Secondary throwing type unmanned aerial vehicle

Abstract

The utility model relates to the technical field of unmanned aerial vehicles, and provides a two-stage throwing type unmanned aerial vehicle which comprises a carrier, the carrier is provided with a throwing cavity, the throwing cavity is located in the middle of the carrier, the throwing cavity is provided with an air inlet and an inlet and outlet, the air inlet and the inlet and outlet are located in the upper side and the lower side of the throwing cavity respectively, and an anti-falling plate is arranged in the throwing cavity. The shuttle machine is arranged on the anti-falling plate, the balancing weight is arranged on the anti-falling plate in a sliding mode, and the balancing weight is used for adjusting the gravity center of the carrier after sliding. According to the technical scheme, the technical problem that in the prior art, a single unmanned aerial vehicle is poor in stability in a complex environment is solved.

Description

Technical Field

[0001] The embodiments disclosed herein relate to the field of unmanned aerial vehicle (UAV) technology, and more specifically, to a two-stage drop-type UAV. Background Technology

[0002] Unmanned aerial vehicles (UAVs), as advanced intelligent equipment, have been widely used in emergency rescue fields such as earthquake relief, flood control and disaster relief, high-rise fire rescue, and water emergency search and rescue in recent years. With their advantages of high speed, high maneuverability, and lack of geographical limitations, UAVs can reach disaster sites immediately after a disaster occurs, transmitting high-definition video data back to the rescue command center in a timely manner. This not only provides crucial information and data support for the command center to assess the disaster situation and deploy rescue work, but also allows them to replace rescue personnel in dangerous areas, effectively reducing rescue risks and ensuring the personal safety of rescue personnel. Currently, the UAVs used in emergency rescue are all single-unit UAVs. However, as application scenarios become increasingly diverse, the limitations of single-unit UAVs are gradually becoming apparent, such as insufficient battery life, limited task scope, and poor stability in complex environments. Utility Model Content

[0003] To overcome the above-mentioned defects, the embodiments of this disclosure provide a two-stage drop-type UAV, which solves the technical problem of poor stability of single UAVs in complex environments in the prior art.

[0004] According to one aspect, at least one embodiment of this disclosure provides a two-stage drop-type unmanned aerial vehicle, comprising:

[0005] A carrier aircraft, the carrier aircraft having a throwing chamber located in the middle of the carrier aircraft, the throwing chamber having an air inlet and an outlet, the air inlet and the outlet being located on the upper and lower sides of the throwing chamber respectively;

[0006] An anti-detachment plate is disposed inside the throwing chamber and located on one side of the inlet / outlet;

[0007] A shuttle, which is mounted on the anti-detachment plate, and the entrance / exit is for the passage of the shuttle;

[0008] A counterweight is slidably mounted on the anti-detachment plate, and the counterweight is used to adjust the center of gravity of the carrier after sliding.

[0009] For example, at least one embodiment of this disclosure provides a two-stage drop-type unmanned aerial vehicle, wherein the carrier includes:

[0010] The housing has the throwing cavity and the mounting cavity, the mounting cavity being located on the front side of the housing and used to install the drive components of the carrier aircraft;

[0011] A tail fin, which is disposed on the housing and located on the side away from the mounting cavity;

[0012] A wing is disposed on the fuselage, the wing is located above the air intake, and partially blocks the air intake;

[0013] A propeller assembly, wherein the propeller assembly is disposed on the wing, and there are two propeller assemblies, which are respectively located on both sides of the fuselage.

[0014] For example, at least one embodiment of this disclosure provides a two-stage drop-type unmanned aerial vehicle, wherein the wings include:

[0015] The main wing plate is disposed on the fuselage, and the propeller assembly is disposed on the lower side of the main wing plate. An air intake gap is formed between the main wing plate and the fuselage, and the air intake gap leads to the air intake.

[0016] An auxiliary wingplate, which is oscillatingly mounted on the main wingplate, is used for the turning and tilting of the carrier aircraft.

[0017] For example, at least one embodiment of this disclosure provides a two-stage throwing drone, wherein the shuttle has a magnetic sheet located on the underside of the shuttle, and the anti-detachment plate includes:

[0018] An anti-demagnetization plate is disposed inside the throwing cavity to attract the magnetic sheet and prevent the shuttle from falling off.

[0019] A slide rail is provided on the anti-magnetic plate, and the slide rail and the shuttle are located on the upper and lower sides of the anti-magnetic plate, respectively. The counterweight is slidably disposed on the slide rail.

[0020] For example, at least one embodiment of this disclosure provides a two-stage throwing drone, wherein the counterweight has a threaded hole, and the carrier further includes:

[0021] A lead screw is rotatably mounted on the housing and threaded into a threaded hole. The lead screw is used to adjust the center of gravity of the carrier after it rotates.

[0022] For example, at least one embodiment of this disclosure provides a two-stage drop-type unmanned aerial vehicle, wherein the carrier further includes:

[0023] A partition is disposed inside the throwing chamber, forming a contraction section with the chamber wall to block the shuttle and prevent it from getting stuck in the contraction section when it leaves the throwing chamber.

[0024] For example, at least one embodiment of this disclosure provides a two-stage drop-type unmanned aerial vehicle, wherein the partition is obliquely disposed within the contraction section, and the partition extends from the inlet / outlet toward the tail fin.

[0025] For example, at least one embodiment of this disclosure provides a two-stage drop-type unmanned aerial vehicle, wherein the carrier further includes:

[0026] A guide plate is disposed inside the throwing chamber and located on one side of the anti-demagnetization plate. The guide plate extends from the inlet / outlet toward the wing and is used to guide the shuttle when it returns to the throwing chamber.

[0027] For example, at least one embodiment of this disclosure provides a two-stage drop-type unmanned aerial vehicle, wherein the carrier further includes:

[0028] A buffer plate is disposed between the throwing chamber and the mounting chamber to prevent the shuttle from flying into the mounting chamber.

[0029] The beneficial effects of the embodiments disclosed herein are as follows:

[0030] In this disclosure, an anti-detachment plate is installed inside the launch chamber and located on the inlet / outlet side. This prevents the shuttle from accidentally detaching during flight, ensuring flight safety. The placement of the air inlet and outlet of the launch chamber ensures that the airflow meets the shuttle's lift requirements during launch. The airflow entering through the air inlet stabilizes the shuttle's initial launch attitude, reducing momentary swaying and thus optimizing the launch trajectory.

[0031] The two-stage drop-type UAV design, where a carrier aircraft deploys a shuttle, gives the UAV more flexible mission execution capabilities. The carrier aircraft can drop the shuttle to areas that are far away or difficult to reach directly, and then the shuttle performs specific tasks, primarily close-range reconnaissance. This two-stage drop-type mode expands the application range of UAVs, enabling them to adapt to more complex mission scenarios. Attached Figure Description

[0032] To more clearly illustrate the technical solutions in the embodiments of this disclosure, the accompanying drawings used in the description of the embodiments of this disclosure will be briefly introduced below. Obviously, the drawings described below are merely some exemplary embodiments of this disclosure. For those skilled in the art, other drawings can be obtained based on the content of the exemplary embodiments of this disclosure and these drawings without any creative effort.

[0033] Figure 1 This is a schematic diagram of the structure of one embodiment of the present disclosure;

[0034] Figure 2 This is a schematic diagram of the external structure of this disclosure;

[0035] Figure 3 for Figure 1 A magnified structural diagram of A.

[0036] In the diagram: Carrier-1, Drop chamber-101, Air inlet-102, Inlet / outlet-103, Casing-104, Tail fin-105, Wing-106, Propeller assembly-107, Main wingplate-108, Air inlet clearance-109, Auxiliary wingplate-110, Lead screw-111, Retractable section-112, Partition-113, Guide plate-114, Buffer plate-115, Mounting cavity-116, Anti-detachment plate-2, Anti-magnetic plate-201, Slide rail-202, Shuttle-3, Magnetic sheet-301, Counterweight-4, Threaded hole-401. Detailed Implementation

[0037] The present disclosure will now be described in further detail with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the present disclosure and are not intended to limit the scope of the disclosure.

[0038] To keep the drawings concise, each drawing only schematically shows the parts relevant to the disclosure; these do not represent the actual structure of the product. Furthermore, for ease of understanding, in some drawings, only one of components with the same structure or function is schematically shown, or only one is labeled. In this document, "one" not only means "only one," but can also mean "more than one," and "several" includes "two" and "more than two."

[0039] In this document, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linkage" should be interpreted broadly. For example, they can refer to fixed connections, detachable connections, or integral connections; they can refer to mechanical connections or electrical connections; they can refer to direct connections or indirect connections through an intermediate medium; and they can refer to the internal connection between two components. Those skilled in the art can understand the specific meaning of the above terms in this disclosure based on the specific circumstances.

[0040] In this disclosure, unless otherwise expressly specified and limited, "above" or "below" the second feature can include direct contact between the first and second features, or contact between the first and second features through another feature between them. Furthermore, "above," "over," and "on top" of the second feature includes the first feature directly above or diagonally above the second feature, or simply indicates that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature includes the first feature directly below or diagonally below the second feature, or simply indicates that the first feature is at a lower horizontal level than the second feature.

[0041] In the description of this embodiment, terms such as "upper," "lower," "left," and "right" are based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of description and simplification of operation, and are not intended to indicate or imply that the device or element 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 disclosure.

[0042] Furthermore, in the description of this application, the terms "first," "second," etc., are used only to distinguish descriptions and should not be construed as indicating or implying relative importance.

[0043] like Figures 1-3 As shown, this invention illustrates a two-stage drop-type unmanned aerial vehicle (UAV) according to an embodiment of the present disclosure, including a carrier 1. The carrier 1 has a drop chamber 101 located in the middle of the carrier 1. The drop chamber 101 has an air inlet 102 and an outlet 103, which are located on the upper and lower sides of the drop chamber 101, respectively. An anti-detachment plate 2 is disposed inside the drop chamber 101 and located on one side of the outlet 103. A shuttle 3 is disposed on the anti-detachment plate 2. The outlet 103 is used for the passage of the shuttle 3. A counterweight 4 is slidably disposed on the anti-detachment plate 2. The counterweight 4 is used to adjust the center of gravity of the carrier 1 after sliding.

[0044] For example, such as Figure 1 As shown, the drop chamber 101 is located in the middle of the carrier aircraft 1, with the air inlet 102 and the outlet 103 respectively located on the upper and lower sides of the drop chamber 101. This layout helps maintain the center of gravity balance of the carrier aircraft 1 during flight. The centrally located drop chamber 101 ensures a relatively uniform overall mass distribution, avoiding flight instability caused by a shift in the center of gravity. During flight, even if the states of the shuttle 3 and the counterweight 4 within the drop chamber 101 change, the impact on the center of gravity is relatively small due to the central position of the chamber. Compared to a design where the drop chamber 101 is located on one side, the carrier aircraft 1 with a central layout exhibits reduced swaying during flight, improving flight stability and providing a more stable platform for mission execution.

[0045] The counterweight 4 is slidably mounted on the anti-detachment plate 2. After the shuttle 3 separates from the anti-detachment plate 2, the center of gravity of the carrier aircraft 1 can be adjusted in real time by adjusting the position of the counterweight 4. After the shuttle 3 is deployed, the mass distribution of the carrier aircraft 1 will change, and the center of gravity will shift slightly. At this time, sliding the counterweight 4 to a suitable position can compensate for the change in the center of gravity caused by the change in mass, ensuring that the carrier aircraft 1 continues to fly stably.

[0046] The anti-detachment plate 2 is installed inside the launch chamber 101 and located on one side of the inlet / outlet 103. During flight, it prevents the shuttle 3 from accidentally detaching, ensuring flight safety. The placement of the air inlet 102 and the inlet / outlet 103 in the launch chamber 101 ensures that the airflow meets the lift requirements of the shuttle 3 during launch. The airflow entering through the air inlet 102 stabilizes the initial launch attitude of the shuttle 3, reducing momentary swaying and thus optimizing the launch trajectory.

[0047] The two-stage drop-type UAV design, where the carrier aircraft 1 deploys the shuttle 3, gives the UAV a more flexible mission execution capability. The carrier aircraft 1 can drop the shuttle 3 to areas that are far away or difficult to reach directly, and then the shuttle 3 will perform specific tasks, primarily close-range reconnaissance. This two-stage drop-type mode expands the application range of UAVs and can adapt to more complex mission scenarios.

[0048] In some examples, the carrier 1 includes a housing 104 having a launch chamber 101 and a mounting chamber 116. The mounting chamber 116 is located on the front side of the housing 104 and is used to mount the drive assembly of the carrier 1. A tail fin 105 is disposed on the housing 104 and is located on the side away from the mounting chamber 116. A wing 106 is disposed on the housing 104 and is located above the air intake 102 and partially blocks the air intake 102. Two propeller assemblies 107 are disposed on the wing 106 and are located on both sides of the housing 104 respectively.

[0049] For example, such as Figure 2 As shown, the mounting cavity 116, located at the front of the housing 104, is used to mount the drive assembly, while the tail fin 105 is positioned on the side of the housing 104 away from the mounting cavity 116. This layout results in a more rational weight distribution for the drone, similar to the layout of a traditional aircraft, effectively improving flight stability. During flight, the front drive assembly provides power, while the rear tail fin 105 acts as a balancer and guide, reducing the drone's swaying and drift.

[0050] The wing 106 includes a main wingplate 108 and an auxiliary wingplate 110. The main wingplate 108 is mounted on the fuselage 104, forming an air intake gap 109 between itself and the fuselage 104 and leading to the air intake 102. During flight, air enters the air intake 102 through the air intake gap 109, and the airflow velocity difference between the upper and lower surfaces of the main wingplate 108 generates lift. This design allows the main wingplate 108 to not only utilize the lift principle of a traditional wing but also optimize airflow through the air intake gap 109, further enhancing lift. Compared to a wing design without the air intake gap 109, the lift generated by the wing using this structure is increased under the influence of airflow, enabling the carrier aircraft 1 to carry a heavier load or fly a longer distance with lower energy consumption under the same power conditions.

[0051] The auxiliary wingplate 110 is pivotally mounted on the main wingplate 108 and its angle can be adjusted according to flight requirements. During flight, the auxiliary wingplate 110 assists the main wingplate 108 in adjusting airflow and maintaining flight stability. When encountering airflow fluctuations or other disturbances, the auxiliary wingplate 110 can react quickly, adjusting the aerodynamic characteristics of the wing and reducing changes in flight attitude.

[0052] The air intake gap 109 leads to the air intake 102, and the main wing plate 108 partially shields the air intake 102, preventing larger debris, rainwater, etc., from directly entering the air intake 102. This design reduces the risk of the air intake 102 being blocked or damaged, protecting the equipment inside the delivery chamber 101 and the entire UAV's power system. The auxiliary wing plate 110 can adjust its angle during flight to change the aerodynamic characteristics of the wing, preventing the carrier aircraft 1 from stalling under certain conditions, such as low-speed flight or sharp turns. When the carrier aircraft 1 approaches a stall, the auxiliary wing plate 110 can increase the lift of the wing, maintaining flight stability.

[0053] The launch chamber 101 is located in the middle of the housing 104, independent of the mounting chamber 116, providing suitable storage and launch space for the shuttle 3 and the counterweight 4. This layout ensures that launching the shuttle 3 will not affect other components such as the drive assembly, guaranteeing a smooth launch process. Simultaneously, the placement of the air inlet 102 and inlet / outlet 103 in the launch chamber 101 facilitates the launch of the shuttle 3 and airflow, improving launch accuracy and safety. Two propeller assemblies 107 are located on the wings 106 on both sides of the housing 104, giving the UAV better maneuverability during flight. By adjusting the speed and direction of the two propeller assemblies 107, the UAV can perform flexible turning, acceleration, and deceleration.

[0054] In some examples, the shuttle 3 has a magnetic plate 301 located on the underside of the shuttle 3. The anti-detachment plate 2 includes an anti-magnetic plate 201, which is disposed in the throwing cavity 101 to attract the magnetic plate 301 and prevent the shuttle 3 from falling off. The slide rail 202 is disposed on the anti-magnetic plate 201, and the slide rail 202 and the shuttle 3 are respectively located on the upper and lower sides of the anti-magnetic plate 201. The counterweight 4 is slidably disposed on the slide rail 202.

[0055] For example, such as Figure 1As shown, the magnetic plate 301 on the underside of the shuttle 3 attracts the anti-detachment magnetic plate 201 on the anti-detachment plate 2, effectively preventing the shuttle 3 from accidentally falling off during flight. This magnetic adsorption provides a reliable fixation effect, ensuring that the shuttle 3 remains stably fixed on the anti-detachment plate 2 even when the carrier aircraft 1 encounters complex situations such as airflow fluctuations or vibrations. A slide rail 202 is mounted on the anti-detachment magnetic plate 201, and a counterweight 4 is slidably mounted on the slide rail 202. The slide rail provides a stable sliding track for the counterweight 4, making the counterweight more stable when adjusting its position, preventing wobbling or displacement. After the shuttle 3 is deployed, the counterweight 4 adjusts the center of gravity of the carrier aircraft 1 by sliding on the slide rail 202. The stable support of the slide rail 202 helps to more accurately adjust the center of gravity position, thereby further enhancing the flight stability of the carrier aircraft 1.

[0056] The magnetic sheet 301 and the anti-derailment plate 201 have relatively simple structures, making them easy for maintenance personnel to inspect and maintain. During regular inspections, maintenance personnel can visually observe the magnetic strength and surface condition of the magnetic sheet 301 and the anti-derailment plate 201 to determine whether maintenance or replacement is necessary. Furthermore, when detached, the lifting force only needs to be greater than the attractive force between the magnetic sheet 301 and the anti-derailment plate 201, resulting in a low probability of damage.

[0057] In some examples, the counterweight 4 has a threaded hole 401, and the carrier 1 also includes a lead screw 111, which is rotatably mounted on the housing 104 and threaded in the threaded hole 401. The lead screw 111 is used to adjust the center of gravity of the carrier 1 after rotation.

[0058] For example, such as Figure 3 As shown, the threaded hole 401 on the counterweight 4 is threadedly engaged with the lead screw 111 of the carrier aircraft 1. When the lead screw 111 rotates, the counterweight 4 can move precisely along the lead screw 111 through threaded transmission. This threaded transmission method has higher precision compared to other simple sliding or pushing methods. The thread pitch can be designed to be very small, so that the movement distance of the counterweight 4 can be precisely controlled for each rotation of the lead screw 111. Precisely adjusting the center of gravity of the carrier aircraft 1 is crucial for flight performance. After the shuttle 3 is deployed, or during flight when the center of gravity shifts due to factors such as load changes, adjusting the position of the counterweight 4 by rotating the lead screw 111 can quickly and accurately restore the balance of the carrier aircraft 1.

[0059] The rotation of the lead screw 111 is relatively simple. The operator only needs to use a control device such as a motor drive to rotate the lead screw 111 to move the counterweight 4, thereby adjusting the center of gravity of the carrier 1.

[0060] Different missions require the carrier aircraft 1 to carry different loads, and the deployment of different numbers of shuttles 3 will cause changes in the center of gravity. The design of the lead screw 111 and the counterweight 4 allows the carrier aircraft 1 to adapt to these different mission load changes. By adjusting the position of the counterweight 4, the center of gravity can be kept balanced under different load conditions, ensuring the normal flight of the UAV.

[0061] In some examples, the carrier 1 also includes a partition 113 disposed within the throwing chamber 101, forming a contraction section 112 with the chamber wall of the throwing chamber 101, which is used to block the shuttle 3 and prevent the shuttle 3 from getting stuck in the contraction section 112 when it flies away from the throwing chamber 101.

[0062] For example, such as Figure 1 As shown, a baffle 113 is installed within the retractable section 112 of the launch chamber 101. Its main function is to prevent the shuttle 3 from getting stuck in the retractable section 112 when it leaves the launch chamber 101. If the shuttle 3 gets stuck in the retractable section 112, it may cause the carrier aircraft 1 to lose its flight attitude balance, or even lead to a flight accident. The presence of the baffle 113 effectively avoids this situation, ensuring the safety of the carrier aircraft 1 during flight. The baffle 113 ensures that the shuttle 3 flies along a predetermined path and direction when it leaves the launch chamber 101, avoiding launch failure due to getting stuck in the retractable section 112. The combination of the retractable section 112 and the baffle 113 reduces the occurrence of malfunctions during the launch of the shuttle 3. The shuttle 3 getting stuck in the retractable section 112 not only affects the launch mission but also damages the shuttle 3 and the carrier aircraft 1. By setting up the baffle 113, the situation of the shuttle 3 getting stuck in the retractable section 112 is avoided, thereby reducing equipment damage and maintenance costs caused by such malfunctions.

[0063] In some examples, the baffle 113 is inclinedly disposed within the contraction section 112, and the baffle 113 extends from the inlet / outlet 103 toward the tail fin 105.

[0064] For example, such as Figure 1 As shown, the baffle 113 is inclinedly disposed within the retraction section 112, guiding the shuttle 3 to fly away from the throwing chamber 101 along a specific path. When the shuttle 3 is released, once it enters the retraction section 112, the inclined baffle 113 prevents the shuttle 3 from entering the interior of the retraction section 112, shutting off the power of the shuttle 3. The baffle 113 then exerts a guiding force on it, causing the shuttle 3 to be thrown out of the throwing chamber 101 in a preset direction. Compared to a vertically disposed baffle 113, the inclined baffle 113 can prevent the shuttle 3 from malfunctioning or failing to detach from the throwing chamber 101 during startup, while also reducing the throwing error caused by attitude deviation during startup.

[0065] In some examples, the carrier 1 also includes a guide plate 114 disposed in the throwing chamber 101 and located on one side of the anti-demagnetization plate 201. The guide plate 114 extends from the inlet / outlet 103 toward the wing 106 and is used to guide the shuttle 3 when it returns to the throwing chamber 101.

[0066] For example, such as Figure 1 As shown, the guide plate 114 is disposed inside the throwing chamber 101 and parallel to the partition 113. When the shuttle 3 completes its mission and returns to the throwing chamber 101, the guide plate 114 provides precise guidance. During the return process, the shuttle 3 can adjust its flight attitude according to the position and orientation of the guide plate 114 to smoothly enter the throwing chamber 101. Compared with the case without the guide plate 114, the success rate of the shuttle 3 returning to the throwing chamber 101 is improved.

[0067] The presence of guide plate 114 simplifies the return operation of shuttle 3. Operators do not need complex operating skills or precise manual control to guide shuttle 3 back; they only need to perform simple operations on shuttle 3 according to the general direction guided by guide plate 114.

[0068] In some examples, the carrier 1 also includes a buffer plate 115 disposed between the throwing chamber 101 and the mounting chamber 116 to prevent the shuttle 3 from flying into the mounting chamber 116.

[0069] For example, such as Figure 1 As shown, the buffer plate 115 is positioned between the launch chamber 101 and the mounting chamber 116, effectively preventing the shuttle 3 from flying into the mounting chamber 116. The mounting chamber 116 houses critical components such as the drive assembly of the carrier aircraft 1. If the shuttle 3 accidentally flies into it, it will cause serious damage to these components, thus affecting the normal flight of the carrier aircraft 1. The buffer plate 115 has a cushioning function; when the shuttle 3 accidentally impacts the buffer plate 115, it can absorb some of the impact energy, reducing the impact on the overall structure of the shuttle 3 and the carrier aircraft 1.

[0070] The buffer plate 115 separates the launching chamber 101 from the mounting chamber 116, achieving a reasonable division of the chamber space. This design clearly defines the functional areas of different chambers, making the internal structure of the carrier 1 more regular. The launching chamber 101 is specifically used for storing and launching the shuttle 3, while the mounting chamber 116 focuses on installing equipment such as drive components, avoiding mutual interference between different functional components.

[0071] It should be noted that the above embodiments are only used to illustrate the technical solutions of this disclosure and are not intended to limit it. Although this disclosure has been described in detail with reference to preferred embodiments, those skilled in the art should understand that modifications or equivalent substitutions can be made to the technical solutions of this disclosure without departing from the spirit and scope of the technical solutions of this disclosure, and all such modifications and substitutions should be covered within the scope of the claims of this disclosure.

Claims

1. A two-stage drop-type unmanned aerial vehicle, characterized in that, include: The carrier (1) has a throwing chamber (101) located in the middle of the carrier (1). The throwing chamber (101) has an air inlet (102) and an outlet (103) located on the upper and lower sides of the throwing chamber (101), respectively. Anti-detachment plate (2), the anti-detachment plate (2) is disposed in the throwing cavity (101) and located on one side of the inlet (103); A shuttle (3) is mounted on the anti-detachment plate (2), and the entrance / exit (103) is used for the passage of the shuttle (3); Counterweight (4) is slidably mounted on the anti-detachment plate (2). The counterweight (4) is used to adjust the center of gravity of the carrier (1) after sliding.

2. The two-stage drop-type unmanned aerial vehicle according to claim 1, characterized in that, The carrier (1) includes: The housing (104) has the throwing cavity (101) and the mounting cavity (116), the mounting cavity (116) being located on the front side of the housing (104) for mounting the drive assembly of the carrier (1); Tail wing (105), the tail wing (105) is disposed on the housing (104) and located on the side away from the mounting cavity (116); Wing (106), the wing (106) is disposed on the housing (104), the wing (106) is located above the air inlet (102) and blocks part of the air inlet (102). Propeller assembly (107), the propeller assembly (107) is disposed on the wing (106), there are two propeller assemblies (107), and they are respectively located on both sides of the housing (104).

3. The two-stage drop-type unmanned aerial vehicle according to claim 2, characterized in that, The wing (106) includes: The main wing plate (108) is disposed on the housing (104), and the propeller assembly (107) is disposed on the lower side of the main wing plate (108). An air intake gap (109) is formed between the main wing plate (108) and the housing (104), and the air intake gap (109) leads to the air intake (102). An auxiliary wingplate (110) is oscillatingly mounted on the main wingplate (108) for turning and tilting of the carrier (1).

4. A two-stage drop-type unmanned aerial vehicle according to claim 2, characterized in that, The shuttle (3) has a magnetic plate (301) located on the underside of the shuttle (3), and the anti-detachment plate (2) includes: Anti-demagnetization plate (201), the anti-demagnetization plate (201) is disposed in the throwing cavity (101) to attract the magnetic sheet (301) and prevent the shuttle (3) from falling off; The slide rail (202) is set on the anti-demagnetization plate (201). The slide rail (202) and the shuttle (3) are respectively located on the upper and lower sides of the anti-demagnetization plate (201). The counterweight (4) is slidably set on the slide rail (202).

5. A two-stage drop-type unmanned aerial vehicle according to claim 4, characterized in that, The counterweight (4) has a threaded hole (401), and the carrier (1) further includes: A lead screw (111) is rotatably mounted on the housing (104) and threaded in the threaded hole (401). After the lead screw (111) rotates, it is used to adjust the center of gravity of the carrier (1).

6. A two-stage drop-type unmanned aerial vehicle according to claim 4, characterized in that, The carrier (1) also includes: A partition (113) is disposed inside the throwing chamber (101) and forms a contraction section (112) with the cavity wall of the throwing chamber (101) to block the shuttle (3) and prevent the shuttle (3) from getting stuck in the contraction section (112) when it flies away from the throwing chamber (101).

7. A two-stage drop-type unmanned aerial vehicle according to claim 6, characterized in that, The partition (113) is inclinedly disposed within the contraction section (112), and the partition (113) extends from the inlet (103) toward the tail fin (105).

8. A two-stage drop-type unmanned aerial vehicle according to claim 6, characterized in that, The carrier (1) also includes: A guide plate (114) is disposed inside the throwing cavity (101) and located on one side of the anti-demagnetization plate (201). The guide plate (114) extends from the inlet (103) toward the wing (106). The guide plate (114) is used to guide the shuttle (3) when it returns to the throwing cavity (101).

9. A two-stage drop-type unmanned aerial vehicle according to claim 2, characterized in that, The carrier (1) also includes: A buffer plate (115) is disposed between the throwing chamber (101) and the mounting chamber (116) to prevent the shuttle (3) from flying into the mounting chamber (116).

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