An emergency detachment device for a drone's power compartment

Abstract

This utility model relates to the field of unmanned aerial vehicle (UAV) safety technology, specifically an emergency detachment device for a UAV's power compartment. It includes a fuselage body and a power compartment body. A groove is formed on the rear side of the fuselage body, and the power compartment body is located within this groove. A drive mechanism for emergency ejection of the power compartment body is provided on the rear side wall of the groove. An inverted U-shaped latch is provided on the upper surface of the power compartment body, and an L-shaped lever lock is located above the power compartment body. The short arm of the L-shaped lever lock faces upward and is movably engaged with the inverted U-shaped latch from the rear. The long arm of the L-shaped lever lock is inclined upward from front to back. The advantages are: employing a double-trigger L-shaped lever + spring ejection structure, physical unlocking is achieved through the thermal shrinkage of a shape memory alloy and the inertial swing of a pendulum, thus achieving passive and rapid separation. The detachment process requires no electricity or signal control, is suitable for extreme environments, and has high reliability.

Description

Technical Field

[0001] This utility model relates to the field of drone safety technology, specifically to an emergency detachment device for a drone's energy compartment. Background Technology

[0002] With the widespread application of drones in logistics, firefighting, and inspection, the safety risks of their lithium-ion batteries are becoming increasingly prominent. Statistics show that globally, over 1200 drone fires are caused by battery thermal runaway each year, with 78% resulting in the complete destruction of the drone. The traditional method of securing the energy compartment, as the battery carrier, poses significant safety hazards, as it hinders emergency detachment in the event of high temperatures or impacts.

[0003] Currently, existing technologies lack a safe, effective, and highly reliable purely mechanical emergency detachment device for drone power compartments, especially suitable for electromagnetic interference-resistant scenarios such as firefighting and military applications, as well as other extreme environments. This device employs an L-shaped lever dual-trigger + spring ejection structure to facilitate physical unlocking in emergency situations, thereby achieving passive and rapid separation. Therefore, an emergency detachment device for drone power compartments is proposed. Utility Model Content

[0004] To overcome the technical deficiencies in the prior art and effectively solve the technical problems in the background art, this utility model provides the following technical solution:

[0005] An emergency ejection device for a drone's power compartment includes a fuselage and a power compartment body. A groove is formed on the rear side of the fuselage, and the power compartment body is located within the groove. A drive mechanism for emergency ejection of the power compartment body is provided on the rear sidewall of the groove. An inverted U-shaped latch is provided on the upper surface of the power compartment body. An L-shaped lever lock is provided above the power compartment body. The short arm of the L-shaped lever lock faces upward and is movably engaged with the inverted U-shaped latch from the rear. The long arm of the L-shaped lever lock is inclined upward from front to back. The position of the long arm of the L-shaped lever lock near the short arm is rotatably connected between the left and right sidewalls of the groove via a support rod. A shape memory alloy spring inclined upward from back to front is provided on the top wall of the groove above the front side of the L-shaped lever lock. The bottom end of the shape memory alloy spring is connected to the upper surface of the L-shaped lever lock at the rear end of the support rod via a hook. An inertial pendulum is provided on the top wall of the groove at the rear side of the L-shaped lever lock, and the inertial pendulum can make corresponding contact with the lower surface of the L-shaped lever lock at the rear end of the support rod.

[0006] In a preferred embodiment of this utility model, the driving mechanism is a compression spring, the rear end of which is fixed to the lower part of the rear side wall of the groove, and the front end of which is in contact with and squeezed against the main body of the energy chamber.

[0007] As a preferred technical solution of this utility model, the front and rear sides of the horizontal end of the inverted U-shaped buckle are provided with guide slopes that slope downward from the outside to the inside.

[0008] As a preferred technical solution of this utility model, a baffle corresponding to the groove is provided on the rear side of the main body. The upper end of the baffle is hinged to the edge of the upper rear side of the groove through a hinge. A torsion spring is provided between the rear side of the baffle and the top wall of the groove.

[0009] As a preferred technical solution of this utility model, T-shaped sliding grooves are provided on both the left and right sides of the groove, and T-shaped sliders that are slidably connected to the T-shaped sliding grooves are respectively provided on both sides of the energy compartment body.

[0010] Compared with existing technologies, the advantages of this invention are as follows: This emergency detachment device for the UAV's energy compartment adopts an L-shaped lever dual-trigger + spring ejection structure. Physical unlocking is achieved through the thermal contraction of shape memory alloy and the inertial swing of a pendulum, thus realizing passive and rapid separation. The detachment process requires no electricity or signal control, is suitable for extreme environments, and has high reliability. Attached Figure Description

[0011] Figure 1 This is a schematic diagram of the structure of this utility model.

[0012] Figure 2 This is a schematic diagram of the internal structure of this utility model.

[0013] Figure 3 This is a side view of the interior of the main body of the present invention.

[0014] Figure 4 This is a partial side view of the present invention.

[0015] Figure 5 This is a partial structural schematic diagram of the present invention.

[0016] Figure 6 This is a schematic diagram of the main structure of the energy storage unit of this utility model.

[0017] Figure 7 This is a schematic diagram of the structure of the baffle of this utility model.

[0018] In the diagram: 1. Main body of the fuselage; 2. Groove; 3. Main body of the energy chamber; 4. Compression spring; 5. Inverted U-shaped lock; 6. Support rod; 7. L-shaped lever lock; 8. Memory alloy spring; 9. Inertial pendulum; 10. Guide slope; 11. Baffle; 12. Torsion spring; 13. T-shaped slide; 14. T-shaped slider. Detailed Implementation

[0019] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0020] Please see Figure 1-7 This utility model provides a technical solution: an emergency ejection device for a drone's energy compartment, comprising a fuselage body 1 and an energy compartment body 3. A groove 2 is formed on the rear side of the fuselage body 1, and the energy compartment body 3 is located within the groove 2. A drive mechanism for emergency ejection of the energy compartment body 3 is provided on the rear sidewall of the groove 2. An inverted U-shaped latch 5 is welded and fixed to the upper surface of the energy compartment body 3. An L-shaped lever lock 7 is provided above the energy compartment body 3. The short arm of the L-shaped lever lock 7 faces upward and is movably engaged with the inverted U-shaped latch 5 from the rear. The long arm of the L-shaped lever lock 7 is inclined upward from front to back. The position of the long arm of the L-shaped lever lock 7 near the short arm is rotatably connected between the left and right sidewalls of the groove 2 via a support rod 6. A memory alloy spring 8, inclined upward from back to front, is fastened and fixed to the top wall of the groove 2 above the front side of the L-shaped lever lock 7 via a hook and latch. The bottom end of the memory alloy spring 8 is connected to the L-shaped lever lock 7 via a hook and latch. The upper surface is connected at the rear end of the support rod 6. During use, the memory alloy spring 8 contracts when the temperature is >75℃, which can pull the rear end of the long arm of the L-shaped lever lock 7 to rotate towards the tail of the drone, so that the L-shaped lever lock 7 disengages from the inverted U-shaped lock 5, so that the main body 1 can be detached from the energy compartment body 3 in case of high temperature. The top wall of the groove 2 is located behind the L-shaped lever lock 7 and a pendulum 9 that can swing back and forth is suspended. The pendulum 9 can contact the surface under the L-shaped lever lock 7 at the rear end of the support rod 6. During use, when the pendulum 9 is subjected to an impact of >6G (that is, the drone is suddenly subjected to an impact force equivalent to 6 times its own weight), it swings and instantly hits the rear end of the long arm of the L-shaped lever lock 7, causing the rear end of the long arm of the L-shaped lever lock 7 to rotate towards the tail of the drone, so that the L-shaped lever lock 7 disengages from the inverted U-shaped lock 5, so that the main body 1 can be detached from the energy compartment body 3 in case of impact.

[0021] Furthermore, such as Figure 3 and 4 As shown, the driving mechanism is a compression spring 4. The rear end of the compression spring 4 is welded and fixed to the lower part of the rear side wall of the groove 2. The front end of the compression spring 4 abuts and squeezes against the energy chamber body 3. In use, the compression spring 4 provides driving force for the energy chamber body 3 to be ejected from the groove 2 in an emergency.

[0022] Furthermore, such as Figure 6As shown, the front and rear sides of the horizontal end of the inverted U-shaped lock 5 are provided with guide slopes 10 that slope downward from the outside to the inside. In use, the guide slopes 10 facilitate the short arm and bend of the L-shaped lever lock 7 to engage or disengage from the inverted U-shaped lock 5.

[0023] Furthermore, such as Figure 1 and 7 As shown, a baffle 11 corresponding to the groove 2 is provided on the rear side of the main body 1. The upper end of the baffle 11 is hinged to the upper edge of the rear side of the groove 2 through a hinge. A torsion spring 12 is provided between the rear side of the baffle 11 and the top wall of the groove 2 (specifically, the two ends of the torsion spring 12 are perpendicular to each other at 90 degrees, and the two ends of the torsion spring 12 respectively fix and support the rear side of the baffle 11 and the top wall of the groove 2. The elastic tension of the torsion spring 12 on the baffle 11 is less than the elastic thrust of the compression spring 4. The principle is a mature existing technology and will not be described in detail here). In use, the elastic tension of the torsion spring 12 on the baffle 11 enables the baffle 11 to play an auxiliary limiting and blocking role for the main body 3 of the energy compartment, and also to play an auxiliary blocking and dust prevention role for the inside of the groove 2.

[0024] Furthermore, such as Figure 3 As shown, T-shaped grooves 13 are provided on both the left and right sides of the groove 2, such as... Figure 6 As shown, T-shaped sliders 14 are provided on both sides of the energy chamber body 3, which are slidably connected to the T-shaped slide groove 13. In use, the sliding of the T-shaped sliders 14 can play an auxiliary limiting and guiding role in the pop-out movement of the energy chamber body 3. It can also play an auxiliary limiting role when the energy chamber body 3 is placed in the groove 2.

[0025] Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the present invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. An emergency detachment device for a drone's power compartment, comprising a fuselage body (1) and a power compartment body (3), characterized in that: The main body (1) of the fuselage has a groove (2) on its rear side. The energy chamber body (3) is located in the groove (2). The rear side wall of the groove (2) is provided with a drive mechanism for driving the energy chamber body (3) to eject in an emergency. The upper surface of the energy chamber body (3) is provided with an inverted U-shaped latch (5). An L-shaped lever lock (7) is provided above the energy chamber body (3). The short arm of the L-shaped lever lock (7) faces upward and is movably engaged with the inverted U-shaped latch (5) from the rear. The long arm of the L-shaped lever lock (7) is inclined upward from front to back. The long arm of the L-shaped lever lock (7) is close to The short arm is rotatably connected between the left and right side walls of the groove (2) via the support rod (6). The top wall of the groove (2) is provided with a memory alloy spring (8) that slopes upward from back to front above the front side of the L-shaped lever lock (7). The bottom end of the memory alloy spring (8) is connected to the upper surface of the L-shaped lever lock (7) at the rear end of the support rod (6) via a hook. An inertial pendulum (9) is suspended on the top wall of the groove (2) at the rear side of the L-shaped lever lock (7). The inertial pendulum (9) can make corresponding contact with the surface under the L-shaped lever lock (7) at the rear end of the support rod (6).

2. The emergency detachment device for the unmanned aerial vehicle (UAV) power compartment according to claim 1, characterized in that: The driving mechanism is a compression spring (4). The rear end of the compression spring (4) is fixed to the lower part of the rear side wall of the groove (2), and the front end of the compression spring (4) is in contact with and squeezed by the energy chamber body (3).

3. The emergency detachment device for the unmanned aerial vehicle (UAV) power compartment according to claim 1, characterized in that: The inverted U-shaped latch (5) has guide slopes (10) that slope downward from the outside to the inside on both the front and back sides of the horizontal end.

4. The emergency detachment device for the unmanned aerial vehicle (UAV) power compartment according to claim 1, characterized in that: The rear side of the main body (1) is provided with a baffle (11) corresponding to the groove (2). The upper end of the baffle (11) is hinged to the edge of the upper rear side of the groove (2) through a hinge. A torsion spring (12) is provided between the rear side of the baffle (11) and the top wall of the groove (2).

5. The emergency detachment device for the unmanned aerial vehicle (UAV) power compartment according to claim 1, characterized in that: T-shaped grooves (13) are provided on both the left and right sides of the groove (2), and T-shaped sliders (14) that are slidably connected to the T-shaped grooves (13) are provided on both sides of the energy chamber body (3).

Images