CN219790561U - Waterproof unmanned aerial vehicle - Google Patents
Waterproof unmanned aerial vehicle Download PDFInfo
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- CN219790561U CN219790561U CN202320457818.0U CN202320457818U CN219790561U CN 219790561 U CN219790561 U CN 219790561U CN 202320457818 U CN202320457818 U CN 202320457818U CN 219790561 U CN219790561 U CN 219790561U
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Abstract
The utility model relates to a waterproof unmanned aerial vehicle, which comprises: the unmanned aerial vehicle comprises an unmanned aerial vehicle body, wherein an parachute landing mechanism is arranged at the top of the unmanned aerial vehicle body; undercarriage is connected to the bottom of unmanned aerial vehicle fuselage, set up gasbag connecting portion on the undercarriage, gasbag connecting portion demountable installation has the gasbag, the height of gasbag is less than unmanned aerial vehicle fuselage. According to the utility model, the unmanned aerial vehicle is ensured to fall at a smaller speed when the unmanned aerial vehicle is in operation and to be ejected out of the parachute during the crash, so that the falling kinetic energy of the unmanned aerial vehicle is prevented from being too large, the stable posture of the unmanned aerial vehicle body is ensured during the crash, the unmanned aerial vehicle is prevented from being overturned, and the set air bag is ensured to be capable of functioning. The gasbag set up in the below of unmanned aerial vehicle fuselage, when waterproof unmanned aerial vehicle falls, the gasbag can make the unmanned aerial vehicle fuselage floats, avoids intake in the unmanned aerial vehicle fuselage.
Description
Technical Field
The utility model relates to the field of unmanned aerial vehicle design, in particular to a waterproof unmanned aerial vehicle.
Background
At present, the unmanned plane can carry various loads to complete various complex tasks, and has wide application in various fields such as photography, pesticide spraying, fire prevention and disaster relief, communication, security and anti-terrorism, anti-drug and anti-smuggling, and the like.
Water often appears in some task scenes that are applied to unmanned aerial vehicle, at present, be limited by battery technology, unmanned aerial vehicle's duration has the defect, and unmanned aerial vehicle of mainstream has less duration to exceed 1 hour, and this has just limited unmanned aerial vehicle's range of motion, in the scene that has water, like surfing shooting, fishing ground monitoring are thrown something and are fed, often can meet unmanned aerial vehicle because of trouble or the unexpected scene of falling into in the water of duration, unmanned aerial vehicle's airborne component and power pack can all damage because of soaking to can not restore basically. There is among the prior art and configures the gasbag so that unmanned aerial vehicle can float the design of water, like a floatable waterproof unmanned aerial vehicle at the surface of water of application number CN201922422237.X, including unmanned aerial vehicle main part, buoyancy gasbag and reset spring, unmanned aerial vehicle main part's outside is fixed with the connecting rod, and the outside of connecting rod is fixed with the base, unmanned aerial vehicle main part's below hub connection has the paddle, and unmanned aerial vehicle main part's lower surface is provided with infrared sensor, the standing groove has been seted up to the inside of connecting rod, the outside butt fusion of connecting rod has the buffering gasbag, the inside of base is provided with buoyancy gasbag, and is connected with the air duct between buoyancy gasbag and the buffering gasbag, the blind groove has been seted up to unmanned aerial vehicle main part's inside, and the inside of blind groove is provided with the electro-magnet. This but float waterproof unmanned aerial vehicle at surface of water can float on the surface of water, is convenient for retrieve waterproof unmanned aerial vehicle in later stage, can reduce waterproof unmanned aerial vehicle's focus simultaneously, avoids waterproof unmanned aerial vehicle to take place to tip over under the unrestrained effect of wind, has improved the practicality of device. However, the unmanned aerial vehicle of this application does not consider unmanned aerial vehicle out of control's condition, and when unmanned aerial vehicle out of control, especially when the electric energy was used up, some components in the comparison file can't work, and the fuselage gesture is uncontrollable, and the impact force is big for the fuselage decline, all probably leads to the gasbag unable to play the guard action.
Disclosure of Invention
In order to solve the technical problems described above or at least partially solve the technical problems described above, the present utility model provides a waterproof unmanned aerial vehicle.
The utility model provides a waterproof unmanned aerial vehicle, comprising: the unmanned aerial vehicle comprises an unmanned aerial vehicle body, wherein an parachute landing mechanism is arranged at the top of the unmanned aerial vehicle body and used for ejecting a parachute when the unmanned aerial vehicle falls down so as to keep the unmanned aerial vehicle body stable in the falling process; undercarriage is connected to the bottom of unmanned aerial vehicle fuselage, set up gasbag connecting portion on the undercarriage, gasbag connecting portion demountable installation has the gasbag, the height of gasbag is less than unmanned aerial vehicle fuselage.
Still further, the parachuting mechanism includes: the parachute comprises a parachute body, a connecting seat and a catapult, wherein the connecting seat is arranged at the top of the unmanned aerial vehicle body, the connecting seat is connected with the parachute surface of the parachute through at least three parachute ropes, the gravity center of the unmanned aerial vehicle falls in a so-called area of a parachute rope connecting point, and the parachute surface of the parachute is arranged on the catapult.
Further, the ejector adopts any one of a pneumatic ejector, a gunpowder ejector or a mechanical spring ejector.
Furthermore, the trigger switch of the catapult is electrically connected with the catapult controller, the catapult controller and the trigger switch are electrically connected with a super capacitor for supplying power, and the super capacitor is connected with a power supply battery of the unmanned aerial vehicle so as to store the electric energy output by the power supply battery.
Furthermore, the ejection controller is connected with a power-down detection circuit, the power-down detection circuit is connected with a motor power input and a power input of a main control board where the unmanned aerial vehicle controller is located, and the power-down detection circuit is electrically connected with the super capacitor.
Still further, the ejection controller is connected with the unmanned aerial vehicle controller through a bus or a PWM port, and the unmanned aerial vehicle controller is electrically connected with the acceleration sensor and the attitude sensor.
Furthermore, the landing gear is provided with a wiring hole, two groups of wire sleeves are arranged outside the air bag in a surrounding mode, connecting wires are inserted into the wire sleeves, and the air bag is fixed by penetrating the wiring hole of the landing gear around the connecting wires inserted into each wire sleeve.
Compared with the prior art, the technical scheme provided by the embodiment of the utility model has the following advantages:
the waterproof unmanned aerial vehicle is provided with the parachute landing mechanism, the parachute landing mechanism works to eject the parachute when the unmanned aerial vehicle is crashed, on one hand, the unmanned aerial vehicle is ensured to fall at a smaller speed, the falling kinetic energy of the unmanned aerial vehicle is prevented from being too large, on the other hand, the stable posture of the unmanned aerial vehicle body is ensured in the process of crashing, the unmanned aerial vehicle is prevented from overturning, and the set air bag is ensured to be capable of functioning. The gasbag set up in the below of unmanned aerial vehicle fuselage, when waterproof unmanned aerial vehicle falls, the gasbag can make the unmanned aerial vehicle fuselage floats, avoids intake in the unmanned aerial vehicle fuselage.
In the utility model, the ejection controller, the trigger switch and the power failure detection circuit are powered by the super capacitor, and the super capacitor outputs stored electric energy when the unmanned aerial vehicle power supply battery is not powered, so that the ejector can work.
According to the utility model, the ejection controller is connected with the unmanned aerial vehicle controller through the bus or the PWM port, and when the unmanned aerial vehicle controller detects that the unmanned aerial vehicle is in a runaway state through the gesture sensor or the acceleration sensor, the ejection controller can be controlled to control the ejector to work, and the parachute can be started when the unmanned aerial vehicle is not in an abnormal state due to lack of electricity.
According to the utility model, the landing gear is provided with the wiring holes, the air bag is externally and circumferentially provided with the two groups of wire sleeves, the wire sleeves are internally inserted with the connecting wires, the connecting wires circumferentially inserted in each wire sleeve penetrate through the wiring holes of the landing gear to fix the air bag, and the fixing mode of the air bag is simple and effective.
According to the utility model, the air bag and the parachute are matched to realize water falling protection, and the unmanned aerial vehicle body can adopt a heat radiation design comprising heat radiation holes during design, so that the heat radiation problem caused by the sealed unmanned aerial vehicle body is avoided.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments consistent with the utility model and together with the description, serve to explain the principles of the utility model.
In order to more clearly illustrate the embodiments of the utility model or the technical solutions of the prior art, the drawings which are used in the description of the embodiments or the prior art will be briefly described, and it will be obvious to a person skilled in the art that other drawings can be obtained from these drawings without inventive effort.
Fig. 1 is a schematic view of a waterproof unmanned aerial vehicle provided by the utility model;
FIG. 2 is a cross-sectional view of the utility model providing a parachute landing mechanism employing a pneumatic ejector;
fig. 3 is a schematic diagram of a structure of an ejector control circuit of a waterproof unmanned aerial vehicle.
The reference numerals and meanings in the figures are as follows: 1. the unmanned aerial vehicle comprises an unmanned aerial vehicle body, 2, a parachute landing mechanism, 21, a parachute, 22, a connecting seat, 23, an ejector, 3, a landing gear, 4 and an air bag.
Detailed Description
For the purpose of making the objects, technical solutions and advantages of the embodiments of the present utility model more apparent, the technical solutions of the embodiments of the present utility model will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present utility model, and it is apparent that the described embodiments are some embodiments of the present utility model, but not all embodiments of the present utility model. All other embodiments, which can be made by those skilled in the art based on the embodiments of the utility model without making any inventive effort, are intended to be within the scope of the utility model.
It should be noted that, in this document, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising one … …" does not exclude the presence of other like elements in a process, method, article, or apparatus that comprises the element.
Referring to fig. 1, an embodiment of the present utility model provides a waterproof unmanned aerial vehicle, including:
the unmanned aerial vehicle comprises an unmanned aerial vehicle body 1, wherein an parachute landing mechanism 2 is arranged at the top of the unmanned aerial vehicle body 1, and the parachute landing mechanism 2 is used for ejecting a parachute 21 when the unmanned aerial vehicle crashes so as to keep the unmanned aerial vehicle body 1 stable in the falling process; unmanned aerial vehicle is in the crash in-process, can't provide the gesture of power control self, parachute landing mechanism 2 ensures on the one hand that unmanned aerial vehicle falls with less speed, on the other hand ensures in the crash in-process the gesture of unmanned aerial vehicle fuselage is stable, ensures that the gasbag 4 of setting can function.
In a specific implementation process, referring to fig. 2, the parachute landing mechanism 2 includes: the parachute comprises a parachute 21, a connecting seat 22 and a catapult 23, wherein the connecting seat 22 is arranged at the top of the unmanned aerial vehicle body 1, the connecting seat 22 is connected with parachute ropes of the parachute 21, the number of the parachute ropes of the parachute 21 is at least 3, the parachute ropes are uniformly connected with the connecting seat 22, and a parachute face of the parachute 21 is arranged on the catapult 23. The trigger switch of the catapult 23 is electrically connected with the catapult controller, the catapult controller and the trigger switch are electrically connected with a super capacitor for supplying power, the super capacitor is connected with a power supply battery of the unmanned aerial vehicle, and electric energy output by the power supply battery is stored.
The ejector 23 is any one of a pneumatic ejector, a gunpowder ejector or a mechanical spring ejector, and is used for ejecting the umbrella surface of the parachute 21. For different types of ejectors, the trigger switch employs different devices, such as: for a pneumatic catapult, the trigger switch adopts an electric air valve; for the gunpowder catapult, the trigger switch adopts an electronic igniter; for a mechanical spring ejector, the trigger switch adopts a spring latch controlled by a steering engine.
Taking a pneumatic ejector as an example, referring to fig. 2, the ejector includes a launch canister disposed in the connection seat 22, and the launch canister includes: the sliding cavity at the bottom and the accommodating chamber at the top are separated by a partition plate provided with perforations. The transmitting cylinder is internally provided with a piston in a sliding manner, specifically, the piston is I-shaped, the lower part of the piston is arranged in the sliding cavity in a sliding manner, the upper part of the piston is arranged in the accommodating chamber in a sliding manner, and the upper part of the piston is connected with the lower part of the piston through a connecting rod penetrating through the through hole. The umbrella surface of the parachute 21 is folded and arranged in the accommodating chamber, and in order to ensure the emitting effect of the umbrella surface, the umbrella surface wraps an emitting bag when folded, and the emitting bag is connected with the upper part of the piston through a connecting wire; the sliding cavity of the launching tube is connected with a pre-inflated air tank through a pipeline provided with an electric control air valve, the air tank is provided with an inflation inlet, and the air valve is arranged at the inflation inlet. The pneumatic catapult uses the electric control air valve as a trigger switch, the electric control air valve is electrically connected with an independent catapulting controller, the catapulting controller is electrically connected with a super capacitor for supplying power, and when the unmanned aerial vehicle loses power, the super capacitor supplies power for the catapulting controller and the electric control air valve, so that the catapulting device 23 can work.
Referring to fig. 3, the ejection controller is connected with a power-down detection circuit, the power-down detection circuit is connected with a power input of a motor and a power input of a main control board where the unmanned aerial vehicle controller is located to detect whether power is down, and the power-down detection circuit is electrically connected with the super capacitor. The power failure detection circuit adopts a current sensor, the current sensor is electrically connected with the ejection controller, and the ejection controller judges whether power failure occurs according to the detected current value. During the working period of the unmanned aerial vehicle, the power failure detection circuit detects that the unmanned aerial vehicle controller or the motor is powered down, and triggers the ejection controller to control the ejector 23 to eject the parachute 21.
In a preferred embodiment, the catapult controller is connected with the unmanned aerial vehicle controller through a bus or a PWM port, and the unmanned aerial vehicle controller can control the action of the catapult controller through bus communication or PWM signals. Specifically, the unmanned aerial vehicle controller detects when unmanned aerial vehicle out of control the ejection controller ejects the parachute, acceleration sensor and attitude sensor are connected to unmanned aerial vehicle controller electricity, unmanned aerial vehicle controller is according to the attitude sensor is measured unmanned aerial vehicle slope and is exceeded and presumes the inclination threshold value or downward acceleration exceeds and presumes acceleration threshold value when judging unmanned aerial vehicle out of control. Or, when the unmanned plane controller works, a heartbeat signal is sent to the ejection controller, and when the heartbeat signal stops accidentally and exceeds a set time, the ejection controller controls the ejector 23 to eject the parachute 21.
Set up undercarriage installation department on the 1 bottom of unmanned aerial vehicle fuselage, undercarriage installation department passes through bolt or grafting structure connection undercarriage 3, undercarriage 3 will unmanned aerial vehicle fuselage 1 supports to be higher than the height of gasbag 4, set up the gasbag connecting portion on the undercarriage 3, gasbag connecting portion demountable installation has gasbag 4. As a specific embodiment, the landing gear 3 is provided with a wiring hole, two groups of wire sleeves are arranged outside the air bag 4 in a surrounding manner, connecting wires are inserted in the wire sleeves, and the connecting wires inserted in the wire sleeves in a surrounding manner penetrate through the wiring hole of the landing gear 3 to fix the air bag 4.
In the embodiments provided in the present utility model, it should be understood that the disclosed apparatus may be implemented in other manners. For example, the above-described apparatus embodiments are merely illustrative, and for example, the described division of circuitry is merely a logical functional division, and there may be additional divisions when actually implemented, for example, multiple units or components may be combined or integrated into another system, or some features may be omitted, or not performed. Alternatively, the coupling shown or discussed as being coupled directly or indirectly to one another through some interface, device or unit, may be in the form of electrical, mechanical, or otherwise.
The foregoing is only a specific embodiment of the utility model to enable those skilled in the art to understand or practice the utility model. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the utility model. Thus, the present utility model is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.
Claims (6)
1. A waterproof unmanned aerial vehicle, comprising: the unmanned aerial vehicle comprises an unmanned aerial vehicle body (1), wherein an parachute landing mechanism (2) is arranged at the top of the unmanned aerial vehicle body (1), the parachute landing mechanism (2) comprises a catapult (23), a trigger switch of the catapult (23) is electrically connected with a catapult controller, the catapult controller is connected with a power-down detection circuit, the power-down detection circuit is connected with a motor power input and a power input of a main control board where the unmanned aerial vehicle controller is located, and the power-down detection circuit is electrically connected with a super capacitor; the ejection controller is electrically connected with the trigger switch and is used for supplying power to the super capacitor, the super capacitor is connected with a power supply battery of the unmanned aerial vehicle so as to store the electric energy output by the power supply battery, and the parachute landing mechanism (2) is used for ejecting a parachute (21) when the unmanned aerial vehicle crashes so as to enable the unmanned aerial vehicle body (1) to keep stable in posture in the falling process; landing gear (3) are connected to the bottom of unmanned aerial vehicle fuselage (1), set up gasbag connecting portion on landing gear (3), gasbag connecting portion demountable installation has gasbag (4), the height of gasbag (4) is less than unmanned aerial vehicle fuselage (1).
2. The waterproof unmanned aerial vehicle according to claim 1, wherein the parachuting mechanism (2) comprises: parachute (21), connecting seat (22) and catapult (23), connecting seat (22) set up in the top of unmanned aerial vehicle fuselage (1), connecting seat (22) are through at least three parachute line connection the umbrella face of parachute (21), and unmanned aerial vehicle focus falls in the so-called region of parachute line tie point, the umbrella face of parachute (21) set up in on catapult (23).
3. The waterproof unmanned aerial vehicle according to claim 2, wherein the ejector (23) is any one of a pneumatic ejector, a powder ejector, or a mechanical spring ejector.
4. A waterproof unmanned aerial vehicle according to claim 3, wherein the pneumatic ejector comprises a launch barrel arranged in the connecting seat (22), the launch barrel comprising: a sliding cavity at the bottom and a containing chamber at the top, wherein the sliding cavity and the containing chamber are separated by a partition plate provided with perforations; the transmitting cylinder is arranged in an I-shaped manner in a sliding manner, the lower part of the piston is arranged in the sliding cavity in a sliding manner, the upper part of the piston is arranged in the accommodating chamber in a sliding manner, and the upper part of the piston is connected with the lower part of the piston through a connecting rod penetrating through the through hole; the parachute (21) is arranged in the accommodating chamber in a folding way, the parachute cover wraps a transmitting bag when being folded, and the transmitting bag is connected with the upper part of the piston through a connecting wire; the sliding cavity of the launching tube is connected with a pre-inflated air tank through a pipeline provided with an electric control air valve, the air tank is provided with an inflation inlet, the air valve is arranged at the inflation inlet, and the electric control air valve is used as a trigger switch of the pneumatic ejector.
5. The waterproof unmanned aerial vehicle of claim 1, wherein the ejection controller is connected to the unmanned aerial vehicle controller via a bus or PWM port, and the unmanned aerial vehicle controller is electrically connected to the acceleration sensor and the attitude sensor.
6. The waterproof unmanned aerial vehicle according to claim 1, wherein the landing gear (3) is provided with a wiring hole, two groups of wire sleeves are arranged on the outer ring of the air bag (4) in a surrounding mode, connecting wires are inserted into the wire sleeves in a penetrating mode, and the connecting wires inserted into each wire sleeve in a surrounding mode penetrate through the wiring hole of the landing gear (3) to fix the air bag (4).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202320457818.0U CN219790561U (en) | 2023-03-09 | 2023-03-09 | Waterproof unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202320457818.0U CN219790561U (en) | 2023-03-09 | 2023-03-09 | Waterproof unmanned aerial vehicle |
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| Publication Number | Publication Date |
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| CN219790561U true CN219790561U (en) | 2023-10-03 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202320457818.0U Active CN219790561U (en) | 2023-03-09 | 2023-03-09 | Waterproof unmanned aerial vehicle |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116986036A (en) * | 2023-09-27 | 2023-11-03 | 杭州牧星科技有限公司 | Recovery system of fixed wing unmanned aerial vehicle |
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2023
- 2023-03-09 CN CN202320457818.0U patent/CN219790561U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116986036A (en) * | 2023-09-27 | 2023-11-03 | 杭州牧星科技有限公司 | Recovery system of fixed wing unmanned aerial vehicle |
| CN116986036B (en) * | 2023-09-27 | 2023-12-22 | 杭州牧星科技有限公司 | Recovery system of fixed wing unmanned aerial vehicle |
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