An emergency lifesaving air signal generating device based on a micro unmanned aerial vehicle

Abstract

The technical problem this invention aims to solve is to provide an emergency rescue aerial signal generator based on a micro-drone. This signal generator effectively increases the probability of being spotted by rescued personnel, can be carried through security checks, and can broadcast GPS coordinates, effectively reducing the difficulty of rescue and location after discovery. The signal generator includes a drone body, a power and control compartment, and a payload compartment. The upper end of the payload compartment is detachably mounted at the lower end of the power and control compartment. The payload compartment is equipped with a radio broadcast chip and a high-intensity illumination device. Based on a micro-drone design, the light signal remains in the air for a longer period, greatly increasing the probability of being spotted by rescued personnel. The device mainly consists of a micro-drone and electronic components, can be carried on public transportation such as trains and airplanes through security checks, and broadcasts GPS coordinates via the radio broadcast chip, facilitating rescue and location.

Description

Technical Field

[0001] This utility model relates to the field of drone rescue technology, specifically to an emergency rescue aerial signal generator based on a micro drone. Background Technology

[0002] With the continuous development of drone technology, the flight performance and mission capabilities of drones are receiving increasing attention. Among them, coaxial dual-rotor drones are widely used in aerial photography, logistics delivery, geological surveying, and rescue due to their advantages such as stability and accuracy. Existing emergency rescue signaling devices are mostly rocket-propelled parachute flares, which have short flight times, with an effective working time of only tens of seconds after launch, a maximum altitude of only 300m, and inevitably descend at a speed of about 5m / s, resulting in a low probability of being observed. In addition, rocket-propelled parachute flares contain gunpowder, which cannot be carried on public transportation such as trains and airplanes, greatly limiting their applicability. Furthermore, the flares can only emit a strong light signal during rocket descent, making them visually identifiable. Utility Model Content

[0003] The technical problem to be solved by this utility model is to provide an emergency rescue aerial signal generator based on a micro drone. This signal generator effectively increases the probability of being discovered by the rescued person, can be carried through security checks, and can broadcast GPS coordinates to the outside world, effectively reducing the difficulty of rescue and positioning after being discovered.

[0004] The technical solution adopted by this utility model to solve its technical problem is as follows: the emergency rescue aerial signal generating device based on micro UAV includes a UAV body, the UAV body includes an energy and power control compartment and a payload compartment, the upper end of the payload compartment is set at the lower end of the energy and power control compartment through a detachable structure, and the payload compartment is equipped with a radio broadcasting chip and a strong light illumination device.

[0005] The radio broadcast chip includes a transmitting chip and a receiving chip, which are respectively embedded on the front and rear side walls of the payload compartment. The transmitting chip and the receiving chip are respectively connected to the energy and power control compartment via signal and electrical connections.

[0006] The high-intensity lighting device includes a first high-intensity lamp and a second high-intensity lamp. The first high-intensity lamp and the second high-intensity lamp are respectively installed on the left and right sides of the payload compartment through a folding structure with the same structure. The first high-intensity lamp and the second high-intensity lamp are respectively connected to the energy and power control compartment for signal and electrical connection.

[0007] Furthermore, the folding structure includes a first storage slot and a second storage slot disposed on the left or right side wall of the payload compartment, the first storage slot and the second storage slot being interconnected.

[0008] The size and shape of the first storage slot are the same as the size and shape of the first or second high-intensity lamp;

[0009] A folding rod is provided at one end of the first or second high-intensity lamp near the load compartment, and the size and shape of the folding rod are the same as the size and shape of the second storage slot.

[0010] One end of the folding rod is set at the lower end of the second storage slot via a pivot and there is a gap between it and the bottom of the second storage slot. Multiple torsion springs are sleeved on the pivot. One end of each torsion spring is fixedly connected to the bottom of the second storage slot, and the other end of each torsion spring is fixedly connected to the end of the folding rod near the pivot.

[0011] The end of the first or second high-intensity lamp away from the rotating shaft is provided with a push-button buckle, and the upper side wall of the first storage slot is provided with a slot that matches the push-button buckle.

[0012] Furthermore, the energy and power control cabin includes a power mechanism, a tilting mechanism, a flight control mechanism, and a power battery pack;

[0013] The power mechanism includes a rotating shaft, a positive propeller hub, a negative propeller hub, a positive propeller motor, and a negative propeller motor;

[0014] The propeller hub is fixedly sleeved on the upper end of the rotating shaft, and two folding propellers are symmetrically arranged on the propeller hub. The propeller motor is sleeved on the lower end of the rotating shaft to drive the rotating shaft to rotate.

[0015] A bushing and a motor stator are sequentially fitted onto the rotating shaft from top to bottom. The bushing and motor stator are both located between the positive propeller hub and the positive propeller motor. The negative propeller motor is fitted onto the lower end of the bushing to drive the bushing to rotate. The bushing rotates relative to the rotating shaft. The negative propeller hub is fitted onto the upper end of the bushing. Two folded negative propellers are symmetrically arranged on the negative propeller hub. The motor stator is located between the positive propeller motor and the negative propeller motor.

[0016] The flight control mechanism includes an electronic speed governor, a flight control computer, and an airborne data link. The electronic speed governor is located below the tilt mechanism. The positive and negative propeller motors are respectively connected to the electronic speed governor via signals. The flight control computer and the airborne data link are respectively located at the lower end of the inner cavity of the power control cabin, with the flight control computer located above the airborne data link. The electronic speed governor, the airborne data link, the transmitter chip, the receiver chip, the first high-intensity light, and the second high-intensity light are respectively connected to the flight control computer via signals.

[0017] The power battery pack is located between the electronic speed governor and the flight control computer. The flight control computer, electronic speed governor, airborne data link, transmitter chip, receiver chip, first high-intensity light, second high-intensity light, positive propeller motor, and negative propeller motor are all electrically connected to the power battery pack.

[0018] Furthermore, the tilting mechanism includes a central mounting base, an inclined plate, a support column, a mounting plate, and a power base;

[0019] The power base is located below the propeller motor with a gap between them. The power base is a cross-shaped bracket with one of its free ends bent upward at a 90-degree angle. Each free end of the power base is provided with a connecting rod, and the upper end of the connecting rod is located on the outer wall of the motor stator.

[0020] The central mounting base is located in the upper middle part of the inner cavity of the energy and power control compartment. The electronic speed controller is located below the central mounting base. The support column is located on the upper surface of the central mounting base. The tilting plate is located directly below the power base. The tilting plate is a cylindrical shell with openings at both the top and bottom. A hemispherical shell with an opening at the bottom is provided inside the tilting plate, and the lower surfaces of the two overlap. An adjusting ball head adapted to it is provided inside the hemispherical shell. The lower end of the adjusting ball head protrudes below the tilting plate and is connected to the upper end of the support column. The mounting plate is fitted on the upper middle part of the support column.

[0021] Three connecting blocks are evenly distributed along the circumferential direction at the lower end of the outer side wall of the swashplate. One of the three connecting blocks is located directly below the upwardly bent free end of the power base and is equipped with a limit rod. A limit plate is provided on one side of the mounting plate via the connecting plate. The limit plate is located outside the upwardly bent free end of the power base and is equipped with a limit groove along its vertical direction. The free end of the limit rod is located in the limit groove. The other two connecting blocks are equipped with pull rods via ball joints. Two servo motors are provided on the central mounting base and are respectively corresponding to the two pull rods. Each servo motor has a drive arm on its output shaft. One end of the drive arm is sleeved on the output shaft of the corresponding servo motor, and the other end of the drive arm is connected to the lower end of the corresponding pull rod via a ball joint. The two servo motors are electrically connected to the power battery pack and signal connected to the flight control computer.

[0022] Furthermore, the detachable structure is a screw connection structure.

[0023] The beneficial effects of this utility model are:

[0024] 1. This device is based on a micro-drone design, with a maximum flight altitude of 500m and the ability to hover stably at high altitudes for more than 10 minutes, allowing the light signal to remain in the air for a longer period of time, which greatly increases the probability of it being discovered by rescue personnel.

[0025] 2. The device is mainly composed of micro-drones and electronic components. It can be carried on public transportation such as trains and airplanes and pass through security checks, which greatly expands its applicability.

[0026] 3. In addition to emitting light signals through the set-up strong light illumination device, the device can also broadcast GPS coordinates to the outside world through the set-up radio broadcast chip, which effectively reduces the difficulty of rescue and location after discovery. Attached Figure Description

[0027] Figure 1 This is a schematic diagram of the structure of the emergency rescue aerial signal generator based on a micro UAV as described in this utility model;

[0028] Figure 2 This is a schematic diagram of the unfolded structure of the high-intensity illumination device of the emergency rescue aerial signal generator based on a micro-UAV described in this utility model;

[0029] Figure 3 This is a schematic diagram of the unfolded structure of the payload compartment, radio broadcasting chip, and high-intensity lighting device described in this utility model;

[0030] Figure 4 This is a structural schematic diagram of the payload compartment described in this utility model from another perspective;

[0031] Figure 5 This is a schematic diagram of the power mechanism described in this utility model;

[0032] Figure 6 This is a schematic diagram of the tilting mechanism described in this utility model;

[0033] Figure 7 This is a schematic diagram of a partial structure of the tilting mechanism described in this utility model;

[0034] Explanation of markings in the diagram: Energy and power control compartment 1, tilting mechanism 11, center mounting base 1101, swashplate 1102, support column 1103, mounting plate 1104, power base 1105, connecting rod 1106, hemispherical shell 1107, adjusting ball head 1108, connecting block 1109, limit rod 1110, connecting plate 1111, limit groove 1112, pull rod 1113, servo motor 1114, drive arm 1115, limit plate 1116, cable hole 1117, power mechanism 12, propeller 1201, rotor hub 1202, propeller motor 1203, propeller motor 1204, folding propeller 1205, folding reverse propeller 1206, shaft 1207, bushing 1208, motor stator 1209, cylindrical fairing 1210, payload compartment 2, radio broadcast chip 3, transmitter chip 301, receiver chip 302, high-intensity lighting device 4, first high-intensity light 401, second high-intensity light 402, first storage slot 5, second storage slot 6, folding rod 7, torsion spring 8, push-button buckle 9, slot 10. Detailed Implementation

[0035] The specific embodiments of this utility model will be further described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this application, and not all embodiments. Based on the embodiments in this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0036] It should be noted that all directional indicator terms such as "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", and "outer" in the embodiments of this application indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this utility model and simplifying the description, and do not indicate or imply that the device or component referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this utility model. They are only used to explain the relative positional relationship and movement of the components in a specific posture. If the specific posture changes, the directional indication will also change accordingly.

[0037] In this application, unless otherwise expressly specified and limited, the terms "connection," "fixed," etc., should be interpreted broadly. For example, "fixed" can mean a fixed connection, a detachable connection, or an integral part; it can mean a mechanical connection or an electrical connection; it can mean a direct connection or an indirect connection through an intermediate medium; it can mean the internal communication of two components or the interaction between two components, unless otherwise expressly limited. Those skilled in the art can understand the specific meaning of the above terms in this application according to the specific circumstances.

[0038] Furthermore, if the embodiments of this application involve descriptions such as "first" or "second," these descriptions are for descriptive purposes only and should not be construed as indicating or implying their relative importance or implicitly specifying the number of technical features indicated. Therefore, a feature defined with "first" or "second" may explicitly or implicitly include at least one of those features. Additionally, the meaning of "and / or" throughout the text includes three parallel solutions; for example, "A and / or B" includes solution A, solution B, or a solution where both A and B are satisfied simultaneously. Furthermore, the technical solutions of the various embodiments can be combined with each other, but this must be based on the ability of those skilled in the art to implement them. When the combination of technical solutions is contradictory or impossible to implement, it should be considered that such a combination of technical solutions does not exist and is not within the scope of protection claimed in this application.

[0039] like Figure 1-7 As shown, this emergency rescue aerial signal generator based on a micro-drone includes a drone body. The drone can fly at a maximum altitude of 500m and can hover stably at high altitude for 10 minutes. The drone body includes an energy and power control cabin 1 and a payload cabin 2. It should be noted that the energy and power control cabin 1 can provide power to all electrical components and control the signals of each component. The upper end of the payload cabin 2 is set at the lower end of the energy and power control cabin 1 through a detachable structure. The payload cabin 2 is equipped with a radio broadcast chip 3 and a high-intensity lighting device 4.

[0040] The radio broadcast chip 3 includes a transmitter chip 301 and a receiver chip, which are respectively embedded on the front and rear side walls of the payload compartment 2. The transmitter chip 301 and the receiver chip are respectively connected to the energy and power control compartment 1 via signal and electrical connections, that is, the transmitter chip 301 and the receiver chip are respectively electrically connected to the energy and power control compartment 1, and the energy and power control compartment 1 provides them with power. The transmitter chip 301 and the receiver chip are respectively connected to the energy and power control compartment 1 via signal, and the energy and power control compartment 1 controls the transmitter chip 301 and the receiver chip to transmit and receive GPS coordinate signals on specific frequency bands as needed, which is convenient for positioning during rescue.

[0041] The high-intensity lighting device 4 includes a first high-intensity lamp 401 and a second high-intensity lamp 402. The first high-intensity lamp 401 and the second high-intensity lamp 402 are respectively mounted on the left and right sides of the payload compartment 2 via identical folding structures. These folding structures allow the first high-intensity lamp 401 and the second high-intensity lamp 402 to be unfolded for use, and folded away for storage when not in use, reducing space occupation. The first high-intensity lamp 401 and the second high-intensity lamp 402 are respectively connected to the power source... The power control cabin 1 is connected to both signal and electrical systems. Specifically, the first high-intensity light 401 and the second high-intensity light 402 are connected to the power control cabin 1 and electrically, respectively. The power control cabin 1 provides them with power so that they can emit high-intensity light signals normally. The first high-intensity light 401 and the second high-intensity light 402 are connected to the power control cabin 1 via signal. The power control cabin 1 can turn the first high-intensity light 401 and the second high-intensity light 402 on and off. The high-intensity light signals emitted by the first high-intensity light 401 and the second high-intensity light 402 can provide continuous illumination at high altitudes for 10 minutes, effectively extending the illumination time and facilitating rescue and search operations.

[0042] like Figure 2-4 As shown, in this embodiment, preferably, the folding structure includes a first storage slot 5 and a second storage slot 6 disposed on the left or right side wall of the load compartment 2, wherein the first storage slot 5 and the second storage slot 6 are interconnected.

[0043] The size and shape of the first storage slot 5 are the same as the size and shape of the first high-intensity lamp 401 or the second high-intensity lamp 402. That is, the first high-intensity lamp 401 or the second high-intensity lamp 402 is adapted to the first storage slot 5. The first storage slot 5 can just completely accommodate the first high-intensity lamp 401 or the second high-intensity lamp 402, and the first high-intensity lamp 401 or the second high-intensity lamp 402 will not protrude from the outer wall surface of the load compartment.

[0044] A folding rod 7 is provided at one end of the first high-intensity lamp 401 or the second high-intensity lamp 402 near the load chamber 2. The size and shape of the folding rod 7 are the same as the size and shape of the second storage slot 6, that is, the second storage slot 6 can just completely accommodate the folding rod 7, so that the folding rod 7 will not protrude from the outer wall surface of the load chamber.

[0045] One end of the folding rod 7 is set at the lower end of the second storage groove 6 via a pivot and there is a gap between it and the bottom of the second storage groove 6. Multiple torsion springs 8 are sleeved on the pivot. One end of each torsion spring 8 is fixedly connected to the bottom of the second storage groove 6, and the other end of each torsion spring 8 is fixedly connected to the end of the folding rod 7 near the pivot.

[0046] A push-button buckle 9 is provided at the end of the first high-intensity lamp 401 or the second high-intensity lamp 402 away from the pivot. A slot 10 adapted to the push-button buckle 9 is provided on the upper side wall of the first storage slot 5. When the push-button buckle 9 is engaged in the slot 10, multiple torsion springs 8 are compressed simultaneously. At this time, the first high-intensity lamp 401 or the second high-intensity lamp 402 is located in the first storage slot 5, and the folding rod 7 is located in the second storage slot 6. When the push-button buckle 9 is disengaged from the slot 10 by external force, the multiple torsion springs 8 return to their original deformation, driving the folding rod 7 to rotate until the folding rod 7 is perpendicular to the bottom of the second storage slot 6. At this time, the folding rod 7 is supported and limited by the lower side wall of the second storage slot 6, and is simultaneously subjected to the force of multiple torsion springs 8, so that the folding rod 7 can be fixed in this state without shaking.

[0047] like Figure 1 , Figure 2 , Figure 5-7 As shown, in this embodiment, preferably, the energy and power control cabin 1 includes a power mechanism 12, a tilting mechanism 11, a flight control mechanism, and a power battery pack;

[0048] The power mechanism 12 includes a rotating shaft 1207, a positive propeller hub 1201, a negative propeller hub 1202, a positive propeller motor 1203, and a negative propeller motor 1204;

[0049] The propeller hub 1201 is fixedly sleeved on the upper end of the rotating shaft 1207. Two folding propellers 1205 are symmetrically arranged on the propeller hub 1201. The propeller motor 1203 is sleeved on the lower end of the rotating shaft 1207 to drive the rotating shaft 1207 to rotate.

[0050] A bushing 1208 and a motor stator 1209 are sequentially fitted onto the rotating shaft 1207 from top to bottom. The bushing 1208 and the motor stator 1209 are both located between the positive propeller hub 1201 and the positive propeller motor 1203. The reverse propeller motor 1204 is fitted onto the lower end of the bushing 1208 to drive the bushing 1208 to rotate. The bushing 1208 rotates relative to the rotating shaft 1207. The reverse propeller hub 1202 is fitted onto the upper end of the bushing 1208. Two folding reverse propellers 1206 are symmetrically arranged on the reverse propeller hub 1202. The motor stator 1209 is located between the positive propeller motor 1203 and the reverse propeller motor 1204.

[0051] The flight control mechanism includes an electronic speed governor, a flight control computer, and an onboard data link. The electronic speed governor is located below the tilt mechanism 11. The propeller motor 1203 and the counter-propeller motor 1204 are respectively connected to the electronic speed governor via signals. The electronic speed governor is used to control the rotation speed of the propeller motor 1203 and the counter-propeller motor 1204. The flight control computer and the onboard data link are respectively located at the lower end of the inner cavity of the power control cabin 1, with the flight control computer located above the onboard data link. The electronic speed governor, the onboard data link, the propeller motor 1203, and the counter-propeller motor 1204 are respectively connected to the flight control computer via signals. The flight control computer is used to control the flight of the entire aircraft. The onboard data link is used for transmitting and receiving onboard data. The power control cabin 1 may also have a built-in gyroscope and compass for detecting the horizontal rotation angle and angular velocity of the aircraft.

[0052] The power battery pack is located between the electronic speed governor and the flight control computer. The power battery pack provides power to the entire aircraft. That is, the electronic speed governor, flight control computer, airborne data link, propeller motor 1203, reverse propeller motor 1204, two servo motors 1114 and other electrical components are electrically connected to the power battery pack. In addition, the power battery pack is installed in a detachable manner on the inner wall of the energy and power control compartment 1, which facilitates the replacement of power battery packs of different capacities in the future to meet the power needs of different missions.

[0053] like Figure 1-2 , Figure 6-7 As shown, in this embodiment, preferably, the tilting mechanism 11 includes a central mounting base 1101, an inclined plate 1102, a support column 1103, a mounting plate 1104, and a power base 1105.

[0054] The power base 1105 is located below the propeller motor 1203 with a gap between them. The power base 1105 is a cross-shaped bracket with one free end bent upward at 90 degrees. The purpose of this bend is to leave space for the subsequent limiting plate 1116, and to prevent the upper end of the limiting plate 1116 from being affected by the free end, which would result in insufficient height of the limiting plate 1116 and thus restrict the tilt angle of the tilting disk 1102. Each free end of the power base 1105 is provided with a connecting rod 1106. The upper end of the connecting rod 1106 is located on the outer wall of the motor stator 1209. It can be a fixed connection or a detachable connection. It should be noted that the length of one of the four connecting rods 1106 is different from the other three due to the upward bend of one of its free ends.

[0055] The central mounting base 1101 is located in the upper middle part of the inner cavity of the energy and power control compartment 1. The electronic speed controller is located below the central mounting base 1101. The support column 1103 is located on the upper surface of the central mounting base 1101. The tilting plate 1102 is located directly below the power base 1105. The tilting plate 1102 can be fixed to the power base 1105 directly below by means of screws or other detachable methods. The tilting plate 1102 is a cylindrical shell with openings at both the top and bottom. The tilting plate 1102 has a hemispherical shell 1107 with an opening at the bottom, and the lower surfaces of both are connected. The hemispherical shell 1107 is provided with an adjustable ball head 1108 that is adapted to it. The lower end of the adjustable ball head 1108 protrudes below the tilting plate 1102 and is connected to the upper end of the support column 1103. The diameter of the lower opening of the hemispherical shell 1107 is smaller than the diameter of the adjustable ball head 1108. The tilting plate 1102 is located below the power base 1105. This ensures that the adjustable ball head 1108 will not detach from the hemispherical shell 1107 when it is located inside the hemispherical shell 1107. The mounting plate 1104 is sleeved on the upper middle part of the support column 1103.

[0056] Three connecting blocks 1109 are evenly distributed along the circumferential direction at the lower end of the outer side wall of the tilting disk 1102. One of the three connecting blocks 1109 is located directly below the upwardly bent free end of the power base 1105, and a limit rod 1110 is provided on this connecting block 1109. A limit plate 1116 is provided on one side of the mounting plate 1104 through the connecting plate 1111. The limit plate 1116 is located outside the upwardly bent free end of the power base 1105. The limit plate 1116 has a limit groove 1112 along its vertical direction. The upper side wall of the limit groove 1112 coincides with the upper end face of the limit plate 1116. The free end of the limit rod 1110 is located in the limit groove 1112. The lateral rotation of the tilting disk 1102 can be restricted by the cooperation of the limit rod 1110 and the limit groove 1112. The other two connecting blocks 1109 are connected by ball joints. The structure includes a pull rod 1113, the upper end of which is connected to the corresponding connecting block 1109 via a ball joint connection. The central mounting base 1101 has two servo motors 1114, each corresponding to one of the two pull rods 1113. Each servo motor 1114 has a drive arm 1115 on its output shaft. One end of the drive arm 1115 is fitted onto the output shaft of the corresponding servo motor 1114, and the other end is connected to the lower end of the corresponding pull rod 1113 via a ball joint connection. The two servo motors 1114 are respectively connected to the flight control computer signal. Additionally, a wiring hole 1117 is provided at the corner of the mounting plate 1104 and another at the corner of the central mounting base. The two wiring holes 1117 are vertically aligned, and their purpose is to facilitate better cable routing.

[0057] In this example, to facilitate the installation and disassembly of the energy and power control compartment 1 and the load compartment 2, the detachable structure is a screw connection structure.

[0058] The above are merely preferred embodiments of this application and do not limit the patent scope of this application. Any equivalent structural or procedural transformations made using the content of this application's specification and drawings, or direct or indirect applications in other related technical fields, are similarly included within the patent protection scope of this application.

Claims

1. An emergency rescue aerial signal generator based on a micro unmanned aerial vehicle (UAV), comprising a UAV body, the UAV body comprising an energy and power control compartment (1) and a payload compartment (2), wherein the upper end of the payload compartment (2) is disposed at the lower end of the energy and power control compartment (1) via a detachable structure, characterized in that: The payload compartment (2) is equipped with a radio broadcast chip (3) and a high-intensity lighting device (4). The radio broadcast chip (3) includes a transmitting chip (301) and a receiving chip. The transmitting chip (301) and the receiving chip are respectively embedded on the front and rear side walls of the payload compartment (2). The transmitting chip (301) and the receiving chip are respectively connected to the energy and power control compartment (1) via signal and electrical connection. The high-intensity lighting device (4) includes a first high-intensity lamp (401) and a second high-intensity lamp (402). The first high-intensity lamp (401) and the second high-intensity lamp (402) are respectively installed on the left and right sides of the load compartment (2) through the same folding structure. The first high-intensity lamp (401) and the second high-intensity lamp (402) are respectively connected to the energy and power control compartment (1) via signal and electrical connections.

2. The emergency rescue aerial signal generator based on a micro-UAV according to claim 1, characterized in that: The folding structure includes a first storage slot (5) and a second storage slot (6) provided on the left or right side wall of the load compartment (2), wherein the first storage slot (5) and the second storage slot (6) are connected to each other. The size and shape of the first storage slot (5) are the same as the size and shape of the first high-intensity lamp (401) or the second high-intensity lamp (402); A folding rod (7) is provided at one end of the first high-intensity lamp (401) or the second high-intensity lamp (402) near the load compartment (2), and the size and shape of the folding rod (7) are the same as the size and shape of the second storage slot (6); One end of the folding rod (7) is set at the lower end of the second storage groove (6) through a pivot and there is a gap between it and the bottom of the second storage groove (6). Multiple torsion springs (8) are sleeved on the pivot. One end of each torsion spring (8) is fixedly connected to the bottom of the second storage groove (6), and the other end of each torsion spring (8) is fixedly connected to the end of the folding rod (7) near the pivot. The first high-intensity lamp (401) or the second high-intensity lamp (402) is provided with a push-type buckle (9) at the end away from the rotating shaft, and the upper side wall of the first storage groove (5) is provided with a slot (10) that is compatible with the push-type buckle (9).

3. The emergency rescue aerial signal generator based on a micro-UAV according to claim 2, characterized in that: The energy and power control cabin (1) includes a power mechanism (12), a tilting mechanism (11), a flight control mechanism, and a power battery pack; The power mechanism (12) includes a rotating shaft (1207), a positive propeller hub (1201), a negative propeller hub (1202), a positive propeller motor (1203), and a negative propeller motor (1204). The propeller hub (1201) is fixedly sleeved on the upper end of the rotating shaft (1207). Two folding propellers (1205) are symmetrically arranged on the propeller hub (1201). The propeller motor (1203) is sleeved on the lower end of the rotating shaft (1207) to drive the rotating shaft (1207) to rotate. The rotating shaft (1207) is fitted with a bushing (1208) and a motor stator (1209) from top to bottom. The bushing (1208) and the motor stator (1209) are both located between the propeller hub (1201) and the propeller motor (1203). The reverse propeller motor (1204) is fitted on the lower end of the bushing (1208) to drive the bushing (1208) to rotate. The bushing (1208) rotates relative to the rotating shaft (1207). The reverse propeller hub (1202) is fitted on the upper end of the bushing (1208). Two folding reverse propellers (1206) are symmetrically arranged on the reverse propeller hub (1202). The motor stator (1209) is located between the propeller motor (1203) and the reverse propeller motor (1204). The flight control mechanism includes an electronic speed governor, a flight control computer, and an airborne data link. The electronic speed governor is located below the tilt mechanism (11). The positive propeller motor (1203) and the negative propeller motor (1204) are respectively connected to the electronic speed governor. The flight control computer and the airborne data link are respectively located at the lower end of the inner cavity of the power control cabin (1), with the flight control computer located above the airborne data link. The electronic speed governor, the airborne data link, the transmitter chip (301), the receiver chip, the first high-intensity light (401), and the second high-intensity light (402) are respectively connected to the flight control computer. The power battery pack is located between the electronic speed governor and the flight control computer. The flight control computer, electronic speed governor, airborne data link, transmitter chip (301), receiver chip, first high-intensity light (401), second high-intensity light (402), propeller motor (1203), and reverse propeller motor (1204) are electrically connected to the power battery pack.

4. The emergency rescue aerial signal generator based on a micro-UAV according to claim 3, characterized in that: The tilting mechanism (11) includes a central mounting base (1101), a tilting plate (1102), a support column (1103), a mounting plate (1104), and a power base (1105). The power base (1105) is located below the propeller motor (1203) with a gap between them. The power base (1105) is a cross-shaped bracket with one of its free ends bent upward at 90 degrees. Each free end of the power base (1105) is provided with a connecting rod (1106). The upper end of the connecting rod (1106) is located on the outer wall of the motor stator (1209). The central mounting base (1101) is located in the upper middle part of the inner cavity of the energy power control compartment (1). The electronic speed controller is located below the central mounting base (1101). The support column (1103) is located on the upper surface of the central mounting base (1101). The tilting plate (1102) is located directly below the power base (1105). The tilting plate (1102) is a cylindrical shell with openings at both the upper and lower ends. A hemispherical shell (1107) with an opening at the lower end is provided inside the tilting plate (1102), and the lower surfaces of the two overlap. An adjusting ball head (1108) is provided inside the hemispherical shell (1107) and is adapted to it. The lower end of the adjusting ball head (1108) protrudes below the tilting plate (1102) and is connected to the upper end of the support column (1103). The mounting plate (1104) is sleeved on the upper middle part of the support column (1103). Three connecting blocks (1109) are evenly distributed along the circumferential direction at the lower end of the outer side wall of the tilting plate (1102). One of the three connecting blocks (1109) is located directly below the upwardly bent free end of the power base (1105), and a limit rod (1110) is provided on the connecting block (1109). A limit plate (1116) is provided on one side of the mounting plate (1104) through the connecting plate (1111). The limit plate (1116) is located outside the upwardly bent free end of the power base (1105). The limit plate (1116) is provided with a limit groove (1112) along its vertical direction. The free end of the limit rod (1110) is located in the limit groove (1112). The remaining two connecting blocks (1109) are each equipped with a pull rod (1113) through a ball joint connection structure. The center mounting base (1101) is equipped with two servo motors (1114) and they are respectively corresponding to the two pull rods (1113). Each servo motor (1114) has a drive arm (1115) on its output shaft. One end of the drive arm (1115) is sleeved on the output shaft of the corresponding servo motor (1114), and the other end of the drive arm (1115) is connected to the lower end of the corresponding pull rod (1113) through a ball joint connection structure. The two servo motors (1114) are electrically connected to the power battery pack and are respectively connected to the flight control computer signal.

5. An emergency rescue aerial signal generator based on a micro-UAV according to claim 4, characterized in that: The detachable structure is a screw connection structure.

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