CN201729276U - Ejection system of small-sized unmanned aircraft - Google Patents
Ejection system of small-sized unmanned aircraft Download PDFInfo
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- CN201729276U CN201729276U CN201020241857XU CN201020241857U CN201729276U CN 201729276 U CN201729276 U CN 201729276U CN 201020241857X U CN201020241857X U CN 201020241857XU CN 201020241857 U CN201020241857 U CN 201020241857U CN 201729276 U CN201729276 U CN 201729276U
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- guide rail
- ejection
- supporting leg
- dolly
- plate
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Abstract
The utility model discloses an ejection system of a small-sized unmanned aircraft. A plurality of supporting legs (8) support a guide rail (7), a front end plate (1) is arranged at the front end of the guide rail (7), a rear supporting base (9) is arranged at the rear end of the guide rail (7), a cushioning base (2) is arranged on the guide rail (7) in the position of the front end plate (1), a winch is mounted on the rear supporting base (9), an ejection trolley (6) is glidingly mounted on the guide rail (7), a localizer (3) is arranged on an auxiliary guide rail (11) positioned close to the front end plate (1), an unlocking rod (34) on the ejection trolley (6) knocks against the localizer (3) to unlock an aircraft locking switch (35), a pulley (33) is arranged on the front end plate (1), an elastic band set (4) bypasses one end of the pulley (33) to be connected with the ejection trolley (6), the other end of the pulley (33) is connected with the wire rope of the winch, and a launching unit acting on the ejection trolley (6) is arranged on the rear supporting base (9). The ejection system provided by the utility model has the advantages of low use cost, simple structure, convenient operation and transportation, high efficiencies of disassembly and assembly as well as regulation, light weight, and easy part disassembly.
Description
Technical field
The utility model relates to a kind of ejection system, particularly relates to a kind of catapult launcher of miniature self-service aircraft.
Background technology
Be born since unmanned plane in 1917, be the military purposes service, in the near future, unmanned plane will replace manned aircraft, becomes the main force of modern battlefield.Under the active demand on digital city, digital territory, repair timely and compile and upgrade map, the dynamic monitoring soil utilizes situation of change, and derive all kinds of when up-to-date the thematic map of phase all be to need the urgent problem that solves.As the new technique means that the space image obtains, the unmanned aerial vehicle remote sensing data-acquisition system has become the world today and has fallen over each other the focus researching and developing and use.
The mode of taking off of unmanned aerial vehicle has ground roll-out to take off, rise that driving rolling start, catapult-assisted take-off, hand-thrown are taken off etc., and hand-thrown takes off and only is suitable for lightweight Micro Aerial Vehicle.Limited when the space, take-off venue, when not having highway and runway, the rolling start mode is also incompatible, at this moment can only take the mode of catapult-assisted take-off, and especially many mountain areas, many water are all the more so in south.
The utility model content
Technical problem to be solved in the utility model provide a kind of system weight light, be convenient to transport, simplify the operation, the ejection system of high efficiency, miniature self-service aircraft that use cost is low.
In order to solve the problems of the technologies described above, the ejection system of the miniature self-service aircraft that the utility model provides, many supporting legs are supported with guide rail and the auxiliary guide rail that is in described guide rail below, front end at described guide rail is provided with front end-plate, the rear end of described guide rail is provided with the back supporting seat, on described front end-plate, be provided with buffing pad, on the supporting seat of described back, winch is installed, on described guide rail, be slidingly fitted with and launch dolly, on described auxiliary guide rail, close on described front end-plate place and be provided with steady arm, described steady arm and the described corresponding collision of unlocking rod of launching on the dolly, open aircraft locking switch, on described front end-plate, be provided with pulley, the bungee group is walked around described pulley one end and is connected with the described dolly that launches, the other end is connected with the steel rope of described winch, is provided with on the supporting seat of described back and acts on the described feedway that launches dolly.
Described feedway is to be provided with to hook the described hook that launches dolly on the supporting seat of described back, and described hook is provided with the hook handle, is inserted with stop pin between the dolly at described back supporting seat and described launching.
Described bungee group is connected with the steel rope of described winch by pulley block.
Described winch is an electric winch.
Described guide rail and auxiliary guide rail are formed by the plurality of sections of steel pipes butt joint, one end of described steel pipe is provided with screw rod, the outside of the other end is provided with interior Hexagonal jacket, and the inboard is provided with negative thread, and the described screw rod of last joint steel pipe can be screwed in the described negative thread of back one joint steel pipe.
The structure of each described supporting leg is to be arranged with two sleeves on connecting panel, be hinged with lock banking stop on each described sleeve, be connected with bungee or spring between the other end of lock banking stop and the sleeve, insert respectively in two described sleeves of described connecting panel the upper end of two supporting leg steel pipes, there is decorative pattern the upper end of two described supporting leg steel pipes car respectively, the lower end of two described supporting leg steel pipes is hinged with the supporting leg base plate that can rotate around the axis respectively, described supporting leg base plate is an one flat plate, described lock banking stop is blocked the decorative pattern of described supporting leg steel pipe by the tension of described bungee or spring, prevent that described supporting leg steel pipe from sliding, described guide rail is installed on the described connecting panel.
Described bungee group and described steel rope and describedly launch being connected and fixed in the pipe end of India rubber tube that structure is described bungee group of dolly and be fitted with the inner cone platform, the taper hole that the pipe end of described India rubber tube passes outer tube make described in frustum cooperate with described outer tube and compress, described outer tube is installed on the mount pad, described mount pad is installed on the installation shaft, and described installation shaft is connected with described steel rope or the described dolly that launches.
The axial centre of frustum is provided with tapped bore in described.
The arrangement prescription of described installation shaft and described India rubber tube when parallel, described installation shaft can prevent described India rubber tube from pipe end is disconnected when taking off described in frustum skid off.When described installation shaft is vertical with the orientation of described India rubber tube, on described installation shaft, be provided with prevent described India rubber tube from pipe end is disconnected when taking off described in the baffle plate that skids off of frustum.
Adopt the ejection system of the miniature self-service aircraft of technique scheme, utilize the elastic force of the India rubber tube of bungee group to do power, with electric winch or crab winch tension rubber band group, after the bungee group discharges and launches dolly, launch the dolly mother aircraft and run, make aircraft reach takeoff speed along guide rail is sliding.But the bungee group is by the electric winch tension of self-locking.But motor is realized slowing down by the worm decelerating machine of self-locking; The veer and haul of rubber band group is realized by changing the DC machine sense of current; When unloaded, can winch and reductor be broken away from by power-transfer clutch, thus can M/C.The method of attachment of bungee group fast and reliable, interior frustum center is a tapped bore, interior frustum is filled in the India rubber tube pipe end of bungee group with threaded handle, the tension India rubber tube, under the taper effect, frustum more and more is close to taper hole and compresses India rubber tube, thereby plays the role of fastening.Frustum may skid off when taking off for preventing India rubber tube just in case from pipe end is disconnected, is blocked by installation shaft or baffle plate, thereby guarantees safety.Back supporting seat is provided with stop pin and hook double insurance, guarantees safe in utilization.
Advantage of the present utility model: 1) guide rail of the present utility model adopts the quick connection mode of screw thread to be formed by connecting by plurality of sections of steel pipes, and dismounting is convenient, transports light; 2) but the supporting leg quick adjustment, to adapt to rugged ground, high efficiency, wide accommodation; 3) but bungee by the electric winch veer and haul of self-locking, safe in utilizationly, laborsaving save trouble again; When unloaded, can winch and reductor be broken away from by power-transfer clutch, thus can M/C.4) elastic rubber pipe pipe end adopts quick connecting method, and is safe in utilization quick.5) stop pin and hook double insurance are adopted in the dolly locking, and be safe in utilization.
In sum, the utility model be a kind of system weight light, be convenient to transport, simplify the operation, the ejection system of high efficiency, miniature self-service aircraft that use cost is low.
Description of drawings
Fig. 1 is the ejection system composition diagram of miniature self-service aircraft of the present utility model;
Fig. 2 is a left view of the present utility model;
Fig. 3 is used to lock stop pin and the hook double insurance structural scheme of mechanism that launches dolly on the supporting seat of back;
Fig. 4 is the constructional drawing of single-unit guide rail;
Fig. 5 is the leg structure scheme drawing;
Fig. 6 is India rubber tube of the present utility model, interior frustum and outer tube assembling scheme drawing;
Fig. 7 and Fig. 8 are outer tube of the present utility model and mount pad structural representation, installation shaft and the parallel assembling of the orientation of India rubber tube;
Fig. 9 and Figure 10 are that installation shaft and India rubber tube are provided with baffle plate assembling scheme drawing, and installation shaft is assembled with the orientation of India rubber tube is vertical.
The specific embodiment
The utility model is described in further detail below in conjunction with the drawings and specific embodiments.
Referring to Fig. 1, Fig. 2 and Fig. 3, many supporting legs 8 are supported with guide rail 7 and the auxiliary guide rail 11 that is in guide rail 7 belows, front end at guide rail 7 is provided with front end-plate 1, the rear end of guide rail 7 is provided with back supporting seat 9, on the guide rail 7 at front end-plate 1 place, be provided with buffing pad 2, on the supporting seat 9 of back, electric winch 10 is installed, on guide rail 7, be slidingly fitted with and launch dolly 6, on auxiliary guide rail 11, close on front end-plate 1 place and be provided with steady arm 3, steady arm 3 with launch dolly 6 on unlocking rod 34 corresponding collisions, open aircraft locking switch 35, on front end-plate 1, be provided with pulley 33, bungee group 4 one ends with launch dolly 6 and be connected, the other end is walked around pulley 33 backs and is connected with the steel rope of electric winch 10 by pulley block 5, be provided with on the supporting seat 9 in the back and hook the hook 12 that launches dolly 6, hook 12 is provided with hook handle 14, at back supporting seat 9 with launch and be inserted with stop pin 13 between the dolly 6.
Referring to Fig. 4, needs according to ejection speed, guide rail 7 and auxiliary guide rail 11 are made up of 16 butt joints of more piece (being generally the 5-6 joint) steel pipe, one end of steel pipe 16 is provided with screw rod 15, the outside of the other end is provided with interior Hexagonal jacket 18, the inboard is provided with negative thread 17, and the screw rod 15 of last joint steel pipe can be screwed in the negative thread 17 of back one joint steel pipe.Guide rail 7 is connected between back supporting seat 9 and the front apron 1,16 of steel pipes adopt quick connection mode to connect, the screw rod 15 of last joint steel pipe passes negative thread 17 ends that hole on the connecting panel 20 of supporting leg 8 is screwed into back one joint steel pipe, relies on the interior Hexagonal jacket 18 inner-hexagon spanner threaded together of last joint steel pipe end.20 one-tenth smooth sides of two joint steel pipes and connecting panel, thus dolly 6 is launched in assurance and pulley block 3 can smoothly on guide rail 7 and auxiliary guide rail 11 be slided unimpededly.
Referring to Fig. 5, the steel pipe junction of guide rail 7 and auxiliary guide rail 11 has supporting leg 8 to support, the structure of each supporting leg 8 is to be provided with to be arranged with two sleeves 21 on connecting panel 20, be hinged with lock banking stop 23 on each sleeve 21, be connected with bungee or spring 22 between the other end of lock banking stop 23 and the sleeve 21, insert respectively in two sleeves 21 of connecting panel 20 upper end of two supporting leg steel pipes 24, there is decorative pattern 19 upper end of two supporting leg steel pipes 24 car respectively, the lower end of two supporting leg steel pipes 24 is hinged with the supporting leg base plate 25 that can rotate around the axis respectively, supporting leg base plate 25 is an one flat plate, lock banking stop 23 is blocked the decorative pattern 19 of supporting leg steel pipe 24 by 22 tensions of bungee or spring, prevent that supporting leg steel pipe 24 from sliding, guide rail 7 is installed on the connecting panel 20.At the bottom of the supporting leg, 25 is a flat board that can rotate around the axis, and when ground is uneven, can adapt to ground and compacting ground; The supporting leg steel pipe 24 of supporting leg 8 upper ends inserts in the sleeve 21 of connecting panel 20, can freely stretch according to the distance between guide rail 7 and ground; The supporting leg steel pipe 24 of the supporting leg 8 upper ends decorative pattern 19 of having got on the bus, after the length adjustment of supporting leg 8 was suitable, lock banking stop 23 was blocked the decorative pattern of supporting leg steel pipe 24 by bungee or spring 22 tensions, prevent that supporting leg 8 from sliding.
Dolly 6 is launched in bungee group 4 one ends tractions, and bungee group 4 other ends by electric winch 10 supporting seat 9 directions tension backward, produce enough tensile forces after walking around pulley 33 on the front apron 1.But the DC machine of electric winch 10 realizes slowing down by the worm decelerating machine of self-locking; The veer and haul of bungee group 4 is realized by changing the DC machine sense of current; When unloaded, can electric winch 10 and reductor be broken away from by power-transfer clutch, thus can M/C.
Referring to Fig. 6, Fig. 7, Fig. 8, Fig. 9 and Figure 10, India rubber tube 26 pipe ends of bungee group 4 adopt quick connecting method to fix.Bungee group 4 is with steel rope and launch being connected and fixed in the pipe end that structure is an India rubber tube 26 of dolly 6 and be fitted with inner cone platform 28, frustum 28 cooperated with outer tube 27 and compresses in the taper hole that the pipe end of India rubber tube 26 passes outer tube 27 made, the axial centre of interior frustum 28 is provided with tapped bore 29, outer tube 27 is installed on the mount pad 30, mount pad 30 is installed on the installation shaft 31, and installation shaft 31 is with steel rope or launch dolly 6 and be connected.India rubber tube 26 passes the taper hole of outer Taper Pipe 27, and interior frustum 28 centers are a tapped bore 29, with threaded handle interior frustum 28 is filled in India rubber tube 26 pipe ends, tension India rubber tube 26, under the taper effect, interior frustum 28 more and more is close to taper hole and compresses India rubber tube 26, thereby plays the role of fastening.For preventing India rubber tube 26 just in case in pipe end is disconnected when taking off frustum 28 may skid off, the arrangement prescription of installation shaft 31 and India rubber tube 26 is when vertical, on installation shaft 31, be provided with and prevent India rubber tube 26 baffle plate 32 that frustum 28 skids off in pipe end is disconnected when taking off, block by baffle plate 26, thereby guarantee safety.When installation shaft 31 was parallel with the orientation of India rubber tube 26, just in case India rubber tube 26 is when taking off from pipe end is disconnected, installation shaft 31 can stop interior frustum 28 to skid off, block by installation shaft 31, thus assurance safety.
For protection bungee group 4 with prevent that bungee group 4 is rocked in the distraction procedure, can be connected by pulley block 5 between the steel rope of bungee group 4 and electric winch 10, pulley block 5 is slided on the auxiliary guide rail 11 of lower floor.Aircraft sets up and is locked in and launches on the dolly 6, during cataplane, extract stop pin 13, draw back hook 12,4 tractions of bungee group are launched dolly 6 and are slided on guide rail 7, when sliding near buffing pad 2 and front apron 1, launch the steady arm 3 on the unlocking rod 34 bump auxiliary guide rails 11 on the dolly 6, the aircraft locking switch 35 on the dolly 6 is launched in unlatching, aircraft relies on and to launch the power that speed that dolly 6 provides and driving engine provide, fly away from launching cradle, the kinetic energy that launches dolly 6 is absorbed by buffing pad 2, thereby the no runway of realizing unmanned aerial vehicle takes off.Back supporting seat 9 is provided with stop pin 13 and hook 12 double insurances, guarantees safe in utilization.The native system use cost is low; Simultaneously native system is simple in structure, simple operation, and the efficient height is regulated in dismounting, and is in light weight and be easy to tear open zero, convenient transport.
Claims (10)
1. the ejection system of a miniature self-service aircraft, it is characterized in that: many supporting legs (8) are supported with guide rail (7), front end at described guide rail (7) is provided with front end-plate (1), the rear end of described guide rail (7) is provided with back supporting seat (9), on the guide rail (7) that front end-plate (1) is located, be provided with buffing pad (2), on described back supporting seat (9), winch is installed, on described guide rail (7), be slidingly fitted with and launch dolly (6), be provided with steady arm (3) closing on the auxiliary guide rail (11) that front end-plate (1) locates, launch unlocking rod (34) and the corresponding collision of steady arm (3) on the dolly (6), open aircraft locking switch (35), on described front end-plate (1), be provided with pulley (33), bungee group (4) is walked around described pulley (33) one ends and is connected with the described dolly (6) that launches, the other end is connected with the steel rope of described winch, is provided with on described back supporting seat (9) and acts on the described feedway that launches dolly (6).
2. the ejection system of miniature self-service aircraft according to claim 1, it is characterized in that: described feedway is to be provided with to hook the described hook (12) that launches dolly (6) on described back supporting seat (9), described hook (12) is provided with hook handle (14), is inserted with stop pin (13) between the dolly (6) at described back supporting seat (9) and described launching.
3. the ejection system of miniature self-service aircraft according to claim 1 and 2, it is characterized in that: described supporting leg (8) is provided with the auxiliary guide rail (11) that is in described guide rail (7) below, and described steady arm (3) is installed on the described auxiliary guide rail (11).
4. the ejection system of miniature self-service aircraft according to claim 1 and 2 is characterized in that: described bungee group (4) is connected with the steel rope of described winch by pulley block (5).
5. the ejection system of miniature self-service aircraft according to claim 1 and 2, it is characterized in that: described guide rail (7) and auxiliary guide rail (11) are formed by plurality of sections of steel pipes (16) butt joint, one end of described steel pipe (16) is provided with screw rod (15), the outside of the other end is provided with interior Hexagonal jacket (18), the inboard is provided with negative thread (17), and the described screw rod (15) of last joint steel pipe can be screwed in the described negative thread (17) of back one joint steel pipe.
6. the ejection system of miniature self-service aircraft according to claim 1 and 2, it is characterized in that: the structure of each described supporting leg (8) is to be arranged with two sleeves (21) on connecting panel (20), be hinged with lock banking stop (23) on each described sleeve (21), be connected with bungee or spring (22) between the other end of lock banking stop (23) and the sleeve (21), insert respectively in two described sleeves (21) of described connecting panel (20) upper end of two supporting leg steel pipes (24), there is decorative pattern (19) upper end of two described supporting leg steel pipes (24) car respectively, the lower end of two described supporting leg steel pipes (24) is hinged with the supporting leg base plate (25) that can rotate around the axis respectively, described supporting leg base plate (25) is an one flat plate, described lock banking stop (23) is blocked the decorative pattern (19) of described supporting leg steel pipe (24) by the tension of described bungee or spring (22), prevent that described supporting leg steel pipe (24) from sliding.
7. the ejection system of miniature self-service aircraft according to claim 1 and 2, it is characterized in that: the screw rod (15) of the last joint steel pipe of described guide rail (7) and auxiliary guide rail (11) passes the mounting hole on the described connecting panel (20), be screwed in the described negative thread (17) of back one joint steel pipe, by supporting leg (8) supporting guide (7) and auxiliary guide rail (11).
8. the ejection system of miniature self-service aircraft according to claim 1 and 2, it is characterized in that: described bungee group (4) and described steel rope and describedly launch being connected and fixed of dolly (6) and be fitted with inner cone platform (28) in the pipe end that structure is India rubber tube (26), the taper hole that the pipe end of described India rubber tube (26) passes outer tube (27) make described in frustum (28) cooperate with described outer tube (27) and compress, described outer tube (27) is installed on the mount pad (30), described mount pad (30) is installed on the installation shaft (31), and described installation shaft (31) is connected with described steel rope or the described dolly (6) that launches.
9. the ejection system of miniature self-service aircraft according to claim 8 is characterized in that: the axial centre of frustum (28) is provided with tapped bore (29) in described.
10. the ejection system of miniature self-service aircraft according to claim 8, it is characterized in that: the arrangement prescription of described installation shaft (31) and described India rubber tube (26) when parallel, described installation shaft (31) can prevent described India rubber tube (26) from pipe end is disconnected when taking off described in frustum (28) skid off.The arrangement prescription of described installation shaft (31) and described India rubber tube (26) when vertical, on described installation shaft (31), be provided with prevent described India rubber tube (26) from pipe end is disconnected when taking off described in the baffle plate (32) that skids off of frustum (28).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201020241857XU CN201729276U (en) | 2010-06-30 | 2010-06-30 | Ejection system of small-sized unmanned aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201020241857XU CN201729276U (en) | 2010-06-30 | 2010-06-30 | Ejection system of small-sized unmanned aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201729276U true CN201729276U (en) | 2011-02-02 |
Family
ID=43520433
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201020241857XU Expired - Fee Related CN201729276U (en) | 2010-06-30 | 2010-06-30 | Ejection system of small-sized unmanned aircraft |
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| CN (1) | CN201729276U (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102616383A (en) * | 2012-04-19 | 2012-08-01 | 哈尔滨工业大学 | Multi-stage catapult-launching device |
| CN102923312A (en) * | 2012-10-18 | 2013-02-13 | 桂林鑫鹰电子科技有限公司 | Small take-off launch frame for unmanned aerial vehicle |
| CN103224032A (en) * | 2013-05-15 | 2013-07-31 | 郝南楠 | Portable ejection mechanism for unmanned aerial vehicle |
| CN103963989A (en) * | 2014-05-29 | 2014-08-06 | 贵州帝三数字技术有限公司 | Portable foldable electromagnetic catapult of unmanned aerial vehicle |
| WO2021142970A1 (en) * | 2020-01-15 | 2021-07-22 | 南京祖航航空科技有限公司 | Quick launcher for small unmanned aerial vehicle |
-
2010
- 2010-06-30 CN CN201020241857XU patent/CN201729276U/en not_active Expired - Fee Related
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102616383A (en) * | 2012-04-19 | 2012-08-01 | 哈尔滨工业大学 | Multi-stage catapult-launching device |
| CN102616383B (en) * | 2012-04-19 | 2014-08-13 | 哈尔滨工业大学 | Multi-stage catapult-launching device |
| CN102923312A (en) * | 2012-10-18 | 2013-02-13 | 桂林鑫鹰电子科技有限公司 | Small take-off launch frame for unmanned aerial vehicle |
| CN103224032A (en) * | 2013-05-15 | 2013-07-31 | 郝南楠 | Portable ejection mechanism for unmanned aerial vehicle |
| CN103224032B (en) * | 2013-05-15 | 2015-11-25 | 郝南楠 | A kind of Portable unmanned machine ejection mechanism |
| CN103963989A (en) * | 2014-05-29 | 2014-08-06 | 贵州帝三数字技术有限公司 | Portable foldable electromagnetic catapult of unmanned aerial vehicle |
| CN103963989B (en) * | 2014-05-29 | 2016-04-06 | 贵州帝三数字技术有限公司 | Portable folding type electromagnetic launch technology of unmanned aerial vehicle device |
| WO2021142970A1 (en) * | 2020-01-15 | 2021-07-22 | 南京祖航航空科技有限公司 | Quick launcher for small unmanned aerial vehicle |
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