UAV field search multi-point placement positioning device

Abstract

A multi-point positioning device for unmanned aerial vehicle (UAV) field searches includes a marker cartridge containing multiple marker cartridges and an inertial cartridge that uses motion inertia to launch the marker cartridges one by one, allowing the marker cartridges to be deployed independently of the UAV's execution system. The inertial cartridges are connected to the marker cartridge cartridge via an inertial cartridge holder or directly, and the marker cartridges contain built-in positioning markers. This invention discloses a method for field search that can deploy and locate markers independently of the UAV's inherent structure, regardless of the UAV's model or structure, and does not require modification or installation of the UAV's control and execution mechanisms.

Description

Technical Field

[0001] The present invention relates to UAV technology or outdoor search and rescue technology, in particular to a UAV field search multi-point placement and positioning device. Background Art

[0002] Using drones for field searches offers safety, convenience, and speed that manual searches lack. However, after a drone locates a suspected location or patrol route, it is difficult to accurately mark and locate the location without satellite positioning equipment. Alternatively, even if a drone has built-in satellite positioning, complex field conditions make it difficult to determine the actual location, making field searches difficult. Furthermore, equipment that requires control over the drone's launch and positioning device relies on the interconnection or control structure between the drone and the target equipment, often making it difficult to select a drone in practical applications. Summary of the Invention

[0003] The technical problem to be solved by the present invention is to fill the above-mentioned gap and provide a multi-point positioning device for field search of unmanned aerial vehicles, which can perform on-site search and bidding independently of the model of the unmanned aerial vehicle and the positioning of the unmanned aerial vehicle itself.

[0004] In order to achieve the above object, the present invention adopts the following technical solutions:

[0005] The multi-point positioning device for field search by unmanned aerial vehicles is characterized by comprising a marker barrel magazine containing a plurality of marker barrels and an inertial barrel that uses motion inertia to launch the marker barrels one by one, so that the release of the marker barrels is independent of the execution system of the unmanned aerial vehicle. The inertial barrel is connected to the marker barrel magazine through an inertial barrel seat or directly, and the marker barrel has a built-in positioning marker.

[0006] As an embodiment, the marker barrel magazine is provided with a drop-in port at the front end of a column of marker barrels, and marker barrel switches are provided at and behind the drop-in port, and the marker barrel switches are controlled by an inertia barrel.

[0007] As an embodiment, the barrel magazine is slidably connected to a push plate behind a row of barrels, so that the push plate can slide along the arrangement direction of the barrels, and a compression spring is provided behind the push plate.

[0008] As an embodiment, the inertia cylinder is cylindrical, and an adjustment nut, a compression spring, an inertia body, a support spring and a push head are arranged in sequence from top to bottom inside. A positioning groove is provided on the side of the inertia body, and a positioning pin that can be partially embedded in the positioning groove is provided on the side wall between the inertia body and the push head. The adjustment nut is threadedly connected to the inner wall of the inertia cylinder.

[0009] As an embodiment, the positioning pin is provided with a cylindrical pin barrel which is only open to the inner side, a positioning bead is movably provided at the opening of the pin barrel, and a positioning spring is provided behind the positioning bead, and the two ends of the positioning spring are respectively fixedly connected to the positioning bead and the bottom of the pin barrel.

[0010] As an embodiment, the mark barrel switch is provided with a switch rod parallel to the arrangement direction of the row of mark barrels, a torsion spring is sleeved on the switch rod, and a pressure plate, a front gate plate and a rear gate plate are fixedly provided on the side of the switch rod. The pressure plate is aligned with the axial direction of the inertia barrel when it is not under force, the front gate plate is provided in front of the mark barrel at the delivery port, and a rear gate plate is provided behind the front gate plate at a distance of one mark barrel. When the pressure plate is pressed down, the rear gate plate is located in front of the rear mark barrel.

[0011] Preferably, a label pushing spring protruding forward is fixedly provided on the front side of the label barrel.

[0012] Preferably, a marker barrel guide sleeve is provided on the outer side surface of the marker barrel, and the marker barrel guide sleeves of a row of marker barrels are penetrated by a guide rod fixedly arranged in the marker barrel box.

[0013] Preferably, a streamer is fixedly carried on the outer side of the positioning mark.

[0014] Furthermore, an axial test guide groove is provided on the side wall of the inertia cylinder, and the inertia body is provided with a test key extending through the test guide groove in a stationary state, and the test key is fixedly connected to the inertia body.

[0015] This invention utilizes the spring-oscillator acceleration principle. The inertial force generated by the specific descent or ascent operation of the drone during a spin-stop condition triggers the inertial body to activate the target barrel switch, releasing the electronic positioning transmitter inside the barrel. After landing, the positioning transmitter transmits electronic information. By tracking the information from the electronic positioning transmitter, the search target's location is determined, shortening the search time. This makes it particularly suitable for rapid search and rescue in extreme terrain.

[0016] The present invention discloses a method for field searching by unmanned aerial vehicles (UAVs) that is independent of the positioning of the UAV itself, or that can be combined with the positioning of an on-site electronic positioning transmitter for positioning of the UAV. The method does not select the model structure of the UAV, and does not require the modification or installation of a control actuator of the UAV, thereby providing a bidding positioning device that is independent of electronic control.

[0017] The present invention has a small size and a simple structure, has multiple positioning markers built in, and can use the same transmitting position to realize the delivery of multiple markers one by one.

[0018] The inertial body, supported by compression and support springs within the inertial cylinder, is locked in place using a positioning pin. A barrel switch, activated by the inertial body via the positioning pin, simultaneously controls the release of the primary marker and the retention of the secondary marker. The barrel switch allows only one marker to be released at a time, while the others remain in place. A positioning marker with a ribbon inside the barrel secures the bid and transmits electronic positioning information. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 This is a schematic diagram of the overall installation structure of the present invention.

[0020] Figure 2 This is a schematic diagram of the standard cartridge structure.

[0021] Figure 3 It is a schematic diagram of the inertia cylinder structure.

[0022] Figure 4 This is a top view of the standard tube switch structure.

[0023] Figure 5 yes Figure 4 Right view,

[0024] Figure 6 This is a schematic diagram of the standard tube structure.

[0025] Figure 7 It is a schematic diagram of the positioning mark structure.

[0026] In the figure: 1-mark barrel cartridge, 2-mark barrel, 3-inertia barrel seat, 4-inertia barrel, 5-positioning mark, 11-box body, 12-compression spring, 13-guide rod, 14-push plate, 15-guide groove, 16-push plate slider, 21-mark barrel guide sleeve, 22-push mark spring, 23-mark barrel body, 30-inertia barrel base, 31-torsion spring, 32-rear gate, 33-switch rod, 34-pressure plate, 35-front gate, 40-locating pin, 401-pin barrel, 402-locating bead, 403-locating spring, 41-adjusting nut, 42-compression spring, 43-inertia body, 44-locating groove, 45-inertia barrel body, 46-support spring, 47-push head, 48-test key, 49-test guide groove, 51-mark body, 52-ribbon. DETAILED DESCRIPTION

[0027] The present invention is further described below with reference to the accompanying drawings and embodiments. It is apparent that the embodiments described are only a portion of the embodiments of the present invention, rather than all of them. All other embodiments derived by persons of ordinary skill in the art based on the embodiments of the present invention without creative effort are intended to fall within the scope of protection of the present invention.

[0028] In the description of the present invention, it should be noted that the terms "upper", "lower", "vertical", "axial", "perpendicular", "inside" or "outside" and the like indicating positional relationships are based on the application state or the orientation or positional relationships shown in the accompanying drawings. They are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or component referred to must have a specific orientation, be constructed and operated in a specific orientation. Therefore, they need to be understood based on the context of the specification and the drawings and cannot be generally understood as restrictions on the features of the present invention. The terms "installed", "connected" and "connected" should be understood in a broad sense. For example, they can be fixedly connected, detachably connected, or integrally connected; they can be directly connected, indirectly connected through an intermediate medium, or connected inside the component. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0029] like Figure 1 An embodiment of the present invention is shown in FIG.

[0030] The UAV field search and multi-point positioning device of the present invention is used to perform on-site physical bidding positioning without relying on satellite signals when searching and observing the target position, path or object in the field using a camera. The basic structure is:

[0031] like Figures 1 to 7 The apparatus comprises an inertia cylinder 4 and a marker cartridge 1 fixed together. During use, the inertia cylinder 4 is vertically arranged, with one end of the marker cartridge 1 fixed to the upper or lower end of the inertia cylinder 4. Within the marker cartridge 1, a row of neatly arranged marker cartridges 2 are movably mounted, with the outermost marker cartridge 2 facing the delivery port of the marker cartridge 1. The delivery port is located on the end face of the marker cartridge 1 and is open during use. A marker cartridge switch is provided between the inertia cylinder 4 and the outermost marker cartridge 2 within the marker cartridge 1, as well as between the second-outermost marker cartridges. The inertia cylinder 4 releases the outermost marker cartridge under control of the marker cartridge switch.

[0032] The basic structure of the inertia cylinder 4 is as follows: Figure 3 As shown, the inner cavity of the inertia cylinder 4 is cylindrical, and an inertia body 43 that can slide along the axial direction is provided inside.

[0033] The first feasible structure is that the inertia cylinder 4 is vertically arranged above the standard cylinder box 1. The structure of the inertia cylinder is as follows: Figure 3As shown, the inertial cylinder 4 is provided with an adjustment nut 41 at the top and a push head 47 at the bottom. The inner sides of the adjustment nut 41 and push head 47 are respectively provided with a compression spring 42 and a support spring 46. The middle part is an inertial body 43. A second feasible structure: The inertial cylinder 4 is vertically arranged below the standard barrel cartridge 1. The inertial cylinder 4 is provided with a push head 47 at the top and an adjustment nut 41 at the bottom. The inertial body 43 is provided with a compression spring 42 and a support spring 46 above and below. The adjustment nut 41 is threadedly connected to the inner wall of the inertial cylinder 4. The adjustment nut 41 can adjust its own axial position, thereby presetting the elastic potential energy of the compression spring 42, so that the inertial body 43 can effectively perform the action after the drone performs a specific bidding or reset action. The push head 47 is fixedly connected to the outer end of the support spring 46, or a limit structure is provided on the inner wall of the inertial cylinder to prevent the push head 47 from completely falling out, but to ensure that the push head can be partially extended when performing the pushing action.

[0034] A positioning groove 44 is provided on the outer side surface of the inertial body 43. In order to facilitate the matching arrangement of the positioning pin 40, the positioning groove 44 is set to be annular. A positioning pin 40 is fixedly provided on the side wall of the inertial cylinder between the inertial body 43 and the push head 47. The inner end of the positioning pin 40 can be partially embedded in the positioning groove 44, which plays the role of determining the state and maintaining the inertial body to perform the action.

[0035] The positioning pin 40 is positioned so that when the drone performs a specific bidding action, it fits into the positioning slot 44. At this point, the pusher head 47 partially extends, triggering the switch of the marker tube, confirming and locking the drone's bidding operation. When the drone performs a specific reset action, the positioning pin can be released from the positioning slot 44, restoring the position of the inertial body 43, so that the inertial body 43 remains balanced between the compression spring 42 and the support spring 46. Furthermore, because the control command does not rely on electronic control but is issued by physical state, the positioning pin 40 is positioned so that this action is completed when the drone's vertical acceleration is sufficiently large, confirming the uniqueness of the bidding and reset action commands.

[0036] like Figure 3 As shown, the structural embodiment of the positioning pin 40 has a cylindrical positioning pin with only the inner end open, and a compressed positioning spring 403 is installed inside. The inner end of the positioning spring 403 is fixedly connected to a positioning bead 402. The positioning bead 402 can be spherical or elongated and can be embedded in the positioning groove 44 of the inertial body 43. When leaving the positioning groove 44, the front end of the positioning bead 402 extends out of the pin barrel 401. The diameter of the proximal end of the inertial body 43 smoothly decreases toward the end, so that when the inertial body 43 passes the positioning pin, the positioning bead 402 is pressed back until it encounters the positioning groove 44. At this time, the positioning bead 402 is embedded in the positioning groove 44 and requires sufficient force to dislodge. Therefore, the inertial body 43 is fixed from a state of relative motion to a state of relative stillness. Until the drone performs a specific reset action, the generated inertial force resets the inertial body 43.

[0037] An axial test guide slot 49 is provided on the outer wall of the inertial cylinder, extending through the inner wall. A protruding test key 48 is fixedly attached to the outer side of the inertial body 43. This key protrudes out of the test guide slot 49 and can be used to manually test the inertial body and adjust the compression spring. Furthermore, pushing the test key 48 to the end can be used to open the standard cylinder switch, allowing the standard cylinders 2 to be loaded one by one.

[0038] As can be seen from the above, the structure of the inertial cylinder 4 can utilize the flight action of the UAV to generate and sufficiently confirm the bidding action and reset action of the inertial cylinder, without relying on the model structure of the UAV, and without passing through the UAV's electronic control signal or actuator, so it can be widely applicable to various different UAVs.

[0039] The marker tubes 2 are arranged in a row in the marker tube box 1. A simple structure of the marker tube box is implemented as follows: Figure 2 As shown, the outer end of a row of mark tubes is the bidding port of the mark tube box 1, and the inner end is a push plate 14 with a compression spring 12. The compression spring 12 is arranged on the inner side of the push plate 14. A push plate slider 16 or a slide groove is provided on the inner side of the push plate 14. A guide groove 15 or a guide rail is provided at the corresponding position of the mark tube box 1. The push plate 14 is embedded in the rear part of the mark tube box 1 and can only slide in translation. The compression spring 12 maintains elastic potential energy in a compressed state, so that the push plate 14 maintains an outward thrust, and the thrust can keep the push plate 14 translated to the bidding port.

[0040] An embodiment of the marking barrel 2 is structured as follows Figure 6 As shown, a marker barrel guide sleeve 21 or marker barrel guide rail is provided at one or both opposing ends. A matching guide rod 13 or guide groove is provided at a corresponding position on the inner sidewall of the marker barrel housing. The marker barrel guide sleeve 21 and guide rod 13, or the marker barrel guide rail and guide groove, are embedded in a coordinated manner to maintain the marker barrel's low-resistance sliding and translational state. The interior of the marker barrel 2 is a cavity that accommodates the positioning marker 5. A marker pusher spring 22 is fixed to the outer side of the marker barrel 2. This spring 22 is an outwardly protruding spring leaf that stores force and pushes the outer marker barrel outward.

[0041] The structure of the positioning mark 5 is as follows Figure 7 As shown, a streamer 52 or a smoke generator is fixed at one end, and a positioning electronic transmitter is installed inside. The positioning electronic transmitter transmits electronic information after landing. The position of the search and rescue target is determined by tracking the information of the electronic positioning transmitter, thereby shortening the rescue time of the search and rescue target.

[0042] When executing the dropping action, in order to simultaneously realize the effects of releasing the outermost marker barrel and holding the second outermost marker barrel, the present invention uses a marker barrel switch to achieve this.

[0043] The structure of the standard tube switch is as follows Figure 4 、 5As shown, there is a columnar switch rod 33, preferably cylindrical. The switch rod 33 is parallel to the arrangement direction of a row of standard barrels. A pressure plate 34, a front gate plate 35 and a rear gate plate 32 are fixedly installed on the side of the switch rod 33. The pressure plate 34, the front gate plate 35 and the rear gate plate 32 can be flat plates or other shapes. The preferred shape is that the front gate plate 35 and the rear gate plate 32 are flat plates or fork-shaped perpendicular to the switch rod 33. The surface of the pressure plate 34 remains parallel to the switch rod 33. The front gate plate 35 and the rear gate plate 32 are respectively inserted into the front and rear of the outermost standard barrel. There can be multiple rear gate plates 32, which can be respectively inserted in front of the position of the controlled standard barrel. The position of the pressure plate 34 is opposite to the push head 47 of the inertia barrel. Figure 4 In the middle, the front gate 35 and the first rear gate 32 on the outside can be inserted into the front and rear of the first mark barrel respectively. When the switch rod 33 is pushed by the push head 47 to rotate around the axis, the front gate 35 and the rear gate 32 on the side are driven to cut into the mark barrel array. When the push head 47 is not extended, Figure 4 yes Figure 2 The position of the pressure plate 34, the front gate plate 35 and the rear gate plate 32 is as follows: Figure 4 Right view Figure 5 When the pusher head 47 is in the unextended and fully extended states, the pressure plate 34 always keeps contact with the end of the pusher head 47 while rotating, and the front gate 35 rotates from blocking the front of the outer end mark barrel to completely axially offset from the mark barrel; the rear gate 32 rotates from the state of completely offsetting the mark barrel to blocking the front of the second outer end mark barrel.

[0044] The switch lever 33 is reset by a torsion spring 31 at one or both ends. Therefore, after the pusher 47 is reset, the switch lever 33 and its attached components automatically return to their initial positions. The torsion spring 31 can be positioned so that one end is inserted into a slot on the switch lever 33 and the other end rests against the inner wall of the cartridge case or inertia cartridge holder.

[0045] Since relative movement occurs during the interaction between the push head 47 and the pressure plate 34 , preferably, the end of the push head 47 is configured as an arc shape or a ball, which can significantly reduce the movement friction.

[0046] As can be seen, the structure of the present invention can achieve bidding and reset actions independently of the drone model, structure, and the drone's electronic control mechanism or actuator. The vertical emergency stop action of the drone made by remote control acts on the marker barrel switch through the inertial body, directly achieving the release of the marker barrel.

[0047] The specific action of the drone generates vertical acceleration. When the push head is at the lower end of the cylinder, the drone makes an emergency stop when descending or turns from descending to ascending. The inertial force generated by the vertical acceleration causes the inertial body 43 to move and locks and opens the marker barrel switch through a precise inertial action. The marker barrel switch releases the outermost marker barrel and keeps the remaining marker barrels in place. Another specific action of the drone: making an emergency stop when ascending or turning from ascending to descending generates a reverse vertical acceleration. The reverse inertial force generated by the reverse vertical acceleration causes the inertial body 43 to overcome the locked and unlocked state and return to its original position, closing the marker barrel switch. After the new outermost marker barrel is released, the second outermost marker barrel is pushed and kept to the outermost position by the compression spring 12.

[0048] When installing, the bidding device of the present invention only needs to be fixed to the drone with glue or screws so that the inertia cylinder is vertical and the bidding port faces outward.

[0049] The working process of the present invention is as follows: taking the inertial cylinder fixed above the target cylinder box as an example, when a drone is needed for target search and rescue, during the drone search process, when the drone finds a suspected target, it will perform a spin stop flight over the target, and then make a vertical rapid descent to a set height to spin stop or turn upward. During the descent process, the inertial body compresses the compression spring 42 due to the inertial force. When the drone descends to the set height to spin stop or turn upward, the inertial body oscillates and, under the action of the inertial force and the tension of the compression spring, the inertial body descends to a sufficient stroke, and the positioning bead 402 is stuck in the inertial body positioning groove 44, controlling the inertial body to Under the tension of the support spring, the push head 47 presses the mark barrel switch, and the front gate 35 opens to release the outer mark barrel. The mark barrel 2 pushes the first mark barrel out of the mark barrel magazine 1 under the tension of the push spring 22 of the next mark barrel, and the guide sleeves 21 of the remaining mark barrels move along the guide rod 13. After the mark barrel magazine 1 is pushed out, the mark barrel rotates 90 degrees under the action of gravity so that the mark barrel mouth faces downward, and the positioning mark with the electronic positioning mark transmitter slides from the mark barrel and the streamer unfolds. The positioning mark 5 slowly falls to the positioning point under the action of the streamer, completing the release of the first positioning mark; the rear gate 32 closes, blocking the second mark barrel from moving forward and remains stationary.

[0050] After completing the first target placement, the drone rapidly ascends vertically to a set altitude, then spins to a stop or turns downward. The inertial body 43, under the combined action of inertial force and support spring tension, releases the control of the positioning bead 402, releasing the pressure plate 34. The switch lever 33, under the action of the torsion spring 31, opens the rear gate 32 and closes the front gate 35. The second target barrel moves to the release position under the action of the target push spring 22. Simultaneously, the inertial body continues upward under the resistance of the compression spring, oscillating in short strokes under the action of the support and compression springs, ultimately settling at a point of equilibrium between the compression and support springs until the drone finds the next target and repeats the flight pattern of the previous inertial barrel placement.

[0051] The above description is only a preferred embodiment of the present invention. The various embodiments may be cross-applied and are not intended to limit the present invention. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art can still modify the technical solutions described in the aforementioned embodiments or replace some of the technical features therein with equivalents. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principles of the present invention should be included in the scope of protection of the present invention.

Claims

1. A multi-point positioning device for field search by unmanned aerial vehicles, characterized by: The invention comprises a barrel magazine (1) containing a row of neatly arranged barrels (2) and an inertia barrel (4) for launching the barrels (2) one by one by utilizing the inertia of movement, wherein a barrel switch is provided between the inertia barrel (4) and the outermost barrel (2) in the barrel magazine (1) and between the second outermost barrel (2), and the barrel switch is controlled by the inertia barrel (4); The specific action of the UAV generates vertical acceleration. When the push head (47) is at the lower end of the cylinder of the inertial cylinder (4), the UAV stops suddenly when descending or turns from descending to ascending. The inertial force generated by the vertical acceleration causes the inertial body (43) to move and locks and opens the marker cylinder switch through a precise inertial action. The marker cylinder switch releases the outermost marker cylinder (2) and keeps the remaining marker cylinders (2) in place. Another specific action of the UAV: ​​stopping suddenly when ascending or turning from ascending to descending generates a reverse vertical acceleration. The reverse inertial force generated by the reverse vertical acceleration causes the inertial body (43) to overcome the locked state and return to its original position. The marker cylinder switch is closed. After the outermost marker cylinder (2) is released, the second outermost marker cylinder (2) is pushed and held to the outermost position by the compression spring (12). This makes the release of the marker cylinder (2) independent of the execution system of the UAV. The inertial cylinder (4) is connected to the marker cylinder box (1) through the inertial cylinder seat (3) or directly. The marker cylinder (2) has a built-in positioning marker (5). The marker tube switch is provided with a switch rod (33) parallel to the arrangement direction of the row of marker tubes (2), a torsion spring (31) is sleeved on the switch rod (33), and a pressure plate (34), a front gate plate (35) and a rear gate plate (32) are fixedly provided on the side of the switch rod (33), the pressure plate (34) is aligned with the axial direction of the inertia tube (4) in a state without force, the front gate plate (35) is provided in front of the marker tube (2) at the injection port, and a rear gate plate (32) is provided at a distance of one marker tube (2) behind the front gate plate (35), and when the pressure plate (34) is pressed down, the rear gate plate (32) is located in front of the rear marker tube (2); The barrel magazine (1) is slidably connected to the barrel magazine (1) with a push plate (14) at the rear of a row of barrels (2), so that the push plate (14) can slide along the direction of arrangement of the barrels, and a compression spring (12) is provided at the rear of the push plate (14); The inertia cylinder (4) is cylindrical, and an adjusting nut (41), a compression spring (42), an inertia body (43), a support spring (46) and a push head (47) are sequentially arranged inside the inertia body (43) from top to bottom. A positioning groove (44) is provided on the side of the inertia body (43). A positioning pin (40) that can be partially embedded in the positioning groove (44) is provided on the side wall between the inertia body (43) and the push head (47). The adjusting nut (41) is threadedly connected to the inner side wall of the inertia cylinder (4). The positioning pin (40) is provided with a cylindrical pin barrel (401) which is open only to the inner side. A positioning bead (402) is movably provided at the opening of the pin barrel (401). A positioning spring (403) is provided behind the positioning bead (402). The two ends of the positioning spring (403) are fixedly connected to the positioning bead (402) and the bottom of the pin barrel (401), respectively.

2. The unmanned aerial vehicle field search multi-point placement positioning device according to claim 1, characterized in that: A mark pushing spring (22) protruding forward is fixedly provided on the front side of the mark barrel (2).

3. The unmanned aerial vehicle field search multi-point placement positioning device according to claim 1, characterized in that: The outer side surface of the mark barrel (2) is provided with a mark barrel guide sleeve (21), and the mark barrel guide sleeve (21) of a row of mark barrels (2) is penetrated by a guide rod (13) fixedly arranged in the mark barrel box (1).

4. The unmanned aerial vehicle field search multi-point placement positioning device according to claim 1, characterized in that: A streamer (52) is fixedly carried on the outer side of the positioning mark (5).

5. The unmanned aerial vehicle field search multi-point placement positioning device according to claim 1, characterized in that: The side wall of the inertia cylinder (4) is provided with an axial test guide groove (49), and in a stationary state, the inertia body (43) is provided with a test key (48) extending through the test guide groove (49), and the test key (48) is fixedly connected to the inertia body (43).

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