Sealed parachute bay of high-speed unmanned aerial vehicle

Abstract

The invention relates to the technical field of unmanned aerial vehicles, and discloses a sealed parachute bay of a high-speed unmanned aerial vehicle, which comprises a bay shell connected with a supporting framework and used for accommodating a parachute landing device; the mounting frame is connected with the supporting framework and serves as an assembly carrier of the driving and limiting component; the driving part is assembled on the mounting frame; the limiting assembly is connected with the power output end of the driving part and has a locking working state and an unlocking working state; the thrust box is connected with the mounting frame, and an elastic thrust structure is arranged in the thrust box; the clamping plate is connected with the thrust box and matched with the limiting assembly, and the cover plate is connected with the clamping plate and used for sealing the cabin shell; in the assembling state, the limiting assembly is in the locking state, the cover plate is driven to move towards the cabin shell and be tightly attached to the cabin shell, cabin sealing is achieved, in the unlocking state, the driving piece drives the limiting assembly to be switched to the unlocking state, constraint on the clamping plate is finished, the thrust box drives the cover plate to be separated from the cabin shell through the clamping plate, and cabin opening is achieved.

Description

Technical Field

[0001] This application relates to the field of unmanned aerial vehicle (UAV) technology, and in particular to a sealed parachute compartment for a high-speed UAV. Background Technology

[0002] The recovery of fixed-wing high-speed drones typically relies on a parachute system. Its core operating logic is as follows: the parachute is pre-stored in a parachute compartment built into the fuselage, sealed and protected by the compartment's cover; when the drone needs to land, an unlocking mechanism is triggered to release the parachute cover, which is then pushed open by an ejection or thrust device, deploying the parachute and using air resistance to slow the drone down, ultimately resulting in a smooth landing. However, high-speed drones often operate in complex and harsh environments, frequently facing severe weather conditions such as high humidity, strong dust storms, and low temperatures. Existing parachute compartment structures have revealed numerous technical defects in practical applications, seriously affecting the stability and safety of the parachute system. Existing parachute canopies mostly use simple snap-fit, pin-locking, or single-bolt fixing structures, resulting in a large sealing gap between the canopy and the canopy body, which cannot effectively block external environmental media. In high-humidity environments, moisture in the air can easily seep into the parachute canopy through the gaps, causing metal components such as springs and pins in the ejection mechanism to rust and become stuck. At the same time, it may cause the propellant power source to become damp and the gas generator to fail, directly hindering the normal ejection of the parachute. The opening of existing parachute canopies mostly relies on a single power source (separate catapult, thrust spring). During high-speed flight, the parachute canopy needs to overcome huge airflow pressure, requiring a high-power power unit to ensure opening. This not only increases the overall weight of the drone and reduces its endurance, but may also result in insufficient power leading to an insufficient opening angle of the parachute canopy, preventing the parachute from being pulled out smoothly and affecting the deceleration effect. Summary of the Invention

[0003] To address the aforementioned problems, this application provides a sealed parachute compartment for a high-speed unmanned aerial vehicle.

[0004] The sealed parachute compartment of a high-speed unmanned aerial vehicle provided in this application adopts the following technical solution: A sealed parachute compartment for a high-speed unmanned aerial vehicle (UAV), applied to a high-speed UAV with an internal support frame, includes: a compartment shell connected to the support frame, the compartment shell for housing a parachute device; a mounting frame connected to the support frame, the mounting frame serving as an assembly carrier for drive and limiting components; a drive component mounted on the mounting frame, the drive component providing the power required for unlocking; a limiting component connected to the power output end of the drive component, the limiting component having two working states: locked and unlocked; a thrust box connected to the mounting frame, the thrust box having a built-in elastic thrust structure; a locking plate connected to the thrust box and adapted to the limiting component, the locking plate enabling force transmission and state connection; and a cover plate connected to the locking plate, the cover plate for sealing the compartment shell. In the assembled state, the limiting component is in a locked state, driving the cover plate to move towards the compartment shell and fit tightly, achieving a compartment seal. In the unlocked state, the drive component drives the limiting component to switch to the unlocked state, releasing the constraint on the locking plate, and the thrust box, through the locking plate, drives the cover plate to separate from the compartment shell, achieving compartment opening.

[0005] Furthermore, the limiting component includes: at least two shafts, at least two swing arms, a flexible transmission component, and an elastic traction component; the shafts are respectively connected to both sides of the mounting frame, the swing arms are rotatably connected to the shafts in a corresponding manner, the two ends of the flexible transmission component are respectively connected to the swing arms and the driving component, and are used to transmit the unlocking power of the driving component; the two ends of the elastic traction component are respectively connected to the swing arms and the thrust box, and are used to provide the traction force of the limiting component in the locked state.

[0006] Furthermore, the swing arm includes a power arm segment and a force-bearing arm segment connected to each other; the force-bearing arm segment is rotatably connected to the shaft, and the power arm segment is respectively connected to the flexible transmission component and the elastic traction component; at least two of the power arm segments are staggered in the assembly space of the mounting frame, and the power arm segment and the force-bearing arm segment form an obtuse angle.

[0007] Furthermore, the distance from the connection point between the elastic traction member and the power arm segment to the axis of the shaft is greater than the length of the force-bearing arm segment.

[0008] Furthermore, the card plate includes: a stop plate, a connecting plate, and a hook plate; the stop plate is slidably adapted to the inner cavity of the thrust box, the connecting plate is fixedly connected to the side of the stop plate away from the thrust box, and the hook plate is connected to the side of the connecting plate near the limiting component, for forming a locking engagement with the limiting component; the longitudinal cross section of the stop plate is trapezoidal, adapted to the shape of the inner cavity of the thrust box.

[0009] In the above scheme, the longitudinal section of the abutment plate is trapezoidal, so that when the tension spring drives the swing arm to move upward, the swing arm will make the side wall of the abutment plate fit tightly against the inner cavity of the thrust box through the hook plate. This effectively improves the sealing effect of the inner cavity of the thrust box. On the other hand, the trapezoidal shape of the abutment plate results in a small contact area with the inner cavity of the thrust box when rotating, which effectively reduces the friction between the abutment plate and the thrust box when the push spring pushes the abutment plate to move.

[0010] Furthermore, the built-in elastic thrust structure of the thrust box is a thrust spring, which is assembled on the inner wall of the thrust box, and one end of the thrust spring is in contact with the abutment plate, for applying a thrust away from the hull to the abutment plate in the unlocked state.

[0011] In the above scheme, when the cover is unlocked, the cover is given initial movement power, causing the front end of the cover to tilt up, thereby realizing the purpose of opening the parachute compartment by driving the cover with wind power. At the same time, the cover pulls on the parachute, which facilitates the opening of the parachute.

[0012] Furthermore, the end of the force-bearing arm segment away from the power arm segment is hook-shaped, and the inclined surface on the outer side of the force-bearing arm segment is provided with an arc-shaped chamfer to reduce the frictional resistance when engaging with the clamping plate.

[0013] Furthermore, the thickness of the cover plate gradually decreases in the direction away from the thrust box, and a sealing ring is provided between the contact surface of the cover plate and the cabin shell to enhance the sealing performance of the cabin.

[0014] Furthermore, the parachute device housed inside the cabin is a two-section parachute, and the two ends of the two-section parachute are respectively connected to the front and rear sides of the center of gravity of the high-speed UAV, which is used to realize the gradual deceleration and center of gravity balance of the high-speed UAV during the descent process.

[0015] The above solution makes the two centers of gravity of the drone tend to be balanced during landing, which effectively improves the stability of the drone during landing. The two-stage parachute allows the drone to decelerate step by step during the parachute opening process, thereby effectively reducing the pulling force generated by the drone stopping during the parachute opening process and achieving effective protection for the drone.

[0016] Furthermore, the flexible transmission component is a steel cable, and the elastic tension component is a tension spring; the mounting frame is provided with a slot adapted to the driving component, the driving component is fixedly assembled to the mounting frame through the slot, and the power output end of the driving component is detachably connected to one end of the steel cable.

[0017] In summary, this application includes the following beneficial technical effects: This invention uses the elastic tension of the limiting and locking components to ensure a tight fit between the cover plate and the cabin structure. Combined with the sealing ring between the cover plate and the cabin structure, and the trapezoidal fitting structure between the clamping plate and the thrust box, multiple layers of sealing protection are formed. This effectively prevents water vapor and dust from entering the parachute cabin, avoids corrosion or jamming of the ejection mechanism, and ensures that the parachute can still be ejected normally in complex environments.

[0018] It adopts a three-stage unlocking mechanism of power drive, elastic thrust, and airflow assistance. The power drive component provides the initial power for unlocking, the thrust spring of the thrust box provides the initial thrust for the cover to lift, and the high-speed airflow further pushes the cover to fully open. Even if a single power source fails, the parachute canopy can still be opened by subsequent power. At the same time, the mechanical transmission structure (steel cable, swing arm) is resistant to electromagnetic interference and has strong low-temperature performance, avoiding unlocking failures caused by electronic component failure. Attached Figure Description

[0019] Figure 1 This is a schematic diagram of the overall structure of the present invention; Figure 2 This is a schematic diagram of the parachute compartment of the present invention; Figure 3 This is a schematic diagram of the limiting component of the present invention; Figure 4 This is a schematic diagram of the card plate portion of the present invention; Figure 5 This is a schematic diagram of the power arm portion of the present invention; Figure 6 This is a schematic diagram of the sealing ring portion of the present invention.

[0020] Explanation of reference numerals in the attached drawings: 1. UAV, 2. Frame, 3. Shell, 4. Parachute, 5. Mounting frame, 6. Drive component, 7. Limiting assembly, 701. Shaft, 702. Swing arm, 7021. Power arm, 7022. Force arm, 7022. Steel cable, 703. Tension spring, 704. Thrust box, 8. Push spring, 801. Clamping plate, 9. Support plate, 901. Connecting plate, 902. Hook plate, 903. Cover plate, 10. Sealing ring, 11. Baffle plate, 12. Detailed Implementation

[0021] The following is in conjunction with the appendix Figure 1-6 This application will be described in further detail.

[0022] This application discloses a sealed parachute compartment for a high-speed unmanned aerial vehicle (UAV). (Refer to...) Figure 1The system includes: a drone 1, a frame 2, a cabin 3, a parachute 4, a mounting bracket 5, a drive unit 6, a limiting assembly 7, a thrust box 8, a retaining plate 9, a cover plate 10, a sealing ring 11, and a baffle 12. The cabin 3 is connected to the lower side of the frame 2 and is connected to the frame 2 by screws. The parachute 4 is housed in the cabin 3. The mounting bracket 5 is fixedly connected to the front side of the frame 2 by screws. The drive unit 6 is connected to the upper side of the mounting bracket 5. The upper side of the mounting bracket 5 has a retaining groove in which the drive unit 6 is installed. The limiting assembly 7 is connected to the power output end of the drive unit 6. The thrust box 8 is fixedly connected to the front side of the mounting bracket 5. At the bottom center, the chamber of the thrust box 8 is opened downwards. The clamping plate 9 is connected to the lower side of the thrust box 8 and is in contact with the limiting component 7. The cover plate 10 is connected to the lower side of the clamping plate 9 and is connected to the clamping plate 9 by screws. The front side of the mounting bracket 5 is connected to the baffle 12. The clamping plate 9 is connected in the gap between the baffle 12 and the inner cavity of the mounting bracket 5. The baffle 12 and the mounting bracket 5 are connected by screws. During assembly, the limiting component 7 moves the cover plate 10 upwards to fit against the cabin shell 3. When the drive component 6 swings, the limiting component 7 releases the lock on the clamping plate 9. Under the action of the thrust box 8, the front end of the clamping plate 9 separates from the cabin shell 3.

[0023] By setting the limiting component 7, an upward pulling force can be applied to the cover plate 10, thereby making the cover plate 10 fit tightly against the cannon shell 3. This effectively improves the sealing between the cannon shell 3 and the cover plate 10, thus preventing water vapor, dust, and other contaminants from entering the parachute compartment during high-altitude, high-speed flight of the UAV 1, which would affect the normal opening of the parachute 4. This effectively improves the protection of the parachute 4. The thrust box 8 provides power to the front end of the cover plate 10 when the parachute compartment needs to be opened, causing the front end of the cover plate 10 to tilt upwards. At this time, airflow acts between the cover plate 10 and the UAV 1, thereby enabling the cover plate 10 to be opened by airflow. The separation of the cover plate 10 will open the parachute 4. Pulling out of the cabin 3, the parachute 4 opens. The airflow opening method reduces the power and stroke required for the thrust box 8 to drive the card plate 9 to open the cover plate 10, thereby reducing the size of the thrust box 8 in the structural design and achieving the goal of reducing the weight of the UAV 1. On the other hand, the upturned front end of the cover plate 10 will create resistance to the UAV 1, reducing the flight speed of the UAV 1. This reduces the tensile stress of the parachute 4's parachute lines on the UAV 1 frame 2 when the parachute 4 deploys and brings the UAV 1 to a stop, thus protecting the structural stability of the UAV 1. At the same time, the mechanical opening method effectively improves the service life of the equipment.

[0024] As one embodiment of the present invention, refer to Figures 2 to 6The limiting assembly 7 includes shafts 701, swing arms 702, steel cables 703, and tension springs 704. Two shafts 701 are respectively connected to the left and right sides of the front of the mounting frame 5, and are fixedly connected to the mounting frame 5. Two swing arms 702 are respectively connected to the two shafts 701, and are rotatably connected to the shafts 701. The two ends of the steel cable 703 are respectively connected to the swing arms 702 and the driving component 6. The upper end of the steel cable 703 is connected to the driving component 6, and the lower end of the steel cable 703 is connected to... The swing arm 702 is connected, and the driving component 6 can drive the swing arm 702 to rotate around the shaft 701 via the steel cable 703. The two ends of the tension spring 704 are connected to the swing arm 702 and the thrust box 8 respectively. The swing arm 702 includes a power arm 7021 and a force-bearing arm 7022. The two force-bearing arms 7022 are rotatably connected to the two shafts 701 respectively, and the two power arms 7021 are connected to the upper sides of the two force-bearing arms 7022 respectively. The two power arms 7021 are staggered front and back. The power arm 7021 increases its usable length within the limited space of the mounting frame 5, thus forming a force-saving lever. This facilitates the rotation of the power arm 7021 by the drive component 6. The smaller driving force required for the rotation of the power arm 7021 reduces the power output requirement of the drive component 6, resulting in a smaller size of the drive component 6. This reduces the equipment cost of the drive component 6 and also reduces the weight of the UAV 1, thereby increasing its range. The distance from the connection point of the tension spring 704 and the power arm 7021 to the axis of the shaft 701 is X. The length of the force arm 7022 is less than X, and the length of X is greater than the length of the force arm 7022, thus forming a force-saving lever. This increases the power of the tension spring 704 when it rotates the swing arm 702, thereby increasing the upward pulling force of the swing arm 702 on the clamping plate 9. This causes the clamping plate 9 to drive the cover plate 10 to fit against the lower side of the cabin shell 3, thereby improving the sealing effect of the parachute compartment.

[0025] By setting a tension spring 704, one end of the tension spring 704 is fixed to the thrust box 8 in a fixed position. The contraction of the tension spring 704 provides the power for the swing arm 702 to move upward. By engaging the locking plate 9 with the swing arm 702, the swing arm 702 drives the locking plate 9 to move upward. The upward movement of the locking plate 9 drives the cover plate 10 to move upward, achieving a tight fit between the cover plate 10 and the cabin shell 3, preventing dust and moisture from entering the cabin shell 3, and achieving effective protection for the parachute 4.

[0026] As one embodiment of the present invention, refer to Figures 4 to 6The card plate 9 includes a stop plate 901, a connecting plate 902, and a hook plate 903. The stop plate 901 is connected to the inner cavity of the thrust box 8, the connecting plate 902 is connected to the lower side of the stop plate 901, and the hook plate 903 is connected to both sides of the top of the connecting plate 902. The stop plate 901 is frustum-shaped, and its longitudinal section is trapezoidal. The lower side of the inner cavity of the thrust box 8 is chamfered. When the stop plate 901 moves upward to the designated position, the chamfer on the lower side of the thrust box 8 and the stop plate 901 are aligned. The side walls are fitted together, and the inner wall of the thrust box 8 is connected to a push spring 801. The lower end of the push spring 801 is fitted with the abutment plate 901. The lower end of the force arm 7022 is hook-shaped, and the inclined surface of the force arm 7022 is provided with an arc-shaped chamfer. The thickness of the cover plate 10 gradually decreases from front to back. A sealing ring 11 is connected between the cover plate 10 and the cabin shell 3. The two ends of the parachute 4 are respectively connected to the front and rear sides of the center of gravity of the UAV 1. The parachute 4 is a two-section parachute 4.

[0027] By setting a stop plate 901, which is truncated pyramidal in shape, when the tension spring 704 moves the locking plate 9 upward via the swing arm 702, the four side walls of the stop plate 901 respectively fit into the chamfer on the lower side of the inner cavity of the thrust box 8, thereby extending the sealing surface, improving the sealing effect, and effectively protecting the thrust spring 801. At the same time, the trapezoidal longitudinal section of the stop plate 901 allows the side walls of the truncated pyramidal stop plate 901 to easily separate from the chamfer of the thrust box 8 when the thrust spring 801 pushes the stop plate 901 to move, effectively reducing the friction when the stop plate 901 moves, thereby reducing the thrust required for the thrust spring 801, and thus reducing the volume requirements for the thrust spring 801, thereby reducing the weight of the UAV 1 and extending the flight time of the UAV 1.

[0028] In actual use, the parachute 4 is placed in the storage cavity of the cabin 3, and the two ends of the parachute 4 are connected to the front and rear sides of the center of gravity of the UAV 1 by ropes respectively; the cover plate 10 is pushed to move upward, so that the hook plate 903 squeezes the arc chamfer of the force arm 7022, causing the swing arm 702 to swing outward around the shaft 701, and the tension spring 704 is stretched; when the protrusion on the upper surface of the cover plate 10 is aligned with the slot of the cabin 3, the hook plate 903 engages with the hook-shaped end of the force arm 7022, the tension spring 704 returns to its original position, and the transmission plate 9 is pulled upward by the swing arm 702, so that the cover plate 10 and the cabin 3 fit tightly together, the sealing ring 11 is compressed, and the cabin is sealed; at this time, the push spring 801 is in a compressed state, storing elastic potential energy.

[0029] When UAV 1 needs to be recovered, the servo motor of the drive component 6 is activated, which pulls the power arm 7021 upward through the steel cable 703; the swing arm 702 rotates around the shaft 701, and the hook-shaped end of the force arm 7022 separates from the hook plate 903, releasing the constraint on the clamping plate 9; the push spring 801 releases elastic potential energy, pushing the stop plate 901 to move downward, causing the front end of the cover plate 10 to tilt up; high-speed airflow enters between the cover plate 10 and the fuselage of UAV 1, generating an upward lifting force, pushing the cover plate 10 to fully open; the cover plate 10 drives the guide parachute of the parachute 4 to be pulled out from the cabin shell 3, and after the guide parachute unfolds, it drives the main parachute to unfold, realizing the gradual deceleration and safe landing of UAV 1.

[0030] Finally, the following points should be noted: First, in the description of this application, it should be noted that, unless otherwise specified and limited, the terms "installation", "connection", and "linkage" should be interpreted broadly, and can be mechanical or electrical connections, or internal connections between two components, or direct connections. "Up", "down", "left", "right", etc. are only used to indicate relative positional relationships. When the absolute position of the described object changes, the relative positional relationship may change. Secondly: The accompanying drawings of the embodiments disclosed in this invention only involve the structures involved in the embodiments disclosed in this invention. Other structures can refer to the general design. In the absence of conflict, the same embodiment and different embodiments of this invention can be combined with each other. In conclusion, the above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

[0031] The above are all preferred embodiments of this application, and are not intended to limit the scope of protection of this application. Therefore, all equivalent changes made in accordance with the structure, shape and principle of this application should be covered within the scope of protection of this application.

Claims

1. A sealed parachute compartment for a high-speed unmanned aerial vehicle (UAV), applied to a high-speed UAV with an internal support frame, characterized in that, include: The cabin shell, connected to the supporting frame, is used to house the parachute device; The mounting bracket is connected to the support frame and serves as an assembly carrier for the driving and limiting components; A drive unit, mounted on the mounting bracket, provides the power required for unlocking; The limiting component is connected to the power output end of the drive component and has two working states: locked and unlocked. The thrust box, connected to the mounting bracket, has a built-in elastic thrust structure. The card plate is connected to the thrust box and adapted to the limiting component to realize the transmission of force and the connection of states; A cover plate, which connects with the retaining plate, is used to close the cabin shell; In the assembled state, the limiting component is in the locked state, driving the cover plate to move towards the cabin and fit tightly to achieve cabin sealing. In the unlocked state, the driving component drives the limiting component to switch to the unlocked state, releasing the constraint on the locking plate. The thrust box drives the cover plate to separate from the cabin through the locking plate, realizing cabin opening.

2. The sealed parachute compartment of a high-speed unmanned aerial vehicle according to claim 1, characterized in that, The limiting assembly includes: at least two shafts, at least two swing arms, a flexible transmission component, and an elastic traction component; the shafts are respectively connected to both sides of the mounting frame, the swing arms are rotatably connected to the shafts in a corresponding manner, the two ends of the flexible transmission component are respectively connected to the swing arms and the driving component, and are used to transmit the unlocking power of the driving component; the two ends of the elastic traction component are respectively connected to the swing arms and the thrust box, and are used to provide the traction force of the limiting assembly in the locked state.

3. The sealed parachute compartment of a high-speed unmanned aerial vehicle according to claim 2, characterized in that, The swing arm includes a power arm segment and a load-bearing arm segment connected to each other; the load-bearing arm segment is rotatably connected to the shaft, and the power arm segment is respectively connected to the flexible transmission component and the elastic traction component; at least two of the power arm segments are staggered in front and behind within the assembly space of the mounting frame, and the power arm segment and the load-bearing arm segment form an obtuse angle.

4. The sealed parachute compartment of a high-speed unmanned aerial vehicle according to claim 3, characterized in that, The distance from the connection point between the elastic traction member and the power arm segment to the axis of the shaft is greater than the length of the force-bearing arm segment.

5. The sealed parachute compartment of a high-speed unmanned aerial vehicle according to claim 3, characterized in that, The card plate includes: a stop plate, a connecting plate, and a hook plate; the stop plate is slidably adapted to the inner cavity of the thrust box, the connecting plate is fixedly connected to the side of the stop plate away from the thrust box, and the hook plate is connected to the side of the connecting plate near the limiting component, for forming a locking engagement with the limiting component; the longitudinal cross section of the stop plate is trapezoidal, adapted to the shape of the inner cavity of the thrust box.

6. The sealed parachute compartment of a high-speed unmanned aerial vehicle according to claim 5, characterized in that, The built-in elastic thrust structure of the thrust box is a thrust spring, which is assembled on the inner wall of the thrust box, and one end of the thrust spring is in contact with the abutment plate, which is used to apply a thrust away from the hull to the abutment plate in the unlocked state.

7. The sealed parachute compartment of a high-speed unmanned aerial vehicle according to claim 3, characterized in that, The end of the force-bearing arm segment away from the power arm segment is hook-shaped, and the inclined surface on the outer side of the force-bearing arm segment is provided with an arc-shaped chamfer to reduce the frictional resistance when it engages with the hook plate of the card plate.

8. The sealed parachute compartment of a high-speed unmanned aerial vehicle according to claim 3, characterized in that, The thickness of the cover plate gradually decreases in the direction away from the thrust box, and a sealing ring is provided between the contact surface of the cover plate and the cabin shell to enhance the sealing performance of the cabin.

9. The sealed parachute compartment of a high-speed unmanned aerial vehicle according to claim 1, characterized in that, The parachute device housed inside the cabin is a two-section parachute, with each end of the two-section parachute connected to the front and rear sides of the center of gravity of the high-speed UAV, respectively, to achieve gradual deceleration and center of gravity balance during the descent of the high-speed UAV.

10. The sealed parachute compartment of a high-speed unmanned aerial vehicle according to claim 2, characterized in that, The flexible transmission component is a steel cable, and the elastic tension component is a tension spring; the mounting frame is provided with a slot that matches the driving component, the driving component is fixedly assembled to the mounting frame through the slot, and the power output end of the driving component is detachably connected to one end of the steel cable.

Images