A special-shaped umbrella cabin device and a partition installation and use method of an umbrella system

Abstract

The application relates to a special-shaped parachute cabin device and a partition installation and use method of a parachute system, and belongs to the field of unmanned aerial vehicle recovery. The device comprises a fuselage cabin, a special-shaped parachute cabin, a launching cabin, a parachute system and a parachute cabin cover. An upper opening of the fuselage cabin is arranged in the fuselage; the special-shaped parachute cabin is a hollow cabin body with an open top; the special-shaped parachute cabin is provided with a concave part for accommodating the launching cabin; the launching cabin is a hollow cabin body with an open top and is used for installing a launching parachute rocket; the launching cabin and the special-shaped parachute cabin are both upwardly open and are independently fixed in the fuselage cabin; the remaining components of the parachute system except the launching parachute rocket are installed in the special-shaped parachute cabin according to the cabin exit order; and the parachute cabin cover covers the opening of the fuselage cabin. The launching cabin and the special-shaped parachute cabin are independently and spatially integrated and installed in the launching cabin, and the parachute system is installed in partitions according to the cabin exit order, so that the problems that the existing launching cabin is installed in the parachute cabin and is easy to cause ablation or impact damage to the parachute cabin and the parachute system and the parachute system is easy to be hooked when exiting the parachute are solved.

Description

Technical Field

[0001] This invention belongs to the field of drone recycling, specifically relating to an irregularly shaped parachute compartment device for drones and a method for partitioning and using the parachute system within the parachute compartment. Background Technology

[0002] Unmanned aerial vehicles (UAVs) are widely used in both military and civilian fields due to their low cost and versatility. UAVs have various takeoff and landing methods, with common recovery methods including parachute recovery, runway recovery, and arrested recovery. Parachute recovery is a conventional method for UAV recovery, characterized by low requirements for ground support and flexible recovery in the field. Small and medium-sized UAVs, especially military UAVs, commonly use parachute recovery.

[0003] Parachute recovery methods can be categorized into passive and active parachute recovery methods based on how the parachute system exits the drone. Passive parachute recovery involves opening the parachute canopy during drone recovery, deploying the pilot chute, and then pulling the main parachute out of the drone once it is fully inflated. In this method, both the pilot and main parachutes need to be pulled back and inflated, making the system prone to snagging and entanglement with propellers, tail fins, and other structural components. Active parachute recovery, on the other hand, involves actively pulling the parachute system vertically upwards in a very short time using a deployment device. The canopy inflates rapidly, and the system effectively avoids propellers, tail fins, and other structural components. Due to its high reliability, active parachute recovery has been increasingly adopted and developed in more and more drone models in recent years.

[0004] The core components of an active parachute recovery device include the parachute compartment, the launch compartment, and the parachute system. Currently, the parachute compartment in active parachute recovery devices is a regular cuboid with an open upper surface. The remaining surfaces, excluding the opening, together form a hollow compartment that accommodates the parachute system. During installation, the launch compartment is first installed on the inner wall of the parachute compartment, and then the parachute pack and accessories are installed in the remaining space according to space requirements. This recovery device has the following problems: 1. With the launch compartment installed inside, the impact overload during parachute launch will act on the side walls of the parachute compartment, and the exhaust plume of the launch rocket will ablate the parachute compartment structure and the parachute system. Therefore, the parachute compartment and parachute system are easily damaged and typically have only a few uses. 2. With the parachute system and launch compartment co-located, the parachute system is prone to snagging with the launch compartment's base structure at the moment of launch. This snagging can damage the parachute system, ranging from reduced recovery performance to failed deployment and potential UAV recovery accidents. Summary of the Invention

[0005] Technical Problem to be Solved: To overcome the shortcomings of existing technologies, this invention provides an irregularly shaped parachute compartment device and a method for partitioned installation and use of the parachute system. The parachute compartment is designed with an irregular shape, with the launch compartment placed in the irregular part of the parachute compartment. Both the launch compartment and the launch compartment are installed independently within the fuselage of the UAV. The interior of the irregularly shaped parachute compartment is partitioned, and the parachute system is installed in a stacked manner according to the order of deployment. This solves the problems of existing systems where the launch compartment installed inside the parachute compartment easily causes ablation or impact damage to the parachute compartment and parachute system, and the problem of snagging during parachute deployment.

[0006] The technical solution of the present invention is: an irregularly shaped parachute compartment device, comprising a fuselage compartment, an irregularly shaped parachute compartment, a launch compartment, a parachute system, and a parachute compartment cover;

[0007] The fuselage compartment is located inside the fuselage of the UAV, with an opening at the top, and is used to accommodate and install other components.

[0008] The irregularly shaped parachute compartment is an open-top, hollow, irregularly shaped cabin structure used to house the parachute system; the side wall of the irregularly shaped parachute compartment has a recessed portion, the axis of which is parallel to the vertical geometric center line of the irregularly shaped parachute compartment, and the recessed portion is used to house the launch compartment.

[0009] The launch compartment is a hollow cabin structure with an open top, used to install the parachute rocket with the parachute system; the outer contour of the side wall of the launch compartment matches the inner concave part, and the launch compartment is coaxially embedded in the inner concave part; both the launch compartment and the irregular parachute compartment have their open ends facing upward and are independently fixed in the fuselage compartment, and the installation height of the open end of the launch compartment is not higher than the open end of the irregular parachute compartment.

[0010] The parachute system, excluding the parachute rocket, consists of other components stacked and installed in the irregularly shaped parachute compartment according to the order of exit. The parachute system is used for the parachute landing and recovery of the UAV.

[0011] The parachute canopy closes onto the opening of the fuselage compartment, and is used to close or open the opening of the fuselage compartment.

[0012] The technical solution of the present invention is as follows: the irregularly shaped parachute compartment device further includes a fireproof plate to prevent the jet stream of the parachute rocket from entering the fuselage compartment; the fireproof plate is located at the open end of the launch compartment and is fixedly connected to the fuselage compartment; the middle part of the fireproof plate is provided with a through hole that is consistent with the top opening of the launch compartment; the plate surface around the through hole covers the gap between the launch compartment and the irregularly shaped parachute compartment, and between the launch compartment and the fuselage compartment.

[0013] The technical solution of the present invention is as follows: the upper opening of the fuselage compartment allows for the vertical assembly and disassembly of the irregularly shaped parachute compartment and the launch compartment; the opening of the fuselage compartment is provided with an inner flange with a recessed structure around its perimeter; the open end of the irregularly shaped parachute compartment is provided with an outer flange structure in addition to the inner recess; the outer flange overlaps the inner flange and is fixedly connected by screws; the launch compartment is fixed to the inner wall of the fuselage compartment through an installation mechanism.

[0014] The open end of the irregularly shaped parachute compartment has a front opening near the head of the drone, and the front end of the upper opening of the fuselage compartment has a parachute strap groove that matches the front opening of the parachute compartment for passing through the front strap of the parachute system; the open end of the irregularly shaped parachute compartment has a rear opening near the tail of the drone for passing through the rear strap of the parachute system.

[0015] The technical solution of this invention is: the formula for calculating the inward flange depression depth of the fuselage compartment is:

[0016] Inward flange recess depth = irregular umbrella compartment outer flange thickness + umbrella compartment cover thickness + sealing coating thickness;

[0017] In the formula, the thickness of the sealing coating refers to the thickness of the sealing coating located between the outer flange of the irregularly shaped umbrella canopy and the umbrella canopy cover, used to seal the irregularly shaped umbrella canopy and the umbrella canopy cover.

[0018] The technical solution of the present invention is as follows: the installation mechanism includes an installation bracket and an installation base; the installation base is fixed to the inner wall of the structure at the front end of the fuselage, and a dovetail groove is vertically provided on one side of the installation base; the installation bracket is fixed to the outer wall of the launch compartment, and a protrusion is provided on one side of the installation bracket along the axial direction of the launch compartment, the protrusion being slidably fitted with the dovetail groove; the installation bracket and the installation base are respectively provided with limit holes, and the limit is locked by a quick-release pin inserted into the limit hole.

[0019] The technical solution of the present invention is as follows: The parachute system includes a front sling, a rear sling, a detachment connector, an upper sling, a main parachute, a connecting strap, and a launch rocket; in the parachute deployment state, one end of each of the two front slings is fixed to a front sling on either side of the UAV fuselage, and one end of the rear sling is fixed to a rear sling located inside the rear end of the fuselage compartment; the other ends of the two front slings and the other end of the rear sling converge and are fixedly connected to one end of the detachment connector; the other end of the detachment connector is connected to the canopy end of the main parachute via the upper sling; the top of the main parachute is connected to the tail of the launch rocket via the connecting strap; in the parachute non-deployment state, the front sling, rear sling, detachment connector, upper sling, and main parachute are all located within the irregularly shaped parachute compartment; the launch rocket is positioned with its nose facing upwards within the launch compartment;

[0020] The parachute rocket is connected to the airborne flight control electromechanical system via a parachute control cable to control the ignition of the parachute rocket; the detachment connector is connected to the airborne flight control electromechanical system via an adapter cable and a main parachute separation control cable to control the detachment connector to separate the main parachute when the UAV touches the ground.

[0021] The technical solution of the present invention is as follows: the adapter cable is pre-embedded in the rear sling, one end of which is electrically connected to the detachment connector, and the other end is connected to the airborne flight control electromechanical system through the main parachute separation control cable fixed at the rear suspension point.

[0022] The technical solution of the present invention is as follows: one end of the parachute canopy is hinged to the rear end of the fuselage compartment via a hinge, and the other end is locked to the front end of the fuselage compartment via a locking mechanism; the hinge adopts an eccentric rotating shaft form, with the hinge axis located behind the parachute canopy, for opening the parachute canopy 180° around the hinge shaft; the locking mechanism is used to lock the parachute canopy; the locking mechanism is connected to the airborne flight control electromechanical system via a parachute opening control cable, for controlling the opening of the parachute canopy.

[0023] The technical solution of this invention is: the longitudinal arrangement of the fuselage compartment on the UAV fuselage ensures that the change in the UAV's center of gravity before and after parachute deployment is within the permissible range of the UAV recovery device; the formula for calculating the overall center of gravity coordinates of the UAV after parachute deployment is as follows:

[0024]

[0025] A method for partitioning and installing the parachute system of the aforementioned irregularly shaped parachute compartment device, wherein the irregularly shaped parachute compartment is divided into three installation areas: A, B, and C, and the launch compartment is designated as installation area D; wherein area A is located at the end of the irregularly shaped parachute compartment near the front opening, and is used to install the front sling, the detachment connector, and the upper sling; area B is located on the side of the irregularly shaped parachute compartment adjacent to the concave portion, and is used to install the rear sling; area C is the area within the irregularly shaped parachute compartment excluding areas A and B, and is used to install the main parachute; area D is used to install the parachute rocket;

[0026] The method for installing and using the umbrella system in a partitioned manner includes the following steps:

[0027] Step 1: Secure the launch capsule to the fuselage using the mounting mechanism, and connect the parachute control cable to the launch capsule;

[0028] Step 2: Install the irregularly shaped parachute compartment into the fuselage compartment and fix the outer flange of the irregularly shaped parachute compartment to the inner flange of the fuselage compartment with fasteners.

[0029] Step 3: Install the front sling, the detachment connector, and the upper sling in section A from bottom to top: After connecting the ends of the two front slings away from the detachment connector to the corresponding front sling points, place them close to the shape of the aircraft body, enter the irregularly shaped parachute compartment through the parachute strap groove and the front opening of the parachute compartment, and fold them in a Z-shape to lay them flat at the bottom of the compartment in section A; place the detachment connector horizontally on the stacked front slings; fold the upper sling in a Z-shape and lay it flat on the detachment connector;

[0030] Step 4: Install the rear sling in area B: Connect the end of the rear sling away from the detachment connector to the rear lifting point, and connect both ends of the adapter cable inside the rear sling to the detachment connector and the main parachute separation control cable respectively; fold the rear sling in a Z-shape and lay it flat on the bottom of the cabin in area B, and secure it with rubber bands.

[0031] Step 5: Install the main umbrella in area C: Wrap the main umbrella with the canopy cover, fold it in a Z-shape and place it flat at the bottom of the cabin in area C, with the opening of the main umbrella at the bottom of the cabin and the top of the main umbrella at the top.

[0032] Step 6: Install the parachute rocket in area D: After connecting the bottom of the parachute rocket and the top of the main parachute with the connecting strap, insert the parachute rocket nose-up into the launch compartment; then connect the parachute rocket to the parachute control cable.

[0033] Step 7: Install fireproof board: Install fireproof board at the open end of the launch compartment top, align the through hole of the fireproof board with the open end of the launch compartment top, and fix the two sides of the fireproof board to the inner flange of the fuselage compartment with fasteners.

[0034] Step 8: Close the parachute canopy and lock it using the locking mechanism.

[0035] Beneficial effects

[0036] The beneficial effects of this invention are as follows: The irregularly shaped parachute device of this invention arranges the launch compartment outside the irregularly shaped parachute compartment, with both the launch compartment and the irregularly shaped parachute compartment independently installed and fixed inside the fuselage compartment, and the parachute rocket installed in the launch compartment. Compared to existing arrangements where the launch compartment is inside the parachute compartment, in this invention, the impact force generated by the launched rocket acts directly on the main load-bearing structure inside the fuselage compartment through its installation mechanism, thus preventing impact damage to the irregularly shaped parachute compartment and improving its service life. Simultaneously, the irregularly shaped parachute compartment does not need to withstand the impact force of the launched rocket, thus reducing the load-bearing strength requirements of the parachute compartment. This allows for a lightweight design of the irregularly shaped parachute compartment, reducing costs and weight, which is beneficial for the UAV's load-bearing capacity. Furthermore, by arranging the launch compartment and the irregularly shaped parachute compartment independently, it avoids the rocket's exhaust flame ablating the parachute compartment structure and parachute system, and also prevents the parachute system from snagging on the bottom of the launch compartment.

[0037] This invention installs a fireproof plate at the top opening of the launch cabin. The fireproof plate blocks and protects the area of ​​the rocket jet from the parachute, eliminating the safety hazard of the rocket jet entering the fuselage cabin and solving the technical problem of protecting the rocket jet from the parachute cabin structure and parachute system.

[0038] In this invention, the parachute system is installed in zones. By designing the irregularly shaped parachute compartment according to functional zones, it is divided into zone A for the front sling, zone B for the rear sling, zone C for the main parachute, and zone D for the launch compartment. Each zone is functionally independent, eliminating adverse interference between different components. Unlike traditional methods of mixing parachute systems in the same area, this invention installs each component of the parachute system in relatively independent functional zones, physically reducing adverse interference between parachute system components and improving the reliability of parachute opening.

[0039] This invention relates to a parachute system component installed in sections within a uniquely shaped parachute compartment. The components are installed using a stacked method according to the order of exit from the compartment. Compared to existing parachute system installation methods, this simplifies the installation and inspection process, eliminating the risk of entanglement between multiple parachute straps. Furthermore, the inner surface of the uniquely shaped parachute compartment is smooth and flat, without any structural parts or gaps. The parachute straps and canopy exit the compartment in sequence, preventing snagging and entanglement, thus avoiding damage to the parachute system, extending its lifespan, and ensuring the safety of drone parachute landings.

[0040] The present invention features a launch compartment and an irregularly shaped parachute compartment with a recessed fit. The launch compartment fills the recessed part of the irregularly shaped parachute compartment, making the installation spaces of the launch compartment and the irregularly shaped parachute compartment both independent of each other and arranged in the same fuselage compartment. This results in high utilization of the fuselage compartment space and facilitates the overall layout design of the UAV. At the same time, the traction offset between the parachute rocket and the main parachute is small, and the parachute system has good stability in the exit direction. Attached Figure Description

[0041] Figure 1 This is a schematic diagram of the overall composition of the irregularly shaped parachute cabin device in an embodiment of the present invention;

[0042] Figure 2 This is a schematic diagram of the umbrella system in the pulled-out state and the composition of the umbrella system in an embodiment of the present invention;

[0043] Figure 3 This is a schematic diagram of the launch bay installation structure in an embodiment of the present invention (the fuselage shape is not shown);

[0044] Figure 4 This is a top view of the launch bay installation state in an embodiment of the present invention (the fuselage shape is not shown);

[0045] Figure 5 This is a diagram of the irregularly shaped parachute compartment installation structure in an embodiment of the present invention;

[0046] Figure 6 This is a schematic diagram of the parachute canopy in closed state in an embodiment of the present invention;

[0047] Figure 7 This is a schematic diagram of the hinge structure of the parachute canopy in an embodiment of the present invention;

[0048] Figure 8 This is a schematic diagram of the parachute canopy in the open state in an embodiment of the present invention;

[0049] Figure 9 This is a schematic diagram of the recessed inward flange structure at the fuselage compartment opening in an embodiment of the present invention;

[0050] Figure 10 This is a schematic diagram (top view) of the partitioning of the irregularly shaped parachute compartment and launch compartment in the fuselage compartment in an embodiment of the present invention;

[0051] Figure 11This is a schematic diagram of the parachute loading method in areas A and B of the irregularly shaped parachute compartment in an embodiment of the present invention (the fuselage shape is not shown);

[0052] Figure 12 This is a schematic diagram of the parachute loading method in the irregularly shaped parachute compartment C area and the launch compartment D area in an embodiment of the present invention (the fuselage shape is not shown);

[0053] Figure 13 This is a schematic diagram of the adapter cable arrangement for the detachable connector in an embodiment of the present invention.

[0054] Explanation of reference numerals in the attached drawings: 1—Fuselage compartment, 2—Irregularly shaped parachute compartment, 3—Launch compartment, 4—Fireproof plate, 5—Parachute system, 6—Parachute compartment cover, 7—Power generator controller, 8—Oil pump assembly; 11—Parachute strap groove, 12—Front lifting point, 13—Rear lifting point, 14—Fuselage frame, 15—Mounting base, 16—Limiting hole, 17—Inner flange, 18—Compartment mounting hole; 21—Outer flange; 22—Parachute compartment mounting hole; 23—Front opening of parachute compartment, 24—Rear opening of parachute compartment; 31—Compartment, 32—Mounting bracket, 33—Quick release pin; 51—Front sling, 52—Rear sling, 53—Drop joint, 54—Upper sling, 55—Main parachute, 56—Connecting strap, 57—Parachute rocket, 58—Transfer cable; 61—Hinge, 62—Locking mechanism. Detailed Implementation

[0055] The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain the invention, and should not be construed as limiting the invention.

[0056] In the description of this invention, it should be understood that the terms "center," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," and "counterclockwise," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this invention.

[0057] Example 1:

[0058] This embodiment provides an irregularly shaped parachute compartment device, which can solve the following problems in existing active parachute recovery devices: the vulnerability of the parachute compartment structure caused by overload and ablation of the parachute rocket, the damage to the parachute canopy caused by parachute ablation, and the potential for entanglement between the parachute system and the internal structural components of the parachute compartment.

[0059] See Figure 1This embodiment describes an irregularly shaped parachute compartment device, including a fuselage compartment 1, an irregularly shaped parachute compartment 2, a launch compartment 3, a fireproof plate 4, a parachute system 5, and a parachute compartment cover 6. The irregularly shaped parachute compartment 2 and the launch compartment 3 are installed within the fuselage compartment 1; the parachute system 5 is installed in sections within the irregularly shaped parachute compartment 2 and the launch compartment 3; the fireproof plate 4 is installed above the launch compartment 3; the parachute compartment cover 6 covers the fuselage compartment 1 and is located directly above the irregularly shaped parachute compartment 2 and the fireproof plate 4. When the parachute compartment cover 6 is closed, it ensures the integrity of the UAV's aerodynamic shape. The following is a detailed description:

[0060] See Figure 1 , 5 9. The fuselage compartment 1 is located within the fuselage of the UAV and is a top-opening compartment structure used to accommodate and install the remaining components. The fuselage compartment 1 consists of the UAV's internal structural frame and the UAV's outer shell. The opening of the fuselage compartment 1 adopts an open-section structure design. The longitudinal sides of the fuselage compartment 1 are reinforced with trusses, and the front and rear fuselage frames 14 provide reinforcement. The top opening of the fuselage compartment 1 is sized to allow the irregularly shaped parachute compartment 2 and the launch compartment 3 to be vertically installed inside the fuselage compartment 1. A recessed inward flange 17 structure is provided around the opening of the fuselage compartment 1 to fix the irregularly shaped parachute compartment 2 and the fireproof plate 4.

[0061] See Figure 1 , 5 9, 11, the irregularly shaped parachute compartment 2 is a hollow cabin structure with an open top, and the irregularly shaped parachute compartment 2 is used to house the parachute system 5. For example... Figure 11 As shown, in this embodiment, the main structure of the irregularly shaped parachute 2 is a cuboid with an open top, and the side walls and bottom wall form the housing. One edge of the irregularly shaped parachute 2 perpendicular to the bottom wall is recessed, forming a square-shaped concave portion. The vertical axis of this concave portion is parallel to the geometric center line of the irregularly shaped parachute 2 perpendicular to its bottom wall. The concave portion is used to accommodate the launch compartment 3, and its shape is consistent with the shape of the launch compartment 3. The open end of the irregularly shaped parachute 2, in addition to the concave portion, has an outer flange 21 structure. When the irregularly shaped parachute 2 is installed vertically with its opening facing upwards in the fuselage compartment 1, the outer flange 21 at the open end of the irregularly shaped parachute 2 overlaps and fits against the inner flange 17 at the open end of the fuselage compartment 1, and the two are fixedly connected by screws. Specifically, the inner flange 17 of the fuselage compartment 1 has a housing mounting hole 18, and the outer flange 21 of the irregularly shaped parachute 2 has a parachute mounting hole 22 with a position and size corresponding to the housing mounting hole 18. Among them, the parachute compartment mounting hole 22 is a countersunk screw hole, and a prefabricated support plate nut is prefabricated at the bottom of the compartment mounting hole 18. The screw passes through the parachute compartment mounting hole 22, the compartment mounting hole 18 and the prefabricated support plate nut in sequence to achieve a fixed connection between the irregular parachute compartment 2 and the fuselage compartment 1.

[0062] See Figure 1 , 34. Launch compartment 3 is a hollow, open-top structure with a sealed interior. Inside launch compartment 3, the parachute rocket 57 of the parachute system 5 is installed. Its sealed structure prevents leakage of the parachute rocket 57's jet from the bottom. The overall structure of launch compartment 3 is columnar, and its sidewall outline matches the concave portion of the irregularly shaped parachute compartment 2, allowing launch compartment 3 to coaxially embed into the concave portion. When launch compartment 3 is placed within the concave portion of the irregularly shaped parachute compartment 2, it fills the concave portion, achieving spatial integration with the irregularly shaped parachute compartment 2. The opening of launch compartment 3 faces upwards and is fixed to the fuselage compartment 1 by a mounting mechanism. Specifically, as shown... Figure 3 , 4 As shown, the installation mechanism includes a mounting bracket 32 ​​and a mounting base 15. The mounting base 15 is fixed to the inner wall of the front end of the fuselage 1, located on the right side of the front fuselage frame 14 when facing the UAV's heading. The mounting base 15 has a dovetail groove along the vertical direction on the side facing away from the fuselage frame 14. The mounting bracket 32 ​​is fixed to the outer wall of the launch compartment 31. The mounting bracket 32 ​​has a protrusion along the axial direction of the launch compartment 3. The protrusion slides into the dovetail groove to form a slide rail installation structure. The mounting bracket 32 ​​and the mounting base 15 are respectively provided with two sets of limiting holes 16. By inserting quick-release pins 33 into the corresponding limiting holes 16 of the mounting bracket 32 ​​and the mounting base 15, the locking and limiting between the mounting bracket 32 ​​and the mounting base 15 can be achieved. This structure realizes tool-less disassembly and assembly of the launch compartment 3.

[0063] During installation, both the launch compartment 3 and the irregularly shaped parachute compartment 2 are installed independently and with their open ends facing upwards within the fuselage compartment 1. First, the launch compartment 3 is installed by vertically inserting the protruding part of the mounting bracket 32 ​​outside the compartment 31 into the dovetail groove of the mounting bracket 32. After sliding into place, it is locked by the quick-release pin 33. Then, the irregularly shaped parachute compartment 2 is installed vertically, and the outer flange 21 of the open end of the irregularly shaped parachute compartment 2 is fixedly connected to the inner flange 17 of the fuselage compartment 1 using screws. During installation, ensure that the height of the open end of the launch compartment 3 is not higher than the open end of the irregularly shaped parachute compartment 2 to facilitate the installation of the fireproof plate 4 and ensure the closure of the parachute compartment cover 6.

[0064] See Figure 1 , 12 The fireproof plate 4 is located directly above the open end of the launch compartment 3, and its two sides adjacent to the fuselage compartment 1 are fixedly connected to the inner flange 17 of the fuselage compartment 1 by screws. The center of the fireproof plate 4 has a through hole with the same shape and size as the open top of the launch compartment 3. The perimeter of the through hole covers the gaps between the launch compartment 3 and the irregularly shaped parachute compartment 2, and between the launch compartment 3 and the fuselage compartment 1, protecting the perimeter area of ​​the top of the launch compartment 3, preventing the exhaust jet of the parachute rocket 57 from ablating the parachute compartment and preventing the jet from entering the fuselage compartment 1 through structural gaps. In this embodiment, the fireproof plate 4 is a flight consumable, made of flame-retardant plastic material, and is characterized by low cost and mass production capability.

[0065] like Figure 8As shown, in addition to the irregularly shaped parachute compartment 2 and the launch compartment 3, the remaining space at the bottom of the fuselage compartment 1 can be used to install other airborne equipment of the UAV, such as the power generation controller 7 and the oil pump assembly 8, making the overall layout of the UAV compact and the space utilization rate high. Moreover, the exhaust flame of the parachute rocket 57 is isolated above the fireproof plate 4, and the airborne equipment and oil lines installed in the bottom space are not affected.

[0066] See Figure 1 , 2 The parachute system 5 unfolds in a spatial order from bottom to top, including the front sling 51, the rear sling 52, the detachment connector 53, the upper sling 54, the main parachute 55, the connecting strap 56, and the parachute rocket 57. When the parachute system 5 is not deployed, the parachute rocket 57 is positioned with its nose facing upward inside the launch compartment 3, while the remaining components are installed in sections within the irregularly shaped parachute compartment 2.

[0067] See Figure 2 , 5 The irregularly shaped parachute compartment 2 has a front opening 23 at the middle position of its open end facing the direction of the drone's flight path. The front end of the opening at the top of the fuselage compartment 1 has a parachute strap groove 11 corresponding to and matching the front opening 23, for the passage of the front sling 51 of the parachute system 5. The open end of the irregularly shaped parachute compartment 2 has a rear opening 24 at the middle position near the tail of the drone, for the passage of the rear sling 52 of the parachute system 5. The rear opening 24 is opposite to the front opening 23. Figure 2 As shown, two front sling points 12 are symmetrically arranged on both sides of the UAV fuselage at the front of the fuselage compartment 1, for fixing the connection end of the front sling 51 to the UAV. A rear sling point 13 is provided in the middle of the interior of the fuselage compartment at the rear of the fuselage compartment 1, for fixing the connection end of the rear sling 52 to the UAV.

[0068] See Figure 1 , 11 When the parachute system 5 is not deployed, the two front slings 51 are fixedly connected to the front slings 12 on both sides of the drone fuselage, and then close to the outer wall of the fuselage. They enter the irregularly shaped parachute 2 through the parachute sling groove 11 in the fuselage compartment 1 and the front opening 23 of the irregularly shaped parachute compartment 2. The rear sling 52 is fixedly connected to the rear sling 13 inside the fuselage compartment 1 and enters the irregularly shaped parachute compartment 2 through the rear opening 24 of the parachute compartment.

[0069] See Figure 2With the parachute system 5 deployed, one end of each of the two front slings 51 is fixedly connected to the front sling points 12 on either side of the UAV fuselage, and one end of the rear sling 52 is fixedly connected to the rear sling point 13 inside the fuselage compartment 1. The other ends of the two front slings 51 and the other ends of the rear sling 52 converge and are fixedly connected to one end of the detachment connector 53. The other end of the detachment connector 53 is connected to the canopy end of the main parachute 55 via the upper sling 54. The main parachute 55 has its canopy opening facing downwards and its top facing upwards. The top of the main parachute 55 is connected to the tail of the parachute rocket 57 via a connecting strap 56. The parachute rocket 57 is a consumable item and can be replaced after use.

[0070] In this embodiment, the detachment connector 53 is equipped with a protective sleeve to prevent damage to the drone from impacts and detachment. The detachment connector 53 is an electrically controlled separation device that separates into two parts at the moment of drone parachute landing, disconnecting the drone from the main parachute 55. The detachment connector 53 is wrapped with a flexible protective sleeve to prevent it from being bumped or snagged when exiting the drone. After the drone lands, the protective sleeve of the detachment connector 53 prevents it from falling downwards and damaging the drone.

[0071] The parachute rocket 57 and the detachment connector 53 are controlled by the airborne flight controller. Specifically, the parachute rocket 57 is connected to the airborne flight controller via a parachute control cable to control its ignition. The detachment connector 53 is connected to the airborne flight controller via a detachment connector adapter cable 58 and a main parachute separation control cable to control the detachment connector 53 to separate the main parachute 55 when the UAV touches the ground. In this embodiment, the detachment connector adapter cable 58 is pre-embedded in the rear sling 52, with one end electrically connected to the detachment connector 53 and the other end connected to the airborne flight controller via the main parachute separation control cable fixed at the rear sling point 13. Figure 13 As shown, the length of the adapter cable 58 of the detachment connector is greater than the length of the rear sling 52. It is embedded in the rear sling 52 in an S-shaped arrangement to prevent the adapter cable 58 from being damaged and detached when the rear sling 52 is under load and tension. The parachute control cable and the main parachute separation control cable are both arranged in the fuselage compartment 1, and the control signals are all given by the airborne flight controller through the control cables.

[0072] See Figure 6-8The parachute canopy 6 closes onto the opening of the fuselage compartment 1, used to close or open the opening of the fuselage compartment 1. One end of the parachute canopy 6 is hinged to the rear end of the fuselage compartment 1 via a hinge 61, and the other end is locked to the front end of the fuselage compartment 1 via a locking mechanism 62. The hinge between the parachute canopy 6 and the fuselage compartment 1 adopts an eccentric pivot type, with its pivot axis located behind the parachute canopy 6, allowing the parachute canopy 6 to rotate freely around the hinge 61 pivot, ensuring a 180° full opening without obstructing the parachute opening passage, thereby preventing the parachute from being snagged. The locking mechanism 62 is an electrically controlled unlocking mechanism; after unlocking, the parachute canopy 6 can rotate freely backward. The locking mechanism 62 is connected to the airborne flight control electromechanical system via a parachute opening control cable, used to control its unlocking. The parachute opening control cable is located inside the fuselage compartment 1. After the parachute canopy 6 is closed, its circumference completely fits and seals the opening of the fuselage compartment 1, and its curvature matches the fuselage shell, ensuring the integrity of the UAV's aerodynamic shape. In this embodiment, the parachute canopy 6 adopts a large opening angle design to reduce the drag plate effect after the parachute canopy is opened, and to avoid the parachute canopy from rebounding after opening backward, thus ensuring unobstructed parachute opening channel.

[0073] It should be noted that the depth of the inward flange 17 of the fuselage compartment 1 is related to the thickness of the outward flange 21 of the irregularly shaped parachute compartment 2 and the edge thickness of the parachute compartment cover 6. The inward flange 17 ensures a smooth fuselage shape after the parachute compartment cover 6 is closed. Specifically, the formula for calculating the depth of the inward flange of the fuselage compartment 1 is as follows:

[0074] Inward flange recess depth = irregular umbrella compartment outer flange thickness + umbrella compartment cover thickness + sealing coating thickness;

[0075] In the formula, the sealing coating thickness refers to the thickness of the sealing coating located between the outer flange 21 of the irregularly shaped parachute compartment and the parachute compartment cover 6, used to seal the irregularly shaped parachute compartment 2 and the parachute compartment cover 6. In this embodiment, the inner flange 17 of the fuselage compartment 1 has a recess depth of 4.5 mm, the outer flange 21 of the irregularly shaped parachute compartment 2 has a thickness of 2 mm, the parachute compartment cover 6 has a thickness of 2 mm, and the sealing coating thickness is 0.5 mm.

[0076] In addition, in this embodiment, the longitudinal arrangement of the fuselage compartment 1 on the UAV needs to take into account the change in the UAV's center of gravity before and after parachute deployment. After parachute deployment, the UAV's center of gravity should be within the allowable range of the recovery device to ensure stable landing support of the UAV's landing gear. The formula for calculating the overall center of gravity coordinates of the UAV after parachute deployment using the irregularly shaped parachute compartment device of this invention is as follows:

[0077]

[0078] Based on the calculated coordinates of the aircraft's center of gravity after parachute deployment, and comparing them with the design positions of the drone recovery system (such as the landing gear) and their permissible range for the center of gravity, ensure that the drone's center of gravity is within the permissible range of the drone recovery system after parachute deployment. If the position exceeds this range during the design phase, corresponding adjustments need to be made to the fuselage compartment 1 or the recovery system position.

[0079] Example 2:

[0080] This embodiment provides a method for partitioned installation and use of the parachute system 5 in the irregularly shaped parachute compartment device described in Embodiment 1. By functionally partitioning the interior of the fuselage compartment 1 according to its structural characteristics, the parachute systems 5 are installed in specific functional partitions of the irregularly shaped parachute compartment device according to the opening sequence, facilitating operation and inspection. During opening, the components of the parachute system 5 are deployed in a reasonable sequence, ensuring safe parachute deployment for UAV recovery.

[0081] See Figure 10-12 This method divides the fuselage compartment 1 into four areas, namely, the irregularly shaped parachute compartment 2 and the launch compartment 3 into four areas. The irregularly shaped parachute compartment 2 is divided into three installation areas, A, B, and C, based on the recessed part of the edge-removed structure. The entire launch compartment 3 is designated as installation area D. Area A is located at the end of the irregularly shaped parachute compartment 2 near the front opening 23, and is used to install the front sling 51, the detachment connector 53, and the upper sling 54. Area B is located on the side of the irregularly shaped parachute compartment 2 adjacent to the recessed part, and is used to install the rear sling 52. Area C is the area outside areas A and B in the irregularly shaped parachute compartment 2, and is used to install the main parachute 55. Area D is used to install the launch parachute 57 rocket.

[0082] The installation and usage method of the umbrella system partition includes the following steps:

[0083] Step 1: Install launch bay 3 inside fuselage bay 1: See Figure 3 , 4 The launch bay 3 is vertically installed on the fuselage bay 1 with its opening facing upwards. Its mounting bracket 32 ​​is fixedly connected to the mounting seat 15 inside the fuselage bay 1, and the parachute control cable is connected to the launch bay 3.

[0084] Step 2: Install the irregularly shaped parachute compartment 2 inside fuselage compartment 1: See [link / reference] Figure 5 The irregularly shaped parachute compartment 2 is positioned with its opening facing upwards, aligning its inner recess with the installation position of the launch compartment 3, and vertically installed inside the fuselage compartment 1. The outer flange 21 of the irregularly shaped parachute compartment 2 is then fixedly connected to the inner flange 17 of the fuselage compartment 1 using multiple screws.

[0085] Step 3: Install the front sling 51, the detachment connector 53, and the upper sling 54 sequentially from bottom to top in area A of the irregularly shaped parachute compartment 2: (See reference) Figure 11Straighten the front sling 1, connect one end of each of the two front slings 51 to the corresponding front sling points 12 on both sides of the UAV, and arrange them close to the shape of the UAV body. Then, they enter the irregularly shaped parachute compartment 2 through the parachute strap groove 11 and the front opening 23 of the parachute compartment. The other ends of the two front slings 51 meet and are fixedly connected to one end of the detachment connector 53. The part of the front sling 51 that enters the irregularly shaped parachute compartment 2 is folded in a Z-shape and placed flat at the bottom of the compartment in area A. The detachment connector 53 connected to the front sling 51 is placed horizontally on the stacked front slings 51. The detachment connector 53 is connected to one end of the upper sling 54 behind the front sling 51. The upper sling 54 is then straightened, folded in a Z-shape, and placed horizontally on the detachment connector 53. The other end of the upper sling 54 extends to area C of the irregularly shaped parachute compartment 2 for connection with the canopy end of the main parachute 55.

[0086] Step 4: Install the rear sling 52 in section B of the irregularly shaped parachute compartment 2: (See reference) Figure 11 , 13 Straighten the rear sling 52, connect one end of the rear sling 52 to the rear lifting point 13, and electrically connect one end of the adapter cable inside the rear sling 52 to the main parachute separation control cable fixed at the rear lifting point 13. Connect the other end of the rear sling 52 to the junction point of the two front slings 51 and then to the drop connector 53, and electrically connect the other end of the adapter cable inside the rear sling 52 to the drop connector 53. Fold the rear sling 52 in a Z-shape and lay it flat at the bottom of the cabin in area B. Secure the folded rear sling 52 with a rubber band to prevent it from getting tangled with the still-rotating propeller at the tail of the UAV when it is not under load and straightened.

[0087] Step 5: Install the main parachute 55 in section C of the irregularly shaped parachute compartment 2: See [link / reference] Figure 12 Wrap the main parachute 55 in a canopy and fold it in a Z-shape to lay it flat at the bottom of the cabin in section C. The opening of the main parachute 55 is located at the bottom of the cabin and is connected to the end of the upper sling 54 away from the detachment connector 53. The top of the main parachute 55 is at the top.

[0088] Step 6: Install parachute rocket 57 in area D: See Figure 12 After connecting the bottom of the parachute rocket 57 and the top of the main parachute 55 with the connecting strap 56, the head of the parachute rocket 57 is installed into the launch chamber 3, and then the parachute rocket 57 is electrically connected to the parachute control cable in the launch chamber 3.

[0089] Step 7: Install fireproof plate 4: Refer to 1 and 12. Install fireproof plate 4 at the top open end of launch compartment 3. Align the through hole of fireproof plate 4 with the top open end of launch compartment 3. Fix the fireproof plate 4 to the inner flange 17 of fuselage compartment 1 on the two adjacent sides of fuselage compartment 1 with screws.

[0090] Step 8: Close the parachute compartment cover 6 and lock it using the locking mechanism 62. See the documentation for the locking effect. Figure 6 .

[0091] Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention. Those skilled in the art can make changes, modifications, substitutions and variations to the above embodiments within the scope of the present invention without departing from the principles and spirit of the present invention.

Claims

1. An irregularly shaped parachute-like device, characterized in that: This includes the fuselage compartment, the irregularly shaped parachute compartment, the launch compartment, the parachute system, and the parachute compartment canopy; The fuselage compartment is located inside the fuselage of the UAV, with an opening at the top, and is used to accommodate and install other components. The irregularly shaped parachute compartment is an open-top, hollow, irregularly shaped cabin structure used to house the parachute system; the side wall of the irregularly shaped parachute compartment has a recessed portion, the axis of which is parallel to the vertical geometric center line of the irregularly shaped parachute compartment, and the recessed portion is used to house the launch compartment. The launch compartment is a hollow, open-top structure used to mount the parachute rocket with a parachute system. The outer contour of the launch compartment's sidewalls matches the inner recess, and the launch compartment is coaxially embedded into the inner recess. Both the launch compartment and the irregularly shaped parachute compartment have their open ends facing upwards and are independently fixed within the fuselage. The installation height of the open end of the launch compartment is no higher than that of the open end of the irregularly shaped parachute compartment. The launch compartment is fixed to the inner structural wall of the fuselage compartment via an installation mechanism. The installation mechanism includes a mounting bracket and a mounting base. The mounting base is fixed to the inner structural wall at the front end of the fuselage compartment, and a dovetail groove is vertically provided on one side of the mounting base. The mounting bracket is fixed to the outer side wall of the launch compartment, and a protrusion is provided on one side of the mounting bracket along the axial direction of the launch compartment. The protrusion slides into the dovetail groove. The mounting bracket and mounting base are respectively provided with limit holes, and quick-release pins are inserted into the limit holes to lock and limit the movement. The parachute system, excluding the parachute rocket, consists of other components stacked and installed in the irregularly shaped parachute compartment according to the order of exit. The parachute system is used for the parachute landing and recovery of the UAV. The parachute canopy closes onto the opening of the fuselage compartment, and is used to close or open the opening of the fuselage compartment.

2. The irregularly shaped parachute device according to claim 1, characterized in that: The irregularly shaped parachute compartment device also includes a fireproof plate to prevent the jet stream of the parachute rocket from entering the fuselage compartment; the fireproof plate is located at the open end of the launch compartment and is fixedly connected to the fuselage compartment; the middle of the fireproof plate is provided with a through hole that matches the top opening of the launch compartment, and the plate surface around the through hole covers the gap between the launch compartment and the irregularly shaped parachute compartment, and between the launch compartment and the fuselage compartment.

3. The irregularly shaped parachute compartment device according to claim 2, characterized in that: The upper opening of the fuselage compartment allows for the vertical assembly and disassembly of the irregularly shaped parachute compartment and the launch compartment. The opening of the fuselage compartment is surrounded by an inner flange with a recessed structure. The open end of the irregularly shaped parachute compartment is surrounded by an outer flange structure in addition to the inner recess. The outer flange overlaps the inner flange and is fixedly connected by screws. The open end of the irregularly shaped parachute compartment has a front opening near the head of the drone, and the front end of the upper opening of the fuselage compartment has a parachute strap groove that matches the front opening of the parachute compartment for passing through the front strap of the parachute system; the open end of the irregularly shaped parachute compartment has a rear opening near the tail of the drone for passing through the rear strap of the parachute system.

4. The irregularly shaped parachute compartment device according to claim 3, characterized in that: The formula for calculating the inward flange depression depth of the fuselage compartment is as follows: Inward flange recess depth = Outward flange thickness of irregularly shaped umbrella compartment + Umbrella compartment cover thickness + Sealing coating thickness; In the formula, the thickness of the sealing coating refers to the thickness of the sealing coating located between the outer flange of the irregularly shaped umbrella canopy and the umbrella canopy cover, used to seal the irregularly shaped umbrella canopy and the umbrella canopy cover.

5. The irregularly shaped parachute compartment device according to claim 3, characterized in that: The parachute system includes a front sling, a rear sling, a detachment connector, an upper sling, a main parachute, a connecting strap, and a launch rocket. When the parachute system is deployed, one end of each of the two front slings is fixed to a front sling on either side of the UAV fuselage, and one end of the rear sling is fixed to a rear sling located inside the rear of the fuselage. The other ends of the two front slings and the other end of the rear sling converge and are fixedly connected to one end of the detachment connector. The other end of the detachment connector is connected to the main parachute opening via the upper sling. The top of the main parachute is connected to the tail of the launch rocket via the connecting strap. When the parachute system is not deployed, the front sling, rear sling, detachment connector, upper sling, and main parachute are all located within a shaped parachute compartment. The launch rocket, nose-up, is placed inside the launch bay. The parachute rocket is connected to the airborne flight control electromechanical system via a parachute control cable to control the ignition of the parachute rocket; the detachment connector is connected to the airborne flight control electromechanical system via an adapter cable and a main parachute separation control cable to control the detachment connector to separate the main parachute when the UAV touches the ground.

6. The irregularly shaped parachute compartment device according to claim 5, characterized in that: The adapter cable is embedded in the rear sling, with one end electrically connected to the detachment connector; the other end is connected to the airborne flight control electromechanical system via the main parachute separation control cable fixed at the rear suspension point.

7. The irregularly shaped parachute compartment device according to claim 6, characterized in that: One end of the parachute canopy is hinged to the rear end of the fuselage compartment via a hinge, and the other end is locked to the front end of the fuselage compartment via a locking mechanism. The hinge adopts an eccentric pivot type, with the hinge axis located behind the parachute canopy, for the parachute canopy to open 180° around the hinge pivot. The locking mechanism is used to lock the parachute canopy. The locking mechanism is connected to the airborne flight control electromechanical system via the parachute canopy opening control cable, and is used to control the opening of the parachute canopy.

8. The irregularly shaped parachute compartment device according to claim 7, characterized in that: The longitudinal arrangement of the fuselage compartment on the UAV fuselage ensures that the change in the UAV's center of gravity before and after parachute deployment is within the permissible range of the UAV recovery device; the formula for calculating the overall center of gravity coordinates of the UAV after parachute deployment is as follows:

9. A method for partitioned installation and use of the umbrella system of the irregularly shaped umbrella compartment device according to claim 7, characterized in that: The method divides the irregularly shaped parachute compartment into three installation areas: A, B, and C. The launch compartment is designated as installation area D. Area A is located within the irregularly shaped parachute compartment near the front opening and is used to install the front sling, detachment connector, and upper sling. Area B is located within the irregularly shaped parachute compartment adjacent to the concave portion and is used to install the rear sling. Area C is the area within the irregularly shaped parachute compartment excluding areas A and B and is used to install the main parachute. Area D is used to install the parachute rocket. The method for installing and using the umbrella system in a partitioned manner includes the following steps: Step 1: Secure the launch capsule to the fuselage using the mounting mechanism, and connect the parachute control cable to the launch capsule; Step 2: Install the irregularly shaped parachute compartment into the fuselage compartment and fix the outer flange of the irregularly shaped parachute compartment to the inner flange of the fuselage compartment with fasteners. Step 3: Install the front sling, the detachment connector, and the top sling in section A from bottom to top: Connect the ends of the two front slings away from the detachment connectors to the corresponding front sling points, and then, close to the shape of the aircraft body, enter the irregularly shaped parachute compartment through the parachute strap groove and the front opening of the parachute compartment. Fold them in a Z-shape and place them flat at the bottom of the compartment in section A; place the detachment connector horizontally on the stacked front slings; fold the top sling in a Z-shape and place it flat on the detachment connector. Step 4: Install the rear sling in area B: Connect the end of the rear sling away from the detachment connector to the rear lifting point, and connect both ends of the adapter cable inside the rear sling to the detachment connector and the main parachute separation control cable respectively; fold the rear sling in a Z-shape and lay it flat on the bottom of the cabin in area B, and secure it with rubber bands. Step 5: Install the main umbrella in area C: Wrap the main umbrella with the canopy cover, fold it in a Z-shape and place it flat at the bottom of the cabin in area C, with the opening of the main umbrella at the bottom of the cabin and the top of the main umbrella at the top. Step 6: Install the parachute rocket in area D: After connecting the bottom of the parachute rocket and the top of the main parachute with the connecting strap, insert the parachute rocket nose-up into the launch compartment; then connect the parachute rocket to the parachute control cable. Step 7: Install fireproof board: Install fireproof board at the open end of the launch compartment top, align the through hole of the fireproof board with the open end of the launch compartment top, and fix the two sides of the fireproof board to the inner flange of the fuselage compartment with fasteners. Step 8: Close the parachute canopy and lock it using the locking mechanism.

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