CN104494841B - Compound electric unit power turns strap towing aircraft ejector - Google Patents
Compound electric unit power turns strap towing aircraft ejector Download PDFInfo
- Publication number
- CN104494841B CN104494841B CN201410775451.2A CN201410775451A CN104494841B CN 104494841 B CN104494841 B CN 104494841B CN 201410775451 A CN201410775451 A CN 201410775451A CN 104494841 B CN104494841 B CN 104494841B
- Authority
- CN
- China
- Prior art keywords
- strap
- deck
- hook
- runway
- traction
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Abstract
The present invention provides a kind of compound electric unit power to turn strap towing aircraft ejector, including traction strap, hook, check cable, pulley, capstan winch, clutch and group of motors.It is characterized in that being provided power in runway underdeck coaxial electrical unit by clutch linkage capstan winch, being pulled through pulley and change the direction fold back traction strap on the runway of deck by being arranged at, traction power-assisted aircraft realizes the accelerator of taking off of aircraft.The present invention is compared with prior art, have with low content of technology, application technology is ripe, simple in construction, the feature such as easily fabricated: the most also have that system overall weight is light, volume is few, the smooth integrity on deck that occupies little space, do not destroys, fold back rear braking distance, be not take up the metric space of runway, it is prone to hold concurrently storage catapult-assisted take-off and slide the double dominant that the formula of jumping is taken off, thus the present invention has good practical value.
Description
One, technical field:
The present invention relates to aircraft carrier equipment, a kind of compound electric unit power turns strap towing aircraft ejector.
Two, background technology:
The modern Aviation mother ship carrier of sharp weapon is striven as blue sea warfare, restriction because of its technical know-how, manufacturing capacity and overall national strength, a few countries is only had to have in the world, the more steam ejection of comprehensive function advantage lets the aircraft carrier of aircraft fly away, the only U.S. can the most successfully manufacture, and has thus achieved the global dominance of USN, has the electromagnetic launch aircraft carrier of Future Significance, though having develop multinational addition, but all the examination stage being ground at place.Use except manufacture and research and develop outside the act of state of ski-jump take-off, steam ejection and electromagnetic launch, how to let aircraft fly away on aircraft carrier, also have many specialties, amateurish fan carries out from omnibearing multiple visual angle considering as and exploring.
Three, summary of the invention:
It is an object of the invention to for above present situation and problem, it is provided that a kind of compound electric unit power with low content of technology, that application technology is ripe, simple in construction, efficiency are high turns strap towing aircraft ejector.
It is an object of the invention to be achieved through the following technical solutions:
A kind of compound electric unit power turns strap towing aircraft ejector, including traction strap, hook, tension rope, check cable, pulley, capstan winch, clutch and group of motors, it is characterized in that by being arranged at runway underdeck coaxial electrical unit by clutch linkage capstan winch offer power, it is pulled through pulley and changes direction fold back traction strap on the runway of deck, traction power-assisted aircraft realizes the accelerator of taking off of aircraft, and the distance of its deck runway initial point to pulley is equal with the distance of deck lower sheave to capstan winch or approximates；Capstan winch is fixed in its traction strap one end, and the other end dissociates, and pile warp pulley break-in fold back is on the runway of deck, and end is arranged in the unidirectional fixing groove hook that bolt knot hangs on hook；Traction strap trend above deck is overlapping with the axis that takes off；Hook is triangular in shape, the most parallel with deck, arrange at anterior angle and tie, with traction strap bolt, the unidirectional fixing groove hook mated, lower end, front is with following front end axle even, upper end hook aircraft nose landing gear, back is the support bar having and launching damping, and the tension rope that relief angle gets loose with controlled specified pulling force is connected, and arranges the tension folder hook of clamping check cable below relief angle；Before check cable is for being arranged at pulley, edge, deck, with the strap of traction strap capwise；Pulley is installed on the runway end, and upper edge is slightly above deck level；Group of motors be coaxial, synchronize, be mounted opposite two set group of motors of rotating in same direction, middle linked with capstan winch by clutch.
Described deck start runway end lights is designed as the sliding seesaw that jumps of arc.
The compound electric unit power of the present invention turns strap towing aircraft ejector compared with prior art, have with low content of technology, application technology is ripe, simple in construction, easily fabricated, application cost is low, length in service life, the maintenance distinguishing feature such as easily, additionally has a following remarkable advantage:
1, using coaxial electrical unit to convert and provide kinetic energy, energy loss is low, modification scope amplitude is big.System designs, calculate, make and installation process is without important technical barrier.Compared with the ski-jump take-off mode fully relying on aircraft self power, provide powerful external power-assisted, compared with numerous and diverse, huge steam, electromagnetic ejection system, simple in construction, volume are little, lightweight, occupy little space, use, reseting procedure simply, applying frequency is high repeatedly, the maintenance time is short, service life is long.
2, drawn by the traction strap of pulley break-in opisthotonos, traction accelerator is made to separate with braking brake process direction, and process is apart from equal or similar, on the one hand braking brake process is made to be not take up the metric space of deck runway, make runway omnidistance for accelerator, extend the acceleration distance of the confined space.Another aspect extends braking brake distance, alleviates and decreases the braking inertia impact to related system at a high speed.
3, traction strap and hook towing aircraft on deck level is used to run, the traction groove of through whole process must be set above deck not necessarily like steam ejection or electromagnetic launch, maintain deck smooth completely, be greatly improved the bulk strength on deck, also improve simultaneously and facilitate deck comprehensively use function.
4, the setting of check cable makes hook i.e. depart from traction strap after completing distraction procedure, the kinetic energy making hook accumulate storage continues forward, check cable and antivibrator absorb release, make the inertia kinetic energy of traction strap be only limitted to sole mass, degree of safety is higher, and destructiveness is less.
5, the design of the sliding seesaw that jumps of runway end lights arc, double stored up the raising that the sliding formula of the jumping mode of taking off had and has departed the external power-assisted double dominant of height and catapult-assisted take-off, makes aircraft obtain bigger takeoff loads.
Thus, the compound electric unit power of the present invention turns strap towing aircraft ejector and has good practical value.
Four, accompanying drawing explanation:
Fig. 1 is the side generalized section that compound electric unit power turns strap towing aircraft ejector.
Fig. 2 is the deck part plan schematic diagram that compound electric unit power turns strap towing aircraft ejector.
Fig. 3 is that compound electric unit power turns the group of motors of strap towing aircraft ejector and arranges floor map.
In figure: 1 deck, 2 take off axis, 3 traction strap, 4 hooks, 5 tension ropes, 6 hook check cables, 7 pulleys, 8 capstan winches, 9 clutches, 10 group of motors.
Five, detailed description of the invention:
In conjunction with Figure of description, the compound electric unit power of the present invention is turned strap towing aircraft ejector to make to illustrate in further detail below:
As shown in Figure 2, arc is set in axis 2 front end of taking off on the most smooth deck 1 and is slightly above the pulley 7 of deck 1 plane, edge, deck 1 before pulley 7 arranges the lateral traction hook check cable 6 vertical with the axis 2 that takes off, and the two ends of hook check cable 6 are connected on the antivibrator that is fixedly installed.The traction strap 3 trend on deck 1 is overlapping with the axis that takes off, and end arranges the bolt knot matched with hook.Initiating terminal at the axis 2 that takes off arranges the tension rope 5 that specified pulling force forward gets loose, hook 4 front is inverted T shape, side is triangular in shape, the long limit of triangle is lower and equipped with pulley, the groove mounting with traction strap 3 end bolt knot tool directivity and departing from anterior angle, the hook arranging controlled tension opening and closing at relief angle mounts with tension rope 5, arranges the grab of hook check cable below relief angle；Front hypotenuse with at anterior angle for axle can swing, top is provided with the drag hook worrying aircraft, and rear hypotenuse is the steady arm with elastic damping effect.
As shown in Figure 1: the traction strap 3 being fixed on capstan winch 8 lays belowdecks, pile warp pulley 7 fold back is laid on the taking off on axis 2 of deck 1.
As shown in Figure 3: the concentric large-size machine group of left and right two row 10 drives capstan winch 8 to operate by clutch.
During use, lay traction strap 3 on the axis 2 that takes off, front keratotic plug suspension towing hook 4, rear keratotic plug hang tension rope 5, upper angle hook aircraft nose landing gear, starting group of motors 10, close clutch 9, traction strap 3 produces tension, after tension reaches rating number, tension rope 5 gets loose, hook 4 pulls aircraft to move ahead acceleration, and after reaching to take off speed, aircraft draws high and separates with hook 4.Hook 4 walks at pulley 7, and traction strap 3 separates with hook 4 because of break-in, and hook 4 moves ahead and fixed deceleration by hook check cable 6 and fall, and clutch 9 separates simultaneously, and the movement system such as group of motors 10 and traction strap 3 enters braking brake.Reclaim hook 4 and overhaul.System enters next round and lets process fly away.
In addition to the technical characteristic described in description, remaining is oneself of those skilled in the art and knows technology.
Claims (2)
1. compound electric unit power turns a strap towing aircraft ejector, including traction strap, traction
Hook, tension rope, check cable, pulley, capstan winch, clutch and group of motors, is characterized in that by being arranged at runway
Underdeck coaxial electrical unit provides power by clutch linkage capstan winch, is pulled through pulley change direction and returns
Rolling over the traction strap on the runway of deck, traction power-assisted aircraft realizes the accelerator of taking off of aircraft, its deck
Runway initial point is equal with the distance of deck lower sheave to capstan winch to the distance of pulley or approximation；It draws strap one
End is fixed on capstan winch, and the other end dissociates, and pile warp pulley break-in fold back is on the runway of deck, and end arranges bolt knot
Hang in the unidirectional fixing groove hook of hook；Traction strap trend above deck is overlapping with the axis that takes off；
Hook is triangular in shape, the most parallel with deck, arranges unidirectional solid with what traction strap bolt knot mated at anterior angle
Determining groove hook, lower end, front with following front end axle even, upper end hook aircraft nose landing gear, launch for having by back
The support bar of damping, the tension rope that relief angle gets loose with controlled specified pulling force is connected, and arranges folder below relief angle
Gu the tension folder hook of check cable；Before check cable is for being arranged at pulley, edge, deck, with traction strap vertical walk
To strap；Pulley is installed on the runway end, and upper edge is slightly above deck level；Group of motors be coaxial, synchronize,
Be mounted opposite two set group of motors of rotating in same direction, the middle clutch that passes through links with capstan winch.
Compound electric unit power the most according to claim 1 turns strap towing aircraft ejector, its
Feature is that deck start runway end lights is designed as the sliding seesaw that jumps of arc.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410775451.2A CN104494841B (en) | 2014-12-16 | 2014-12-16 | Compound electric unit power turns strap towing aircraft ejector |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410775451.2A CN104494841B (en) | 2014-12-16 | 2014-12-16 | Compound electric unit power turns strap towing aircraft ejector |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104494841A CN104494841A (en) | 2015-04-08 |
| CN104494841B true CN104494841B (en) | 2016-10-12 |
Family
ID=52936327
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410775451.2A Active CN104494841B (en) | 2014-12-16 | 2014-12-16 | Compound electric unit power turns strap towing aircraft ejector |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104494841B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110182377B (en) * | 2019-05-06 | 2022-11-15 | 沈观清 | Winglet-loaded large-scale unmanned plane traction takeoff system and method |
| CN115871948B (en) * | 2023-02-17 | 2023-06-06 | 秦皇岛优益创联特种车辆制造有限公司 | Motor aircraft runway |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB302945A (en) * | 1926-10-05 | 1927-12-23 | Peter Regan | Apparatus for launching aircraft |
| RU2159200C2 (en) * | 1995-10-18 | 2000-11-20 | Инофирма Дассо Авиасьон | Absorber of catapult escape shock wave |
| CN102020021A (en) * | 2011-01-04 | 2011-04-20 | 贾正跃 | Reverse pulling and prompt release assisted takeoff method for realizing short-range take-off of aircraft carrier-based plane |
| CN102267571A (en) * | 2011-06-03 | 2011-12-07 | 清华大学 | Spring-pulley combined unmanned aerial vehicle ejector |
| CN103863571A (en) * | 2012-12-12 | 2014-06-18 | 中航商用航空发动机有限责任公司 | Aircraft catapulting device and aircraft catapulting method |
-
2014
- 2014-12-16 CN CN201410775451.2A patent/CN104494841B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB302945A (en) * | 1926-10-05 | 1927-12-23 | Peter Regan | Apparatus for launching aircraft |
| RU2159200C2 (en) * | 1995-10-18 | 2000-11-20 | Инофирма Дассо Авиасьон | Absorber of catapult escape shock wave |
| CN102020021A (en) * | 2011-01-04 | 2011-04-20 | 贾正跃 | Reverse pulling and prompt release assisted takeoff method for realizing short-range take-off of aircraft carrier-based plane |
| CN102267571A (en) * | 2011-06-03 | 2011-12-07 | 清华大学 | Spring-pulley combined unmanned aerial vehicle ejector |
| CN103863571A (en) * | 2012-12-12 | 2014-06-18 | 中航商用航空发动机有限责任公司 | Aircraft catapulting device and aircraft catapulting method |
Non-Patent Citations (1)
| Title |
|---|
| 舰载机的电磁弹射器设计探讨;王福金等;《电子工业专用设备》;20090930(第179期);第59-64页 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN104494841A (en) | 2015-04-08 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN201927943U (en) | Onboard electric stringing device for unmanned air vehicle | |
| CN104401493A (en) | Cabin type guide rope locked aircraft carrier for releasing and recycling airborne aircraft | |
| CN107265329A (en) | A kind of special guide pulley of unmanned plane | |
| CN104494841B (en) | Compound electric unit power turns strap towing aircraft ejector | |
| CN209776830U (en) | Vehicle-mounted take-off device of unmanned aerial vehicle with parallelogram structure | |
| CN102627245B (en) | Foldable square cabin lifting device | |
| CN103212171A (en) | Intelligent traction type throwing device of forest fire fighting bomb | |
| CN104129506A (en) | Shipboard aircraft spring catapult | |
| CN104548419B (en) | Runner type bomb launching device | |
| CN103241667A (en) | Tower crane worker climbing safety device | |
| RU2592963C2 (en) | Method for parachute landing of drone and drone with electric propulsor and parachute landing system | |
| CN102951297B (en) | Device for realizing high-speed take-off of shipboard aircraft by spring combination mechanical ejection | |
| CN110182377B (en) | Winglet-loaded large-scale unmanned plane traction takeoff system and method | |
| CN107804457B (en) | Parafoil rope protection device for parafoil unmanned aerial vehicle | |
| CN202988602U (en) | Hawser type derrick crane | |
| CN103465933B (en) | A kind of passive automatic energy-absorbing winch and braking method thereof | |
| CN203269422U (en) | Safe device for climbing by tower crane workers | |
| CN105946819B (en) | Pulling formula complemental brake system and apply its automobile | |
| CN207142720U (en) | A kind of unmanned plane special guide pulley and its jettison system | |
| CN203428043U (en) | Assisting system for short takeoff of carrier-borne aircrafts | |
| CN203996919U (en) | A kind of carrier-borne aircraft spring catapult | |
| CN207782288U (en) | Sliding equipment applied to unmanned plane | |
| CN203728459U (en) | Traction device | |
| CN203865930U (en) | Cable cover plate lifting device | |
| CN202988610U (en) | Mooring rope type mast crane |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20191205 Address after: 221000 No.1, Zhangjiagang East Road, Yitang Town, Pizhou City, Xuzhou City, Jiangsu Province Patentee after: Pizhou Binhe SME Management Service Co., Ltd. Address before: 250013 Shandong Province, Lixia District of Ji'nan City Luo River District No. 8 unit 4, Room 301 Patentee before: Dong Lantian |