CN201380967Y - Takeoff ejector rack of small-sized pilotless aircraft - Google Patents
Takeoff ejector rack of small-sized pilotless aircraft Download PDFInfo
- Publication number
- CN201380967Y CN201380967Y CN200920107578U CN200920107578U CN201380967Y CN 201380967 Y CN201380967 Y CN 201380967Y CN 200920107578 U CN200920107578 U CN 200920107578U CN 200920107578 U CN200920107578 U CN 200920107578U CN 201380967 Y CN201380967 Y CN 201380967Y
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- pin
- dolly
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- takes
- support
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Abstract
The utility model relates to a takeoff ejector rack of a small-sized pilotless aircraft, which is characterized in that the takeoff ejector rack comprises a support, wherein the front end of the support is provided with a shock absorbing seat and a change gear, the rear end is provided with a lock seat and a first hook, a slide rail is arranged on the support, a trolley is slidingly arranged on the slide rail, the front end of the trolley is provided with a shock absorbing block corresponding to the shock absorbing seat and a second hook which is connected with the first hook through a rubber band, the rubber band is supported by the change gear, and the rear end of the trolley is provided with a lock part which can lock the trolley on the slide rail and corresponds to the lock seat. A movable impact rod is further longitudinally arranged on the trolley, a pull pin is transversely arranged corresponding to the impact rod, the impact rod is connected with the pull pin through a guy, the aircraft is locked through the pull pin on the trolley, when the aircraft is located in a lock state, the impact rod stretches the front end of the trolley. Therefore, the takeoff ejector rack of the small-sized pilotless aircraft is particularly suitable to take off without runways for sliding devices which are the small-sized pilotless aircraft or model airplanes and the like.
Description
Technical field
The utility model relates to a kind of aircraft launching apparatus, particularly about a kind of launching cradle that takes off of miniature self-service aircraft.
Background technology
At the characteristic of low-altitude remote sensing, when rising and falling in the field, the miniature self-service aircraft do not have taking off of special-purpose runway, particularly aircraft, and the method in past is normally used hand-thrown, perhaps provides power with hydraulic pressure or pneumatic mode for taking off.The artificial property and the randomness of hand-thrown are all very big, depend merely on the experience of throwing hand, and target is difficult to hold, and success ratio is lower, and the dynamics of hand-thrown is also very little in addition, and the power of taking off of aircraft is not enough.Hydraulic pressure or the pneumatic energy resource consumption type equipment that belongs to.
Summary of the invention
At the problems referred to above, the purpose of this utility model is the launching cradle that takes off that proposes a kind of miniature self-service aircraft.
For achieving the above object, the utility model is taked following technical scheme: a kind of launching cradle that takes off of miniature self-service aircraft, it comprises a support, described support front end is provided with shockproof mount and change gear, the rear end is provided with the locking seat and first hook, be provided with slide rail above the support, the sliding dolly of establishing on the described slide rail, the front end of described dolly is provided with the cooresponding snubber block of described shockproof mount with described first hook and links up with by rubber reinforcement bonded assembly second, described rubber reinforcement is supported by described change gear, the rear end of described dolly be provided with dolly can be locked on the described slide rail with the cooresponding locking piece of described locking seat, also be vertically arranged with movable drop bar on the described dolly, with described drop bar accordingly, be horizontally arranged with and draw pin, described drop bar connects by backguy with corresponding described the drawing between pin that is provided with, and aircraft is fixed by the described lock that draws, when aircraft was in the lock state, described drop bar stretched out the front end of described dolly.
Described change gear is arranged on the front end of described shockproof mount.
Described shockproof mount comprises that two are arranged on the crossbeam on the described support, is supported with spring between the two described crossbeams.
Locking seat on the described support comprises that one is arranged on the crossbeam on the described support, and described crossbeam is provided with the spanner of a pin-and-hole and an activity; Locking piece on the described dolly comprise with described crossbeam on pin-and-hole bonded assembly pin, comprise the lock that hooks described spanner.
Described spanner is provided with pin-and-hole, and the pin-and-hole of described spanner is connected by another pin-and-hole that is provided with on pin and the described crossbeam.
By the described drop bar of described backguy bonded assembly with draw pin to be provided with two covers altogether, and on described dolly, be symmetrical arranged.
The utility model is owing to take above technical scheme, and it has the following advantages: 1, the utility model is provided with an elastomeric element, and elastic energy is converted into kinetic energy, and aircraft is discharged, and is simple in structure, and energy resource consumption is little, belongs to the economizing type product.2, the utility model utilizes dolly to slide on slide rail, aircraft is locked on the dolly, produce motional inertia with dolly, at the slide rail front end damping part is set, when dolly is stopped suddenly, aircraft moment release, under effect of inertia, break away from dolly, acceleration is taken off, and this mode of utilizing inertia to take off compares with artificial mode of throwing, and is comparatively laborsaving.3, the utility model is provided with Lock Part at the afterbody of dolly, one place is locked in dolly on the support by spanner, one place is locked in dolly on the support by pin, one place is locked in spanner on the support by pin, the retrocession mode is hurted sb.'s feelings even if make dolly also can not eject under strong elastomeric element pulling force energetically.Therefore the utility model is particularly suitable for the running take off of miniature device.
Description of drawings
Fig. 1 is that the master of the utility model support looks scheme drawing
Fig. 2 is the schematic top plan view of Fig. 1
Fig. 3 is the shockproof mount scheme drawing of support front end
Fig. 4 is the change gear scheme drawing of shockproof mount front end
Fig. 5 is the locking seat scheme drawing of back-end support
Fig. 6 is the scheme drawing that the support upper end base is provided with dolly
Fig. 7 is the vehicle structure scheme drawing
Fig. 8 is the scheme drawing that sets up aircraft on the utility model
The specific embodiment
Below in conjunction with drawings and Examples the utility model is described in detail.
Basic functional principle of the present utility model is: utilize elastomeric element to produce elastic force, slide unit is quickened on slide rail to front slide, aircraft is locked on the slide unit, when slide unit slides into track end, releasing mechanism discharges blocked aircraft, and aircraft takes off under self power and effect of inertia.A concrete embodiment is:
As shown in Figure 1 and Figure 2, it comprises a support 1 with certain-length and elevation angle, and the elevation angle of support 1 can be regulated by the rack leg of bottom.Support 1 top is provided with two parallel slide rails 2, and the support 1 of slide rail 2 front ends is provided with a shockproof mount 3 and a change gear 4.As shown in Figure 3, shockproof mount 3 comprises that two crossbeams, 31, two crossbeams 31 are supported on the support 1, are connected with several damping springs 32 between two crossbeams 31.As Fig. 2, shown in Figure 4, change gear 4 comprises that a movable pulley 41 and is connected the wheel shaft 42 on the support 1, and change gear 4 the bests are arranged on the front end of shockproof mount 3, and turning to the track of slide rail 2 of pulley 41 is equidirectional.
As Fig. 1, shown in Figure 5, be provided with locking seat 5 in support 1 rear end, locking seat 5 is used for the slide unit on the slide rail 2 is locked.Locking seat 5 comprises that one is fixed on the locking crossbeam 51 on the support 1, the two ends of locking crossbeam 51 are provided with two pin-and-holes 52, the middle part connects a hook spanner 53 rotationally by pin, the handle of hook spanner 53 is provided with one or two pin-and-hole 54, locks crossbeam 51 accordingly with pin-and-hole 54 positions and is provided with pin-and-hole 54 '.The bottom of locking crossbeam 51 also is provided with one first hook 55.
As Fig. 6, shown in Figure 7, slide rail 2 is provided with a dolly 6 as slide unit, and the rear end of dolly 6 is provided with and locks the pin-and-hole 52 cooresponding pin-and-holes 52 ' on the crossbeam 51, is provided with and the cooresponding lock 53 ' in hook spanner 53 positions.Pass cooresponding pin-and-hole 52 and pin-and-hole 52 ' with pin, hook lock 53 ', just dolly has been locked on the slide rail by second class protection with hook spanner 53; Pin-and-hole 54 ' on pin-and-hole on the hook spanner 53 54 and the cooresponding locking crossbeam 51 with the pin locking, has just reached the effect of three-level protective more in addition.The positive front end of dolly 6 is provided with several snubber blocks 7, and snubber block 7 is corresponding with shockproof mount 3, and when dolly 6 slided into the slide rail front end, snubber block 7 struck on the shockproof mount 3, made the dolly damping.Be connected a rubber reinforcement 9 between the front end of dolly 6 also is provided with one second hook, 8, the second hooks 8 and first links up with 55, rubber reinforcement 9 is supported by change gear 4 simultaneously.The car body of dolly 6 be provided with two can longitudinally-moving drop bar 10, corresponding with two drop bars 10, on the car body of dolly 6, be horizontally arranged with two and draw pin 11.Get wherein a drop bar 10 with wherein one draw pin 11 as one group, preferably each other two of offside be one group, link to each other with backguy 12, another group is provided with too.Draw pin 11 to be used for aircraft 13 is locked onto dolly 6 (as shown in Figure 8) when not working, drop bar 10 vertically moves along car body during work, drives backguy 12 and will draw pin 11 to extract when its displacement, makes the aircraft release.When aircraft was in the lock state, the front end of drop bar 10 will stretch out a car body part, was longer than snubber block 7, when dolly 6 forward during slippage, drop bar 10 takes the lead in striking on the shockproof mount 3, displacement backward, make the aircraft release, snubber block 7 bumps against on the shockproof mount 3 then, makes the dolly damping.
As shown in Figure 8, before the release, ajust the direction of support 1, adjust the elevation angle according to wind direction.Dolly 6 is placed the rear end of slide rail 2, pull hook spanner 53, gib head is hooked on the lock 53 ' of dolly, and passes pin-and-hole 52 and pin-and-hole 52 ' with pin, dolly 6 is fixing.Hook spanner 53 is by passing the pin locking of pin-and-hole 54 and pin-and-hole 54 '.After fixing dolly 6, walk around change gear 4 between 55 at second hook, 8 and first hook and strain rubber reinforcements 9, rubber reinforcement 9 also can be good at bolt before the fixing dolly.Aircraft 13 is locked on the dolly 6 by drawing pin 11, and the work of locking aircraft also can be done before dolly locks onto on the slide rail, just can start the driving engine on the aircraft after aircraft locks.After above-mentioned dead work is carried out, listen instruction to pull out pin on pin on pin-and-hole 52, the pin-and-hole 52 ' and pin-and-hole 54, the pin-and-hole 54 ' earlier, pull open hook spanner 53 then, discharge dolly 6, dolly 6 under the pulling force of rubber reinforcement 9 fast to front slide.When dolly slided into the slide rail front end, drop bar 10 took the lead in striking on the support, displacement backward.Drop bar 10 displacement time pulling backguy 12 backward will draw pin 11 to extract, the aircraft release.Meanwhile, the snubber block 7 of dolly strikes on the shockproof mount 3, and dolly is cushioned and stops, and under effect of inertia, quickens to fly away from dolly after the aircraft release.
Claims (10)
1, the launching cradle that takes off of miniature self-service aircraft, it is characterized in that: it comprises a support, described support front end is provided with shockproof mount and change gear, the rear end is provided with the locking seat and first hook, be provided with slide rail above the support, the sliding dolly of establishing on the described slide rail, the front end of described dolly is provided with the cooresponding snubber block of described shockproof mount with described first hook and links up with by rubber reinforcement bonded assembly second, described rubber reinforcement is supported by described change gear, the rear end of described dolly be provided with dolly can be locked on the described slide rail with the cooresponding locking piece of described locking seat, also be vertically arranged with movable drop bar on the described dolly, with described drop bar accordingly, be horizontally arranged with and draw pin, described drop bar connects by backguy with described the drawing between pin of corresponding setting, aircraft is fixed by the described lock that draws, and when aircraft was in the lock state, described drop bar stretched out the front end of described dolly.
2, the launching cradle that takes off of miniature self-service aircraft as claimed in claim 1, it is characterized in that: described change gear is arranged on the front end of described shockproof mount.
3, the launching cradle that takes off of miniature self-service aircraft as claimed in claim 1 is characterized in that: described shockproof mount comprises that two are arranged on the crossbeam on the described support, is supported with spring between the two described crossbeams.
4, the launching cradle that takes off of miniature self-service aircraft as claimed in claim 2 is characterized in that: described shockproof mount comprises that two are arranged on the crossbeam on the described support, is supported with spring between the two described crossbeams.
5, as the launching cradle that takes off of claim 1 or 2 or 3 or 4 described miniature self-service aircrafts, it is characterized in that: the locking seat on the described support comprises that one is arranged on the crossbeam on the described support, and described crossbeam is provided with the spanner of a pin-and-hole and an activity; Locking piece on the described dolly comprise with described crossbeam on pin-and-hole bonded assembly pin, comprise the lock that hooks described spanner.
6, as the launching cradle that takes off of claim 1 or 2 or 3 or 4 described miniature self-service aircrafts, it is characterized in that: described spanner is provided with pin-and-hole, and the pin-and-hole of described spanner is connected by another pin-and-hole that is provided with on pin and the described crossbeam.
7, the launching cradle that takes off of miniature self-service aircraft as claimed in claim 5, it is characterized in that: described spanner is provided with pin-and-hole, and the pin-and-hole of described spanner is connected by another pin-and-hole that is provided with on pin and the described crossbeam.
8, as the launching cradle that takes off of claim 1 or 2 or 3 or 4 described miniature self-service aircrafts, it is characterized in that: by the described drop bar of described backguy bonded assembly with draw pin to be provided with two covers altogether, and on described dolly, be symmetrical arranged.
9, the launching cradle that takes off of miniature self-service aircraft as claimed in claim 5 is characterized in that: by the described drop bar of described backguy bonded assembly with draw pin to be provided with two covers altogether, and on described dolly, be symmetrical arranged.
10, the launching cradle that takes off of miniature self-service aircraft as claimed in claim 6 is characterized in that: by the described drop bar of described backguy bonded assembly with draw pin to be provided with two covers altogether, and on described dolly, be symmetrical arranged.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200920107578U CN201380967Y (en) | 2009-04-28 | 2009-04-28 | Takeoff ejector rack of small-sized pilotless aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200920107578U CN201380967Y (en) | 2009-04-28 | 2009-04-28 | Takeoff ejector rack of small-sized pilotless aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201380967Y true CN201380967Y (en) | 2010-01-13 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN200920107578U Expired - Fee Related CN201380967Y (en) | 2009-04-28 | 2009-04-28 | Takeoff ejector rack of small-sized pilotless aircraft |
Country Status (1)
| Country | Link |
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| CN (1) | CN201380967Y (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102259705A (en) * | 2011-06-09 | 2011-11-30 | 刘忠德 | Aircraft launching steam ejection boosting device |
| CN102530260A (en) * | 2010-12-20 | 2012-07-04 | 西安韦德沃德航空科技有限公司 | Method and system for short-distance taking off of unmanned aerial vehicles |
| CN104015934A (en) * | 2014-07-02 | 2014-09-03 | 张峰 | Aviation station for flying airplane by ground-based track catapult locomotive replacing undercarriage |
| CN104071347A (en) * | 2014-06-30 | 2014-10-01 | 中国人民解放军国防科学技术大学 | Folding unmanned aerial vehicle launch frame based on ejection of rubber band |
| CN105667789A (en) * | 2016-01-13 | 2016-06-15 | 中国科学院自动化研究所 | Universal type elastic potential energy mechanical catapult for single tandem wing unmanned aerial vehicle with rear propeller |
| CN114291247A (en) * | 2022-01-20 | 2022-04-08 | 北京航空航天大学 | Foldable full-motion film wing micro unmanned aerial vehicle system |
| CN116642722A (en) * | 2023-07-27 | 2023-08-25 | 哈尔滨工程大学 | Motion simulation rotary accelerating device of non-rotary body aircraft on water |
-
2009
- 2009-04-28 CN CN200920107578U patent/CN201380967Y/en not_active Expired - Fee Related
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102530260A (en) * | 2010-12-20 | 2012-07-04 | 西安韦德沃德航空科技有限公司 | Method and system for short-distance taking off of unmanned aerial vehicles |
| CN102259705A (en) * | 2011-06-09 | 2011-11-30 | 刘忠德 | Aircraft launching steam ejection boosting device |
| CN104071347A (en) * | 2014-06-30 | 2014-10-01 | 中国人民解放军国防科学技术大学 | Folding unmanned aerial vehicle launch frame based on ejection of rubber band |
| CN104071347B (en) * | 2014-06-30 | 2017-01-25 | 中国人民解放军国防科学技术大学 | Folding unmanned aerial vehicle launch frame based on ejection of rubber band |
| CN104015934A (en) * | 2014-07-02 | 2014-09-03 | 张峰 | Aviation station for flying airplane by ground-based track catapult locomotive replacing undercarriage |
| CN104015934B (en) * | 2014-07-02 | 2015-12-30 | 张峰 | The aviation station of aircraft let fly away by the continental rise orbit shot locomotive substituting alighting gear |
| CN105667789A (en) * | 2016-01-13 | 2016-06-15 | 中国科学院自动化研究所 | Universal type elastic potential energy mechanical catapult for single tandem wing unmanned aerial vehicle with rear propeller |
| CN105667789B (en) * | 2016-01-13 | 2017-12-05 | 中国科学院自动化研究所 | The rearmounted single string universal elastic potential energy mechanical ejection device of wing unmanned plane of propeller |
| CN114291247A (en) * | 2022-01-20 | 2022-04-08 | 北京航空航天大学 | Foldable full-motion film wing micro unmanned aerial vehicle system |
| CN116642722A (en) * | 2023-07-27 | 2023-08-25 | 哈尔滨工程大学 | Motion simulation rotary accelerating device of non-rotary body aircraft on water |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20100113 Termination date: 20120428 |