Multi-rotor unmanned aerial vehicle for artificial precipitation enhancement

Abstract

The utility model discloses a multi-rotor unmanned aerial vehicle for artificial precipitation enhancement, which belongs to the technical field of artificial precipitation enhancement and comprises a fuselage platform. An undercarriage, a photoelectric monitoring holder and a temperature and humidity measurement and control device are fixedly mounted at the bottom of the fuselage platform; a quick release device for fixing the flame bomb is mounted on the undercarriage; the quick release device comprises a hanging frame, a first mounting frame and a second mounting frame; the two hanging racks are symmetrically and fixedly mounted on the lower side of the undercarriage, and a first mounting rack and a second mounting rack are fixedly mounted at the two ends of each hanging rack; an ignition assembly is fixedly mounted at the end part of the first mounting frame; and a locking assembly is mounted on the outer wall of the second mounting frame. In this way, the flame bomb can be quickly disassembled, and the replacement speed is increased; when the rain increasing demand quantity is large, the multiple unmanned aerial vehicles can be operated to work cooperatively and repeatedly to achieve the sowing purpose, so that the cost is saved, the sowing effect is guaranteed, the sowing range and metering are accurately controlled, the rain increasing efficiency is improved, and waste is avoided.

Description

Technical Field

[0001] The utility model relates to the technical field of artificial rainfall enhancement, and particularly relates to a multi-rotor unmanned aerial vehicle for artificial rainfall enhancement. Background Art

[0002] The commonly used methods of artificial rainfall and cloud dissipation in China are to spread rainfall agents and cloud dissipation agents into the air through airplanes and ground devices to achieve artificial rainfall and cloud dissipation. However, using ground devices for artificial rainfall requires large-scale movement of the launching devices, which is inconvenient to operate. Moreover, during the cloud dissipation process, it is difficult to control the launching height and accuracy of the cloud dissipation bombs. To achieve the desired effect, a large number of ammunitions with a large charge need to be launched, which will cause a certain degree of pollution to the environment and lead to a certain degree of waste of resources. In the artificial rainfall enhancement project that emphasizes precise operation and efficient operation, it is very necessary to use a more environmentally friendly and precise method to replace the artificial rainfall with ground devices.

[0003] For example, Chinese Patent CN214524409U discloses an artificial rainfall unmanned aerial vehicle. A heat preservation box is fixedly installed on the lower side of the unmanned aerial vehicle. The bottom of the heat preservation box is provided with a first spraying hole. A catalyst for rainfall enhancement is installed in the heat preservation box, and the catalyst is sprayed out through the first spraying hole after reaching the designated position.

[0004] However, it is difficult for this device to accurately find the core area of cloud catalysis; and by spraying the catalyst, the spraying range is small, and it is necessary to operate the unmanned aerial vehicle to move frequently in the high-humidity cloud layer, which is difficult to operate; the currently common method is to diffuse the catalyst by burning a flare strip with a catalyst, but it is difficult to quickly install and replace the flare strip.

[0005] Based on this, the utility model designs a multi-rotor unmanned aerial vehicle for artificial rainfall enhancement to solve the above problems. Summary of the Utility Model

[0006] In view of the above-mentioned drawbacks of the prior art, the utility model provides a multi-rotor unmanned aerial vehicle for artificial rainfall enhancement.

[0007] To achieve the above object, the utility model is realized through the following technical solutions:

[0008] A multi-rotor unmanned aerial vehicle for artificial rainfall enhancement, comprising a fuselage platform;

[0009] The bottom of the fuselage platform is fixedly installed with landing gears, an optoelectronic monitoring pan-tilt, and a temperature and humidity measurement and control device; a quick-release device for fixing flare bombs is installed on the landing gears;

[0010] The quick-release device includes a hanging bracket, a first mounting bracket, and a second mounting bracket; two hanging brackets are symmetrically and fixedly mounted on the lower side of the landing gear, and the first mounting bracket and the second mounting bracket are fixedly mounted at both ends of the hanging bracket; an ignition component is fixedly mounted at the end of the first mounting bracket; a locking component is mounted on the outer wall of the second mounting bracket.

[0011] Furthermore, the quick-release device further includes a cross tie rod, and a cross tie rod is fixedly mounted between the two hanging brackets.

[0012] Furthermore, a parachute is fixedly mounted on the upper side of the fuselage platform by screws.

[0013] Furthermore, positioning grooves are symmetrically formed on the outer wall of the flare, a first ignition electrode plate is fixedly mounted at the end of the flare, and a plurality of locking grooves are evenly formed at equal intervals in a circumferential array on the outer wall of the flare.

[0014] Furthermore, the ignition component includes a moving plate, a first spring, a guide rod, and a second ignition electrode plate; a controller is fixedly mounted in the first mounting bracket; a second ignition electrode plate that cooperates with the first ignition electrode plate is fixedly mounted on the inner side of the moving plate; the second ignition electrode plate is electrically connected to the controller; a plurality of guide rods are fixedly mounted on the outer side of the moving plate, and the guide rods are slidably connected to the first mounting bracket with limited displacement; a plurality of first springs are fixedly mounted at equal intervals in a circumferential array between the first mounting bracket and the moving plate.

[0015] Furthermore, positioning blocks are symmetrically and fixedly mounted on the inner wall of the second mounting bracket, and the positioning blocks are inserted into the positioning grooves.

[0016] Furthermore, the locking component includes an adjusting component, steel balls, and moving grooves, a plurality of moving grooves are evenly formed at equal intervals in a circumferential array on the second mounting bracket, steel balls are arranged in the moving grooves, and the steel balls are clamped with the locking grooves; the adjusting component is mounted on the outside of the second mounting bracket.

[0017] Furthermore, the adjusting component includes a locking sleeve, an inclined groove, and a second spring, the locking sleeve is sleeved on the outside of the second mounting bracket and is slidably connected to the second mounting bracket with limited displacement; an inclined groove with a large outer and small inner shape is formed at one end of the locking sleeve, and a second spring is fixedly mounted between the other end of the locking sleeve and the second mounting bracket; the inner wall of the locking sleeve abuts against the steel balls.

[0018] The beneficial effects of the present utility model compared with the prior art are as follows:

[0019] Install the flare into the first mounting bracket and the second mounting bracket, enhance the structural stability through the cross tie rod, lock the flare through the locking component to prevent the flare from falling off; and achieve quick disassembly of the flare to improve the replacement speed;

[0020] The remotely controlled fuselage platform and landing gear drive out of the hangar and fly into the clouds. The optoelectronic monitoring cloud platform and the temperature and humidity measurement and control device are used to detect the temperature, humidity and visual area range within the cloud area, and the collected information is fed back to the ground control personnel. The ground control personnel determine the precise spreading area based on the information. After reaching the spreading area, the flare is ignited through the ignition device. After the spreading is completed, the UAV is controlled to return to the hangar, and the battery and flares are replaced according to the mission situation. When the demand for rainfall augmentation is large, multiple UAVs can be controlled to work together and work multiple times to achieve the spreading purpose, thereby saving costs, ensuring the spreading effect, accurately controlling the spreading range and dosage, improving the rainfall augmentation efficiency, and avoiding waste.

[0021] By setting up a parachute, it effectively solves the sudden unconventional landing situation, improves the flight safety factor, reduces losses and lowers the operation cost.

[0022] The fuselage platform is powered by a battery, which effectively improves the flight stability, effectively improves the work efficiency, and has no pollution to the environment. Brief Description of the Drawings

[0023] In order to more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the following will briefly introduce the drawings required for the description of the embodiments or the prior art. Obviously, the drawings in the following description are only some embodiments of the present invention. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without creative efforts.

[0024] Figure 1 is a three-dimensional view of a multi-rotor UAV for artificial rainfall augmentation of the present invention Figure 1 ;

[0025] Figure 2 is a schematic diagram of the landing gear and its connection structure;

[0026] Figure 3 is a schematic diagram of the flare and its structure;

[0027] Figure 4 is a schematic diagram of the moving plate and its connection structure;

[0028] Figure 5 is a schematic diagram of the locking sleeve and its connection structure.

[0029] The reference numerals in the drawings respectively represent:

[0030] 1. Airframe platform; 2. Landing gear; 3. Optoelectronic monitoring pan-tilt; 4. Temperature and humidity measurement and control device; 5. Parachute; 6. Quick-release device; 61. Hanger; 62. Cross bar; 63. First mounting bracket; 64. Second mounting bracket; 7. Flare; 71. Positioning groove; 72. First ignition electrode plate; 73. Locking groove; 631. Moving plate; 632. First spring; 633. Guide rod; 634. Second ignition electrode plate; 641. Locking sleeve; 642. Inclined groove; 643. Second spring; 644. Steel ball; 645. Moving groove; 646. Positioning block. Detailed implementation manners

[0031] To make the objectives, technical solutions and advantages of the embodiments of the present utility model clearer, the technical solutions in 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. Apparently, the described embodiments are some but not all of the embodiments of the present utility model. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present utility model without creative efforts shall fall within the protection scope of the present utility model.

[0032] The "left", "right", "front", "rear", "upper" and "lower" mentioned in the following description are oriented in the perspective direction of the front view.

[0033] Embodiment 1

[0034] In some embodiments, please refer to the attached drawings of the specification Figures 1 - 3 , a multi-rotor unmanned aerial vehicle for artificial rainfall enhancement, comprising an airframe platform 1;

[0035] The bottom of the airframe platform 1 is fixedly installed with a landing gear 2, an optoelectronic monitoring pan-tilt 3 and a temperature and humidity measurement and control device 4; a quick-release device 6 for fixing a flare 7 is installed on the landing gear 2;

[0036] The quick-release device 6 includes a hanger 61, a first mounting bracket 63 and a second mounting bracket 64; two hangers 61 are symmetrically and fixedly installed on the lower side of the landing gear 2, and the two ends of the hanger 61 are fixedly installed with a first mounting bracket 63 and a second mounting bracket 64; an ignition assembly is fixedly installed at the end of the first mounting bracket 63; a locking assembly is installed on the outer wall of the second mounting bracket 64.

[0037] The quick-release device 6 further includes a cross bar 62, and a cross bar 62 is fixedly installed between the two hangers 61.

[0038] A parachute 5 is fixedly installed on the upper side of the airframe platform 1 by screws.

[0039] The airframe platform 1 and the landing gear 2 serve as the basic flight platform of the unmanned aerial vehicle, and adopt a six-rotor structure.

[0040] The fuselage platform 1 is powered by a battery. In cooperation with the drone hangar, the battery can be quickly replaced, and the drone can continue to work within a short period of time.

[0041] In this embodiment, when the multi-rotor drone for artificial rainfall enhancement is working normally, the operator installs the flare 7 into the first mounting bracket 63 and the second mounting bracket 64, enhances the structural stability through the cross tie rod 62, and locks the flare 7 through the locking component to prevent the flare 7 from falling off; remotely controls the fuselage platform 1 and the landing gear 2 to drive out of the hangar and fly into the cloud layer, detects the temperature, humidity and visible area range within the cloud layer area through the optoelectronic monitoring cloud platform 3 and the temperature and humidity measurement and control device 4, and feeds back the collected information to the ground control personnel; the ground control personnel judges the precise spreading area through the information, and ignites the flare 7 through the ignition device after reaching the spreading area; after the spreading is completed, operates the drone to return to the hangar, and replaces the battery and the flare 7 according to the task situation; when the demand for rainfall enhancement is large, multiple drones can be operated to work together and work multiple times to achieve the spreading purpose, thereby saving costs, ensuring the spreading effect, precisely controlling the spreading range and dosage, improving the rainfall enhancement efficiency, and avoiding waste; at the same time, quickly disassemble the flare 7 through the first mounting bracket 63 and the second mounting bracket 64 to improve the replacement speed; by setting the parachute 5, effectively solve the sudden unconventional landing situation, improve the flight safety factor, reduce losses, and reduce the operation cost.

[0042] Embodiment 2

[0043] In some embodiments, as Figures 1 - 5 shown, as a preferred embodiment of the present invention, positioning grooves 71 are symmetrically formed on the outer wall of the flare 7, a first ignition electrode sheet 72 is fixedly installed at the end of the flare 7, and a plurality of locking grooves 73 are evenly formed on the outer wall of the flare 7 at equal intervals in a circumferential array.

[0044] The ignition component includes a moving plate 631, a first spring 632, a guide rod 633 and a second ignition electrode sheet 634; a controller is fixedly installed in the first mounting bracket 63; a second ignition electrode sheet 634 cooperating with the first ignition electrode sheet 72 is fixedly installed on the inner side surface of the moving plate 631; the second ignition electrode sheet 634 is electrically connected to the controller; a plurality of guide rods 633 are fixedly installed on the outer side surface of the moving plate 631, and the guide rods 633 are slidably connected to the first mounting bracket 63 in a limited manner; a plurality of first springs 632 are fixedly installed between the first mounting bracket 63 and the moving plate 631 at equal intervals in a circumferential array.

[0045] Positioning blocks 646 are symmetrically fixedly installed on the inner wall of the second mounting bracket 64, and the positioning blocks 646 are inserted into the positioning grooves 71.

[0046] The locking component includes an adjusting component, steel balls 644 and moving grooves 645. A plurality of moving grooves 645 are evenly formed in a circumferential array on the second mounting bracket 64 at equal intervals. Steel balls 644 are arranged in the moving grooves 645, and the steel balls 644 are clamped with the locking grooves 73; the adjusting component is installed on the outer side of the second mounting bracket 64;

[0047] The adjusting component includes a locking sleeve 641, an inclined groove 642 and a second spring 643. The locking sleeve 641 is sleeved on the outer side of the second mounting bracket 64 and is connected with the second mounting bracket 64 in a limited sliding manner; an inclined groove 642 with a large outer and small inner shape is formed at one end of the locking sleeve 641, and a second spring 643 is fixedly installed between the other end of the locking sleeve 641 and the second mounting bracket 64; the inner wall of the locking sleeve 641 abuts against the steel balls 644.

[0048] In this embodiment, when the flare bomb 7, the first mounting bracket 63 and the second mounting bracket 64 are working normally, the locking sleeve 641 is pushed. The locking sleeve 641 moves horizontally under the limiting action of the second mounting bracket 64, so that the inner wall of the locking sleeve 641 is separated from the steel balls 644, and the steel balls 644 are no longer extruded by the locking sleeve 641, so that they can move outwards in the moving grooves 645; the second spring 643 is compressed; at this time, the used flare bomb 7 can be taken out, and the positioning groove 71 on the new flare bomb 7 is aligned with the positioning block 646 on the inner wall of the second mounting bracket 64 and then inserted. The flare bomb 7 moves horizontally under the limiting action of the second mounting bracket 64 until it is inserted into the first mounting bracket 63, and the moving groove 645 is aligned with the locking groove 73; at this time, the first ignition electrode sheet 72 at the end of the flare bomb 7 abuts against the second ignition electrode sheet 634; the first ignition electrode sheet 72 pushes the moving plate 631 to move through the second ignition electrode sheet 634. The moving plate 631 moves horizontally under the limiting action of the guide rod 633 and the first mounting bracket 63, and the first spring 632 is compressed, so that the second ignition electrode sheet 634 is closely attached to the first ignition electrode sheet 72 to ensure stable contact; at this time, the locking sleeve 641 is released, and the second spring 643 resets to drive the locking sleeve 641 to reset, so that the inner wall of the locking sleeve 641 is pressed against the steel balls 644, and the steel balls 644 are pushed inwards. The steel balls 644 move towards the inner side of the second mounting bracket 64 in the moving grooves 645 until the steel balls 644 are clamped into the locking grooves 73 to complete the locking of the flare bomb 7, so as to realize the quick locking of the flare bomb 7; after reaching the spreading area, the controller connected to the second ignition electrode sheet 634 controls the circuit to be connected, and is connected through the second ignition electrode sheet 634 and the first ignition electrode sheet 72. The first ignition electrode sheet 72 is energized to ignite the flare bomb 7; then the controller is turned off; thus realizing the remote control ignition of the flare bomb 7.

[0049] The above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it; although the present invention has been described in detail with reference to the foregoing embodiments, those of ordinary skill in the art should understand that: they can still modify the technical solutions recorded in the foregoing embodiments, or perform equivalent replacements on some of the technical features; and these modifications or replacements will not make the essence of the corresponding technical solutions deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A multi-rotor drone for artificial rainfall enhancement, comprising a fuselage platform (1), characterized in that: The bottom of the fuselage platform (1) is fixedly mounted with a landing gear (2), an optoelectronic monitoring platform (3) and a temperature and humidity measurement and control device (4); the landing gear (2) is mounted with a quick-release device (6) for fixing the flare (7); The quick-release device (6) comprises a hanger (61), a first mounting frame (63) and a second mounting frame (64); the two hangers (61) are symmetrically fixedly mounted on the lower side of the landing gear (2), and the first mounting frame (63) and the second mounting frame (64) are fixedly mounted at both ends of the hanger (61); an ignition assembly is fixedly mounted at the end of the first mounting frame (63); and a locking assembly is mounted on the outer wall of the second mounting frame (64).

2. The multi-rotor drone for artificial rainfall enhancement according to claim 1, characterized in that: The quick-release device (6) further comprises a cross-tie rod (62), and the cross-tie rod (62) is fixedly mounted between the two hangers (61).

3. The multi-rotor drone for artificial rainfall enhancement according to claim 2, characterized in that: A parachute (5) is fixedly mounted on the upper side of the fuselage platform (1) by means of screws.

4. The multi-rotor drone for artificial rainfall enhancement according to claim 3, characterized in that: The outer wall of the flame bomb (7) is symmetrically provided with positioning grooves (71), a first ignition electrode sheet (72) is fixedly mounted at the end of the flame bomb (7), and the outer wall of the flame bomb (7) is evenly provided with a plurality of locking grooves (73) at equal intervals in a circular array.

5. The multi-rotor drone for artificial rainfall enhancement according to claim 4, characterized in that: The ignition assembly comprises a movable plate (631), a first spring (632), a guide rod (633) and a second ignition electrode plate (634); a controller is fixedly installed in the first mounting frame (63); a second ignition electrode plate (634) matched with the first ignition electrode plate (72) is fixedly installed on the inner side surface of the movable plate (631); the second ignition electrode plate (634) is electrically connected to the controller; a plurality of guide rods (633) are fixedly installed on the outer side surface of the movable plate (631), and the guide rods (633) are limitedly slidably connected to the first mounting frame (63); a plurality of first springs (632) are evenly fixedly installed in a circular array at equal intervals between the first mounting frame (63) and the movable plate (631).

6. The multi-rotor drone for artificial rainfall enhancement according to claim 5, characterized in that: Positioning blocks (646) are symmetrically fixedly mounted on the inner wall of the second mounting frame (64), and the positioning blocks (646) are plugged into the positioning grooves (71).

7. The multi-rotor drone for artificial rainfall enhancement according to claim 6, characterized in that: The locking assembly comprises an adjusting assembly, a steel ball (644) and a moving groove (645); a plurality of moving grooves (645) are evenly arranged in a circular array at equal intervals on the second mounting frame (64); a steel ball (644) is arranged in the moving groove (645); the steel ball (644) is engaged with the locking groove (73); and the adjusting assembly is mounted on the outside of the second mounting frame (64).

8. The multi-rotor drone for artificial rainfall enhancement according to claim 7, characterized in that: The adjustment component comprises a locking sleeve (641), an inclined groove (642) and a second spring (643); the locking sleeve (641) is sleeved on the outside of the second mounting frame (64) and is limitedly slidably connected to the second mounting frame (64); one end of the locking sleeve (641) is provided with an inclined groove (642) which is larger on the outside and smaller on the inside; the second spring (643) is fixedly installed between the other end of the locking sleeve (641) and the second mounting frame (64); the inner wall of the locking sleeve (641) is in contact with the steel ball (644).

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