High-reliability unmanned aerial vehicle parachute cabin
The UAV parachute compartment device, designed with an electric latch and external hinge, solves the problems of high cost of gunpowder power source and hatch hooking, achieving high reliability and low cost of parachute recovery, and supporting multiple reuses.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- MINYIN INTERNATIONAL AVIATION VEHICLE IND (BEIJING) CO LTD
- Filing Date
- 2025-06-27
- Publication Date
- 2026-07-21
AI Technical Summary
Existing drone parachute mechanisms use gunpowder power sources to drive and control the opening of the canopy, resulting in high costs and poor reliability. Furthermore, the canopy hinges are located inside the canopy, which can easily lead to parachute failure.
The hatch opening is controlled by an electric latch, and the hatch hinge is designed on the outside of the hatch body. Combined with a torsion spring to drive the hatch to rotate, a reliable hatch opening and resetting operation is achieved.
It achieves highly reliable and low-cost parachute recovery, avoids snagging problems during parachute opening, and supports multiple reuses.
Smart Images
Figure CN224528986U_ABST
Abstract
Description
Technical Field
[0001] This utility model relates to a highly reliable unmanned aerial vehicle (UAV) parachute compartment. Background Technology
[0002] A drone is an unmanned aerial vehicle (UAV) that is reusable and flies under radio remote control or automated program control. Parachute recovery is one of the most widely used recovery methods for UAVs. Currently, the parachute opening mechanism generally uses a propellant-powered control system. However, using a propellant-powered control system for opening the parachute is not reusable and is costly; it is also prone to abnormal situations such as premature opening or failure to open. In addition, the conventional parachute canopy hinge is located inside the canopy, and during parachute opening, the parachute lines and parachute body are prone to snagging on the hinge, leading to opening failure and poor reliability. Utility Model Content
[0003] To address the aforementioned problems in the prior art, the inventors have proposed an innovative and highly reliable UAV parachute compartment device. This device employs an electric latch to control the opening of the compartment, ensuring high control accuracy. The compartment cover hinge is located outside the compartment body, preventing snagging with the parachute lines and body during opening, thus guaranteeing the safety and reliability of the UAV's parachute landing and recovery. The device can be reused multiple times after landing.
[0004] According to this utility model, a parachute compartment device is provided, characterized in that it includes:
[0005] Locking pin, connecting bracket, parachute canopy, parachute canopy body, parachute canopy hinge, latch, electric locking pin.
[0006] in:
[0007] The upper surface of the connecting bracket has a through hole for fixing it to the drone body with bolts.
[0008] The right end of the connecting bracket is inserted into the parachute compartment, and the upper end of the pin seat is fixed to the connecting bracket.
[0009] The electric latch is cylindrical. When positively energized, it extends into the latch seat and passes through the latch hole in the latch. When negatively energized, it retracts into the latch seat.
[0010] The latch is secured to the inside of the parachute compartment canopy.
[0011] The parachute canopy hinge connects the parachute canopy to the drone fuselage. An embedded torsion spring drives the parachute canopy to rotate.
[0012] When the canopy is closed, the electric latch extends and inserts into the latch's round hole and the connecting bracket's round hole. At this time, the canopy is locked and closed by the latch.
[0013] When the parachute compartment is opened, the control circuit applies negative power to the electric latch, causing the electric latch to retract to the left into the latch seat. The latch on the parachute compartment cover is unlocked, and driven by the torsion spring inside the parachute compartment hinge, the parachute compartment cover rotates clockwise around the parachute compartment hinge to the open state. At this time, the parachute is released and the parachute opening is completed. Attached Figure Description
[0014] Figure 1 This is a schematic diagram of the parachute compartment in the closed state according to an embodiment of the present invention.
[0015] Figure 2 This is a schematic diagram of an opening mechanism according to an embodiment of the present invention.
[0016] Figure 3 This is a schematic diagram of the parachute compartment in the open state according to an embodiment of the present invention.
[0017] Figure 4 This is a schematic diagram of a drone equipped with a parachute compartment according to the present invention.
[0018] Figure 5 The image shows a parachute cabin hinge with an embedded torsion spring according to the present invention. Detailed Implementation
[0019] The embodiments of this utility model will be described below with reference to the accompanying drawings.
[0020] like Figure 1 and Figure 2 As shown, according to one embodiment of the present invention, the drone parachute compartment includes: a pin seat 1, a connecting bracket 2, a parachute compartment cover 3, a parachute compartment body 4, a parachute compartment hinge 5, a latch 6, and an electric pin 7.
[0021] The upper surface of the connecting bracket 2 has a through hole, which is fixed to the drone body with bolts.
[0022] The right end of the connecting bracket 2 is inserted into the umbrella compartment body 4, and the upper end of the pin seat 1 is fixed on the connecting bracket 2.
[0023] The electric latch 7 is a cylinder. When positive power is applied, it extends into the latch seat 1 and passes through the latch hole 8 in the latch 6. When negative power is applied, it retracts into the latch seat 1.
[0024] The latch 6 is fixed to the inside of the parachute compartment cover.
[0025] The parachute hinge 5 connects the parachute canopy 3 and the drone fuselage 10. The parachute hinge 5 has a torsion spring 11 embedded in it, which can drive the parachute canopy 3 to rotate.
[0026] When the cabin is not open, the electric latch 7 extends and inserts into the latch hole 8 of the latch 6 and the bracket hole 9 of the connecting bracket 2. At this time, the parachute cabin cover 3 is closed due to the constraint of the latch 6.
[0027] When the parachute compartment is opened, the control circuit energizes the electric latch 7 with negative current, causing the electric latch 7 to retract to the left into the latch seat 1. The latch 6 on the parachute compartment cover 3 is unlocked. Driven by the torsion spring inside the parachute compartment hinge 5, the parachute compartment cover 3 rotates clockwise around the parachute compartment hinge 5 to the open state of 120°. At this time, the parachute is released and the parachute opening is completed, and the UAV begins its parachute descent and landing.
[0028] When performing the umbrella compartment reset operation, first retract the umbrella body into the umbrella compartment 4, then press down the umbrella compartment cover 3 counterclockwise to the closed state. The control circuit energizes the electric latch 7 in the positive direction. The electric latch 7 extends out of the latch seat 1 and inserts to the right into the latch hole 8 of the latch 6 and the bracket hole 9 of the connecting bracket 2 to lock it, thus completing the reset of the umbrella compartment, which can be used for the next opening of the umbrella.
[0029] The advantages and / or beneficial effects of this utility model include:
[0030] 1) Use electric latch control.
[0031] Conventional parachute compartment opening mechanisms are generally driven and controlled by gunpowder power sources. However, gunpowder power sources cannot be reused and need to be replaced after each opening action, resulting in high costs. In addition, abnormal situations such as premature opening or failure to open the compartment are prone to occur during control.
[0032] This invention uses an electric latch mechanism to unlock and lock the parachute compartment, enabling repeated opening and resetting operations without replacing parts. It is simple to operate, highly reliable, and can effectively reduce the recovery cost of drones.
[0033] 2) An external hinge design is adopted to ensure the reliability of the umbrella opening process.
[0034] The hinges of conventional parachute canopies are located inside the canopy. When a drone lands and opens the parachute canopy, the parachute lines and parachute body are prone to snagging on the hinges inside the canopy, leading to failure to open the parachute and resulting in poor reliability.
[0035] The hinge of the canopy in this invention is located on the outside of the canopy. When the canopy is opened, the canopy rotates clockwise to open by 120°. During the opening process, the hinge is located outside the canopy and does not interfere with the release of the canopy, thus preventing snagging and ensuring the reliability of the opening process.
[0036] 3) It adopts a modular design, which is easy to process and has low cost.
[0037] The parachute canopy of this utility model adopts a modular design and production, and the components are easy to disassemble and assemble, meeting the needs of rapid on-site replacement and debugging. The canopy canopy cover and canopy body are integrally molded from composite materials, which can be produced quickly and in large quantities, with short processing time and low cost.
Claims
1. A highly reliable unmanned aerial vehicle (UAV) parachute compartment, characterized in that... include: Socket (1), connecting bracket (2), parachute canopy (3), parachute canopy body (4), parachute canopy hinge (5), latch (6), electric socket (7). in: The upper surface of the connecting bracket (2) has a through hole, which is used to fix it to the body of the drone with bolts. The right end of the connecting bracket (2) is inserted into the parachute compartment body (4), and the upper end of the pin seat (1) is fixed on the connecting bracket (2). The electric latch (7) is a cylinder. When positive power is applied, it extends into the latch seat (1) and passes through the latch hole (8) in the latch (6). When negative power is applied, it retracts into the latch seat (1). The latch (6) is fixed to the inside of the parachute compartment canopy. The parachute canopy hinge (5) connects the parachute canopy (3) and the UAV fuselage (10). The parachute canopy hinge (5) has a torsion spring (11) embedded in it, which is used to drive the parachute canopy (3) to rotate. When the hatch is closed, the electric latch (7) extends and inserts into the latch hole (8) of the latch (6) and the bracket hole (9) of the connecting bracket (2). At this time, the canopy (3) is closed due to the latch (6). When the parachute compartment is opened, the control circuit energizes the electric latch (7) with negative current, and the electric latch (7) retracts to the left into the latch seat (1). The latch (6) on the parachute compartment cover (3) is unlocked. Driven by the torsion spring inside the parachute compartment hinge (5), the parachute compartment cover (3) rotates clockwise around the parachute compartment hinge (5) to the open state. At this time, the parachute is released and the parachute is opened.
2. The high-reliability UAV parachute compartment according to claim 1, characterized in that: When performing the parachute compartment reset operation, first put the parachute body into the parachute compartment (4), press down the parachute compartment cover (3) counterclockwise to the closed state, the control circuit makes the electric plug (7) positively energized, the electric plug (7) extends out of the plug seat (1) and inserts to the right into the locking hole (8) of the latch (6) and the bracket hole (9) of the connecting bracket (2) to achieve locking, and complete the reset of the parachute compartment.
3. The high-reliability UAV parachute compartment according to claim 1, characterized in that: The canopy cover (3) is rotated clockwise around the canopy hinge (5) to the open position at 120°.