CN101081639B - Ejecting system applied for unmanned aerial plane launching system - Google Patents
Ejecting system applied for unmanned aerial plane launching system Download PDFInfo
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- CN101081639B CN101081639B CN200610035764XA CN200610035764A CN101081639B CN 101081639 B CN101081639 B CN 101081639B CN 200610035764X A CN200610035764X A CN 200610035764XA CN 200610035764 A CN200610035764 A CN 200610035764A CN 101081639 B CN101081639 B CN 101081639B
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- unmanned aerial
- coaster
- plane launching
- aerial plane
- ejection system
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Abstract
The present invention relates to drone, and is especially one ejecting system for launching drone. The ejecting system includes one tackle and one power system, the tackle moves along a guide rail under the action of the power system, and the power system includes one elastomer possessing one fixed end and one free end, one winch truck and one steel cable possessing one end connected to the winch truck and the other end connected to the free end of the elastomer. During being launched, the drone is powered by the energy the elastomer accumulates to accelerate in the guide rail. The present invention has low drone launching cost.
Description
Technical field
The present invention relates to a kind of UAS, particularly a kind of ejection system that is applied to unmanned aerial plane launching system.
Background technology
Unmanned plane (UAV) is the abbreviation of " robot airplane ", mainly relies on radio telecommand or realizes Autonomous Control flight through modes such as autopilots.It is one of current advanced technological arms, extensively applies to many warlike operations such as battle reconnaissance, electronic countermeasure, air attack, is described as the " prying eyes " and " trump card " of modern battlefield.At present, the UAV emission coefficient of China mainly adopts hydraulic pressure, pneumatic, these several kinds of launch modes of rocket assist.These several kinds of launch modes exist complex structure, and it is high to make use cost, the problem of maintenance difficulty.The safety measure of using like the transportation of booster rocket, storage requires high, for its use brings very big inconvenience.And the rocket assist emission coefficient, because of rocket can not repeated usage, each launch cost only one in rocket just needs thousands of units.The manufacturing cost of hydraulic pressure emission coefficient is up to 1,000,000 yuan.
Summary of the invention
The objective of the invention is to, a kind of simple in structure, cheap, ejection system that is applied to unmanned aerial plane launching system that can be reusable, safe and reliable is provided.
The objective of the invention is to realize through following technical scheme:
A kind of ejection system that is applied to unmanned aerial plane launching system, said ejection system comprise a coaster and a power system, said coaster under the effect of said power system along a guide rail movement; Said power system comprises the elastic body that can stretch and shrink.
Said power system also comprises a winch truck, a cable wire; Said cable wire one termination is gone into said winch truck, and an end links to each other with said coaster, and said cable wire links to each other with said elastomeric free end versatilely, and the said elastomeric other end is fixed.
Said elastic body is the elastic bundle.
Said elastic body is the spring bundle.
The present invention utilizes energy moment output that elastic body the accumulates power as unmanned aerial vehicle ejecting, utilizes guide rail to quicken to unmanned plane, makes unmanned plane reach the scheme of leaving guide rail behind certain rate of onset; The most basic low price of utilizing, the energy storage characteristic of the elastic body that can be repeatedly used (elastic) applies in the concrete UAV emission coefficient, reaches the reduction use cost; Native system is simple in structure simultaneously, is convenient to grasp, and is easy to use, reaches safe, the easy and failure-free requirement when using.
Description of drawings:
Fig. 1 is a kind of scheme drawing of unmanned aerial plane launching system;
Fig. 2 is the scheme drawing of ejection system of the present invention.
Fig. 3 is the scheme drawing of the running block of ejection system of the present invention
The specific embodiment
Embodiment one
As shown in Figure 1, a kind of unmanned aerial plane launching system comprises guide track system, ejection system, control system and propulsion source; Said ejection system and brake system are arranged on the said guide track system; Said control system is controlled said ejection system and guide track system, and propulsion source is that whole emission coefficient provides the energy.
As shown in Figure 2; For being applied to the ejection system of unmanned aerial plane launching system shown in Figure 1; Said ejection system comprises power system and coaster 1; Said coaster 1 can be under the effect of said power system guide rail 2 in the said guide track system move, unmanned plane is placed on the said coaster 1 through the body carriage, locks through body locking and releasing mechanism.Said power system comprises a winch truck 5, the elastic body 7 that a cable wire 6 and can stretch and shrink under said drive power source, and adopts the elastic bundle in the present embodiment; Said cable wire 6 one terminations are gone into said winch truck 5; One end links to each other with said coaster 1; And said cable wire 6 links to each other with the free end of said elastic body 7 versatilely, and the other end of said elastic body 7 is fixed on support body 4 one terminal 41 (or the title rear ends) in the said guide track system; For the size of measuring the elastic body energy accumulation can be installed resistance dynamometer on the elastic body near the support body rear end.Said winch truck 5 is fixed on the said support body 4, and its position and said terminal 41 distance are greater than the extreme length in when elongation in said elastic body 7 mode of operations.When said coaster 1 was fixed on initial position through safety pin and hub lock releasing, said elastic body 7 was stretched under the effect of said winch truck 5 and cable wire 6, accumulates elastic energy.If the power drive shaft owner on the said coaster 1 is made up of main shaft bearing and rotatable cable connector and the wheel disc etc. of going in ring; Said cable wire 6 joins through said rotatable belt cable connector and said coaster 1.
Free end at said elastic body 7 is connected with a running block 3, and said cable wire 6 is movably connected through the free end of said running block 3 with said elastic body 7.As shown in Figure 3; Said running block 3 comprises that one roughly is the support body 31 of " well "; Correspondence is equipped with steady wheel 32 on the both lateral sides limit of said support body 31; Under the effect of said steady wheel, said running block 3 can be in the said support body 4 under the drive of said cable wire 6 along an orbiting motion of support body elongated lengthwise.Said movable pulley 33 be installed in said support body 31 vertical left side on, present embodiment is defined as 33 cores of movable pulley; The free end of said elastic body 7 is connected on the said support body 31 vertical right edge.The said elastic body that when said running block 3 moves under the effect of said cable wire 6, will stretch makes it accumulate elastic energy.Also be to drive said cable wire 6 through said running block 3 further to drive said coaster motion when said elastic body releases energy, for said unmanned plane provides rate of onset.
In order to make said cable wire 6 drive said running block 3 motions smoothly,, one first fixed pulley 8 is set preferably between said winch truck and said running block 3 along said rope length direction; One second fixed pulley 9 is set between said running block 3 and coaster 1.Said cable wire 6 walk around said first and second fixed pulleys can be better for said elastic body 7 energy accumulations with release energy.Said first and second fixed pulleys all are fixed on the said support body 4, and said terminal 41 distance is arrived in its position, the extreme length when extending greater than said elastic body 7.
Above-mentioned introduction be the related device of accelerator of said ejection system, introduce the related device of braking procedure of said ejection system below.Said braking procedure is after being used for reducing unmanned plane and obtaining rate of onset and leave said coaster, continue with higher speed to the terminal motion of guide rail and smash said guide track system in order to prevent said coaster, even said coaster 1 flies out.In the present embodiment, the shared power system of the accelerating sections of said ejection system and said retaining segment.After unmanned plane obtains rate of onset and leaves said coaster and said coaster and stride across said second fixed pulley 9; Along with the change of cable wire 6 directions, elastomeric contraction, coaster will receive pulling force backward; Speed reduces can not produce harmful effect to guide track system until stopping gradually.In order better to make said coaster obtain slowing down; In left side (away from said support body terminal 41) near said second fixed pulley; Being provided with one the 3rd fixed pulley 10, when said cable wire 6 commutates under the drive of said coaster 1, and will be bigger touching the resistance that receives behind said the 3rd fixed pulley 10.
[0019]The working process of said unmanned aerial plane launching system is following: earlier slide trucks is locked in the initial point of emission, unmanned plane is locked on the carriage again, insert safety pin.Propulsion source is that power system provides the energy, makes elastic body reach certain elastic potential energy.Remove safety pin then, emission coefficient is in battery, and after launch intruction was assigned, the lockout mechanism of coaster was opened, and discharges coaster.Coaster is under the effect of elastomer contracts power, and during the position on the guide rail of launcher, quicken to arrive set for unmanned plane through carriage, the body blocking device on the carriage is opened unmanned plane from the frame lift-off.Simultaneously, coaster gets into the braking job procedure.Coaster is under the effect of elastomer contracts power, and slowing down also rapidly, pulsation-free obtains braking.
Embodiment two
The difference of the present embodiment and first embodiment is that said elastic body is large-scale extension spring bundle.
Embodiment three
The difference of the present embodiment and first embodiment is, the not shared power system of the said retaining segment of said ejection system.But the elastic body that independent employing can stretch comes to said coaster 1 resistance.Certainly, must be after unmanned plane takes off to the opportunity of coaster 1 resistance.Said elastic body is separately positioned on the both sides of said guide rail, and said elastic body one end is fixed, and a termination has latching device, and when said coaster 1 arrives assigned address, latching device will be hung up above-mentioned coaster.
[0024] the present invention also has other distortion such as elastomeric selection can make corresponding variation; Said cable wire can be other materials with toughness, like bigger plastic ties of intensity etc.Fixed pulley and running block also can change other reversing arrangements into.If those skilled in the art does not need performing creative labour to make corresponding variation through inspiration of the present invention.All should fall into the protection domain of claim of the present invention.
Claims (9)
1. ejection system that is applied to unmanned aerial plane launching system, said ejection system comprises a coaster and a power system, said coaster under the effect of said power system along a guide rail movement; Said power system comprises the elastic body that can stretch and shrink; Said power system also comprises a winch truck, a cable wire; It is characterized in that said cable wire one termination is gone into said winch truck, an end links to each other with said coaster, and said cable wire links to each other with said elastomeric free end versatilely, and the said elastomeric other end is fixed.
2. the ejection system that is applied to unmanned aerial plane launching system according to claim 1 is characterized in that, is connected with a movable pulley assembly at said elastomeric free end, and said cable wire is movably connected through said movable pulley assembly and said elastomeric free end.
3. the ejection system that is applied to unmanned aerial plane launching system according to claim 2; It is characterized in that; Said movable pulley assembly comprises the support body that is " well " font; The both lateral sides limit correspondence of support body of " well " font is equipped with steady wheel in said being, a movable pulley be installed in the vertical left side of said support body on, said elastomeric free end is connected on the vertical right edge of support body of " well " font of said being.
4. the ejection system that is applied to unmanned aerial plane launching system according to claim 3 is characterized in that, along said rope length, between said winch truck and said movable pulley assembly, one first fixed pulley is set.
5. the ejection system that is applied to unmanned aerial plane launching system according to claim 4 is characterized in that, along said rope length, one second fixed pulley is set between said movable pulley assembly and coaster.
6. the ejection system that is applied to unmanned aerial plane launching system according to claim 5; It is characterized in that; Said first fixed pulley and second fixed pulley all are fixed on the guide rail support body, and the present position is to the terminal distance of said guide rail support body, the extreme length when extending greater than said elastic body.
7. according to any described ejection system that is applied to unmanned aerial plane launching system of claim 1-5, it is characterized in that said elastic body is the elastic bundle.
8. according to any described ejection system that is applied to unmanned aerial plane launching system of claim 1-5, it is characterized in that said elastic body is the spring bundle.
9. the ejection system that is applied to unmanned aerial plane launching system according to claim 5 is characterized in that, in the left side near said second fixed pulley, is provided with one the 3rd fixed pulley.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200610035764XA CN101081639B (en) | 2006-06-02 | 2006-06-02 | Ejecting system applied for unmanned aerial plane launching system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200610035764XA CN101081639B (en) | 2006-06-02 | 2006-06-02 | Ejecting system applied for unmanned aerial plane launching system |
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| Publication Number | Publication Date |
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| CN101081639A CN101081639A (en) | 2007-12-05 |
| CN101081639B true CN101081639B (en) | 2012-08-22 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN200610035764XA Expired - Fee Related CN101081639B (en) | 2006-06-02 | 2006-06-02 | Ejecting system applied for unmanned aerial plane launching system |
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Families Citing this family (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101607602A (en) * | 2008-06-18 | 2009-12-23 | 上海奇谋能源技术开发有限公司 | A kind of launching power method and device |
| CN103277353B (en) * | 2013-05-08 | 2015-06-10 | 燕山大学 | Unmanned aerial vehicle low impact catapult pneumatic and hydraulic system |
| CN103434649B (en) * | 2013-07-22 | 2015-08-05 | 燕山大学 | Unmanned aerial vehicle ejecting device slows down and backhaul Gas fluid pressure control system |
| CN103803095B (en) * | 2014-03-03 | 2016-05-25 | 重庆翼动科技有限公司 | The Pneumatic catapult of SUAV |
| CN104477400A (en) * | 2014-11-28 | 2015-04-01 | 四川航空工业川西机器有限责任公司 | Unmanned aerial vehicle hydraulic catapult launching system |
| MX2018005328A (en) | 2015-10-27 | 2018-09-21 | Walmart Apollo Llc | Method and apparatus for an airborne drone training track. |
| CN109398741B (en) * | 2018-12-12 | 2024-03-19 | 威海广泰空港设备股份有限公司 | Trailer type unmanned aerial vehicle launching device |
| CN112406911B (en) * | 2020-11-24 | 2021-07-16 | 广东技术师范大学 | Forest and fruit transportation method and device based on cable-rail combination and computer equipment |
| CN112704864B (en) * | 2020-12-10 | 2022-04-08 | 北京航天益森风洞工程技术有限公司 | Athlete ejection device for ice and snow sports |
| CN113357205B (en) * | 2021-06-16 | 2022-11-29 | 浙江大学 | Gas-liquid ejection servo actuating system |
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- 2006-06-02 CN CN200610035764XA patent/CN101081639B/en not_active Expired - Fee Related
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