CN101503115B - Folding unmanned plane ejection system - Google Patents
Folding unmanned plane ejection system Download PDFInfo
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- CN101503115B CN101503115B CN2009100801051A CN200910080105A CN101503115B CN 101503115 B CN101503115 B CN 101503115B CN 2009100801051 A CN2009100801051 A CN 2009100801051A CN 200910080105 A CN200910080105 A CN 200910080105A CN 101503115 B CN101503115 B CN 101503115B
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- locking mechanisms
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- ejection system
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- lock
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Abstract
The invention discloses a foldable UAV launch system, comprising multistage launch guide ways, turning hinges, hinge locking mechanisms and fold locking mechanisms. The system is characterized in that the turning hinges are fixed at the end parts of two adjacent launch guide ways; and the launch guide ways take the rotating shafts of the turning hinges as rotating centers, are folded or unfolded at least once in a plane which is perpendicular to the launch guide ways, so that the launch system is in the state of folding transportation or the work state of emission. The old locking mechanisms are arranged on the guide ways, when the launch system is in the state of folding transportation, the fold locking mechanisms are used for locking the two launch guide ways which are folded together; the hinge locking mechanisms are arranged on the turning hinges, when the launch system is in the work state of emission, the hinge locking mechanisms are used for locking the turning hinges, so that the launch guide ways can not move relatively. The foldable UAV launch system has the advantages of simple structure, low price, safety, stableness, convenient operation and repeated use.
Description
Technical field
The present invention relates to the ejection system of unmanned aerial plane launching system, particularly a kind of folding unmanned plane ejection system.
Background technology
Unmanned plane is a kind of by unpiloted aerocraft on power driven, the machine.It is made up of body, engine installation, flicon and managerial tools, emission reclaiming scrap etc. usually, can remote control or flight automatically, can disposablely use, and also can reclaim, repeated use.It is one of current new-and high-tech weaponry and equipment, is widely used in battlefield investigation, electronic countermeasure, lesion assessment, many warlike operations such as attack over the ground after the war, is the requisite equipment of IT-based warfare.At civil area, it has been widely used in fields such as air remote sensing, aerial mapping, forest fire protection, coastline patrol.At present, unmanned aerial plane launching system mainly adopts hydraulic pressure, pneumatic, launch mode such as elastic launches.Its emission coefficient all comprises ejector rail, but emission coefficient exists problems such as operating mechanism complexity, structural weight is big, operating process is numerous and diverse by folding travelling position when the emission mode of operation is changed mutually at present.And emission coefficient take up room when after folding, existing transportation big, shortcoming such as damage easily in the transportation.
Summary of the invention
The object of the present invention is to provide a kind of simple in structure, cheap, safe and reliable, easy to operate, can repeat nonexpondable folding unmanned plane ejection system.
The invention discloses a kind of folding unmanned plane ejection system, comprise multistage ejector rail, turnover hinge, hinge locking mechanisms and fold locking mechanisms, it is characterized in that: the turnover hinge is fixed on the end of adjacent two ejector rail, ejector rail is a centre of gration with the rotating shaft of turnover hinge, in perpendicular to the ejector rail plane,, make ejection system be in folding travelling position or emission mode of operation through at least once folding or expansion.
Fold locking mechanisms is arranged on the guide rail, when ejection system is in folding travelling position, is used to lock two ejector rail that fold; Hinge locking mechanisms is located on the turnover hinge, when ejection system is in the emission mode of operation, is used for locking turnover hinge, makes between the ejector rail relative motion can not take place.
Fold locking mechanisms is identical with the hinge locking mechanisms structure, comprise on the blade that is arranged on the turnover hinge or the retainer on one section ejector rail, be arranged on another blade of turnover hinge or the support on another section ejector rail, pass support and be inserted into the lock(ing) bolt in the retainer jack, lever and the retaining nut who makes lock(ing) bolt on retainer, lock or unclamp, support is provided with the orienting sleeve of lock(ing) bolt, which is provided with tapped bore, lock(ing) bolt is a screw-rod structure, reaches the required tightening force of locking adjacent component by rotating screw bolt.
The turnover hinge is fixed by bolt and ejector rail end; Fold locking mechanisms is fixed by bolt and ejector rail; Turnover hinge end face is provided with position-limited trough.
The characteristics that the present invention gives prominence to are:
1, in the folding or expansion process, used lever principle at the ejection system guide rail dexterously, operating personal can be finished the work under effortless situation;
2, ejection system of the present invention has reduced the usable floor area of ejection system in transportation, the usage space of having saved transport vehicle after folding.Simultaneously, owing to locked ejection system after folding, to make do not have relative motion between guide rail, and safety when having improved entrucking, transportation reduces in the transportation destruction to ejection system that causes because of jolting etc.;
3, in this ejection system emission working process, reduced the ejection system guide rail because of the stressed distortion that causes, improved the reliability of whole system.
Description of drawings
Fig. 1 is launching to prepare to launch scheme drawing under the mode of operation for ejection system;
Fig. 2 is ejection system partial schematic diagram under deployed condition;
Fig. 3 is ejection system scheme drawing under folded state;
Fig. 4 A is that the turnover hinge is at ejection system in running condition scheme drawing;
Fig. 4 B is that the turnover hinge is at ejection system scheme drawing in folding process;
Fig. 4 C is in scheme drawing under the folding locking travelling position for the turnover hinge at ejection system;
Fig. 5 is turnover hinge scheme drawing and cutaway view when the ejection system mode of operation;
Fig. 6 is the lockout mechanism scheme drawing.
Description of reference numerals:
1, ejector rail; 2, turnover hinge; 3, hinge rotating shaft; 4, hinge locking mechanisms;
5, fold locking mechanisms; 6, position-limited trough;
41-retaining nut; The 42-retainer; The 43-lock(ing) bolt; The 44-lever; The 45-support
The specific embodiment
Below in conjunction with accompanying drawing the present invention is specifically described.
Fig. 1,2 is depicted as the scheme drawing under the unmanned aerial vehicle ejecting system mode of operation, wherein ejection system comprises three sections ejector rail 1, connect by turnover hinge 2 between the guide rail 1, the turnover hinge 2 of this moment is in the state that closes, turnover hinge 2 is provided with hinge locking mechanisms 4, be used for locking turnover hinge 2, make between the ejector rail 1 relative motion can not take place, to finish the unmanned aerial vehicle ejecting take-off process.
Figure 3 shows that scheme drawing under the unmanned aerial vehicle ejecting system folded state, the hinge 2 of transferring this moment is in the state of opening.Ejector rail 1 is fixing by fold locking mechanisms 5 between any two, the guide rail 1 of whole ejection system is in the lock state, can not relative motion between its guide rail 1, safety when having improved entrucking, transportation like this reduces in the transportation destruction to ejection system that causes because of jolting etc.
Fig. 4 A-4C shows turnover hinge 2 from the course of action of state to open mode that close.Shown in Fig. 4 A, when ejection system was in running order, turnover hinge 2 was in the state of closing, and lock(ing) bolt 43 is inserted in the jack in the retainer 42; When ejection system need fold, unclamp lock(ing) bolt 43, turnover hinge 2 is around hinge rotating shaft 3 rotations, and shown in Fig. 4 C, turnover hinge 2 rotates to open mode, and this moment, ejector rail 1 was in folded state.
As can be seen, the end of turnover hinge 2 is provided with position-limited trough 6 in the A-A of Fig. 5 cutaway view and B-B cutaway view, is the very little transition fit of gap value between it is relative.In the unmanned aerial vehicle ejecting process, ejector rail 1 is owing to be subjected to tension and compression meeting generation distortion, because the end of turnover hinge 2 is provided with position-limited trough 6, this position-limited trough 6 can limit turnover hinge 2 relative torsional deflectioies, and then the relative deformation of restriction ejector rail 1.
When ejection system is in folded state, lock(ing) bolt 43 is inserted in the retainer 42 in the jack, close down lever 44, make support 45 and lock(ing) bolt 43 be in latched position.Mention lever 44, tighten retaining nut 41, make lock(ing) bolt 43 and support 45 relative fixed.Like this, by closing down or mentioning lever 44, can realize lock(ing) bolt 43 on retainer 42 locking or unclamp, and then realize the folding locking or the opening procedure of ejector rail 1.
In conjunction with Fig. 1, Fig. 2 as can be known, the guide rail 1 of ejection system is with perpendicular to guide level rotary folding and opening, operating personal is away from 1 rotation of centre of gration place operation ejector rail, and according to the lever principle effect, operating personal can be finished the folding or expansion of ejection system under effortless situation.Like this with respect to folding in the mode that is parallel to guide level rotation and when opening area occupied little, therefore area occupied is little relatively in conveying carriage, this has just saved the transport vehicle carriage inner area greatly, can load more equipment under the same conditions.
Above-mentioned embodiment of the present invention can not be thought restriction that claim of the present invention is done; if those skilled in the art does not need performing creative labour to make corresponding variation by inspiration of the present invention, all should fall into the protection domain of claim of the present invention.
Claims (4)
1. folding unmanned plane ejection system, comprise multistage ejector rail (1), turnover hinge (2), hinge locking mechanisms (4) and fold locking mechanisms (5), it is characterized in that: turnover hinge (2) is fixed on the end of adjacent two ejector rail (1), ejector rail (1) is a centre of gration with the rotating shaft (3) of turnover hinge, in perpendicular to the ejector rail plane through at least once folding or launch, make ejection system be in folding travelling position or emission mode of operation, fold locking mechanisms (5) is arranged on the ejector rail (1), when ejection system is in folding travelling position, be used to lock two ejector rail (1) that fold; Hinge locking mechanisms (4) is located on the turnover hinge (2), when ejection system is in the emission mode of operation, is used for locking turnover hinge (2), makes between the ejector rail relative motion can not take place.
2. folding unmanned plane ejection system according to claim 1, it is characterized in that: hinge locking mechanisms (4) comprises the retainer (42) on the blade that is arranged on turnover hinge (2), be arranged on the support (45) on another blade of turnover hinge (2), pass support (45) and be inserted into lock(ing) bolt (43) in the retainer jack, the lever that makes lock(ing) bolt on retainer, lock or unclamp, and retaining nut (41), support is provided with the orienting sleeve of lock(ing) bolt, which is provided with tapped bore, lock(ing) bolt (43) is a screw-rod structure, and the screw rod by twist-lock bolt (43) reaches the required tightening force of locking adjacent component;
Fold locking mechanisms (5) is identical with hinge locking mechanisms (4) structure, and its retainer (42) is arranged on one section ejector rail (1), and its support (45) is arranged on another section ejector rail (1).
3. folding unmanned plane ejection system according to claim 1 and 2 is characterized in that: turnover hinge (2) is fixed by bolt and ejector rail (1) end; Fold locking mechanisms (5) is fixing by bolt and ejector rail (1).
4. folding unmanned plane ejection system according to claim 1 and 2 is characterized in that: turnover hinge (2) end face is provided with position-limited trough (6).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009100801051A CN101503115B (en) | 2009-03-20 | 2009-03-20 | Folding unmanned plane ejection system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009100801051A CN101503115B (en) | 2009-03-20 | 2009-03-20 | Folding unmanned plane ejection system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101503115A CN101503115A (en) | 2009-08-12 |
| CN101503115B true CN101503115B (en) | 2011-04-27 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2009100801051A Expired - Fee Related CN101503115B (en) | 2009-03-20 | 2009-03-20 | Folding unmanned plane ejection system |
Country Status (1)
| Country | Link |
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| CN (1) | CN101503115B (en) |
Families Citing this family (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102020021B (en) * | 2011-01-04 | 2013-02-06 | 贾正跃 | Reverse pulling and prompt release assisted takeoff method for realizing short-range take-off of aircraft carrier-based plane |
| CN103803095B (en) * | 2014-03-03 | 2016-05-25 | 重庆翼动科技有限公司 | The Pneumatic catapult of SUAV |
| CN104015933B (en) * | 2014-06-11 | 2016-03-30 | 毕和军 | Collapsible unmanned aerial vehicle ejecting regenerative apparatus |
| CN108551905B (en) * | 2018-03-08 | 2024-03-26 | 贵州电网有限责任公司 | Folding joint for tree obstacle cleaning aerial robot |
| CN110857148A (en) * | 2018-08-22 | 2020-03-03 | 北京理工大学 | Rotor unmanned aerial vehicle ejection device on carrying system |
| CN110857146B (en) * | 2018-08-24 | 2021-12-24 | 北京理工大学 | Carry on many rotor unmanned aerial vehicle's delivery system |
| CN110316398B (en) * | 2019-08-02 | 2024-08-06 | 西安探索鹰航空科技有限公司 | Unmanned aerial vehicle takes off and retrieves integrated operation car |
| CN110605726A (en) * | 2019-09-26 | 2019-12-24 | 上海电力大学 | External mechanical arm span-type window cleaning robot |
| CN110803292B (en) * | 2019-11-25 | 2021-05-11 | 航天时代飞鸿技术有限公司 | Steel cable retaining mechanism |
| CN112077579A (en) * | 2020-08-20 | 2020-12-15 | 商乐琪 | Device for quickly disassembling and assembling oil filling valve of extruder |
| CN112509399A (en) * | 2020-12-28 | 2021-03-16 | 石家庄信息工程职业学院 | Professional english teacher teaching is with playback devices |
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2009
- 2009-03-20 CN CN2009100801051A patent/CN101503115B/en not_active Expired - Fee Related
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| Publication number | Publication date |
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| CN101503115A (en) | 2009-08-12 |
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