WO2013034054A1

WO2013034054A1 - Assisted takeoff system for aircraft

Info

Publication number: WO2013034054A1
Application number: PCT/CN2012/080496
Authority: WO
Inventors: 刘建平
Original assignee: Liu Jianping
Priority date: 2011-09-07
Filing date: 2012-08-23
Publication date: 2013-03-14
Also published as: CN102358432A

Abstract

An assisted takeoff system for an aircraft, comprising a slope slideway (3) and a sliding carrier (4), wherein one end of the slideway is smoothly connected to a horizontal track (1) and the other end thereof is fixed to the island (2) of the aircraft carrier, and the starting end of the slideway located at the island is horizontal; a device (5) for fastening and unlocking between the aircraft and the sliding carrier is provided on the sliding carrier to prevent vibration. In use, the aircraft is placed at the starting end of the slideway at the island; and the sliding carrier accelerates downwards together with the aircraft; when the aircraft reaches the bottom of the slope, a travel switch activates an electromagnetic machine to release the fastening; and the aircraft continues to accelerate and takes off. The system utilises the gravitational potential energy of the aircraft itself to assist the takeoff, which avoids the restriction on the weight of the aircraft in ski jump takeoff and the disdavantage of the catapult in being difficult to manufacture, enabling the aircraft to reach the takeoff initial speed swiftly. It can be used both in assisted takeoff of aircraft from an aircraft carrier and in short-distance assisted takeoff such as on an isle.

Description

Aircraft assisted take-off system

Technical field

The invention relates to the field of aircraft assisted take-off technology, in particular to an aircraft carrier and a short island auxiliary take-off system on a narrow island. Background technique

Due to the limited length of warships, the carrier-based aircraft usually needs to adopt the auxiliary take-off method to make the aircraft leave the warship with no speed greater than or equal to the ground speed of the aircraft, otherwise the aircraft cannot take off normally. For example, an aircraft carrier aircraft usually takes two modes when it takes off. One is to use a ski lift. This method requires that the aircraft should not take too much weight when it takes off, that is, it cannot carry more fuel and ammunition, so its combat The range is greatly limited; the other is the use of catapult take-off, although this method has a small weight limit on the aircraft, but the structure of the catapult is complex and the manufacturing precision is high, so the cost is high and the difficulty is very large. The monopoly held by a handful of countries such as the United States. Summary of the invention

The technical problem mainly solved by the present invention is to provide an aircraft auxiliary take-off system, which can avoid the limitation of the weight of the aircraft by the take-off take-off and the difficulty of manufacturing the high precision of the ejector structure, and reduce the ship. The cost of equipment for aircraft-assisted take-off, as well as the initial speed required for the aircraft to take off.

In order to solve the above problems, the present invention provides an aircraft assisted take-off system, the aircraft assisted take-off system comprising: a slope slide that converts gravitational potential energy into kinetic energy and a trolley that cooperates with and moves along the slideway, the slide end is The aircraft carrier's flight deck is smoothly connected, the other end is fixed to the aircraft carrier island, and the starting end of the slide at the island is horizontal.

Further, the lower portion of the trolley is provided with at least three sliders, and the slider cooperates with the guide groove on the slide rail, and is provided with a sliding joint with the guide groove in the lower portion and the longitudinal direction of the lower portion of the slider. The wheel is provided with fixing means for fixing the front, rear, left and right directions of the aircraft respectively, wherein each fixing device comprises a fixing cable and a fixing seat, the fixing seat is provided with a fixing pin, and the fixing cable is provided at one end The fixing pin is fixed on the fixing pin, and the other end is fixed to the trolley. On the side of the fixing pin, an electromagnetic motor for releasing the fixing and a stroke switch provided at the end of the sliding rail and connected to the electromagnetic motor control circuit are provided.

Further, the fixing cable comprises nylon.

Further, the trolley is provided with a linear motor that is drivingly coupled to a pulley disposed laterally.

Further, a trolley deceleration blocking device is disposed at the end of the slide. The invention discloses an aircraft auxiliary take-off system, which comprises a slope slide which converts gravitational potential energy into kinetic energy and a trolley which moves along the slideway, one end of which is smoothly connected with the horizontal runway, the other end is fixed with the aircraft carrier ship island, and is located at the ship island. The starting end of the chute is horizontal. When in use, lift the aircraft to be taken off to the starting end of the slide at the island end, fix the aircraft wheel and the locking device on the pulley; then, with the pulley, dive down and accelerate, when the aircraft will leave the slope of the flight guide, When the take-off speed is reached, the electromagnetic motor is controlled by the travel switch, so that the fixing cable on the fixing device is loosened, the fixing is released, and the aircraft is emptied. The system utilizes the aircraft's own gravity potential energy to assist the aircraft to take off. The slope-assisted flight chute can avoid the difficulty of adopting the sliding take-off to limit the weight of the aircraft and the high precision of the projectile structure. It is reliable, effective and stable. The ground provides the auxiliary boosting force required for the aircraft to take off, and quickly reaches the initial takeoff speed. It can be used for aircraft to take off in the aircraft carrier, or for short-distance auxiliary take-off of islands and other aircraft. DRAWINGS

1 is a schematic structural view of an embodiment of an aircraft auxiliary take-off system of the present invention.

Figure 2 is an enlarged schematic view of the structure of Part B in Figure 1.

Figure 3 is a schematic view of the structure of the pulley and the slide.

Figure 4 is a schematic view of the structure of the aircraft fixture and the aircraft hook.

Figure 5 is a schematic view of the structure of part C in Figure 4. The implementation, functional features and advantages of the object of the present invention will be further described below in conjunction with the embodiments and with reference to the accompanying drawings. detailed description

As shown in Figures 1 and 2, the present invention provides an embodiment of an aircraft assisted take-off system. The aircraft auxiliary take-off system includes: a slope chute 3 that converts gravitational potential energy into kinetic energy and a troch 4 that cooperates with and moves along the chute 3, the chute 3 end is smoothly connected with the aircraft carrier flight deck 1 and the other end It is fixed with the aircraft carrier island 2, and the starting end of the slide at the island end 2 is horizontal.

Specifically, a trolley 4 is disposed at a starting end of the slideway 3, and a lower portion of the trolley 4 is provided with three sliders 40 hinged thereto, and the slider 40 and the guide groove 41 on the slideway 3 The sliding fit, that is, the lower portion of the slider 40 is embedded in the guide groove 41 on the slide 3, and the upper portion of the slider 40 is hinged to the trolley 4.

As shown in FIG. 3, pulleys are slidably engaged with the guide grooves 41 in the lower portion and the longitudinal direction of the slider 40, that is, the lower portion of the slider 40 is provided with a lateral pulley 43 and a longitudinal pulley 42, respectively, due to the slider 40. The lower portion is embedded in the guide groove 41 on the slide 3, and the lateral pulley 43 and the longitudinal pulley 42 are respectively in contact with the upper and lower sides and the side surfaces of the guide groove 41, thereby reducing the frictional force with the guide groove 41 and increasing the speed thereof.

The lower portion of the trolley 4 is provided with at least three sliders 40. The slider 40 cooperates with the guide slots 41 on the slide rails 3. In the lower portion and the longitudinal direction of the slider 40, a pulley matched with the guide slots 41 is respectively disposed. (42, 43); the trolley 4 is provided with fixing devices 5 for fixing the front, rear, left and right directions of the aircraft respectively, wherein each fixing device 5 includes a fixing cable 54 and a fixing seat 52, and the fixing seat 52 is provided There is a fixing pin 50, the fixing cable 54 is sleeved on the fixing pin 50, and the other end is fixed to the trolley 4. On the side of the fixing pin 50, an electromagnetic motor 53 for performing the unfixing is disposed and disposed on the sliding path 3. A trip switch (not shown) connected to the control circuit of the electromagnetic motor 53 at the end.

As shown in FIG. 2, FIG. 4 and FIG. 5, an aircraft four upper fixing device 5 is provided on the trolley 4, and each fixing device 5 is hooked to the aircraft by the fixing cable 54 respectively, the rear wheel and the front wheel. The fit makes the aircraft A fixed.

When in use, the aircraft A to be taken off is lifted to the starting end of the slide 3 at the end of the ship, and the aircraft is fixed by four fixing devices 5 on the trolley 4.

When the aircraft A and the trolley 4 are synchronized to slide to the end of the slide 3, under the action of the travel switch, the potential energy of the aircraft is converted into kinetic energy, that is, the aircraft A slides to the end of the slide 3 to generate a certain initial speed; when the aircraft A leaves When the assisted fly chute of the slope, that is, the end of the chute 3, the electromagnetic motor 53 is activated by the stroke switch to disengage the fixing pin 50, and the fixing cable sleeved on the fixing pin 50 is quickly hooked to the aircraft, the rear wheel Separate from the front wheels to release the aircraft.

The speed at which the aircraft leaves the horizontal runway can be relatively easily achieved by the proper power of the aircraft to reach the takeoff speed of the aircraft. The aircraft auxiliary take-off system utilizes the aircraft's own gravitational potential energy to provide partial speed-assisted take-off. The slope-assisted flight chute can avoid the difficulty of manufacturing by using the take-off take-off to limit the weight of the aircraft and the high precision of the projectile structure. It reduces the equipment cost of the aircraft's auxiliary take-off, and also provides the initial speed required for the aircraft to take off. It can be used for aircraft to take off in the aircraft carrier, or for short-distance auxiliary take-off of islands.

In the above embodiment, the trolley 4 is provided with a linear motor (not shown in the drawing), and the linear motor is drivingly coupled to the lateral pulley 43 or the longitudinal pulley 42. The linear motor is powered during the sliding of the trolley 4 so that it reaches the end of the slide 3 to provide sufficient initial velocity for the aircraft. The retaining cable 54 comprises a cord made of nylon or other high strength material. Said

A pulley deceleration blocking device (not shown in the drawing) may be disposed at the end of the chute as needed, and the deceleration blocking device includes a telescopic spring disposed at the end of the chute 3 (not shown in the drawing), and the trolley 4 may be reduced on the one hand. Impact on the equipment, prolong the service life; on the other hand, it can avoid or reduce the external power to make the telescopic spring bounce the pulley 4 back to the slide 3

The above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the patents of the present invention.

4 Transformations, or direct or indirect use in other related technical fields, are equally included in the scope of patent protection of the present invention.

Claims

Claim

An aircraft assisted take-off system characterized by:

The utility model comprises a slope slide which converts gravitational potential energy into kinetic energy and a trolley which cooperates with and moves along the slideway, and one end of the slideway is smoothly connected with the flight deck of the aircraft carrier, and the other end is fixed with the aircraft carrier island and is located at the slide of the island. The starting end is horizontal.

2. The aircraft assisted take-off system according to claim 1, wherein: the lower portion of the trolley is provided with at least three sliders, and the slider cooperates with a guide groove on the slide rail, and laterally at a lower portion of the slider The longitudinal direction is respectively provided with a pulley that cooperates with the guide groove; the trolley is provided with fixing means for fixing the front, rear, left and right directions of the aircraft respectively, wherein each fixing device comprises a fixing cable and a fixing seat, and the fixing seat is provided with a fixing pin, one end of the fixing cable is sleeved on the fixing pin, and the other end is fixed to the trolley, and an electromagnetic motor for performing the unfixing is disposed on the side of the fixing pin and is disposed at the end of the sliding channel and connected to the electromagnetic motor control circuit. Limit switch.

3. The aircraft assisted take-off system of claim 2, wherein: the fixing cable comprises nylon.

The aircraft-assisted take-off system according to claim 1 or 2, characterized in that the trolley is provided with a linear motor which is connected to a laterally disposed pulley drive.

The aircraft auxiliary take-off system according to claim 1 or 2, characterized in that: a pulley deceleration blocking device is arranged at the end of the slide.