CN201816739U - Hydraulic power hinge connecting rod type aircraft catapult - Google Patents
Hydraulic power hinge connecting rod type aircraft catapult Download PDFInfo
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- CN201816739U CN201816739U CN2010202677112U CN201020267711U CN201816739U CN 201816739 U CN201816739 U CN 201816739U CN 2010202677112 U CN2010202677112 U CN 2010202677112U CN 201020267711 U CN201020267711 U CN 201020267711U CN 201816739 U CN201816739 U CN 201816739U
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- 230000009347 mechanical transmission Effects 0.000 claims abstract description 5
- 239000003921 oil Substances 0.000 claims description 44
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- 230000002706 hydrostatic effect Effects 0.000 claims description 3
- 238000000034 method Methods 0.000 abstract description 5
- 230000008569 process Effects 0.000 abstract description 3
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- 238000010276 construction Methods 0.000 abstract description 2
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- 230000009191 jumping Effects 0.000 description 6
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- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 description 4
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- 238000002485 combustion reaction Methods 0.000 description 1
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- 238000004590 computer program Methods 0.000 description 1
- 238000011033 desalting Methods 0.000 description 1
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- 230000006872 improvement Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
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- 238000003466 welding Methods 0.000 description 1
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Abstract
The utility model relates to a hydraulic hinge connecting rod type aircraft catapult consisting of a hydraulic power part, a mechanical transmission part and an engine base. A hydraulic transmission part consists of five high-pressure oil cylinders; a hinge structure is adopted among all connecting rods (5) of a hinge connecting rod type structure; a guide rod (8) is arranged transversely in front of an engine base (1); hinging lug bases (9) are respectively arranged at two ends of the guide rod (8), and can slide along the guide rod (8); the purpose of ejecting an aircraft is achieved by adopting the five high-pressure oil cylinders to drive the hinge connecting rod type structure. In the catapult, the volume is small, the space occupied on a naval vessel is small, and the efficiency is high. The catapult provides ideal driving force and injection force for the launching of various types of aircrafts; the driving force is large, thus providing possibility for the launching of heavy aircraft on an aircraft carrier; and the process is simple, the construction cost is low, and the invaluable fresh water resource can not be consumed during the sea trip.
Description
Technical field
The utility model relates to the aircraft ejection kit of aircraft carrier, especially relates to the aircraft catapult that utilizes hydraulic power and link-hinge-type mechanical device.
Background technology
At present, the fixed-wing carrier-borne aircraft of aircraft carrier has two kinds of modes of taking off from carrier-based, and a kind of is that sliding jumping up flies, and a kind of is catapult-assisted take-off.Because political and military, blockade on new techniques is carried out before to the China and the Soviet Union in the west, and the former Soviet Union or Russia use the sliding formula of jumping to play sudden alternative steam catapult when the development aircraft carrier.Can substitute ejector though use the sliding formula of jumping to take off, according to reports, carrier-borne aircraft Soviet Union sliding the jumping up of-33 usefulness flies, having the load that to hang under 60% the fuel condition about 2 tons, if use ejector just can make the plug-in ability of Soviet Union-33 under full oil condition, bring up to 6 tons, wait whole operational performances that can give full play of by this as heavy weight fighter.
Use catapult-launching gear, the carrier-borne aircraft that takes off from aircraft carrier relies on the steam ejector to obtain an initial acceleration, thereby is issued to enough takeoff speeds in the limited condition of ground run distance.Catapult-assisted take-off flies to compare with sliding jumping up, the catapult-assisted take-off large-scale early warning plane that can take off, and heavy weight fighter can be expired oily high gross weight takeoff: because of catapult-assisted take-off can reduce the oil consumption of taking off, thereby increased early warning range and combat radius.The sliding formula of the jumping large-scale early warning plane that can not take off that takes off, and since heavy weight fighter when taking off bullet-loading capacity and fuel load be restricted, consumption of fuel is big when taking off, thereby has influenced fighting effect greatly.
The steam ejector is one of visual plant of present large-scale through type aircraft carrier, and an ejector per minute can launch two carrier-borne aircrafts.The steam ejector has high reliability, up to now, does not have airplane fault because of device proper in nearly ten million time catapult-assisted take-off to meet accident.
But, though the steam ejector has above-mentioned advantage, but its complex structure, the steam ejector is made up of external equipment and ejection machine and control system, and external equipment comprises: devices such as desalting plant, hydraulic accumulator, high-pressure hydraulic pump, high-pressure pump, high pressure tank, ventilation flue, operated pneumatic valve, safety valve, ejection valve, gas line and boiler; Ejection machine comprises: open cylinder, piston, sealing arrangement, sealing cutter, transmission arm, tow rope, reciprocal cable wire, dead sheave, directive slide track etc.; Control system has: pressure sensor, temperature sensor, position transduser and computer system etc. constitute complete ejector system.It relates to multi-field technology: metal smelt technology, metalworking technology, welding technique, computer software control technology and field engineering etc.Require all very highly from design to installation, what especially the steam ejector adopted is open cylinder, its maximum difficult point be piston in the open cylinder motion, the sealing problem of sealing cutter during through opening.If the big more sealing of the sealing intensity of sealing band is good more, the resistance that petty sealing cutter is subjected to is just big more, and the wearing and tearing of sealing band are also fast more, therefore, cause gas leakage, lowers efficiency, and it is said that the efficient of steam ejector only can reach about 5%.
It is the direction that China naval develops in the future to a certain extent that China builds aircraft carrier voluntarily.From world wide, it is extremely challenging making a strong aircraft-carrier battle group.Technology such as the steam ejector of indispensability, carrier-borne aircraft, check cable, large-scale elevator are all grasped in America and Europe and even the U.S.'s one tame hand on the aircraft carrier, and also can not have any country to sell Chinese advanced military technology abroad, the following construction of Chinese Navy aircraft carrier need solve the problem of ejector, do not solve and handle well if this problem Chinese Navy is not made great efforts, progress that petty following aircraft carrier that will directly influence Chinese Navy is built and Chinese Navy blue-water capable fleet establish an army the time.
Summary of the invention
The purpose of this utility model is to overcome the vice proper of steam catapult, and the idea that the steam that discards tradition launches proposes a kind of employing hydraulic pressure and Pneumatic pressure power, utilize the mechanical lever action principle, implementation structure is simple, and ejection force is big, the aircraft catapult that efficient is high.
For realizing the purpose of this utility model, adopt a kind of aircraft catapult utilizing hydraulic power and hinge connecting rod structure, this ejector is made of hydraulic power partial sum mechanical driving part and support.
Described hydrostatic drive part is made of 5 high-voltage oil cylinders, is respectively the vertical oil cylinder 3 with 2 of 4,2 cross cylinders 2 of 1 load-bearing seat oil cylinder, and described load-bearing seat oil cylinder 4 is installed in the center-point of support 1, and 2 cross cylinders 2 are installed in support 1 two ends sidewall respectively;
Described mechanical transmission structure is the hinge connecting rod structure, is fixed on the support 1, adopts articulated structure between each connecting rod 5 of described hinge connecting rod structure;
Described support 1 the place ahead is horizontally installed with pilot bar 8) described pilot bar 8 two ends are provided with hinge ear seat 9 respectively, and described hinge ear seat 9 can slide along pilot bar 8;
Wherein, the point articulated piston rod and the first hinge-point A fixing and load-bearing seat oil cylinder 4 of the load-bearing seat 10 at support 1 center and the second hinge-point B is point articulated; About hinge ear seat 9 be articulated in the 5th hinge-point D, the 6th hinge-point D ' point with connecting rod 5 respectively, about the mount pad of vertical oil cylinder 3 point articulated with the 3rd hinge-point C, the 4th hinge-point C ' of connecting rod 5 respectively, the cross cylinder 2 on the left side is fixed on the hinge ear seat 9 on the left side with the piston rod of vertical oil cylinder 3, the cross cylinder 2 on the right and the piston rod of vertical oil cylinder 3 are fixed on the hinge ear seat 9 on the right, the 7th hinge-point E that is positioned at the top articulates the front-wheel hook of towing aircraft as thrust point 7.
Adopt 320kg/cm
2-210kg/cm
2High pressure gear oil pump, 30 centimetres of the diameter of pistons of cross cylinder 2, piston rod thrust is 226 tons-148 tons, the 7 traction thrusts that are in farthest in short-term are 160 tons in the thrust point, relative 30 tons airplane thrust weight ratio 5.3: 1,60 tons of airplane thrust weight ratios 2.6: 1.
According to another embodiment of the present utility model, described 2 cross cylinders 2 are hinged on the two ends of support 1, its structure enables to swing on the horizontal surface of support 1, the piston rod of cross cylinder 2 and hinged from the connecting rod 5 of the 5th hinge-point D extension, along with moving of hinge ear seat 9, cross cylinder 2 counter-clockwise swings, piston rod and connecting rod 5 remain plumbness.
Ejector volume of the present utility model is little, and the space that takies naval vessels is little, the efficient height.Be various types of propelling thrust and the ejection forces that provide desirable of taking off on the aircraft carrier; Thrust is big, provides possibility for heavy airplane takes off on aircraft carrier; Technology is simple, and cost is low, does not consume the naval vessels very valuable freshwater resources that ride the sea.
Description of drawings
Fig. 1 is an ejector structural representation of the present utility model;
Fig. 2 shows that ejector of the present utility model ejects view;
Fig. 3 is an ejector hydraulic tubing scheme drawing;
The another kind of mounting means of Fig. 4 cross cylinder is at the position view of initial condition;
Fig. 5 is the position view of the another kind of mounting means of cross cylinder in ejection status.
Among the figure
1 support, 12 gear type pumps
2 cross cylinders, 13 electrical motors
3 vertical oil cylinder 14 compression indicators
4 load-bearing seat oil cylinders, 15 electric liquid variable pressure regulating valves
5 connecting rods, 16 electromagnetic relief valves
6 load-bearing seats, 17 pressure petrol storage tanks
7 thrust points, 18 load-bearing seat oil cylinder control cock
8 pilot bars, 19 vertical oil cylinder control cock
9 hinge ear seats, 20 cross cylinder control cock
10 load-bearing seats, 21 petrol storage tanks
11 fils
The specific embodiment
For making the purpose of this utility model, technical scheme and advantage clearer,, the utility model is further described below in conjunction with specific embodiment.
The utility model is a kind of quick ejector that utilizes hydraulic power, its mechanical transmission structure adopts hinge connecting rod mechanism, the mechanical transmission structure of this ejector is fixed on the support 1, the hydrostatic drive part is made of 5 high-voltage oil cylinders, be respectively 1 load-bearing seat oil cylinder 4,2 vertical oil cylinders 3 with 2 of cross cylinder 2 adopt articulated structure between each connecting rod 5 of hinge connecting rod structure.Load-bearing seat oil cylinder 4 the place aheads are horizontally installed with pilot bar 8, and pilot bar 8 two ends are provided with hinge ear seat 9 respectively, and hinge ear seat 9 can slide along pilot bar 8.
Load-bearing seat oil cylinder 4 is installed in the center-point of support 1, and 2 cross cylinders 2 are installed in support 1 two ends sidewall respectively.According to the utility model, in whole hinge-points of hinge connecting rod mechanism, 7 key points are arranged, be respectively two some A, the B of the below that is in the middle of the connecting rod mechanism and the some E of the top, be positioned at the connecting rod mechanism left side two some C, D of below, be positioned at the right two some C ', D ' of below, wherein, the load-bearing seat 10 at B point and support 1 center is connected and fixed, and the piston rod of A point and load-bearing seat oil cylinder 4 is hinged; D, D ' point respectively with about hinge ear seat 9 hinged, C, C ' respectively with about the mount pad of vertical oil cylinder 3 hinged.The cross cylinder 2 on the left side is fixed on the hinge ear seat 9 on the left side with the piston rod of vertical oil cylinder 3, the cross cylinder 2 on the right and the piston rod of vertical oil cylinder 3 are fixed on the hinge ear seat 9 on the right, the point E point that is positioned at the top articulates the front-wheel hook of towing aircraft as thrust point 7.
Fig. 3 is an ejector hydraulic tubing scheme drawing; By motor or combustion engine is that drive power source oil pump (big discharge capacity geared oil pump) extracts hydraulic oil from fuel tank, filter through fil, be pressed into working connection, split time and distance by computer control ejection process, required system pressure is by electric liquid variable pressure regulating valve and the interactive regulation and control of electromagnetic relief valve, hydraulic oil enters compressed nitrogen behind the pressure petrol storage tank, increases oil reserve.During ejector work, open load-bearing seat oil cylinder 4 by computer instruction, cross cylinder 3 and vertical oil cylinder 2, then, by the effect of solenoid directional control valve, whole ejector is finished a working cycle.
In conjunction with the accompanying drawings 1,2 and 3, illustrate that the principle of work of ejector of the present utility model is as follows:
Open distributing valve shown in Figure 3, hydraulic oil enters the vertical oil cylinder 3 with 2 of 4,2 cross cylinders 2 of load-bearing seat oil cylinder rapidly under the effect of high pressure nitrogen, promotes separately piston and piston rod movement.For load-bearing seat oil cylinder 4, because the B point is fixing, the A point forwards slides under load-bearing seat oil cylinder 4 promotes; Simultaneously, about hinge ear seat 9 respectively under the promotion of 2 cross cylinders 2 to the central slide of support 1, drive D and D ' point and move to the center of support 1,2 vertical oil cylinders 3 move up respectively; 2 vertical oil cylinders 3 and about under the combined action of hinge ear seat 9, C and C ' point move up in vertical direction respectively when move at the center.The motion of above-mentioned hinge-point changes the angle between the hinge connecting rod, and two angles are by diminishing gradually greater than 90 ° up and down, about two angles by becoming big gradually less than 90 °, whole hinge connecting rod finally forms state shown in Figure 2 by state shown in Figure 1.
7 the state analysis from the thrust point, because the variation of angle between the connecting rod, the thrust that thrust point 7 is subjected to is descending progressively to be changed, simultaneously, the speed that thrust point 7 moves forward is progressively accelerated again from slow to fast, and the aircraft safety that is articulated in thrust point 7 is launched lift-off.。
The maximum thrust of thrust point 7 can reach single oil cylinder 2 or single oil cylinder 4 piston rod thrusts about 1.5 times, electric liquid variable pressure regulating valve by computer program controlled hydraulic efficiency pressure system, by pass valve, bidirectional throttling valve etc., the piston rod thrust and the speed of 5 hydraulic rams of regulation and control, the aircraft that can finish various weight (20 tons-60 tons) takes off on 100 meters deck.
The parameter setting of hydraulic efficiency pressure system: adopt big discharge capacity high pressure gear oil pump (320kg/cm
2-210kg/cm
2), 30 centimetres of the diameter of pistons of cross cylinder 2, piston rod thrust can reach 226 tons-148 tons, and traction thrust reaches about 160 tons, relative 30 tons airplane thrust weight ratio 5.3: 1,60 tons of airplane thrust weight ratios 2.6: 1.
Fig. 4 and Fig. 5 are the embodiment of the utility model cross cylinder 2 another kind of mounting meanss, show initial condition and ejection status.The piston rod of analysis level fuel tank 2 is to the application force of connecting rod, when starting, hinge ear seat 9 is positioned at the position of two ends distance center distal-most end, piston rod and connecting rod have certain included angle, angle during startup is than minimum, piston rod is to the component minimum on the connecting rod vertical direction, and along with hinge ear seat 9 moves to the center, piston rod just strengthens gradually to the component on the connecting rod vertical direction.At present embodiment, horizontal fuel tank 2 is articulated in the two side of support 1, the piston rod of horizontal fuel tank 2 and the rod hinge connection that extends from the D point, like this, in entire work process, along with the gathering of connecting rod, horizontal fuel tank 2 is done counter-clockwise swing, make piston rod keep vertical with connecting rod all the time,, make this connecting rod be in the maximum weighted state all the time by the effect of lever.
Ejector of the present utility model can be widely used in lade, is used for impelling material etc. when implementing flood control.
More than aircraft catapult utilizing hydraulic power and hinge connecting rod structure provided by the utility model is described in detail, used specific embodiment herein principle of the present utility model and embodiment set forth.
Described specific embodiment; the purpose of this utility model, technical scheme and beneficial effect have been carried out further detailed description; institute is understood that; the above only is a specific embodiment of the utility model; be not limited to the utility model; all within spirit of the present utility model and principle, any modification of being made, be equal to replacement, improvement etc., all should be included within the protection domain of the present utility model.
Claims (3)
1. aircraft catapult utilizing hydraulic power and hinge connecting rod structure, this ejector is made of hydraulic power partial sum mechanical driving part and support, it is characterized in that,
Described hydrostatic drive part is made of 5 high-voltage oil cylinders, be respectively 1 load-bearing seat oil cylinder (4), 2 cross cylinders (2) are installed in the center-point of support 1 with 2 vertical oil cylinders (3), described load-bearing seat oil cylinder (4), and 2 cross cylinders (2) are installed in support 1 two ends sidewall respectively;
Described mechanical transmission structure is the hinge connecting rod structure, is fixed on the support (1), adopts articulated structure between each connecting rod (5) of described hinge connecting rod structure;
Described support (1) the place ahead is horizontally installed with pilot bar (8), and described pilot bar (8) two ends are provided with hinge ear seat (9) respectively, and described hinge ear seat (9) can slide along pilot bar (8);
Wherein, the load-bearing seat (10) at support (1) center is hinged with the piston rod and first hinge-point (A) of second hinge-point (B) hinged securement and load-bearing seat oil cylinder (4); About hinge ear seat (9) respectively and connecting rod (5) be articulated in the 5th hinge-point (D), the 6th hinge-point (D '), about vertical oil cylinder (3) mount pad respectively and the 3rd hinge-point (C) of connecting rod (5), the 4th hinge-point (C ') hinged, the piston rod of cross cylinder on the left side (2) and vertical oil cylinder (3) is fixed on the hinge ear seat (9) on the left side, the cross cylinder (2) on the right and the piston rod of vertical oil cylinder (3) are fixed on the hinge ear seat (9) on the right, the 7th hinge-point (E) that is positioned at the top articulates the front-wheel hook of towing aircraft as thrust point (7).
2. aircraft catapult according to claim 1 is characterized in that, adopts 320kg/cm
2-210kg/cm
2High pressure gear oil pump, 30 centimetres of the diameter of pistons of cross cylinder (2), piston rod thrust is 226 tons-148 tons, (7) to be in farthest traction thrust in short-term be 160 tons in the thrust point, relative 30 tons airplane thrust weight ratio 5.3: 1,60 tons of airplane thrust weight ratios 2.6: 1.
3. aircraft catapult according to claim 1, it is characterized in that, described 2 cross cylinders (2) are hinged on the two ends of support (1), its structure enables to swing on the horizontal surface of support (1), the piston rod of cross cylinder (2) and hinged from the connecting rod (5) of the 5th hinge-point (D) extension, along with moving of hinge ear seat (9), cross cylinder (2) counter-clockwise swing, piston rod and connecting rod (5) remain plumbness.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010202677112U CN201816739U (en) | 2010-07-22 | 2010-07-22 | Hydraulic power hinge connecting rod type aircraft catapult |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010202677112U CN201816739U (en) | 2010-07-22 | 2010-07-22 | Hydraulic power hinge connecting rod type aircraft catapult |
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| Publication Number | Publication Date |
|---|---|
| CN201816739U true CN201816739U (en) | 2011-05-04 |
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ID=43914703
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2010202677112U Expired - Fee Related CN201816739U (en) | 2010-07-22 | 2010-07-22 | Hydraulic power hinge connecting rod type aircraft catapult |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN201816739U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103213688A (en) * | 2013-04-30 | 2013-07-24 | 张春平 | Shipboard aircraft ejector |
| CN103604619A (en) * | 2013-11-21 | 2014-02-26 | 南京航空航天大学 | Front undercarriage static force test loading device for frame-type catapult-assisted take-off shipboard aircraft |
| CN105480721A (en) * | 2015-12-15 | 2016-04-13 | 桐乡市濮院毛针织技术服务中心 | Material throwing device |
-
2010
- 2010-07-22 CN CN2010202677112U patent/CN201816739U/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103213688A (en) * | 2013-04-30 | 2013-07-24 | 张春平 | Shipboard aircraft ejector |
| CN103604619A (en) * | 2013-11-21 | 2014-02-26 | 南京航空航天大学 | Front undercarriage static force test loading device for frame-type catapult-assisted take-off shipboard aircraft |
| CN103604619B (en) * | 2013-11-21 | 2016-01-20 | 南京航空航天大学 | Frame-type catapult-assisted take-off carrier-borne aircraft nose-gear slow test charger |
| CN105480721A (en) * | 2015-12-15 | 2016-04-13 | 桐乡市濮院毛针织技术服务中心 | Material throwing device |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| 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: 20110504 Termination date: 20160722 |