaving water flat reaches the takeoff speed of aircraft.This aircraft Assisted Take Off system utilizes the gravitional force of aircraft self that the partial velocity Assisted Take Off is provided; The difficulty of the help-fly slideway on the slope manufacturing that restriction and ejector complex structure accuracy requirement height to aircraft weight bring of can avoiding adopting the sliding formula of jumping to take off; Reduce the equipment cost of ship-board aircraft Assisted Take Off; Simultaneously also initial velocity required when taking off can be provided, it both can be used for aircraft at the aircraft carrier Assisted Take Off, also can be used for aircraft short range Assisted Take Offs such as island.
In the above-described embodiments, said coaster 4 is provided with linear electric motors (accompanying drawing does not indicate), and these linear electric motors are with laterally pulley 43 or vertical pulley 42 are in transmission connection.These linear electric motors provide power for it in coaster 4 downslide processes, when making it arrive slideway 3 ends, can enough initial velocity be provided for aircraft.Said preventer 54 comprises the rope that nylon or other high strength materials are processed.Said
Can not hold at said slideway as required and be provided with coaster deceleration arrester (accompanying drawing does not indicate); This deceleration arrester comprises the coil tension spring (accompanying drawing does not indicate) that is arranged on slideway 3 ends; Can reduce the impulsive force of 4 pairs of equipment of coaster on the one hand, increase the service life; Can avoid or reduce additionaling power on the other hand makes this coil tension spring with coaster 4 slideway 3 initiating terminals that rebound.
The above is merely the preferred embodiment of the utility model; Be not thus the restriction the utility model claim; Every equivalent structure or equivalent flow process conversion that utilizes the utility model specification sheets and accompanying drawing content to be done; Or directly or indirectly be used in other relevant technical fields, all in like manner be included in the scope of patent protection of the utility model.
Claims (5)
1. aircraft Assisted Take Off system is characterized in that:
Comprise gravitional force is changed into the runway of kinetic energy and cooperates with this slideway and along its coaster that moves; This slideway one end and the smooth connection of aircraft carrier flight deck; The other end and aircraft carrier warship island are fixed, and the slideway initiating terminal that is positioned at the warship island is a horizontality.
2. aircraft Assisted Take Off according to claim 1 system is characterized in that:
The bottom of said coaster is provided with at least three slide blocks, and this slide block cooperates with guide groove on the slideway, in the lower, transverse of said slide block with vertically be respectively equipped with the pulley that cooperates with guide groove; On this coaster, be provided with the aircraft anchor fitting fixed respectively of four direction all around; Wherein, Each anchor fitting comprises preventer and permanent seat, and this permanent seat is provided with set pin, and said preventer one end is set on the set pin; The other end and coaster are fixed, this set pin one side be provided with carry out to remove fixing electromagnetic machine be arranged on this way end and with electromagnetic machine control circuit bonded assembly travel switch.
3. aircraft Assisted Take Off according to claim 2 system is characterized in that:
Said preventer comprises nylon.
4. aircraft Assisted Take Off according to claim 1 and 2 system is characterized in that:
Said coaster is provided with linear electric motors, and these linear electric motors are connected with the pulley drive of horizontally set.
5. aircraft Assisted Take Off according to claim 1 and 2 system is characterized in that:
Do not hold at said slideway and to be provided with coaster deceleration arrester.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011203351618U CN202219842U (en) | 2011-09-07 | 2011-09-07 | Auxiliary taking-off system of airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011203351618U CN202219842U (en) | 2011-09-07 | 2011-09-07 | Auxiliary taking-off system of airplane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202219842U true CN202219842U (en) | 2012-05-16 |
Family
ID=46041873
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2011203351618U Expired - Fee Related CN202219842U (en) | 2011-09-07 | 2011-09-07 | Auxiliary taking-off system of airplane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202219842U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102358432A (en) * | 2011-09-07 | 2012-02-22 | 刘建平 | Assisted takeoff system of airplane |
| CN104002982A (en) * | 2013-02-26 | 2014-08-27 | 邓先勇 | Rapid taking-off device for aircraft carrier plane |
| CN105015789A (en) * | 2014-08-25 | 2015-11-04 | 韩淮生 | Potential-energy runway |
| CN105752303A (en) * | 2015-12-29 | 2016-07-13 | 深圳前海联合邮轮有限公司 | Method for assisting short takeoff of fixed wing aircraft and ship form |
-
2011
- 2011-09-07 CN CN2011203351618U patent/CN202219842U/en not_active Expired - Fee Related
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102358432A (en) * | 2011-09-07 | 2012-02-22 | 刘建平 | Assisted takeoff system of airplane |
| WO2013034054A1 (en) * | 2011-09-07 | 2013-03-14 | Liu Jianping | Assisted takeoff system for aircraft |
| CN104002982A (en) * | 2013-02-26 | 2014-08-27 | 邓先勇 | Rapid taking-off device for aircraft carrier plane |
| CN105015789A (en) * | 2014-08-25 | 2015-11-04 | 韩淮生 | Potential-energy runway |
| CN105752303A (en) * | 2015-12-29 | 2016-07-13 | 深圳前海联合邮轮有限公司 | Method for assisting short takeoff of fixed wing aircraft and ship form |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| DD01 | Delivery of document by public notice |
Addressee: Liu Jianping Document name: Notification of Passing Examination on Formalities |
|
| DD01 | Delivery of document by public notice | ||
| DD01 | Delivery of document by public notice |
Addressee: Liu Jianping Document name: Notification to Pay the Fees |
|
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20120516 Termination date: 20180907 |