CN210653686U - Unmanned aerial vehicle inertial energy storage ejection system - Google Patents
Unmanned aerial vehicle inertial energy storage ejection system Download PDFInfo
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- CN210653686U CN210653686U CN201921911385.1U CN201921911385U CN210653686U CN 210653686 U CN210653686 U CN 210653686U CN 201921911385 U CN201921911385 U CN 201921911385U CN 210653686 U CN210653686 U CN 210653686U
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Abstract
The utility model relates to an inertial energy storage ejection system of an unmanned aerial vehicle, which comprises an ejection rack; the catapult rack is characterized in that a driving mechanism, a releasing mechanism and a catapult trolley are installed at the tail end of the catapult rack, a pulley is installed at the front end of the catapult rack, a buffering device and a supporting frame are installed at the front end of the catapult rack, the driving mechanism comprises a motor, a flywheel, a clutch and a belt collecting disc, the motor is installed on the catapult rack through a motor base, the flywheel is installed on an output shaft of the motor, the flywheel is connected with the belt collecting disc through the clutch, a belt is wound on the belt collecting disc, a rotating shaft. The utility model has the advantages that: such design has solved the possibility of ejecting heavy weight aircraft through the energy storage release of flywheel under the small volume condition and has guaranteed that the initial velocity when ejecting the beginning is lower and increase gradually, compares with traditional ejection system, greatly reduced to unmanned aerial vehicle's impact force in the twinkling of an eye, greatly prolonged unmanned aerial vehicle's life.
Description
Technical Field
The utility model relates to an aircraft technical field especially relates to an unmanned aerial vehicle inertial energy storage ejection system.
Background
At present, the takeoff of a small and medium-sized unmanned aerial vehicle is limited by a field, and an ejection device is mostly adopted to assist the takeoff of the unmanned aerial vehicle. The existing unmanned aerial vehicle ejection system has various forms, and has more application modes such as pneumatic ejection, electromagnetic ejection, spring ejection and the like; and these unmanned aerial vehicle launches need to accumulate certain energy in the process, then releases the energy totally and launches the unmanned aerial vehicle takeoff, and this must cause very big impulsive force to unmanned aerial vehicle, consequently makes unmanned aerial vehicle damage very easily.
SUMMERY OF THE UTILITY MODEL
The utility model aims to solve the technical problem that an unmanned aerial vehicle inertia energy storage ejection system is provided, solve the not enough of prior art.
The utility model provides an above-mentioned technical problem's technical scheme as follows: an inertial energy storage ejection system of an unmanned aerial vehicle comprises an ejection rack; actuating mechanism, release mechanism and ejection dolly are installed to the ejection rack tail end, pulley, buffer and support frame are installed to the ejection rack front end, actuating mechanism includes motor, flywheel, clutch and belt catch tray, the motor passes through the motor cabinet and installs on the ejection rack, install on the output shaft of motor the flywheel, the flywheel passes through the clutch with the belt catch tray is connected, around being equipped with the belt on the belt catch tray, the belt catch tray is kept away from one side of flywheel is equipped with the pivot, the pivot is passed through the bearing and is installed on the bearing frame, the bearing frame is installed on the ejection rack, the belt has walked around the pulley with the ejection dolly is connected.
The utility model has the advantages that: can drive the flywheel through the motor and rotate, the flywheel passes through the clutch and drives the belt catch tray rotation, the belt catch tray passes through the belt pulling and launches the dolly and move on the launching cradle, the belt rolling is on the belt catch tray simultaneously, when the belt just begins the rolling, the center of belt catch tray is less to the diameter of outermost circle belt, therefore the rolling speed is less, thereby the moving speed of dolly is less, along with the belt of rolling increases, the center of belt catch tray is to the diameter grow of outermost circle belt, consequently, the rolling speed increases, thereby the moving speed increase of dolly, such design has guaranteed that launch the initial velocity when beginning lower and increase gradually, compare with traditional ejection system, greatly reduced the impact force in the twinkling of an eye to unmanned aerial vehicle, unmanned aerial vehicle's life has greatly been prolonged.
Further: the ejection rack is characterized in that the number of the buffer devices is two, the two buffer devices are respectively arranged on two sides of the top of the ejection rack, each buffer device comprises a fixed block, a spring and a buffer block, the fixed blocks are fixedly arranged on the top of the ejection rack, the buffer blocks are in sliding connection with the ejection rack, and the fixed blocks are connected with the buffer blocks through the springs.
The beneficial effects of the further scheme are as follows: the buffer device has a simple structure, and can greatly reduce the impact force of the ejection trolley on the ejection rack in the ejection process.
Further: the support frame includes two bracing pieces, two the bracing piece is articulated with launching cradle both sides respectively.
The beneficial effects of the further scheme are as follows: the two supporting plates and the ground at the tail end of the catapult form a triangular structure, so that the catapult frame is stable when placed.
Further: the clutch comprises a first clutch gear and a second clutch gear, the first clutch gear is installed on one side, close to the belt collecting disc, of the flywheel, the second clutch gear is installed on one side, close to the flywheel, of the belt collecting disc, and the first clutch gear and the second clutch gear are meshed through sawteeth.
The beneficial effects of the further scheme are as follows: according to the clutch, the first clutch gear and the second clutch gear are meshed through the saw teeth, so that the first clutch gear and the second clutch gear can be well combined and separated, power can be reliably transmitted, and the reliability of a product is improved.
Further: and the ejection trolley is provided with a hook mechanism and a supporting structure for installing the unmanned aerial vehicle.
Drawings
Fig. 1 is a schematic structural view of an inertial energy storage ejection system of an unmanned aerial vehicle according to an embodiment of the present invention;
fig. 2 is a schematic structural diagram of a driving mechanism according to an embodiment of the present invention;
in the figure: 1. an ejection machine; 2. a drive mechanism; 21. a motor; 22. a flywheel; 23. a clutch; 131. a first clutch gear; 232. a second clutch gear; 24. a belt collection pan; 25. a motor base; 26. a belt; 27. a rotating shaft; 28. a bearing; 29. a bearing seat; 3. a release mechanism; 4. ejecting the trolley; 41. a hooking mechanism; 42. a support structure; 5. a pulley; 6. a buffer device; 61. a fixed block; 62. a spring; 63. a buffer block; 7. a support frame; 71. a support rod.
Detailed Description
The principles and features of the present invention are described below in conjunction with the following drawings, the examples given are only intended to illustrate the present invention and are not intended to limit the scope of the present invention.
As shown in fig. 1-2, an inertial energy storage ejection system for an unmanned aerial vehicle comprises an ejection rack 1; the tail end of the ejection frame 1 is provided with a driving mechanism 2, a release mechanism 3 and an ejection trolley 4; the front end of the ejection rack 1 is provided with a pulley 5, a buffer device 6 and a support frame 7; the driving mechanism 2 comprises a motor 21, a flywheel 22, a clutch 23 and a belt collecting disc 24, the motor 21 is installed on the ejection rack 1 through a motor base 25, the flywheel 22 is installed on an output shaft of the motor 21, the flywheel 22 is connected with the belt collecting disc 24 through the clutch 23, a belt 26 is wound on the belt collecting disc 24, a rotating shaft 27 is arranged on one side, away from the flywheel 22, of the belt collecting disc 24, the rotating shaft 27 is installed on a bearing block 29 through a bearing 28, the bearing block 29 is installed on the ejection rack 1, and the belt 26 is connected with the ejection trolley 4 by bypassing a pulley 5.
During the use, it is fixed with ejection trolley 4 through release mechanism 3 before launching, then fix unmanned aerial vehicle on ejection trolley 4, when unmanned aerial vehicle launches, release mechanism 3 release ejection trolley 4, can drive flywheel 22 through motor 21 and rotate, flywheel 22 drives belt catch tray 24 through clutch 23 and rotates, belt catch tray 24 passes through the belt 26 pulling ejection trolley 4 and moves on launching cradle 1, buffer 6 restricts ejection trolley 4 when ejection trolley 4 moves to launching cradle 1 front end, unmanned aerial vehicle launches and takes off.
Example two
As shown in fig. 1-2, an inertial energy storage ejection system for an unmanned aerial vehicle comprises an ejection rack 1; the tail end of the ejection frame 1 is provided with a driving mechanism 2, a release mechanism 3 and an ejection trolley 4; the front end of the ejection rack 1 is provided with a pulley 5, a buffer device 6 and a support frame 7; the driving mechanism 2 comprises a motor 21, a flywheel 22, a clutch 23 and a belt collecting disc 24, the motor 21 is installed on the ejection rack 1 through a motor base 25, the flywheel 22 is installed on an output shaft of the motor 21, the flywheel 22 is connected with the belt collecting disc 24 through the clutch 23, a belt 26 is wound on the belt collecting disc 24, a rotating shaft 27 is arranged on one side, away from the flywheel 22, of the belt collecting disc 24, the rotating shaft 27 is installed on a bearing block 29 through a bearing 28, the bearing block 29 is installed on the ejection rack 1, and the belt 26 is connected with the ejection trolley 4 by bypassing a pulley 5.
The two buffer devices 6 are respectively arranged on two sides of the top of the ejection frame 1, each buffer device 6 comprises a fixed block 61, a spring 62 and a buffer block 63, the fixed blocks 61 are fixedly arranged on the top of the ejection frame 1, the buffer blocks 63 are slidably connected with the ejection frame 1, and the fixed blocks 61 are connected with the buffer blocks 63 through the springs 62.
EXAMPLE III
As shown in fig. 1-2, an inertial energy storage ejection system for an unmanned aerial vehicle comprises an ejection rack 1; the tail end of the ejection frame 1 is provided with a driving mechanism 2, a release mechanism 3 and an ejection trolley 4; the front end of the ejection rack 1 is provided with a pulley 5, a buffer device 6 and a support frame 7; the driving mechanism 2 comprises a motor 21, a flywheel 22, a clutch 23 and a belt collecting disc 24, the motor 21 is installed on the ejection rack 1 through a motor base 25, the flywheel 22 is installed on an output shaft of the motor 21, the flywheel 22 is connected with the belt collecting disc 24 through the clutch 23, a belt 26 is wound on the belt collecting disc 24, a rotating shaft 27 is arranged on one side, away from the flywheel 22, of the belt collecting disc 24, the rotating shaft 27 is installed on a bearing block 29 through a bearing 28, the bearing block 29 is installed on the ejection rack 1, and the belt 26 is connected with the ejection trolley 4 by bypassing a pulley 5.
The support frame 7 comprises two support rods 71, and the two support rods 71 are respectively hinged with two sides of the ejection rack 1.
EXAMPLE III
As shown in fig. 1-2, an inertial energy storage ejection system for an unmanned aerial vehicle comprises an ejection rack 1; the tail end of the ejection frame 1 is provided with a driving mechanism 2, a release mechanism 3 and an ejection trolley 4; the front end of the ejection rack 1 is provided with a pulley 5, a buffer device 6 and a support frame 7; the driving mechanism 2 comprises a motor 21, a flywheel 22, a clutch 23 and a belt collecting disc 24, the motor 21 is installed on the ejection rack 1 through a motor base 25, the flywheel 22 is installed on an output shaft of the motor 21, the flywheel 22 is connected with the belt collecting disc 24 through the clutch 23, a belt 26 is wound on the belt collecting disc 24, a rotating shaft 27 is arranged on one side, away from the flywheel 22, of the belt collecting disc 24, the rotating shaft 27 is installed on a bearing block 29 through a bearing 28, the bearing block 29 is installed on the ejection rack 1, and the belt 26 is connected with the ejection trolley 4 by bypassing a pulley 5.
The clutch 23 includes a first clutch gear 231 and a second clutch gear 232, the first clutch gear 231 is installed on one side of the flywheel 22 close to the belt catch tray 24, the second clutch gear 232 is installed on one side of the belt catch tray 24 close to the flywheel 22, and the first clutch gear 231 and the second clutch gear 232 are engaged with each other by a serration.
Example four
As shown in fig. 1-2, an inertial energy storage ejection system for an unmanned aerial vehicle comprises an ejection rack 1; the tail end of the ejection frame 1 is provided with a driving mechanism 2, a release mechanism 3 and an ejection trolley 4; the front end of the ejection rack 1 is provided with a pulley 5, a buffer device 6 and a support frame 7; the driving mechanism 2 comprises a motor 21, a flywheel 22, a clutch 23 and a belt collecting disc 24, the motor 21 is installed on the ejection rack 1 through a motor base 25, the flywheel 22 is installed on an output shaft of the motor 21, the flywheel 22 is connected with the belt collecting disc 24 through the clutch 23, a belt 26 is wound on the belt collecting disc 24, a rotating shaft 27 is arranged on one side, away from the flywheel 22, of the belt collecting disc 24, the rotating shaft 27 is installed on a bearing block 29 through a bearing 28, the bearing block 29 is installed on the ejection rack 1, and the belt 26 is connected with the ejection trolley 4 by bypassing a pulley 5.
The ejection trolley 4 is provided with a hook mechanism 41 for mounting the unmanned aerial vehicle and a supporting structure 42.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential", and the like, indicate the orientation or positional relationship indicated based on the drawings, and are only for convenience of description and simplicity of description, and do not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore, should not be construed as limiting the present invention.
Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature. In the description of the present invention, "a plurality" means at least two, e.g., two, three, etc., unless specifically limited otherwise.
In the present invention, unless otherwise expressly stated or limited, the terms "mounted," "connected," and "fixed" are to be construed broadly and may, for example, be fixedly connected, detachably connected, or integrally formed; can be mechanically or electrically connected; they may be directly connected or indirectly connected through intervening media, or they may be connected internally or in any other suitable relationship, unless expressly stated otherwise. The specific meaning of the above terms in the present invention can be understood according to specific situations by those skilled in the art.
In the present application, unless expressly stated or limited otherwise, the first feature may be directly on or directly under the second feature or indirectly via intermediate members. Also, a first feature "on," "over," and "above" a second feature may be directly or diagonally above the second feature, or may simply indicate that the first feature is at a higher level than the second feature. A first feature being "under," "below," and "beneath" a second feature may be directly under or obliquely under the first feature, or may simply mean that the first feature is at a lesser elevation than the second feature.
In the description herein, references to the description of the term "one embodiment," "some embodiments," "an example," "a specific example," or "some examples," etc., mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the invention. In this specification, the schematic representations of the terms used above are not necessarily intended to refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples. Furthermore, various embodiments or examples and features of different embodiments or examples described in this specification can be combined and combined by one skilled in the art without contradiction.
Although embodiments of the present invention have been shown and described, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention, and that variations, modifications, substitutions and alterations can be made to the above embodiments by those of ordinary skill in the art without departing from the scope of the present invention.
Claims (5)
1. An inertial energy storage ejection system of an unmanned aerial vehicle is characterized by comprising an ejection rack (1); the tail end of the ejection frame (1) is provided with a driving mechanism (2), a release mechanism (3) and an ejection trolley (4); the front end of the ejection rack (1) is provided with a pulley (5), a buffer device (6) and a support frame (7); actuating mechanism (2) are including motor (21), flywheel (22), clutch (23) and belt catch tray (24), motor (21) are installed through motor cabinet (25) on launching cradle (1), install on the output shaft of motor (21) flywheel (22), flywheel (22) are passed through clutch (23) with belt catch tray (24) are connected, around being equipped with belt (26) on belt catch tray (24), belt catch tray (24) are kept away from one side of flywheel (22) is equipped with pivot (27), pivot (27) are installed on bearing frame (29) through bearing (28), install bearing frame (29) on launching cradle (1), belt (26) are walked around pulley (5) with launch dolly (4) and connect.
2. The inertial energy storage ejection system of an unmanned aerial vehicle as claimed in claim 1, wherein the number of the buffer devices (6) is two and the two buffer devices are respectively disposed on two sides of the top of the ejection frame (1), each buffer device (6) comprises a fixed block (61), a spring (62) and a buffer block (63), the fixed block (61) is fixedly mounted on the top of the ejection frame (1), the buffer block (63) is slidably connected with the ejection frame (1), and the fixed block (61) is connected with the buffer block (63) through the spring (62).
3. The inertial energy storage ejection system of an unmanned aerial vehicle as claimed in claim 1, wherein the support frame (7) comprises two support rods (71), and the two support rods (71) are respectively hinged with two sides of the ejection frame (1).
4. An unmanned aerial vehicle inertial energy storage ejection system according to claim 1, wherein the clutch (23) comprises a first clutch gear (231) and a second clutch gear (232), the first clutch gear (231) is installed on one side of the flywheel (22) close to the belt collecting tray (24), the second clutch gear (232) is installed on one side of the belt collecting tray (24) close to the flywheel (22), and the first clutch gear (231) and the second clutch gear (232) are engaged through saw teeth.
5. The inertial energy storage ejection system of an unmanned aerial vehicle as claimed in claim 1, wherein the ejection trolley (4) is provided with a hook mechanism (41) and a support structure (42) for mounting the unmanned aerial vehicle.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921911385.1U CN210653686U (en) | 2019-11-07 | 2019-11-07 | Unmanned aerial vehicle inertial energy storage ejection system |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921911385.1U CN210653686U (en) | 2019-11-07 | 2019-11-07 | Unmanned aerial vehicle inertial energy storage ejection system |
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| CN210653686U true CN210653686U (en) | 2020-06-02 |
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| CN201921911385.1U Active CN210653686U (en) | 2019-11-07 | 2019-11-07 | Unmanned aerial vehicle inertial energy storage ejection system |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112173154A (en) * | 2020-11-05 | 2021-01-05 | 湖南浩天翼航空技术有限公司 | Automatic unlocking device for ejection unmanned aerial vehicle |
| CN113753253A (en) * | 2021-09-24 | 2021-12-07 | 哈尔滨工程大学 | Unmanned aerial vehicle jettison device |
-
2019
- 2019-11-07 CN CN201921911385.1U patent/CN210653686U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112173154A (en) * | 2020-11-05 | 2021-01-05 | 湖南浩天翼航空技术有限公司 | Automatic unlocking device for ejection unmanned aerial vehicle |
| CN113753253A (en) * | 2021-09-24 | 2021-12-07 | 哈尔滨工程大学 | Unmanned aerial vehicle jettison device |
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