CN101920785A - Motor-driven friction traction band-type catapult - Google Patents
Motor-driven friction traction band-type catapult Download PDFInfo
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- CN101920785A CN101920785A CN2009103031392A CN200910303139A CN101920785A CN 101920785 A CN101920785 A CN 101920785A CN 2009103031392 A CN2009103031392 A CN 2009103031392A CN 200910303139 A CN200910303139 A CN 200910303139A CN 101920785 A CN101920785 A CN 101920785A
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Abstract
The invention relates to a plane-assisted take-off accelerator on the ground or deck, aiming at overcoming the defects of low energy density and high cost of an electromagnetic catapult and providing an electromagnetic mechanical catapult which is more simple and portable, low in cost, small in volume and simple to maintain for catapult-assisted take-off planes and unmanned planes. The catapult has the advantage of stable acceleration of the electromagnetic catapult. The invention achieves the purpose as follows: two rows of parallel-mounted rotating motors in pairs are used as the catapult power and drive friction wheels with the same amount to rotate in the opposite direction at high speed; a friction traction belt is arranged between the two rows of friction wheels and is pulled forward by the friction force generated by the friction wheels as long as the two rows of motors rotate in the opposite direction; and catapult pulleys connected on the traction belt are pulled and accelerated so that the catapult pulley drags the plane to take off to achieve the purpose of catapulting the plane. Compared with the electromagnetic catapult, the motor-driven friction traction band-type catapult has the advantages of small volume, light weight, simple structure and high conversion rate of catapult energy.
Description
The present invention relates to a kind of ground or the deck take-off-helping acceleration device of boarding a plane.
Ejector is to help the device of aircraft at short field take-off, till preceding, various forms of ejectors occurred, and this wherein has hydraulic catapult and the steam catapult that is widely used, and just also comprises now the electromagnetic launch device in practicability.The electromagnetic launch device utilizes the linear electric motors principle to reach and quickens to promote to take off, have advantages such as acceleration capability is good, easy maintenance, electromagnetism airplane catapult system is made up of closed-center system, large power, electrically force control apparatus, central microcomputer industry control control and line inductance electromotor etc.Closed-centre system requires to be full of rapidly energy needed in the cycle of launching, when launching, want in several milliseconds, to flow through rapidly that part of coil of corresponding mover in the stator coil, so just cause the electric current that flows through this part coil in the short time very big, produce superheat, stator coils all in ejection process all will be heated once at short notice, and the time of each stator coil work is very short, so have half all to be converted into heat energy with the energy that launches, the conversion loss of launching energy is very big.Compare with steam catapult with hydraulic catapult, the electromagnetic launch utensil has shortcomings such as mechanical energy density is low, cost is high, launch generation heat is too big.Compare the big and weight of the volume of steam catapult electromagnetic launch device and allegedly can reduce more than 40%, but from the current situation of U.S.'s electromagnetic launch device, how much low the weight of electromagnetic launch device is unlike steam catapult.
Purpose of the present invention is exactly in order to solve the defective that electromagnetic launch device energy density is low, price is high, for the various aircrafts that need catapult-assisted take-off and unmanned plane provide a kind of more simple, light, cost is low, volume is little, easy to maintenance electrodynamic mechanical type ejector, this ejector also has the electromagnetic launch device simultaneously and quickens the pulsation-free advantage.
The object of the present invention is achieved like this, use two is lined up power is launched in the rotating machine conduct of installation arranged side by side, the frictional wheel that these rotating machines drive same quantity is high speed rotating in opposite directions, between two row's frictional wheels, be provided with the friction traction band, as long as this two rows electrical motor rotates in opposite directions, traction belt will constantly be spurred forward by the friction that frictional wheel produces, the coaster that launches that is connected on the traction belt also just is pulled acceleration, just can make and launch coaster and drag and take off, reach the purpose of cataplane.
Compare with the electromagnetic launch device that has occurred, the motor friction traction band-type catapult have volume little, in light weight, simple in structure, launch the high advantage of energy transformation ratio, do not have coil heating and electric current ablation problem, there is not the electric current assignment problem, power peak is lower, has reduced launching the requirement of energy device.Because the friction traction band is accelerated in distraction procedure part is continuous shortening, therefore after launching end, need the part quality of braking also very little, almost only remainingly launch coaster and need braking deceleration, this has just created condition for simplifying braking.Ejection travel can extend as required, this needs to increase traction belt length and just can achieve the goal, launching power strengthens and can realize by increasing the motor unit power, also can achieve the goal, can also utilize many forms arranged side by side to realize launching power and become multiple to increase by increasing electrical motor quantity.
Accompanying drawing is motor-driven friction belt traction ejector schematic perspective view.Fig. 1 adjusts structure for motor-driven friction belt traction ejector frictional wheel spacing distance, and Fig. 2 is the traction belt Storage case work scheme drawing of motor-driven friction belt traction ejector.Fig. 3 is combined electric friction belt traction ejector.
With reference to accompanying drawing 1; Motor-driven friction belt traction ejector by launch with electrical motor 1, by motor-operated frictional wheel 2, friction traction band 3, launch coaster 4, ejection orbit 5, launch energy power supply 6, brake equipment 7 and traction belt retracting motor 8 etc. partly form.Launch and be divided into two rows with motor and vertically be set up in parallel, frictional wheel is installed on the concentric position of motor shaft, and perhaps clear-cut and motor coaxle has the distance that is equivalent to the friction traction tape thickness with the frictional wheel that is in friction traction band another side.Friction traction band cross section is inclined to one side flat rectangular, forms with high tensile strength fibrous material braiding 9, scribbles the abrasion resistant paint 10 that increases coefficient of friction on the attrition surface of both sides.One of friction traction band is fixed on the axle 11 of traction belt retracting motor, the other end is fixed on launches below the coaster in the coupling sleeve 12, be not coated with abrasion resistant paint near one section traction belt two sides 13 of launching coaster, thickness reduces to some extent, and scribble wear-resisting lubricant, sagging for the traction belt that reduces friction, its underpart is provided with several carrier wheels 14.Consider that motor power increase when starting just is slower, the starting that several minor diameters also can be set adds speed motor 15, the traction belt retracting motor also can play accelerating action when launching beginning, stressed for dealing with elevator, the drum shaft of traction belt retracting motor need be strengthened bearing seat.
With reference to accompanying drawing 2: the frictional wheel of motor-driven friction belt traction ejector is together with launching on the wheel carrier that motor is installed in rigidity jointly, for improving the equilibrium and the validity of friction in the ejection process, prevent to skid, at the frictional wheel 2 of traction belt one side and launch motor 1 and be fixedly mounted on the aircraft carrier structure 17 by rigidity wheel carrier 16 or on the pedestal of ground, the frictional wheel rigidity wheel carrier of opposite side then be arranged on can about adjust on the glide base 18 of position, this pedestal is fixed on aircraft carrier structure or the ground pedestal, the adjustable bolt 19 that is used for adjusting two frictional wheel gaps is set between this wheel carrier and glide base, in the specific implementation, the structure of adjusting the wheel gap can have optimized structure, finish with the computer program that weaves the adjusting play, employing has the control system of automatic guidance feedback closed loop and determines the pressure of two-wheeled with respect to the friction traction band, can be according to power of motor, rotating speed, the haulage speed of friction traction band is determined the variation of pressure automatically.
With reference to accompanying drawing 3; For the small-sized ejector that launches unmanned plane, the folding and unfolding of traction belt also can be finished by a Storage case groove 20, whole catapult-launching gear in the course of the work, friction traction band 3 is brought in the traction belt Storage case 21 by the frictional wheel 2 of high speed revolution, traction belt 22 parts of being braked just rely on inertia to swing, be automatically folded into " S " shape, two walls of traction belt Storage case are provided with and help fold mechanism 23, can compress traction belt 24 parts that are " S " shape.Launch finish after, launch supratrochlear time wilful trailing cable and drive coaster and return and launch initial point, traction belt also just is drawn out the traction belt Storage case once more, and is tightened up, and enters ejection status next time.
In concrete enforcement, motor-driven friction traction band-type catapult can be designed to the model of various power, also two ejectors can be combined the device that forms one times of power boosting.Gap between a pair of frictional wheel can be by clashing into machinery or the electronics opening device leaves the friction traction band in moment.It can be power autonomous launching the energy power supply, also can use electric current on the cable transmission naval vessel.Braking model can be according to the size and the size of whole ejector power, purposes is optimized selection, can be the hydro retarder device, also can be hydraulic efficiency gear, and small-sized ejector then can use simple spring device.Launch acceleration distance for increasing in limited distance, the friction wheels can be considered to adopt and can change the design in crack between the two-wheeled fast in moment as far as possible, launch supratrochlear traction belt coupling sleeve and pass through smoothly so that can allow.For drawing the friction traction band smoothly in, also can combine use to the folding and unfolding of motor elevator and two kinds of methods of serpentine gathering.For the small-sized ejector of vehicle frame formula that launches unmanned plane, usually ejection orbit is to be inclined upwardly, if the motor-driven friction device is arranged on the top of track, will make that ejector is top-heavy, in order to reach ejector optimal design generally, also can drive the initiating terminal of device 25 designs to motor-driven friction traction at ejector, by connecting the fixed pulley pulling unmanned plane of a trailing cable and change of direction, the general design that helps ejector like this, it is also conceivable that motor-driven friction traction principle and pulley acceleration device are combined, utilize the assembly pulley of motor-driven friction traction band pulling ejector.
Claims (3)
1. one kind helps aircraft to quicken to take off to launch the motor-driven friction traction band-type catapult of usefulness, it is characterized in that this device is taken turns by double-type motor-driven friction and the friction traction band is formed, double-type frictional wheel reaches by the friction traction band between friction drive two frictional wheels rotation of motor is quickened to become the straight line acceleration of launching coaster, the traction belt cross section is rectangular, and both side surface scribbles the coating that increases friction.
2. by the motor-driven friction traction band-type catapult of claim 1 regulation, one that it is characterized in that being extruded by frictional wheel at traction belt is provided with the traction belt draw off gear.
3. by the motor-driven friction traction band-type catapult of claim 1 and 2 regulations, it is characterized in that being provided with several minor diameter frictional wheels, the electric winch power of traction belt far surpasses take-up and needs.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009103031392A CN101920785A (en) | 2009-06-10 | 2009-06-10 | Motor-driven friction traction band-type catapult |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009103031392A CN101920785A (en) | 2009-06-10 | 2009-06-10 | Motor-driven friction traction band-type catapult |
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| Publication Number | Publication Date |
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| CN101920785A true CN101920785A (en) | 2010-12-22 |
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| CN2009103031392A Pending CN101920785A (en) | 2009-06-10 | 2009-06-10 | Motor-driven friction traction band-type catapult |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102826233A (en) * | 2012-08-24 | 2012-12-19 | 朱惠芬 | Combined multipurpose aircraft carrier land-based catapult-assisted take-off training device |
| CN103761901A (en) * | 2014-01-24 | 2014-04-30 | 吴佳明 | Carrier-based aircraft pilot dynamic simulated training system |
| CN104071347A (en) * | 2014-06-30 | 2014-10-01 | 中国人民解放军国防科学技术大学 | Folding unmanned aerial vehicle launch frame based on ejection of rubber band |
| CN105730709A (en) * | 2016-03-24 | 2016-07-06 | 上海寰鹰航空技术有限公司 | Catapult rack |
| CN106956903A (en) * | 2017-04-12 | 2017-07-18 | 奥美森智能装备股份有限公司 | A kind of accelerator |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1076660A (en) * | 1992-09-28 | 1993-09-29 | 马兴彪 | Synchronous bidirectional slide device for plane takeoff and landing |
| US20020185569A1 (en) * | 2001-03-19 | 2002-12-12 | Kurt Henne | Airplane training and amusement device for traveling on a fixed track |
| EP1877669A1 (en) * | 2005-04-28 | 2008-01-16 | Bosch Rexroth AG | Hydraulic catapult drive |
-
2009
- 2009-06-10 CN CN2009103031392A patent/CN101920785A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1076660A (en) * | 1992-09-28 | 1993-09-29 | 马兴彪 | Synchronous bidirectional slide device for plane takeoff and landing |
| US20020185569A1 (en) * | 2001-03-19 | 2002-12-12 | Kurt Henne | Airplane training and amusement device for traveling on a fixed track |
| EP1877669A1 (en) * | 2005-04-28 | 2008-01-16 | Bosch Rexroth AG | Hydraulic catapult drive |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102826233A (en) * | 2012-08-24 | 2012-12-19 | 朱惠芬 | Combined multipurpose aircraft carrier land-based catapult-assisted take-off training device |
| CN102826233B (en) * | 2012-08-24 | 2015-02-25 | 朱惠芬 | Combined multipurpose aircraft carrier land-based catapult-assisted take-off training device |
| CN103761901A (en) * | 2014-01-24 | 2014-04-30 | 吴佳明 | Carrier-based aircraft pilot dynamic simulated training system |
| CN104071347A (en) * | 2014-06-30 | 2014-10-01 | 中国人民解放军国防科学技术大学 | Folding unmanned aerial vehicle launch frame based on ejection of rubber band |
| CN104071347B (en) * | 2014-06-30 | 2017-01-25 | 中国人民解放军国防科学技术大学 | Folding unmanned aerial vehicle launch frame based on ejection of rubber band |
| CN105730709A (en) * | 2016-03-24 | 2016-07-06 | 上海寰鹰航空技术有限公司 | Catapult rack |
| CN106956903A (en) * | 2017-04-12 | 2017-07-18 | 奥美森智能装备股份有限公司 | A kind of accelerator |
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Application publication date: 20101222 |