CN206606366U - The device of two-level spring joint ejection carrier-borne aircraft - Google Patents
The device of two-level spring joint ejection carrier-borne aircraft Download PDFInfo
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- CN206606366U CN206606366U CN201720351533.3U CN201720351533U CN206606366U CN 206606366 U CN206606366 U CN 206606366U CN 201720351533 U CN201720351533 U CN 201720351533U CN 206606366 U CN206606366 U CN 206606366U
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- spring
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- ejection
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Abstract
It can ensure device of the carrier-borne aircraft from the two-level spring joint ejection carrier-borne aircraft of warship speed again the utility model discloses a kind of peak ejection acceleration that can limit.Device includes bounce-back beam, brake, rebound beam, spring groove is set between brake, a piece one-level ejection-spring and two two grades of ejection-springs are installed in spring groove, linked between one-level ejection-spring and two two grades of ejection-springs by linkage rack formation, the linkage rack includes the first concave shaped portion and two second concave shaped portions, first concave shaped portion nesting one-level ejection-spring bottom, the top of second concave shaped portion, two grades of ejection-springs of nesting, top plate is set at the top of one-level ejection-spring, the first cable wire is connected between top plate and bounce-back beam, the second cable wire is connected between second concave shaped portion and bounce-back beam, first cable wire, electromagnet disconnection device is set on second cable wire respectively, first hoist is set on bounce-back beam, second hoist, first hoist is connected with the first cable wire, second hoist is connected with the second cable wire.
Description
Technical field
The utility model belongs in Technologies of Shipboard Plane Taking Off field, and in particular to a kind of two-level spring joint ejection carrier-borne aircraft
Device.
Background technology
Carrier-borne aircraft from warship mode mainly include ski-jump take-off and ejection, ejection with ski-jump take-off compared with have significantly make
Main on war advantage, current aircraft carrier to use steam ejection and electromagnetic launch, steam ejection use cost is high, to seal
Performance requirement under material at high temperature high pressure is high, and current China does not grasp the technology also completely.Electromagnetic launch technical sophistication, although
Initial success has been obtained in the model test that naval engineering university Ma Weiming academician dominates, but real warship real machine effect is also to be tested
Card.Compared with steam ejection, spring ejection has the advantages that use cost is low, not high to apparatus and process and material performance requirement,
Compared with electromagnetic launch, spring ejection have the advantages that technology simply, low cost, power consumption be small, performance is stable.Spring is launched most
Main problem is that ejection acceleration at initial stage is too high, pilot, which occurs, to faint, and later stage acceleration is too low, and carrier-borne aircraft is from warship speed
Degree is unsatisfactory for requiring.
Utility model content
The purpose of this utility model is to overcome the shortcomings of that current carrier-borne aircraft ejection mode is combined there is provided a kind of two-level spring
The device of carrier-borne aircraft is launched, with the utility model device, carrier-borne aircraft is launched stage by stage by two grades, ejection can be limited and accelerated
Spend peak value, it is ensured that the physical safety of pilot, can ensure that carrier-borne aircraft meets flight from warship speed and required again；Meanwhile, this practicality
New device structures are simple, and ejection travel is short, and performance is stable, it is possible to achieve quick continuous ejection, use cost and maintenance cost
It is low.
What the purpose of this utility model was realized in：
A kind of device of two-level spring joint ejection carrier-borne aircraft, including bounce-back beam, brake, between bounce-back beam, brake
Set and axially slidable ejection-spring is installed in the spring groove perpendicular to bounce-back beam, spring groove, the brake is used for bullet
Penetrate spring braking, the ejection-spring includes an one-level ejection-spring and is symmetrically set in two of one-level ejection-spring both sides
Two grades of ejection-springs, are linked between the one-level ejection-spring and two two grades of ejection-springs by linkage rack formation, described
Moving frame includes the first concave shaped portion and two second concave shaped portions, and first concave shaped portion is nested in one-level ejection-spring bottom, described
Two second concave shaped portions are respectively nested in the top of two two grades of ejection-springs, and the top of the one-level ejection-spring sets top plate,
Connected between the top plate and bounce-back beam and the first electromagnet disconnection device, the linkage are set on the first cable wire, first cable wire
Connected between two second concave shaped portions and bounce-back beam of frame and the second electromagnet disconnection device be set on the second cable wire, second cable wire,
First hoist, second hoist are set on the bounce-back beam, and the first hoist is connected with the first cable wire, the volume Two
Machine is raised to be connected with the second cable wire.
Further, the spring groove includes an one-level spring groove and two two-level spring grooves, the one-level spring
Groove is used to install one-level spring, and described two two-level spring grooves are used to installing two two-level springs, the one-level spring groove and
The cross section of two two-level spring grooves is the semicircle to lower recess, and the linkage rack is located at one-level spring groove, two-level spring groove
On.
Further, the one-level spring, two-level spring use hollow spring.
Further, the brake is stopped device using oil, and the brake is used to brake one-level ejection-spring.
By adopting the above-described technical solution, the utility model has the advantages that：
Ejection-spring by one-level, two grades totally three springs constitute, one-level spring is larger spring, two-level spring bag
Containing two less springs, point row one-level spring both sides, the bottom surface of one-level spring is connected with the top surface of two-level spring by linkage rack.
Hoist engine is respectively adopted by cable wire compression spring, during ejection, first bounce is provided by one-level spring, when one-level springback power
Certain phase is discharged into, two-level spring continues to provide bounce.The utility model launches carrier-borne aircraft by two-stage spring, limits
Carrier-borne aircraft launches the acceleration at initial stage, prevents pilot from fainting, while in turn ensure that later stage acceleration, makes carrier-borne aircraft from warship
Speed, which is met, to be required.
Brief description of the drawings
Fig. 1 is plan of the utility model when launching；
Fig. 2 is plan when the utility model ejection is finished；
Fig. 3 is the profile of each ejection status of the utility model；
Reference
1 one-level spring, 2 two-level springs, 3 one-level spring grooves, 4 one-level spring top plates, 5 first electromagnet disconnection device, 6 first
Cable wire, 7 bounce-back beams, 8 first hoist, 9 two-level spring grooves, 10 linkage racks, 11 second electromagnet disconnection device, 12 second cable wires,
13 second hoist, 14 brakes.
Embodiment
It is that a kind of two-level spring joint launches the device of carrier-borne aircraft referring to Fig. 1 to Fig. 3, including rebound beam, brake, instead
Play and axially slidable ejection-spring is installed in the spring groove set between beam, brake perpendicular to bounce-back beam, spring groove, it is described
Brake is used to brake ejection-spring, and the ejection-spring includes an one-level ejection-spring and is symmetrically set in one-level ejection
Two two grades of ejection-springs of spring both sides, the equal on-fixed of I and II spring basal surface position, bounce release, which is finished, may exit off
Rebound beam.By calculating contrast, the one-level spring, two-level spring use hollow spring, i.e. spring by the steel of certain wall thickness
Pipe coiling is formed, and 40% or so spring-mass can not only be reduced by so doing, moreover it is possible to increase the driving velocity of carrier-borne aircraft.It is described
Linked between one-level ejection-spring and two two grades of ejection-springs by linkage rack formation.
The linkage rack includes the first concave shaped portion and two second concave shaped portions, and first concave shaped portion is nested in one-level ejection
Spring bottom, two second concave shaped portion is respectively nested in the top of two two grades of ejection-springs, and the spring groove includes one
One-level spring groove and two two-level spring grooves, the one-level spring groove are used to install one-level spring, described two two-level springs
Groove is used to install two two-level springs, and the cross section of the one-level spring groove and two two-level spring grooves is half to lower recess
Circle, the linkage rack is on one-level spring groove, two-level spring groove.
The top of the one-level ejection-spring sets top plate, and the first cable wire is connected between the top plate and bounce-back beam, described
First electromagnet disconnection device is set on the first cable wire, the second steel is connected between two second concave shaped portions and bounce-back beam of the linkage rack
The second electromagnet disconnection device is set on rope, second cable wire, electromagnet disconnection device utilizes electromagnetic principle, connected during energization, stopped
Disconnected when electric.In the present embodiment, a magnetic suck end of each electromagnet disconnection device is fixed on correspondence cable wire, another magnetic suck end
It is fixed on top plate or linkage rack.First hoist, second hoist, the first hoist and the are set on the bounce-back beam
One cable wire is connected, and the second hoist is connected with the second cable wire.The brake is stopped device using oil, and the brake is used for pair
One-level ejection-spring is braked, and replaces conventional water to stop device with oil device of stopping, that is, stop fast container content is hydraulic oil.
Preferably, the bounce-back beam is provided with the telescopic bracket (not shown on figure) that extends to brake, and described the
First, the second cable wire is placed on bracket, it is ensured that correspondence cable wire will not be wound in one-level, the axial hole of two-level spring.
A kind of method of two-level spring joint ejection carrier-borne aircraft, the second electromagnet disconnection device is powered, and linkage rack passes through the
Two cable wires are connected with second hoist, start second hoist, when linkage rack, which is pulled to the first concave shaped portion, to be contacted with bounce-back beam,
Second hoist is stopped operating, keep state of tension, the first electromagnet disconnection device is powered, top plate passes through the first cable wire and the
One hoist engine is connected, and starts first hoist, when one-level spring is compressed into design pressure, makes first hoist stop turning
It is dynamic, state of tension is kept, ejection status is treated in formation, and now springs at different levels are in compressive state；
After carrier-borne aircraft is in place, the power supply of the first electromagnet disconnection device and first hoist is simultaneously switched off, one-level spring is released
Elastic force is put back, promotes carrier-borne aircraft peak acceleration to design within 10g, carrier-borne aircraft is obtained 150km/h or so most
Big speed, then simultaneously switches off the power supply of the second electromagnet disconnection device and second hoist, two-level spring release bounce, bounce-back
Power is by linkage rack and one-level spring effect in carrier-borne aircraft, and continuation promotes forward carrier-borne aircraft, increases to carrier-borne aircraft maximal rate
250-270km/h, makes carrier-borne aircraft speed increase to from warship speed level, completes carrier-borne aircraft ejection, completes after carrier-borne aircraft ejection, one
Level spring rushes at brake, stops under the drag effect of brake, now springs at different levels are in stress balance state.
Second electromagnet disconnection device and the first electromagnet disconnection device are respectively led into after half concave shape linkage rack and top plate, can
Start the ejection of another frame carrier-borne aircraft.
Following state is from top to bottom followed successively by Fig. 3：
(1) springs at different levels are in compressive state when launching；
(2) one-level springback power all discharges, and two-level spring is in compressive state；
(3) two-level spring bounce is all discharged, and ejection is finished；
(4) carrier-borne aircraft is from warship, and one-level spring starts to pour oil and stopped device.
Embodiment：
One-level spring line footpath 0.235m, external diameter 1.2m, around the number of turns 84, overall length 39.5m compresses 20m, length after compression
Empty footpath takes 0.235m × 0.6=0.141m, one-level spring-mass 60.8T in 19.5m, spring, and compared with solid spring, quality can
Reduce 36%, it is considered to which carrier-borne aircraft quality is 50T, maximum promotes acceleration 99m/s^2, maximal rate 160km/h.Two-level spring line
Footpath 0.15m, external diameter 0.7m, around the number of turns 93, overall length 27m compresses 13m, after compression in length 14m, spring empty footpath take 0.15m ×
0.7=0.105m, single two-level spring quality 12.5T, compared with solid spring, quality can reduce by 49%, two two-level springs
Carrier-borne aircraft and one-level spring, peak acceleration 60.5m/s^2, maximum driving velocity 101km/h are promoted simultaneously.Finally, warship can be made
Carrier aircraft obtain 160+101=261km/h from warship speed.Ejection total kilometres are calculated according to the total compression gauge of I and II spring
20+13=33m, oil device of stopping considers by 7m, spring groove overall length 7+33+14=54m.
Finally illustrate, preferred embodiment above is only unrestricted to illustrate the technical solution of the utility model, to the greatest extent
The utility model is described in detail by above preferred embodiment for pipe, but those skilled in the art should manage
Solution, can make various changes, without departing from the utility model claims institute to it in the form and details
The scope of restriction.
Claims (4)
1. a kind of device of two-level spring joint ejection carrier-borne aircraft, including bounce-back beam, brake, set between bounce-back beam, brake
Put and axially slidable ejection-spring is installed in the spring groove perpendicular to bounce-back beam, spring groove, the brake is used for ejection
Spring braking, it is characterised in that：The ejection-spring includes an one-level ejection-spring and is symmetrically set in one-level ejection-spring
Two two grades of ejection-springs of both sides, are joined between the one-level ejection-spring and two two grades of ejection-springs by linkage rack formation
Dynamic, the linkage rack includes the first concave shaped portion and two second concave shaped portions, and first concave shaped portion is nested in one-level ejection-spring
Bottom, two second concave shaped portion is respectively nested in the top of two two grades of ejection-springs, the top of the one-level ejection-spring
Top plate is set, is connected between the top plate and bounce-back beam and the first electromagnet disconnection device is set on the first cable wire, first cable wire,
Connected between two second concave shaped portions and bounce-back beam of the linkage rack and the second electromagnet is set on the second cable wire, second cable wire
First hoist, second hoist are set on disconnection device, the bounce-back beam, and the first hoist is connected with the first cable wire, institute
Second hoist is stated to be connected with the second cable wire.
2. the device of two-level spring joint ejection carrier-borne aircraft according to claim 1, it is characterised in that：The spring groove bag
An one-level spring groove and two two-level spring grooves are included, the one-level spring groove is used to install one-level spring, described two two
Level spring groove is used to install two two-level springs, and the cross section of the one-level spring groove and two two-level spring grooves is to recessed
Sunken semicircle, the linkage rack is on one-level spring groove, two-level spring groove.
3. the device of two-level spring joint ejection carrier-borne aircraft according to claim 1, it is characterised in that：The one-level bullet
Spring, two-level spring use hollow spring.
4. the device of two-level spring joint ejection carrier-borne aircraft according to claim 1, it is characterised in that：The brake is adopted
Stopped with oil device, the brake is used to brake one-level ejection-spring.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720351533.3U CN206606366U (en) | 2017-04-06 | 2017-04-06 | The device of two-level spring joint ejection carrier-borne aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720351533.3U CN206606366U (en) | 2017-04-06 | 2017-04-06 | The device of two-level spring joint ejection carrier-borne aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206606366U true CN206606366U (en) | 2017-11-03 |
Family
ID=60174116
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720351533.3U Expired - Fee Related CN206606366U (en) | 2017-04-06 | 2017-04-06 | The device of two-level spring joint ejection carrier-borne aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206606366U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106742028A (en) * | 2017-04-06 | 2017-05-31 | 重庆科技学院 | The apparatus and method of two-level spring joint ejection carrier-borne aircraft |
| CN108082524A (en) * | 2018-01-20 | 2018-05-29 | 北京正兴弘业科技有限公司 | A kind of controllable two-stage of unmanned plane launches vehicle control syetem and catapult technique |
| CN108177792A (en) * | 2017-12-28 | 2018-06-19 | 郑州光之源电子科技有限公司 | A kind of launching technique of small drone |
| CN113018881A (en) * | 2021-04-25 | 2021-06-25 | 航天创客（北京）科技有限公司 | Aerospace science popularization model self-adaptive ejection device |
-
2017
- 2017-04-06 CN CN201720351533.3U patent/CN206606366U/en not_active Expired - Fee Related
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106742028A (en) * | 2017-04-06 | 2017-05-31 | 重庆科技学院 | The apparatus and method of two-level spring joint ejection carrier-borne aircraft |
| CN108177792A (en) * | 2017-12-28 | 2018-06-19 | 郑州光之源电子科技有限公司 | A kind of launching technique of small drone |
| CN108082524A (en) * | 2018-01-20 | 2018-05-29 | 北京正兴弘业科技有限公司 | A kind of controllable two-stage of unmanned plane launches vehicle control syetem and catapult technique |
| CN108082524B (en) * | 2018-01-20 | 2023-10-10 | 沈观清 | Unmanned plane controllable two-stage ejection vehicle-mounted control system and ejection method |
| CN113018881A (en) * | 2021-04-25 | 2021-06-25 | 航天创客（北京）科技有限公司 | Aerospace science popularization model self-adaptive ejection device |
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| Date | Code | Title | Description |
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| GR01 | Patent grant | ||
| 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: 20171103 Termination date: 20200406 |