A trigger-type drone booster ejection device

Abstract

This invention discloses a trigger-type drone booster ejection device, relating to the field of drones, comprising: a push rod, a locking mechanism, and a top cover; one end of the push rod is provided with a first elastic element, the end of the first elastic element away from the push rod is restricted to move by the fuselage, and the first elastic element compresses and stores elastic potential energy; the locking mechanism releases the elastic potential energy stored in the first elastic element; the top cover is connected to the fuselage, and the top cover is provided with a push rod hole; the booster is connected to the fuselage through a booster support foot inserted into the push rod hole; the elastic potential energy of the first elastic element is converted into kinetic energy, driving the push rod to slide in the push rod hole, applying a push-out force to the booster, and the booster moves away from the fuselage under the action of the push-out force, causing the booster to detach from the fuselage. This invention, by adding an active detachment function to the booster, ensures that the booster reliably detaches from the fuselage; using this ejection device, the booster can be arranged on the fuselage axis, reducing the difficulty of adjusting the thrust line.

Description

Technical Field

[0001] This invention relates to the field of drones, and more specifically to a trigger-type drone booster ejection device. Background Technology

[0002] Some drones take off using a booster launch method. After launch, the drone enters normal flight mode, and the booster needs to detach from the fuselage to match the drone's center of gravity with its center of pressure. Existing technologies mostly use a conical docking method to install the booster. When the booster loses power after launch, it will automatically detach under the action of gravity. However, due to changes in flight attitude or the self-locking of the conical docking, there is a certain probability that the booster will not be able to detach from the fuselage, causing the drone to fail to enter level flight. At the same time, the booster is installed at a certain angle to the fuselage axis, making it difficult to adjust the thrust line. Summary of the Invention

[0003] The purpose of this invention is to address the problems that most current UAVs rely on gravity to detach the booster from the fuselage, but due to changes in flight attitude or conical docking self-locking, there is a certain probability that the booster will fail to detach from the fuselage. Furthermore, the invention provides a trigger-type UAV booster ejection device that adds an active detachment function to the booster, ensuring reliable detachment from the fuselage. This solution also facilitates the placement of the booster on the fuselage axis, reducing the difficulty of thrust line adjustment and solving the aforementioned problems.

[0004] The technical solution of the present invention is as follows:

[0005] A trigger-type drone booster ejection device specifically includes the following structure:

[0006] A push rod, one end of which is provided with a first elastic element, the end of which is away from the push rod and its movement is restricted by the machine body; the first elastic element is compressed and stores elastic potential energy; preferably, the first elastic element is a push rod compression spring;

[0007] The locking mechanism releases the elastic potential energy stored in the first elastic element; that is, the locking mechanism can fix the first elastic element in a compressed state, and the movement of the locking mechanism can release the elastic potential energy stored in the first elastic element, so as to ensure that the booster detaches from the fuselage at a specific time point.

[0008] A top cover is connected to the body, and a top rod hole is provided on the top cover; preferably, in order to ensure that the movement direction of the top rod is directional, when the pop-out device is not activated, a portion of the rear end of the top rod can be inserted into the top rod hole;

[0009] The booster is connected to the fuselage via a booster support foot inserted into a push rod hole; the elastic potential energy stored in the first elastic element is converted into kinetic energy, driving the push rod to slide in the push rod hole, applying a push force to the booster, and the booster moves away from the fuselage under the action of the push force, causing the booster to detach from the fuselage.

[0010] Furthermore, both the booster and the ejection device are installed directly behind the fuselage, and the direction of movement of the push rod is parallel to the fuselage axis. This ensures that the push force applied by the push rod is directed towards the rear of the fuselage and parallel to the fuselage axis, while simultaneously generating a reaction force on the fuselage, allowing the UAV to more smoothly transition into level flight. At the same time, since the booster is installed directly behind the fuselage, and the thrust line is parallel to the fuselage axis, it is easy to accurately and easily adjust the thrust line of the UAV.

[0011] Furthermore, the ejection device further includes: a base; the base is connected to the body, the top cover is connected to the base, the push rod is placed between the base and the top cover, and the end of the first elastic member away from the push rod is restricted to move by the base; preferably, the base is fixed to the rear end frame of the body by fasteners, and the top cover is installed to the rear end of the base by fasteners, the fasteners can be screws, bolts, rivets, etc., which are not limited in this invention; a first groove for placing the first elastic member can also be formed on the base, one end of the first elastic member is placed in the first groove, and the first elastic member is made to ensure that the first elastic member undergoes small deformation in directions other than the axial direction as much as possible; at the same time, the first elastic member and the base can be fixedly connected or not fixedly connected, which is not limited in this invention.

[0012] Furthermore, the locking mechanism includes:

[0013] A trigger is provided, one end of which is provided with a second elastic element, the end of which is restricted from movement by a base; the other end of the trigger is provided with a drive system that moves the trigger toward the base; preferably, the second elastic element is a trigger spring, and a second groove may be provided on the base for placing the second elastic element, one end of which is placed in the second groove, to ensure that the second elastic element undergoes minimal deformation in directions other than the axial direction; the second elastic element and the base can be fixedly connected or not, and this invention is not limited thereto;

[0014] A limiting rocker arm is provided, one end of which is rotatably mounted on the base. A limiting protrusion is provided in the middle of the limiting rocker arm, and a limiting member is provided at the other end of the limiting rocker arm. The limiting rocker arm is located between the push rod and the trigger. Preferably, the front end of the limiting rocker arm is connected to the middle of the base through a rotating shaft.

[0015] The top rod is provided with a limiting part that cooperates with the limiting member; the surface of the trigger is provided with a slot that cooperates with the limiting protrusion;

[0016] The limiting protrusion contacts the trigger surface, and the limiting member contacts the limiting part, keeping the locking mechanism in a balanced state, while the first elastic member is in a compressed state. The drive system moves the trigger, causing the limiting protrusion to fall into the slot, breaking the balance. The limiting rocker arm rotates, causing the limiting member to separate from the limiting part, and the push rod slides in the push rod hole under the drive of the first elastic member. Because the limiting protrusion contacts the trigger surface, it prevents the limiting rocker arm from rotating, so the limiting member holds the limiting part, keeping the push rod stationary. As the drive system moves the trigger, the limiting protrusion falls into the slot, and the limiting rocker arm, no longer restricted, rotates around the axis. The limiting member on the limiting rocker arm separates from the limiting part, and the push rod, no longer restricted, immediately converts its elastic potential energy into kinetic energy, driving the push rod to slide in the push rod hole.

[0017] Furthermore, the push rod includes a sleeve section and a push head section, the outer diameter of the sleeve section being larger than the outer diameter of the push head section; the first elastic element is disposed between the sleeve section and the base; the push head section can slide within the push rod hole;

[0018] The limiting part is the boundary between the sleeve section and the top section; preferably, in order to ensure the smoothness of mechanical movement, an inclined transition can be provided between the sleeve section and the top section.

[0019] Furthermore, the length of the trigger is adjustable. Preferably, the trigger includes a spindle section and a trigger section, which are sleeved together and can be extended and shortened. At the same time, the position is fixed by a trigger limiting member, thereby realizing the adjustable length of the trigger, that is, adjusting the length of the trigger extending out of the trigger hole. Preferably, the trigger limiting member is a screw.

[0020] Furthermore, the drive system is based on a motor located at the rear of the fuselage and a propeller bracket driven by the motor; the drive system is designed using the existing motor and propeller bracket at the rear of the fuselage, which further simplifies the structure; at the same time, a propeller is connected to the propeller bracket.

[0021] The drive system includes: a trigger hole on the top cover for sliding of the trigger and a spiral protrusion with a height difference on the propeller support; that is, the trigger segment on the trigger passes through the trigger hole and extends out, corresponding to the spiral protrusion; preferably, the spiral protrusion is an inclined surface, and there is a certain gap between the end of the trigger segment and the lowest point of the spiral protrusion when the ejection device is not activated, which can effectively prevent the ejection device from being activated by mistake.

[0022] The motor drives the propeller bracket to rotate, and the spiral protrusion rotates together with the propeller bracket. Then, as the height of the point on the spiral protrusion corresponding to the trigger gradually increases, the spiral protrusion pushes the trigger to move towards the base. That is, the distance between the end of the trigger segment on the trigger and the spiral protrusion gradually decreases, and then after contact, the spiral protrusion pushes the trigger to move towards the base.

[0023] Furthermore, the other end of the trigger is provided with a trigger roller that cooperates with the helical protrusion; that is, the trigger section of the trigger is provided with a trigger roller at its end.

[0024] The limiting component is a limiting roller; by setting the trigger roller and the limiting roller, the movement of the ejection device is made smoother, and at the same time, the friction is reduced.

[0025] Furthermore, there are two ejection devices and two booster legs, which are symmetrically arranged with respect to the booster axis. Preferably, one ejection device and one booster leg form a group, with a total of two groups, and they are arranged around the motor at 180°. This ensures the force balance of the booster and improves the reliability of the ejection device.

[0026] Compared with existing technologies, the advantages of this invention are:

[0027] 1. A trigger-type UAV booster ejection device, wherein a first elastic element pushes a push rod, which applies an ejection force to the booster. Under the action of the ejection force, the booster moves away from the fuselage, thereby detaching from the fuselage. By adding an active detachment function to the booster, it is ensured that the booster reliably detaches from the fuselage and that the booster does not self-lock. At the same time, the ejection device of the present invention can directly arrange the booster on the fuselage axis, reducing the difficulty of adjusting the thrust line.

[0028] 2. A trigger-type drone booster ejection device, which allows the booster to be placed behind the fuselage. While the push rod applies an ejection force, the fuselage is subjected to a reaction force, enabling the drone to smoothly transition into the level flight phase. Attached Figure Description

[0029] Figure 1 A layout diagram of a trigger-type drone booster ejection device;

[0030] Figure 2 for Figure 1 Enlarged view of point A in the middle;

[0031] Figure 3 Exploded view of a trigger-type drone booster ejection device;

[0032] Figure 4 This is a schematic diagram of the propeller support structure in a trigger-type drone booster ejection device.

[0033] Figure 5 A schematic diagram of the limiting rocker arm in a trigger-type UAV booster ejection device;

[0034] Figure 6 This is a schematic diagram of the trigger mechanism in a trigger-type drone booster ejection device.

[0035] Figure 7 This is a schematic diagram of the top rod in a trigger-type drone booster ejection device.

[0036] Reference numerals: 1-Fuselage, 2-Booster, 3-Ejection device, 4-Motor, 5-Propeller bracket, 6-Propeller, 301-Top rod, 302-First elastic element, 303-Top cover, 304-Top rod hole, 305-Booster support foot, 306-Base, 307-First groove, 308-Trigger, 309-Second elastic element, 310-Second groove, 311-Limiting rocker arm, 312-Limiting protrusion, 313-Shaft, 314-Limiting part, 315-Slot, 316-Sleeve section, 317-Top section, 318-Spindle section, 319-Trigger section, 320-Trigger limiting element, 321-Trigger hole, 322-Spiral protrusion, 323-Trigger roller, 324-Limiting roller. Detailed Implementation

[0037] It should be noted that relational terms such as "first" and "second" are used merely to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitations, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes said element.

[0038] The features and performance of the present invention will be further described in detail below with reference to embodiments.

[0039] Currently, the booster is mostly installed using a conical docking method. When the booster loses power after launch, it will automatically detach under the action of gravity. However, due to changes in flight attitude or the self-locking of the conical docking, there is a certain probability that the booster will not be able to detach from the fuselage, causing the UAV to fail to switch to level flight. At the same time, the booster is installed at a certain angle to the fuselage axis, making it difficult to adjust the thrust line.

[0040] This embodiment addresses the aforementioned problems by proposing a trigger-type UAV booster ejection device. By adding an active detachment function to the booster, it ensures that the booster reliably detaches from the fuselage. At the same time, using the ejection device in this embodiment allows the booster to be directly placed on the fuselage axis, reducing the difficulty of adjusting the thrust line.

[0041] Please see Figure 1-7 A trigger-type drone booster 2 ejection device 3 specifically includes the following structure:

[0042] A push rod 301 is provided at one end of a first elastic element 302. The end of the first elastic element 302 away from the push rod 301 is restricted from movement by the body 1. The first elastic element 302 is compressed to store elastic potential energy. Preferably, the first elastic element 302 is a compression spring of the push rod 301.

[0043] The locking mechanism releases the elastic potential energy stored in the first elastic element 302; that is, the locking mechanism can fix the first elastic element 302 in a compressed state, and the movement of the locking mechanism can release the elastic potential energy stored in the first elastic element 302, so as to ensure that the booster 2 is separated from the fuselage 1 at a specific time point.

[0044] Top cover 303 is connected to body 1, and top cover 303 is provided with top rod hole 304; preferably, in order to ensure that the movement direction of top rod 301 is directional, when the pop-out device 3 is not activated, a portion of the rear end of top rod 301 can be inserted into top rod hole 304.

[0045] The booster 2 is connected to the fuselage 1 by inserting the booster support foot 305 into the push rod hole 304; the elastic potential energy stored in the first elastic element 302 is converted into kinetic energy, which drives the push rod 301 to slide in the push rod hole 304, applying a push force to the booster 2. Under the action of the push force, the booster 2 moves away from the fuselage 1, causing the booster 2 to detach from the fuselage 1.

[0046] In this embodiment, specifically, such as Figure 1 As shown, the booster 2 and the ejection device 3 are both installed directly behind the fuselage 1, and the movement direction of the push rod 301 is parallel to the axis of the fuselage 1. This makes the push force applied by the push rod 301 directed towards the rear of the fuselage 1 and parallel to the axis of the fuselage 1, while generating a reaction force on the fuselage 1, allowing the UAV to smoothly transition into the level flight phase. At the same time, since the booster 2 is installed directly behind the fuselage 1 and the thrust line is parallel to the axis of the fuselage 1, it is easy for the booster 2 to accurately and easily adjust the thrust line of the UAV.

[0047] In this embodiment, specifically, the ejection device 3 further includes: a base 306; the base 306 is connected to the body 1, the top cover 303 is connected to the base 306, the push rod 301 is placed between the base 306 and the top cover 303, and the end of the first elastic member 302 away from the push rod 301 is restricted from movement by the base 306; the structure of the base 306 is as follows Figure 3 As shown, preferably, the base 306 is fixed to the rear end frame of the body 1 by fasteners, and the top cover 303 is installed to the rear end of the base 306 by fasteners. The fasteners can be screws, bolts, rivets, etc., and the present invention is not limited thereto. The base 306 may also have a first groove 307 for placing the first elastic member 302. One end of the first elastic member 302 is placed in the first groove 307 to ensure that the first elastic member 302 undergoes small deformation in directions other than the axial direction. At the same time, the first elastic member 302 and the base 306 can be fixedly connected or not fixedly connected, and the present invention is not limited thereto.

[0048] In this embodiment, specifically, the locking mechanism includes:

[0049] A trigger 308 is provided, one end of which is provided with a second elastic element 309. The end of the second elastic element 309 away from the trigger 308 is restricted from movement by a base 306. The other end of the trigger 308 is provided with a drive system for moving the trigger 308 toward the base 306. Preferably, the second elastic element 309 is a trigger spring. A second groove 310 for placing the second elastic element 309 can also be provided on the base 306. One end of the second elastic element 309 is placed in the second groove 310 to ensure that the second elastic element 309 undergoes minimal deformation in directions other than the axial direction. At the same time, the second elastic element 309 and the base 306 can be fixedly connected or not fixedly connected, which is not limited in this invention.

[0050] A limiting rocker arm 311 is provided, one end of which is rotatably mounted on the base 306. A limiting protrusion 312 is provided in the middle of the limiting rocker arm 311, and a limiting member is provided at the other end. The limiting rocker arm 311 is located between the push rod 301 and the trigger 308. The structure of the limiting rocker arm 311 is as follows: Figure 5 As shown, preferably, the front end of the limiting rocker arm 311 is connected to the middle of the base 306 via a pivot 313;

[0051] The push rod 301 is provided with a limiting part 314 that cooperates with the limiting member; the trigger 308 is provided with a slot 315 on its surface that cooperates with the limiting protrusion 312;

[0052] The limiting protrusion 312 contacts the surface of the trigger 308, and the limiting member contacts the limiting part 314, putting the locking mechanism in a balanced state, with the first elastic member 302 in a compressed state. The drive system moves the trigger 308, causing the limiting protrusion 312 to fall into the slot 315, breaking the balance. The limiting rocker arm 311 rotates, separating the limiting member from the limiting part 314, and the push rod 301 slides in the push rod hole 304 under the drive of the first elastic member 302. Because the limiting protrusion 312 contacts the surface of the trigger 308, the locking mechanism is in a balanced state, and the first elastic member 302 is in a compressed state. The surface contact prevents the rocker arm 311 from rotating, so the limiting member abuts against the limiting part 314, keeping the push rod 301 stationary. As the drive system moves the trigger 308, the limiting protrusion 312 falls into the slot 315. After the rocker arm 311 loses its restriction, it rotates around the pivot 313. The limiting member on the rocker arm 311 separates from the limiting part 314. After the push rod 301 loses its restriction, the first elastic member 302 immediately converts the elastic potential energy into kinetic energy, driving the push rod 301 to slide in the push rod hole 304.

[0053] In this embodiment, specifically, the push rod 301 includes a sleeve section 316 and a push head section 317, the outer diameter of the sleeve section 316 is larger than the outer diameter of the push head section 317; the first elastic member 302 is disposed between the sleeve section 316 and the base 306; the push head section 317 can slide within the push rod hole 304;

[0054] like Figure 7 As shown, the limiting part 314 is the boundary between the sleeve section 316 and the top section 317; preferably, in order to ensure the smoothness of mechanical movement, a slope transition can be provided between the sleeve section 316 and the top section 317.

[0055] Please see Figure 6 In this embodiment, specifically, the length of the trigger 308 is adjustable. Preferably, the trigger 308 includes a spindle section 318 and a trigger section 319, which are fitted together as a single unit and can be extended and shortened. At the same time, the position is fixed by the trigger limiting member 320, thereby realizing the adjustable length of the trigger 308, that is, adjusting the length of the trigger 308 extending out of the trigger hole 321. Preferably, the trigger limiting member 320 is a screw.

[0056] Please see Figure 1 , Figure 2 and Figure 4 The drive system is based on the motor 4 located at the rear of the fuselage 1 and the propeller bracket 5 driven by the motor 4; that is, in this embodiment, the drive system is designed using the existing motor 4 and propeller bracket 5 located at the rear of the fuselage 1, which further simplifies the structure; at the same time, a propeller 6 is connected to the propeller bracket 5.

[0057] The drive system includes: a trigger hole 321 on the top cover 303 for sliding of the trigger 308, and a spiral protrusion 322 with a height difference on the propeller bracket 5; that is, the trigger segment 319 on the trigger 308 passes through the trigger hole 321 and extends out, corresponding to the spiral protrusion 322; preferably, the spiral protrusion 322 is an inclined surface, and there is a certain gap between the end of the trigger segment 319 and the lowest point of the spiral protrusion 322 when the ejection device 3 is not activated, which can effectively prevent the ejection device 3 from being accidentally activated;

[0058] Motor 4 drives propeller bracket 5 to rotate, and the spiral protrusion 322 rotates together with propeller bracket 5. Then, as the height of the point on the spiral protrusion 322 corresponding to the trigger 308 gradually increases, the spiral protrusion 322 pushes the trigger 308 to move towards the base 306. That is, the distance between the end of the trigger segment 319 on the trigger 308 and the spiral protrusion 322 gradually decreases, and then after contact, the spiral protrusion 322 pushes the trigger 308 to move towards the base 306.

[0059] In this embodiment, specifically, the other end of the trigger 308 is provided with a trigger roller 323 that cooperates with the spiral protrusion 322; that is, the trigger section 319 in the trigger 308 is provided with a trigger roller 323 at its end.

[0060] The limiting component is the limiting roller 324; the setting of the trigger roller 323 and the limiting roller 324 makes the movement of the ejection device 3 smoother, and also reduces friction.

[0061] In this embodiment, specifically, there are two ejection devices 3 and two booster legs 305, which are symmetrically arranged with respect to the axis of the booster 2. Preferably, one ejection device 3 and one booster leg 305 form a group, and there are two groups in this embodiment, which are arranged around the motor 4 at 180°. This ensures the force balance of the booster 2 and improves the reliability of the ejection device 3.

[0062] The working principle of the trigger-type UAV booster 2 ejection device 3 proposed in this embodiment is as follows.

[0063] After the drone takes off via booster 2, the motor 4 at the rear of the fuselage 1 starts and drives the propeller bracket 5 to rotate. The spiral protrusion 322 on the propeller bracket 5 pushes the trigger 308 to move towards the fuselage 1. The limiting protrusion 312 falls into the slot 315, causing the limiting rocker arm 311 to rotate clockwise, thereby unlocking the structure. The push rod 301 pops out under the action of the push rod 301 compression spring. The push rod 301 collides with the booster support leg 305 at the front of the booster 2, thereby popping out the booster 2 and realizing the separation of the booster 2 from the fuselage 1.

[0064] The embodiments described above merely illustrate specific implementation methods of this application, and while the descriptions are detailed and specific, they should not be construed as limiting the scope of protection of this application. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of the technical solution of this application, and these modifications and improvements all fall within the scope of protection of this application.

Claims

1. A trigger-type UAV booster ejection device, characterized in that, include: A push rod (301) is provided at one end of the push rod (301), and the end of the first elastic element (302) away from the push rod (301) is restricted from movement by the body (1); the first elastic element (302) compresses and stores elastic potential energy; A locking mechanism that releases the elastic potential energy stored in the first elastic element (302); Top cover (303), the top cover (303) is connected to the body (1), and the top cover (303) is provided with a top rod hole (304); The booster (2) is connected to the fuselage (1) by inserting the booster support foot (305) into the push rod hole (304); the elastic potential energy stored in the first elastic element (302) is converted into kinetic energy, which drives the push rod (301) to slide in the push rod hole (304) and apply a push force to the booster (2). Under the action of the push force, the booster (2) moves away from the fuselage (1) and causes the booster (2) to detach from the fuselage (1). It also includes: a base (306); the base (306) is connected to the body (1), the top cover (303) is connected to the base (306), the top rod (301) is placed between the base (306) and the top cover (303), and the first elastic member (302) is restricted from moving at one end away from the top rod (301) by the base (306); The locking mechanism includes: A trigger (308) is provided at one end, and a second elastic element (309) is provided at one end of the trigger (308). The end of the second elastic element (309) away from the trigger (308) is restricted from moving by a base (306). The other end of the trigger (308) is provided with a drive system that moves the trigger (308) toward the base (306). A limiting rocker arm (311) is provided, one end of which is rotatably mounted on the base (306). A limiting protrusion (312) is provided in the middle of the limiting rocker arm (311), and a limiting member is provided at the other end of the limiting rocker arm (311). The limiting rocker arm (311) is located between the push rod (301) and the trigger (308). The push rod (301) is provided with a limiting part (314) that cooperates with the limiting member; the trigger (308) has a slot (315) on its surface that cooperates with the limiting protrusion (312); The limiting protrusion (312) contacts the surface of the trigger (308), and the limiting member contacts the limiting part (314), so that the locking mechanism is in a balanced state and the first elastic member (302) is in a compressed state. The drive system moves the trigger (308), the limiting protrusion (312) falls into the slot (315), the balance state is broken, the limiting rocker arm (311) rotates, so that the limiting member separates from the limiting part (314), and the push rod (301) slides in the push rod hole (304) under the drive of the first elastic member (302).

2. The trigger-type UAV booster ejection device according to claim 1, characterized in that, The push rod (301) includes a sleeve section (316) and a top section (317), wherein the outer diameter of the sleeve section (316) is larger than the outer diameter of the top section (317); the first elastic element (302) is disposed between the sleeve section (316) and the base (306); The limiting part (314) is the boundary between the sleeve section (316) and the top section (317).

3. The trigger-type UAV booster ejection device according to claim 1, characterized in that, The length of the trigger (308) is adjustable.

4. The trigger-type UAV booster ejection device according to claim 1, characterized in that, The booster (2) and the ejection device (3) are both installed directly behind the fuselage (1), and the movement direction of the push rod (301) is parallel to the axis of the fuselage (1).

5. The trigger-type UAV booster ejection device according to claim 4, characterized in that, The drive system is based on a motor (4) located directly behind the fuselage (1) and a propeller support (5) driven by the motor (4); The drive system includes: a trigger hole (321) on the top cover (303) for sliding the trigger (308) and a spiral protrusion (322) with a height difference on the propeller support (5); The motor (4) drives the propeller bracket (5) to rotate. As the height of the point on the spiral protrusion (322) corresponding to the trigger (308) gradually increases, the spiral protrusion (322) pushes the trigger (308) to move towards the base (306).

6. The trigger-type UAV booster ejection device according to claim 5, characterized in that, The other end of the trigger (308) is provided with a trigger roller (323) that cooperates with the spiral protrusion (322); The limiting component is a limiting roller (324).

7. A trigger-type UAV booster ejection device according to any one of claims 1-6, characterized in that, Both the first elastic element (302) and the second elastic element (309) are compression springs.

8. A trigger-type UAV booster ejection device according to any one of claims 1-6, characterized in that, The ejection device (3) and the booster support (305) are both two in number and are arranged symmetrically with respect to the axis of the booster (2).

Images