A deceleration separation device

Abstract

This application discloses a deceleration separation device, comprising: a deceleration parachute compartment, a combined actuator, a deceleration parachute pack, a battery box, and a slave unit control board; the deceleration parachute compartment includes a compartment body and a compartment cover; a first port of the compartment body is snapped into the compartment cover; a second port of the compartment body is connected to the slave unit protective cylinder of a UAV via a first connector; the combined actuator is fixedly disposed inside the compartment body; one end of the combined actuator is a parachute ejector and connected to the compartment cover; the other end of the combined actuator is an explosive bolt and connected to the UAV's transition joint; the deceleration parachute pack is disposed inside the deceleration parachute compartment and connected to the compartment cover and the combined actuator via a second connector; the battery box is disposed inside the compartment body and connected to the parachute ejector and the explosive bolt; the slave unit control board is disposed inside the compartment body and communicatively connected to the parachute ejector and the explosive bolt. This application enables separation from the aircraft, reducing weight during free flight and improving the aircraft's endurance.

Description

Technical Field

[0001] This application relates to the field of unmanned aerial vehicle (UAV) technology, and more particularly to a deceleration and separation device. Background Technology

[0002] Currently, most deceleration devices for unmanned aerial vehicles (UAVs) are modular, single devices such as a single-stage drag chute or a dorsal deceleration plate. These are relatively expensive, and using a drag chute for a rear-propeller UAV can easily cause interference between the chute and the propeller blades. Furthermore, a dorsal deceleration plate can generate additional torque during deceleration, resulting in poor deceleration performance. In addition, existing deceleration devices do not include a separation mechanism. Summary of the Invention

[0003] The purpose of this application is to provide a deceleration and separation device that, after achieving the deceleration function, can effectively separate from the aircraft, reduce the weight of the aircraft during free flight, and improve the aircraft's endurance.

[0004] To achieve the above objectives, this application provides a deceleration separation device, comprising: a deceleration parachute compartment, a combined actuator, a deceleration parachute pack, a battery box, and a slave unit control board; the deceleration parachute compartment includes a compartment body and a compartment cover; a first port of the compartment body is snapped into the compartment cover; a second port of the compartment body is connected to the slave unit protective cylinder of the UAV via a first connector; the combined actuator is fixedly disposed inside the compartment body; one end of the combined actuator is a parachute ejector and is connected to the compartment cover; the other end of the combined actuator is an explosive bolt and is connected to the transition joint of the UAV; the deceleration parachute pack is disposed inside the deceleration parachute compartment and is connected to the compartment cover and the combined actuator via a second connector; the battery box is disposed inside the compartment body and is connected to the parachute ejector and the explosive bolt; the slave unit control board is disposed inside the compartment body and is communicatively connected to the parachute ejector and the explosive bolt.

[0005] As described above, the combined actuator also includes a receiving umbrella tray, a connecting central shaft, and a cutter; one side of the receiving umbrella tray is fixedly connected to the connecting central shaft, the end of the connecting central shaft away from the bearing umbrella tray is connected to the cutter, and the end of the cutter away from the connecting central shaft is connected to the umbrella thrower; the other side of the receiving umbrella tray is threadedly connected to an explosion bolt.

[0006] As described above, the receiving umbrella disc includes an outer ring and an inner ring; the outer ring is fitted onto the outside of the inner ring; the first side of the inner ring is fixed to the connecting central shaft via a third connector; the second side of the inner ring has threads, and an explosion bolt is threadedly connected to the inner ring.

[0007] As described above, the inner ring of the umbrella disc includes the umbrella disc body and the bearing inner ring; the first side of the umbrella disc body is connected to the connecting central shaft by screws; the second side of the umbrella disc body is provided with the bearing inner ring, which is threadedly connected to the explosion bolt.

[0008] As shown above, at least one umbrella pack connector is provided on the outer ring of the umbrella disc; the position of the umbrella pack connector and the position of the connecting central axis are located on the same side of the umbrella disc.

[0009] As mentioned above, the parachute launcher, explosive bolt, and cutter are all pyrotechnic devices.

[0010] As shown above, the interior of the parachute canopy is provided with a partition; the partition divides the interior of the parachute canopy into a first cavity and a second cavity; the partition has a connecting through hole; the combined actuator is fixedly installed inside the parachute canopy through the connecting through hole.

[0011] As shown above, the main body of the parachute canopy is also provided with multiple stabilizing surfaces. The stabilizing surfaces are located on the side of the main body of the parachute canopy near the canopy cover and are evenly spaced in a circular pattern along the outer wall of the main body of the parachute canopy.

[0012] As shown above, the canopy cover is a truncated cone with the bottom side being larger than the top side. A protrusion is provided on the outer edge of the canopy cover near the bottom side, and the protrusion is engaged with the inner edge of the canopy body.

[0013] As described above, the deceleration parachute pack includes a main parachute and a pilot parachute; the main parachute is connected to the parachute pack connector via a second connector; the pilot parachute is connected to the canopy cover, the cutter, and the main parachute via two second connectors respectively; wherein, the length of the second connector connecting the pilot parachute to the cutter is less than the length of the second connector connecting the pilot parachute to the main parachute.

[0014] The beneficial effects achieved by this application are as follows:

[0015] (1) The stabilizer of the deceleration separation device of this application has a rectifying effect during the take-off phase and has a certain stabilizing effect on the flight attitude of the UAV during the deceleration process.

[0016] (2) The deceleration and separation device of this application has sufficient rigidity and strength and can withstand a certain overload impact during the opening stage.

[0017] (3) The deceleration separation device of this application achieves graded deceleration through a deceleration parachute, which effectively reduces the overload impact of the UAV aircraft.

[0018] (4) The deceleration separation device of this application has reliable separation components, which improves the reliability of multi-stage separation and ensures smooth separation from the aircraft during the separation stage. Attached Figure Description

[0019] To more clearly illustrate the technical solutions in the embodiments of this application or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments recorded in this application. For those skilled in the art, other drawings can be obtained based on these drawings.

[0020] Figure 1 A structural diagram of one embodiment of the deceleration and separation device;

[0021] Figure 2 A half-sectional view of one embodiment of the deceleration and separation device;

[0022] Figure 3 A structural diagram of one embodiment of the combined actuator;

[0023] Figure 4 for Figure 3 A three-dimensional image;

[0024] Figure 5 This is a diagram showing the connection structure between the inner ring of the umbrella disc and the partition.

[0025] Figure 6a and Figure 6b All are structural diagrams of one embodiment of the parachute canopy;

[0026] Figure 7 A diagram showing the deceleration parachute in the deployed state;

[0027] 1 is the deceleration parachute compartment; 11 is the main body of the parachute compartment; 12 is the parachute compartment cover; 13 is the stabilizing surface; 14 is the partition; 111 is the first port; 112 is the second port; 121 is the bottom side; 122 is the top side; 123 is the boss; 124 is the nut; 125 is the parachute rope buckle; 1121 is the first connecting flange; 2 is the combined actuator; 21 is the parachute launcher; 22 is the explosion bolt; 23 is the cutter; 24 is the connecting shaft; 25 is the receiving parachute disc; 26 is the bearing roller; 231 is the cutter hole; 251 is the parachute pack connector; 252 is the inner ring of the parachute disc; 253 is the outer ring of the parachute disc; 2521 is the parachute disc body; 2522 is the inner ring of the bearing; 3 is the deceleration parachute pack; 31 is the main parachute; 32 is the guide parachute; 33 is the second connector; 4 is the battery box; 5 is the gasket; A is the breakage location. Detailed Implementation

[0028] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0029] like Figure 1 and Figure 2 As shown, this application provides a deceleration separation device, including: a deceleration parachute compartment 1, a combined actuator 2, a deceleration parachute pack 3, a battery box 4, and a slave unit control board. The deceleration parachute compartment 1 includes a compartment body 11 and a compartment cover 12. The compartment body 11 is made of composite material and has an integral structure. The first port 111 of the compartment body 11 is snapped into the compartment cover 12; the second port 112 of the compartment body 11 is connected to the slave unit protective sleeve clamp of the UAV via a first connector. The compartment body 11 is a hollow cylinder; the hollow cylinder can be a hollow round cylinder, a hollow rectangular cylinder, a hollow H-shaped cylinder, a hollow T-shaped cylinder, or a hollow irregular cylinder, etc. This application preferably uses a hollow round cylinder, which helps reduce air resistance and facilitates the installation of internal components. Furthermore, the second port 112 is provided with a first connecting flange 1121, which is connected to the parachute compartment body 11 by riveting; the submachine gun protective cylinder is provided with a second connecting flange, and the first connecting flange 1121 and the second connecting flange are connected by clamps. The combined actuator 2 is fixedly installed inside the parachute compartment body 11; one end of the combined actuator 2 is a parachute ejector 21, which is connected to the parachute compartment cover 12. Figure 3 As shown, the other end of the actuator 2 is an explosive bolt 22, which is connected to the transition joint of the UAV. Specifically, both ends of the explosive bolt 22 are threaded. The UAV's connector is connected to one end of the transition joint by a screw, and the other end of the transition joint is connected to the explosive bolt 22 by a nut. The explosive bolt 22 is a pyrotechnic device, similar in shape to a bolt, filled with gunpowder and a fuse. It is detonated by electricity, and the explosive bolt 22 breaks at its weakest point (e.g., Figure 5 As shown (A is the break point), the two connected parts are separated, enabling the separation of the deceleration parachute 3 from the UAV's sub-unit protective casing. The deceleration parachute 3 is located inside the deceleration parachute compartment and is connected to the compartment cover 12 and the combined actuator 2 via the second connector 33. The battery box 4 is located inside the compartment body 11 and is connected to the parachute ejector 21 and the explosive bolt 22. The sub-unit control board is located inside the compartment body 11 and is communicatively connected to the parachute ejector 21 and the explosive bolt 22, used to control the receiving commands of pyrotechnic devices.

[0030] Furthermore, such as Figure 3 and Figure 4As shown, the combined actuator 2 also includes a receiving parachute tray 25, a connecting central shaft 24, and a cutter 23. One side of the receiving parachute tray 25 is fixedly connected to the connecting central shaft 24. The end of the connecting central shaft 24 away from the bearing parachute tray is connected to the cutter 23. The end of the cutter 23 away from the connecting central shaft 24 is connected to the parachute ejector 21. The parachute ejector 21 is connected to the parachute canopy 12. The other side of the receiving parachute tray 25 is threadedly connected to an explosion bolt 22. Specifically, the connecting central shaft 24 and the cutter 23 are threadedly connected; the cutter 23 and the parachute ejector 21 are threadedly connected.

[0031] Furthermore, the receiving umbrella disc 25 includes an outer ring 253 and an inner ring 252. The outer ring 253 is fitted onto the outside of the inner ring 252. The first side of the inner ring 252 is fixed to the connecting central shaft 24 via a third connector, wherein the third connector is a screw. The second side of the inner ring 252 has threads, and an expansion bolt 22 is threadedly connected to the inner ring 252.

[0032] Furthermore, the inner ring 252 of the umbrella disc includes the umbrella disc body 2521 and the bearing inner ring 2522; the first side of the umbrella disc body 2521 is connected to the connecting central shaft 24 by screws; the second side of the umbrella disc body 2521 is provided with the bearing inner ring 2522, and the bearing inner ring 2522 is threadedly connected to the explosion bolt 22.

[0033] Furthermore, at least one umbrella pack connector 251 is provided on the outer ring 253 of the umbrella tray; the position of the umbrella pack connector 251 and the position of the connecting central axis 24 are located on the same side of the umbrella tray 25.

[0034] Specifically, the umbrella bag connector 251 is a lifting lug. This lug is connected to the outer ring 253 of the umbrella tray by screws and nuts. The specific number of umbrella bag connectors 251 depends on the actual situation; in this application, two are preferred. The two lugs are respectively located on the outer ring 253 of the umbrella tray on opposite sides of the connecting central shaft 24. The lugs and the receiving umbrella tray 25 are used to transmit the tension of the main umbrella 31 and also serve to prevent the umbrella lines from tangling.

[0035] Furthermore, such as Figure 3 As shown, the combined actuator 2 also includes bearing rollers 26. Specifically, the bearing rollers 26 enable the outer ring 253 of the umbrella disc to rotate relative to the inner ring 252 of the umbrella disc, thereby preventing the umbrella lines from tangling.

[0036] Furthermore, the cutter 23 is a cylindrical body with a cutter hole 231. The cutter 23 is electrically connected to the battery box and communicatively connected to the submachine control board. The cylindrical body can be a cylinder, a rectangular cylinder, or an irregular cylinder, etc., and is preferably cylindrical in this application. Specifically, the cutter 23 is a pyrotechnic device with threads at both ends, one end being an internal thread and the other an external thread. The cutter 23 is filled with gunpowder and a fuse, and also contains a cutting blade. When energized and detonated, the cutting blade cuts the parachute rope under the impact of the explosion.

[0037] Specifically, the parachute ejector 21 is a pyrotechnic device filled with gunpowder and a fuse. It also contains a piston rod. When ignited, the piston rod, under the impact of the explosion, generates an impact force on the head of the ejector 21, causing it to break. Simultaneously, the parachute canopy 12, under the impact, accelerates and detaches from the main body 11. At this point, the parachute cord pull 125 pulls out the guide parachute 32, which opens to decelerate the drone. The ejector 21 is used to connect or separate the parachute canopy 12 from the main body 11.

[0038] Furthermore, a partition 14 is provided inside the parachute compartment body 11; this partition 14 divides the interior of the parachute compartment body 11 into a first cavity and a second cavity; the partition 14 has connecting through holes; the combined actuator 2 is fixedly installed inside the parachute compartment body 11 through the connecting through holes. Specifically, the first cavity is used to accommodate the deceleration parachute pack 3 under compression; the second cavity is used to accommodate equipment such as antennas. The partition 14 is made of fiberglass composite material.

[0039] Specifically, such as Figure 5 As shown, the inner ring 252 of the umbrella disc is disposed in the first cavity, and the inner ring 2522 of the bearing passes through the connecting through hole of the partition 14. The umbrella disc body 11 is located on the side of the partition 14 adjacent to the first cavity. A gasket 5 is provided on the side of the partition 14 adjacent to the second cavity. The gasket 5, the partition 14 and the inner ring 252 of the umbrella disc are connected by screws passing through the gasket 5, the partition 14 and the inner ring 252 of the umbrella disc in sequence.

[0040] Furthermore, the submachine integrated control board is located in the second cavity and is connected to the partition 14.

[0041] Furthermore, such as Figure 1 and Figure 2 As shown, the main body 11 of the parachute canopy is also provided with a plurality of stabilizing surfaces 13. The stabilizing surfaces 13 are located on the side of the main body 11 of the parachute canopy near the parachute canopy cover 12 and are evenly spaced in a circular pattern along the outer wall of the main body 11 of the parachute canopy.

[0042] Specifically, the exact number of stabilizers 13 depends on the actual situation, and in this application, four are preferred.

[0043] Furthermore, the stabilizer 13 has a streamlined structure and is connected to the parachute compartment body 11 by rivets. Specifically, the stabilizer 13 is used for rectification during the takeoff phase.

[0044] Furthermore, such as Figure 6a and Figure 6b As shown, the canopy cover 12 is a frustum, with the bottom side 121 of the frustum being larger than the top side 122. A protrusion 123 is provided on the outer edge of the canopy cover 12 near the bottom side 121, and the protrusion 123 is engaged in the inner edge of the canopy body 11.

[0045] Furthermore, the parachute compartment cover 12 is also equipped with a parachute line buckle 125 and a nut 124. The parachute compartment cover 12 is connected to the parachute launcher 21 via the nut 124. The parachute compartment cover 12 is connected to the deceleration parachute pack 3 via the parachute line buckle 125.

[0046] Furthermore, such as Figure 7 As shown, the deceleration parachute pack 3 includes a main parachute 31 and a guide parachute 32. The main parachute 31 is connected to the parachute pack connector 251 via a second connector 33. The guide parachute 32 is connected to the canopy cover 12, the cutter 23, and the main parachute 31 via two second connectors 33, respectively. The length of the second connector 33 connected to the cutter 23 is shorter than the length of the second connector 33 connected to the main parachute 31. Specifically, the second connector 33 is a rope, but not limited to rope; in this application, it is preferably parachute cord. The parachute pack connector 251 is a lifting lug.

[0047] Furthermore, the guide umbrella 32 includes a guide umbrella body and guide umbrella lines. The lower part of the guide umbrella body is connected to the guide umbrella lines. The upper part of the guide umbrella lines is connected to the umbrella line buckle 125 of the umbrella canopy 12 via a second connector 33. The lower part of the guide umbrella lines is connected to the upper part of the main umbrella body of the main umbrella 31 via a second connector 33. The guide umbrella lines are connected to the cutter hole 231 of the cutter 23 via a second connector 33.

[0048] Furthermore, the main umbrella 31 is larger than the pilot umbrella 32.

[0049] Furthermore, the battery box 4 is connected to the main body 11 of the parachute compartment by screws and is located in the second cavity. Specifically, the function of the battery box 4 is to supply power to the pyrotechnic devices.

[0050] The working principle of the deceleration and separation device in this application is as follows:

[0051] Specifically, in one embodiment, the deceleration and separation device of this application is installed on a drop-type unmanned aerial vehicle (UAV). Its flight phases are sequentially: the take-off phase, the drop phase, the deceleration and descent phase, and the separation phase. The drop-type UAV is dropped by another aircraft. The deceleration and separation device first performs two-stage deceleration on the drop-type UAV. After reaching the target altitude, the deceleration and separation device separates the deceleration system from the drop-type UAV. After separation, the drop-type UAV enters the autonomous flight phase.

[0052] During the deceleration and descent phase, the parachute ejector 21 receives a command from the slave control board and energizes the battery box 4 to detonate. The impact force generated during detonation causes the parachute compartment cover 12 to detach from the main body 11. The parachute cord buckle 125 on the parachute compartment cover 12 pulls out the guide parachute 32 through the parachute cords. The guide parachute 32 opens, providing the first stage of deceleration for the drone. After the guide parachute 32 opens, the resistance is transmitted to the deceleration separation device through the second connector 33 connected to the cutter 23. The second connector 33 connected to the main parachute 31 is in a slack state.

[0053] When the first-stage deceleration of the drop-type UAV reaches a certain condition, the cutter 23 receives the command from the submachine control board and cuts the parachute rope (the second connecting piece 33 that connects the guide parachute 32 pack to the cutter 23) set in the cutter hole 231. The second connecting piece 33 (parachute rope) connecting the guide parachute 32 pack to the main parachute 31 pack is straightened, and the main parachute 31 is pulled out of the parachute pack by the guide parachute 32. The main parachute 31 opens, and the drop-type UAV is decelerated in the second stage.

[0054] When the drop-type UAV descends to a certain altitude (i.e., the separation phase), the explosive bolt 22 receives the command from the submachine control board and works. The explosive impact force inside breaks the bolt, thereby completing the separation of the deceleration separation device from the UAV (after separation, the transition connector will remain connected to the UAV).

[0055] The beneficial effects achieved by this application are as follows:

[0056] (1) The stabilizer of the deceleration separation device of this application has a rectifying effect during the take-off phase and has a certain stabilizing effect on the flight attitude of the UAV during the deceleration process.

[0057] (2) The deceleration and separation device of this application has sufficient rigidity and strength and can withstand a certain overload impact during the opening stage.

[0058] (3) The deceleration separation device of this application achieves graded deceleration through a deceleration parachute, which effectively reduces the overload impact of the UAV aircraft.

[0059] (4) The deceleration separation device of this application has reliable separation components, which improves the reliability of multi-stage separation and ensures smooth separation from the aircraft during the separation stage.

[0060] Although preferred embodiments of this application have been described, those skilled in the art, upon learning the basic inventive concept, can make other changes and modifications to these embodiments. Therefore, the scope of protection of this appended application is intended to be interpreted as including the preferred embodiments as well as all changes and modifications falling within the scope of this application. Clearly, those skilled in the art can make various alterations and modifications to this application without departing from the spirit and scope of this application. Thus, if these modifications and modifications of this application fall within the scope of protection of this application and its equivalents, this application also intends to include these modifications and modifications.

Claims

1. A deceleration and separation device, characterized in that, include: Deceleration parachute compartment, combined actuator, deceleration parachute pack, battery box and submachine gun control board; The deceleration parachute compartment includes the main body of the parachute compartment and the parachute compartment cover; The first port of the parachute compartment body is snapped into the parachute compartment cover; the second port of the parachute compartment body is connected to the drone's sub-unit protective cylinder via the first connector; The combined actuator is fixedly installed inside the main body of the parachute compartment; one end of the combined actuator is a parachute ejector and is connected to the parachute compartment cover; the other end of the combined actuator is an explosive bolt and is connected to the transition joint of the UAV. The drag chute pack is located inside the drag chute compartment and is connected to the compartment cover and the combined actuator via a second connector. The battery box is located inside the main body of the parachute compartment and is connected to the parachute ejector and the explosive bolts respectively; The submachine gun control board is located inside the main body of the parachute compartment and is communicatively connected to the parachute ejector and the explosive bolts, respectively. The combined actuator also includes a receiving umbrella disc, a connecting central shaft, and a cutter; One side of the receiving umbrella tray is fixedly connected to the connecting central shaft; the end of the connecting central shaft away from the bearing umbrella tray is connected to the cutter; the end of the cutter away from the connecting central shaft is connected to the umbrella thrower; the other side of the receiving umbrella tray is threadedly connected to the explosion bolt. The umbrella tray includes an outer ring and an inner ring; the outer ring is fitted onto the outside of the inner ring; the first side of the inner ring is fixed to the connecting shaft via a third connector; the second side of the inner ring has threads, and an explosion bolt is threaded to the inner ring. At least one umbrella pack connector is provided on the outer ring of the umbrella tray; the position of the umbrella pack connector and the position of the connecting central axis are located on the same side of the umbrella tray. The deceleration parachute pack includes a main parachute and a pilot parachute; the main parachute is connected to the parachute pack connector via a second connector; the pilot parachute is connected to the canopy cover, the cutter, and the main parachute via two second connectors respectively; wherein, the length of the second connector connecting the pilot parachute to the cutter is shorter than the length of the second connector connecting the pilot parachute to the main parachute. The cutter is electrically connected to the battery box and communicatively connected to the submachine control board; the cutter is filled with gunpowder and a fuse, and also has a cutting blade inside.

2. The deceleration and separation device according to claim 1, characterized in that, The inner ring of the umbrella disc includes the umbrella disc body and the bearing inner ring; the first side of the umbrella disc body is connected to the connecting central shaft by screws; the second side of the umbrella disc body is provided with the bearing inner ring, which is threadedly connected to the explosion bolt.

3. The deceleration and separation device according to claim 1, characterized in that, Parachute launchers, explosive bolts, and cutters are all pyrotechnic devices.

4. The deceleration and separation device according to claim 1, characterized in that, The main body of the parachute canopy is equipped with a partition; the partition divides the interior of the main body of the parachute canopy into a first cavity and a second cavity; the partition has a connecting through hole; the combined actuator is fixedly installed inside the main body of the parachute canopy through the connecting through hole.

5. The deceleration and separation device according to claim 1 or 4, characterized in that, The main body of the parachute canopy is also equipped with multiple stabilizing surfaces, which are located on the side of the main body of the parachute canopy near the canopy cover and are evenly spaced in a circular pattern along the outer wall of the main body of the parachute canopy.

6. The deceleration and separation device according to claim 1, characterized in that, The canopy is a truncated cone with the bottom side being larger than the top side. A protrusion is provided on the outer edge of the canopy near the bottom side, and the protrusion is engaged with the inner edge of the canopy body.

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