CN204956950U - Small -sized unmanned aerial vehicle ejector - Google Patents
Small -sized unmanned aerial vehicle ejector Download PDFInfo
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- CN204956950U CN204956950U CN201520633592.0U CN201520633592U CN204956950U CN 204956950 U CN204956950 U CN 204956950U CN 201520633592 U CN201520633592 U CN 201520633592U CN 204956950 U CN204956950 U CN 204956950U
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- aerial vehicle
- unmanned aerial
- adjustable support
- track
- hydraulic motor
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Abstract
The utility model relates to a small -sized unmanned aerial vehicle ejector, including hydraulic motor piston rod, elasticity preloading device, back adjustable support, dragging track, clamping device, preceding adjustable support, buffer, back adjustable support and preceding adjustable support articulate respectively the dragging track both ends comprise 4 telescopic rigidity poles, the hydraulic motor piston rod links to each other with elasticity preloading device, elasticity preloading device can remote control, the dragging track design is the ball slide rail, and the track can splice, and for the folded cascade track, orbital length is by unmanned aerial vehicle's complete machine weight and the initial velocity decision of taking off and requiring. This catapult can provide great elasticity in the short distance, occupation space is less, the performance is more stable, and can realize remote control, and is lower to the unmanned aerial vehicle weight and the place requirement of taking off to can improve unmanned aerial vehicle's operating efficiency.
Description
Technical field
The utility model relates to unmanned aerial vehicle ejecting technical field, is specifically related to a kind of novel unmanned aerial vehicle ejector.
Background technology
Due to SUAV (small unmanned aerial vehicle) have do not need special airport, motor-driven fast, use cost is low, safeguard and use the features such as simple, be therefore at home and abroad extensively employed, wherein the lift-off technology of unmanned plane occupies critical role in use unmanned plane process always.Present stage is less than 25m/s for takeoff speed, the mode of taking off that take-off weight is less than the SUAV (small unmanned aerial vehicle) of 100kg selects rubber-band ejection usually, in unmanned aerial vehicle ejecting take-off process, mainly the elastic potential energy that bungee stores is converted into the mechanical kinetic energy of unmanned plane, make the requirement speed accelerating to safe take-off in the unmanned plane short time, so the length of bungee in traditional ejection system needs several meters even tens meters long usually, floor area is large, expansion is removed and is received difficulty, standby for takeoff overlong time, also limit the take-off weight of unmanned plane in addition on the one hand, Fit Models is less.Relative to rubber-band ejection, fluid pressure type ejector, can provide larger elastic force in short range, the type catapult-launching gear take up room less, performance is more stable.
Utility model content
According to above technical matters, the purpose of this utility model is to provide a kind of SUAV (small unmanned aerial vehicle) ejector.
A kind of SUAV (small unmanned aerial vehicle) ejector, it comprises hydraulic motor piston bar, elastic force pre-tightening apparatus, rear adjustable support, dragging track, front adjustable support, holding device, shock absorber; Wherein front adjustable support and rear adjustable support are made up of 4 telescopic rigid rods, by length and the opening angle thereof of adjustable telescopic rod, regulate the elevation angle of ejector; Hydraulic motor piston bar is wherein connected with elastic force pre-tightening apparatus, and elastic force pre-tightening apparatus is made up of piezoelectric transducer, micro controller system, remote control switch receptor, electromagnetic relay, sleeve, spring, baffle plate and work shape push rod, and by lithium battery power supply; Remote control switch receptor can pass received signal, Long-distance Control launching cradle by bluetooth or number; Dragging track is designed to ball slide rail, and track can splice, and is two joint folding tracks, convenient transportation, and the length of track is determined by the complete machine weight of unmanned plane and the unmanned plane initial velocity required that takes off.
In described elastic force pre-tightening apparatus, spring is positioned at sleeve, can only move between hydraulic motor piston bar and work shape push rod, and the folding of electromagnetic relay is controlled by remote control switch, to control baffle plate upward movement, thus the spring reset be compressed before making it produces deformation, and promote work shape push rod simultaneously; Wherein work shape push rod one end contacts with sleeve inner spring, and the other end contacts with firm banking, and with one end of spring contact all the time in sleeve.
Described holding device, comprises the clamp of firm banking, stay bearing plate and angle adjustable; Described firm banking is designed to ball slide rail, and wherein firm banking is by ball and rail contact, by the rotation of ball, reduces the friction between firm banking and track.
Described clamp adjustable angle, before carrying out unmanned aerial vehicle ejecting, by the angle of the length and opening angle and clamp that adjust front adjustable support and rear adjustable support expansion link, what adjust unmanned plane launches the elevation angle.
The beneficial effects of the utility model are: this novel unmanned plane hydraulic catapult, and frame adopts aluminum alloy materials, and quality is light, launches great efforts, and take-off attitude is stablized, and success ratio of taking off is high; Control to open ejection switch by one-chip computer module on the one hand in addition, the automation mechanized operation of catapult-launching gear can be realized; Require lower to unmanned plane weight and take-off venue, and economic security, the operating efficiency of unmanned plane can be improved.
Accompanying drawing explanation
Fig. 1 is unmanned plane take-off launch frame integral structure schematic diagram.
Fig. 2 is elastic force pre-tightening apparatus schematic diagram.
Fig. 3 is the structural representation of holding device and track transmission.
Fig. 4 is collapsible dragging track partial schematic diagram.
In accompanying drawing, the corresponding relation of each component names and Reference numeral is:
1, hydraulic motor piston bar, 2, elastic force pre-tightening apparatus, 3, remote control switch receptor, 4, work shape push rod, 5, holding device, 6, shock absorber, 7, rear adjustable support, 8, dragging track, 9, front adjustable support, 10, piezoelectric transducer, 11, spring, 12, sleeve, 13, baffle plate, 14, micro controller system, 15, lithium cell, 16, electromagnetic relay, 17, clamp, 18, ball, 19, stay bearing plate, 20, firm banking, 21, hinge.
Detailed description of the invention
By reference to the accompanying drawings, the utility model is described in further details.
As shown in Figure 1, a kind of SUAV (small unmanned aerial vehicle) ejector, comprises hydraulic motor piston bar (1), elastic force pre-tightening apparatus (2), holding device (5), shock absorber (6), rear adjustable support (7), dragging track (8), front adjustable support (9); Described front adjustable support (9) and rear adjustable support (7) are all made up of telescopic bar; Described hydraulic motor piston bar (1) is connected with elastic force pre-tightening apparatus (2).
As shown in Figure 2, described elastic force pre-tightening apparatus (2) is by remote control switch receptor (3), work shape push rod (4), piezoelectric transducer (10), spring (11), sleeve (12), baffle plate (13), micro controller system (14) and electromagnetic relay (16) composition, and powered by lithium cell (15).Described remote control switch receptor (3) can pass received signal, Long-distance Control launching cradle by bluetooth or number; In described elastic force pre-tightening apparatus (2), spring (11) is positioned at sleeve (12), can only move between hydraulic motor piston bar (1) and work shape push rod (4), and the folding of electromagnetic relay (16) is controlled by remote control switch, to control baffle plate (13) upward movement, the generation deformation thus the spring be compressed before making it (11) resets, and promote work shape push rod (4) simultaneously; Wherein work shape push rod (4) one end contacts with sleeve (12) inner spring (11), the other end contacts with firm banking (20), and the one end contacted with spring (11) is all the time in sleeve (12).Described hydraulic motor piston bar (1) and elastic force pre-tightening apparatus (2) are installed on slide rail (8), and make the axis direction of hydraulic motor piston bar (1) spring (11) in elastic force pre-tightening apparatus (2), to promote spring (11).
As shown in Figure 3, described dragging track (8) is designed to ball slide rail, track can splice, be two joint folding tracks, centre is connected by hinge (21), to make launching cradle convenient transportation, the length of track is determined by the complete machine weight of unmanned plane and the unmanned plane initial velocity required that takes off.Described holding device (5), comprises the clamp (17) of angle adjustable, stay bearing plate (19), and firm banking (20); The angle of described clamp (17) and horizontal surface and to clamp angle all adjustable; Described firm banking (20) is designed to ball slide rail, wherein firm banking (20) is contacted with track (8) by ball, by the rotation of ball, reduce the friction between firm banking (20) and dragging track (8).Described clamp (17) adjustable angle, before launching unmanned plane, by the angle of the length and opening angle and clamp (17) that adjust front adjustable support (9) and rear adjustable support (7) expansion link, what adjust unmanned plane launches the elevation angle.
As shown in Figures 2 and 3, first fixed-wing unmanned plane is positioned on clamp (17) by the utility model, by angle and the front adjustable support (9) of adjustment clamp (17), the length of rear adjustable support (7) expansion link and opening angle thereof, what adjust unmanned plane launches the elevation angle, then primer fluid pressure motor, make the spring (11) in hydraulic motor piston bar (1) promotion elastic force pre-tightening apparatus (2), spring (11) is compressed under the effect of hydraulic motor piston bar (1), because hydraulic motor piston bar (1) is contacted with the spring (11) of elastic force pre-tightening apparatus (2) by piezoelectric transducer (10), so the pressure signal of hydraulic motor piston bar (1) can be converted into electric signal by piezoelectric transducer (10) comparatively accurately, this electric signal passes to the micro controller system (14) having write program after analogue to digital conversion, after pressure reaches required size, can Long-distance Control micro controller system (14) by long-range opening the light, thus make micro controller system (14) control electromagnetic relay (16) open spring stop (13), spring (11) starts to promote push rod (4), holding device (5) is made to obtain a larger acceleration/accel instantaneously, and start to travel forward along the slideway on guide-rail plate (8), when holding device (5) arrives way end, due to the effect of shock absorber (6), holding device (5) slows down instantaneously, unmanned plane moves forward under the effect of inertia, reach the object of catapult-assisted take-off.
More than show and describe groundwork of the present utility model; principal character and advantage of the present utility model; under the prerequisite not departing from the utility model spirit and scope, the utility model also has various changes and modifications, and these changes and improvements all fall into claimed scope of the present utility model.
Claims (4)
1. a SUAV (small unmanned aerial vehicle) ejector, is characterized in that: comprise hydraulic motor piston bar, elastic force pre-tightening apparatus, rear adjustable support, dragging track, front adjustable support, holding device, shock absorber; Wherein front adjustable support and rear adjustable support are made up of 4 telescopic rigid rods, by length and the opening angle thereof of adjustable telescopic rod, regulate the elevation angle of ejector; Hydraulic motor piston bar is wherein connected with elastic force pre-tightening apparatus, and elastic force pre-tightening apparatus is made up of piezoelectric transducer, micro controller system, remote control switch receptor, electromagnetic relay, sleeve, spring, baffle plate and work shape push rod, and by lithium battery power supply; Remote control switch receptor can pass received signal, Long-distance Control launching cradle by bluetooth or number; Dragging track is designed to ball slide rail, and track can splice, and is two joint folding tracks, convenient transportation, and the length of track is determined by the complete machine weight of unmanned plane and the unmanned plane initial velocity required that takes off.
2. a kind of SUAV (small unmanned aerial vehicle) ejector according to claim 1, it is characterized in that: in described elastic force pre-tightening apparatus, spring is positioned at sleeve, can only move between hydraulic motor piston bar and work shape push rod, and the folding of electromagnetic relay is controlled by remote control switch, to control baffle plate upward movement, thus the spring reset be compressed before making it produces deformation, and promotes work shape push rod simultaneously; Wherein work shape push rod one end contacts with sleeve inner spring, and the other end contacts with firm banking, and with one end of spring contact all the time in sleeve.
3. a kind of SUAV (small unmanned aerial vehicle) ejector according to claim 1, is characterized in that: described holding device, comprises the clamp of firm banking, stay bearing plate and angle adjustable; Described firm banking is designed to ball slide rail, and wherein firm banking is contacted with dragging track by ball, by the rotation of ball, reduces the friction between firm banking and dragging track.
4. a kind of SUAV (small unmanned aerial vehicle) ejector according to claim 3, it is characterized in that: described clamp adjustable angle, before carrying out unmanned aerial vehicle ejecting, by the angle of the length and opening angle and clamp that adjust front adjustable support and rear adjustable support expansion link, what adjust unmanned plane launches the elevation angle.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520633592.0U CN204956950U (en) | 2015-08-17 | 2015-08-17 | Small -sized unmanned aerial vehicle ejector |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520633592.0U CN204956950U (en) | 2015-08-17 | 2015-08-17 | Small -sized unmanned aerial vehicle ejector |
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| Publication Number | Publication Date |
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| CN204956950U true CN204956950U (en) | 2016-01-13 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201520633592.0U Expired - Fee Related CN204956950U (en) | 2015-08-17 | 2015-08-17 | Small -sized unmanned aerial vehicle ejector |
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| CN (1) | CN204956950U (en) |
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105599917A (en) * | 2016-02-29 | 2016-05-25 | 郑州彩通科技股份有限公司 | Towing and carrying cart for catapult unmanned aerial vehicle |
| CN105775154A (en) * | 2016-05-12 | 2016-07-20 | 孙立民 | General launching platform for unmanned aerial vehicle |
| CN105799948A (en) * | 2016-03-18 | 2016-07-27 | 北京理工大学 | Catapult of flywheel-type high-speed unmanned aerial vehicle |
| CN106114890A (en) * | 2016-07-15 | 2016-11-16 | 天峋（常州）智能科技有限公司 | A kind of SUAV catapult-launching gear and unmanned plane takeoff method |
| CN106428604A (en) * | 2016-11-16 | 2017-02-22 | 北京韦加无人机科技股份有限公司 | Launching frame and system for launching unmanned aerial vehicle |
| CN107600449A (en) * | 2017-09-06 | 2018-01-19 | 哈尔滨工业大学 | A kind of unmanned aerial vehicle ejecting device |
| 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 |
| CN108298107A (en) * | 2018-03-19 | 2018-07-20 | 中国科学院光电研究院 | A kind of small drone high ejection device |
| CN108639369A (en) * | 2018-04-27 | 2018-10-12 | 宋忠春 | A kind of model plane JATO engine |
| CN110920924A (en) * | 2019-12-28 | 2020-03-27 | 北京工业大学 | Auxiliary hydraulic ejection device for unmanned aerial vehicle |
| CN110920925A (en) * | 2019-12-28 | 2020-03-27 | 北京工业大学 | Pneumatic auxiliary ejection device of unmanned aerial vehicle |
| CN113820389A (en) * | 2021-06-30 | 2021-12-21 | 天津中德应用技术大学 | Outer wall finish coat detection device and detection method based on unmanned aerial vehicle |
-
2015
- 2015-08-17 CN CN201520633592.0U patent/CN204956950U/en not_active Expired - Fee Related
Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105599917A (en) * | 2016-02-29 | 2016-05-25 | 郑州彩通科技股份有限公司 | Towing and carrying cart for catapult unmanned aerial vehicle |
| CN105799948A (en) * | 2016-03-18 | 2016-07-27 | 北京理工大学 | Catapult of flywheel-type high-speed unmanned aerial vehicle |
| CN105775154A (en) * | 2016-05-12 | 2016-07-20 | 孙立民 | General launching platform for unmanned aerial vehicle |
| CN106114890B (en) * | 2016-07-15 | 2019-04-02 | 天峋（常州）智能科技有限公司 | A kind of small drone catapult-launching gear and unmanned plane takeoff method |
| CN106114890A (en) * | 2016-07-15 | 2016-11-16 | 天峋（常州）智能科技有限公司 | A kind of SUAV catapult-launching gear and unmanned plane takeoff method |
| CN106428604A (en) * | 2016-11-16 | 2017-02-22 | 北京韦加无人机科技股份有限公司 | Launching frame and system for launching unmanned aerial vehicle |
| CN107600449A (en) * | 2017-09-06 | 2018-01-19 | 哈尔滨工业大学 | A kind of unmanned aerial vehicle ejecting device |
| 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 |
| CN108298107A (en) * | 2018-03-19 | 2018-07-20 | 中国科学院光电研究院 | A kind of small drone high ejection device |
| CN108298107B (en) * | 2018-03-19 | 2024-01-30 | 中国科学院光电研究院 | High-altitude missile shooting device of small unmanned aerial vehicle |
| CN108639369A (en) * | 2018-04-27 | 2018-10-12 | 宋忠春 | A kind of model plane JATO engine |
| CN110920924A (en) * | 2019-12-28 | 2020-03-27 | 北京工业大学 | Auxiliary hydraulic ejection device for unmanned aerial vehicle |
| CN110920925A (en) * | 2019-12-28 | 2020-03-27 | 北京工业大学 | Pneumatic auxiliary ejection device of unmanned aerial vehicle |
| CN113820389A (en) * | 2021-06-30 | 2021-12-21 | 天津中德应用技术大学 | Outer wall finish coat detection device and detection method based on unmanned aerial vehicle |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| 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: 20160113 Termination date: 20160817 |