Battery safety separation and recovery device for electric aircraft with replaceable batteries

Abstract

The present invention relates to the technical field of safe separation and recovery of batteries for electric aircraft, and in particular to a battery safe separation and recovery device for electric aircraft with replaceable batteries, which is installed on the aircraft body and includes an aluminum alloy bracket, a limit lock, a battery pack, a parachute bag body, a rotating device, an opening and closing mechanism, and a battery protection frame. The invention solves the problems of the difficulty in separating the battery and the aircraft during the landing of traditional electric aircraft, the difficulty in controlling the deceleration and precise landing after separation, and the battery safe separation is achieved by pushing the upper and lower hydraulic rods forward to open the hydraulic rods, so as to achieve the smooth release of the battery pack and the landing from the aircraft; when the battery pack falls, the parachute quickly and fully unfolds, and the entire battery system automatically adjusts to a horizontal state. The parachute adopts magnetorheological control to achieve segmented contraction to prevent the parachute from being mixed with the propeller, and then the propeller works further to allow the battery pack to land accurately.

Description

Technical Field

[0001] The present invention relates to battery replacement technology for electric aircraft, and in particular to a battery safety separation and recovery device for an electric aircraft with replaceable batteries, which can safely separate and release the battery in advance, accurately land in a specified area, and realize efficient and automatic battery recovery, thereby avoiding damage to the electric aircraft and the battery during battery separation and recovery. Background Art

[0002] With the development of electric aircraft technology, battery management of aircraft has become a key issue. The take-off and landing phases of an aircraft are the key phases of its operation, and electric aircraft need to deal with the energy supply and load issues of the battery during landing. Therefore, how to ensure the safe separation and recovery of used batteries during aircraft landing is a key technology to reduce the flight load and ensure the safe and efficient landing of the aircraft. The traditional battery separation method not only has the problems of cumbersome operation and long time consumption, but also may cause battery collision, falling to the ground, and fire during operation, threatening the flight safety of the aircraft. Therefore, it is necessary to design a battery separation device that allows the aircraft to release the used battery in advance when it is about to land, and unload the used battery in advance through a safe device to reduce the flight load during the landing phase of the aircraft, thereby ensuring the safety of the aircraft while improving maneuverability. In addition, in order to ensure the safe landing and efficient recovery of the unloaded battery, it is necessary to design a recovery device that can accurately control the descent speed and position of the battery, and realize automatic recovery after the battery lands safely. However, the battery recovery technology and equipment on the market cannot achieve the above functions. The general battery recovery technology is relatively complicated to operate, and there are also problems such as low automation and heavy environmental pollution. Therefore, the battery safety separation and recovery device for an electric aircraft with replaceable batteries designed in the present invention aims to solve the problems existing in the battery separation and recovery of the above electric aircraft, realize the safe separation and efficient automatic recovery of the battery, reduce environmental pollution during operation, provide greater flexibility for the electric aircraft, and ensure the overall flight safety and efficiency of the aircraft.

[0003] For example, the patent with publication number CN116161235A designs a device for replacing batteries in electric aircraft, which involves the field of replacing batteries in electric aircraft. The device for replacing batteries in electric aircraft includes an AGV body equipped with walking wheels, the AGV body is provided with a power device and a control system, and a lifting platform is provided on the top side; the lifting platform is provided with two station components, one for removing empty batteries from the electric aircraft, and the other for installing fully charged batteries on the electric aircraft; a cover assembly is provided above one side of the two station components, and the cover assembly and the lifting platform cooperate to form a storage space for the battery; a positioning assembly is provided on the cover assembly, which can monitor the position of the AGV body relative to the electric aircraft; the device invented by the patent can replace manual labor to efficiently replace batteries weighing more than 150kg for electric aircraft, saving the cost of aircraft flight while avoiding the hidden dangers of personal injury and other hazards caused by manual operation. The disadvantage of this patent is that due to the use of the AGV body, the equipment may be limited by the working area and cannot move freely in a wider range of scenarios; in addition, the equipment may need to adapt to batteries of different specifications and sizes, and if the battery specifications change, the equipment may need to be modified or upgraded.

[0004] For example, the patent with publication number CN214356714U designs a battery pack limit and quick replacement mechanism for an electric aircraft, which relates to the technical field of electric aircraft. The battery pack limit and quick replacement mechanism for an electric aircraft is provided by setting a mounting seat, a transmission shaft, an external spline sleeve 1, a driving gear 1, a rotating head, a locking device, a groove, a movable seat, a pad, a battery body, a vertical threaded hole, a vertical screw, a driving gear 2, an external spline sleeve 2 and a driven gear 2; when in use, the rotating head is moved outward and rotated, thereby driving the dynamic pressure block to move up and down to separate or lock the battery body, so as to improve the efficiency of installation and disassembly; then the rotating head is moved inward and rotated, thereby driving the vertical screw to rotate so that the movable seat and the pad drive the battery body to move up to the mounting seat to realize the replacement of the battery body; the groove is used to realize the fixed installation of the battery body and avoid displacement during use. The disadvantage of this patent is that the design of the replacement mechanism involves multiple moving parts. For example, components such as the rotating head and screw may be worn or damaged due to frequent movement and rotation during use, resulting in obstruction of the battery replacement operation. In addition, the replacement mechanism is relatively complex, which increases the difficulty and cost of maintenance.

[0005] For example, the patent with publication number CN116280223A designs an electric vertical take-off and landing aircraft with a replaceable battery pack, which relates to the field of aviation aircraft. The proposed invention includes wings, motor arms, and battery packs; the wings extend along the left and right directions of the electric vertical take-off and landing aircraft, and the wings are connected to the motor arms; the motor arms are used to install motors, propellers, and battery packs; the battery packs are cylindrical and can be detachably connected to the motor arms and the lower sides of the wings, and extend along the front and rear directions of the electric vertical take-off and landing aircraft; the battery pack of this patent invention is far away from important flight function structures on the aircraft, and when the battery pack fails or thermally runs away, it will not directly threaten the flight function structure, thereby improving the safety of flight; when in use, the battery pack is disassembled from the aircraft and then inspected and maintained in detail, leaving the space around the battery pack open for convenient inspection, repair, and maintenance of the battery pack. The disadvantage of this patent is that the battery pack extends along the front and rear directions of the aircraft, which may cause uneven load distribution in the front and rear directions of the aircraft, and the uneven load distribution may have a negative impact on the stability and maneuverability of the aircraft; in addition, the battery pack is connected to the underside of the wing, which may increase the complexity of the aircraft during landing and ground operations. Summary of the invention

[0006] The present invention aims to solve the problem existing in the replacement of batteries in existing electric aircraft, and provides a battery safety separation and recovery device for an electric aircraft with replaceable batteries, which can safely separate and release the batteries in advance, accurately land in a designated area, and realize efficient and automatic battery recovery, thereby avoiding damage to the electric aircraft and the batteries during the battery separation and recovery process.

[0007] The battery safety separation and recovery device of the replaceable battery electric aircraft of the present invention is characterized in that the separation and recovery device is installed in the aircraft body, and comprises an aluminum alloy bracket, a battery pack, a parachute pack body, a battery protection frame, and the aluminum alloy bracket is arranged at the battery hatch near the bottom of the tail of the electric aircraft body, the battery protection frame is arranged in the aluminum alloy bracket, the battery pack is arranged in the battery protection frame, and the parachute pack body is fixed on the top of the battery protection frame, wherein:

[0008] The aluminum alloy bracket includes an upper bracket, a lower bracket, a limit lock, a slider, an opening and closing mechanism and a rotating shaft. The upper bracket is attached to the upper surface of the battery hatch, and the lower bracket is attached to the lower surface of the battery hatch. The upper bracket and the lower bracket are connected by a rotating shaft. The opening and closing mechanism is arranged between the upper bracket and the lower bracket, and is connected to the rotating shaft, the upper bracket and the lower bracket. Several sliders are symmetrically installed on the upper and lower sides of the lower bracket on the left and right sides, respectively contacting the top and bottom of the battery protection frame; eight limit locks are symmetrically fixed on both sides of the lower bracket and located on the outside of the sliders;

[0009] The battery protection frame includes a slide rail, a propeller bracket, a propeller, a buffer rod, an electrical channel and a height sensor. The battery protection frame is a rectangular parallelepiped structure, the frame is an internal hollow structure, and the interior of the frame is set as an electrical channel; four slide rails are respectively arranged at the four long edges of the upper surface and the lower bottom surface of the battery protection frame; there are four propeller brackets, which are symmetrically arranged on both sides of the front end and the rear end of the battery protection frame, the propeller is installed on the propeller bracket, and the buffer rod is fixed to the bottom of the propeller bracket; a height sensor is respectively arranged on the four bottom corners of the battery protection frame; the battery protection frame is provided with conductive contacts, which are in contact with the positive and negative poles of the battery pack, and the electrical channel is energized through the conductive contacts;

[0010] The parachute bag main body includes a parachute cloth, a parachute rope, a retractable assembly, an opening and closing assembly, and a recovery assembly. The parachute cloth is arranged on the top of the battery protection frame. The retractable assembly, the opening and closing assembly, and the recovery assembly are all fixedly installed on the top of the battery protection frame. The parachute cloth is connected to the retractable assembly, the opening and closing assembly, and the recovery assembly through the parachute rope.

[0011] The opening and closing mechanism includes a hydraulic push rod, a knob and a hinge. The hydraulic push rod is divided into an upper push rod and a lower push rod. The upper push rod and the lower push rod respectively pass through the interior of the connecting frame on the knob, and their tails pass through the interior of the hinge and are fixed on the hinge; there are two hinges, one with an opening facing downward and fixed under the upper bracket, and the other with an opening facing upward and fixed on the lower bracket; the hydraulic push rod is connected to the hydraulic system of the electric aircraft through a hydraulic oil pipe. When working, the hydraulic push rod of the opening and closing mechanism is pushed and acts on the front of the rotating shaft, causing the upper push rod and the lower push rod to be pushed forward and opened to form a certain angle, so that a certain angle difference is generated between the upper bracket and the lower bracket, so that the battery protection frame can slide down along the slide rail when released, thereby achieving a smooth release and landing action.

[0012] The propeller bracket is installed on the side wall of the battery protection frame through a rotating rod. The propeller bracket rotates around the rotating rod. A brushless DC motor is arranged at the bottom of the propeller bracket. The brushless DC motor is fixed on the battery protection frame and connected to the electrical channel through a wire. The brushless DC motor is connected to the propeller through a transmission gear and a transmission belt to drive the propeller to rotate; the propeller is a foldable blade, which is convenient for folding and folding when not working. When the battery pack reaches a relatively stable descending state, the brushless DC motor is started, and the propeller bracket is rotated outward by 135° along the rotating rod to the unfolded position; the foldable propeller is driven by the brushless DC motor and transmits rotation through internal gears to start rotating to provide necessary lift.

[0013] The retractable and deployable assembly includes a retractable and deployable ratchet and a retractable and discharge motor, the opening and closing assembly includes an opening and closing ratchet and an opening and closing motor, and the recovery assembly includes a recovery ratchet and a recovery motor. There are eight retractable and deployable ratchets divided into two groups, which are symmetrically installed on the left and right edges of the battery protection frame, and the side surfaces of the retractable and deployable ratchets are connected to the retractable and discharge motors through connecting shafts; there are four opening and closing ratchets divided into two groups, which are symmetrically installed on the front and rear ends of the battery protection frame, and the opening and closing motor is arranged between the two opening and closing ratchets, and the two ends of the opening and closing motor are respectively linked to the two opening and closing ratchets through transmission shafts; the two recovery ratchets are installed in the middle of the battery protection frame, and the recovery motor is arranged next to the recovery ratchet, and is linked to the recovery ratchet through a transmission shaft; the retractable and deployable ratchet, the opening and closing ratchet, and the recovery ratchet are connected to the umbrella cloth through umbrella ropes.

[0014] Two umbrella openings are symmetrically arranged on both sides of the umbrella cloth, and the umbrella openings are connected to the opening and closing components through umbrella ropes. When the parachute is unfolded, the opening and closing ratchet is driven by the opening and closing motor to drive the umbrella rope to pull the umbrella surface inward, thereby opening or closing the umbrella opening. By adjusting the size of the umbrella opening, the descent speed of the parachute can be effectively controlled.

[0015] The parachute rope adopts a three-layer structural design, the outer layer is a protective layer made of high-strength polymer; the middle layer is a shielding layer, which is composed of a copper braided mesh or a metal foil, and is used to shield external electromagnetic interference and ensure the stability of internal current control; the inner layer contains a hollow cavity filled with magnetorheological fluid, and a plurality of segmented coils are arranged around the cavity; the conduction of the current in each segment of the coil is controlled separately by a controller; the controller is composed of a single-chip microcomputer chip, an OA port and a current control module, and is used to control the conduction and disconnection of the current of the multiple segments of the coils in the parachute rope, and adjust the hardening and softening of the magnetorheological fluid in the hollow cavity inside the parachute rope; after the battery pack and other components are separated from the aircraft, the parachute opening mechanism is started, and at the same time, all the parachute ropes on the parachute are arranged from top to bottom by the internal coils. The current is passed for the first time, at which time the parachute rope is hardened from top to bottom by the magnetorheological fluid arranged inside, so that the parachute is opened and a supporting structure is provided for the parachute cloth, the descending speed of components such as the battery pack is effectively controlled, and a smooth landing is ensured; when the parachute starts to be recovered, the parachute rope connected to the recovery ratchet is firstly powered off from bottom to top by the internal coil, at which time the parachute rope is softened from bottom to top by the magnetorheological fluid arranged inside, so that the middle parachute rope is contracted section by section, and the recovery motor is immediately started, driving the recovery ratchet to rotate synchronously, gradually winding the softened parachute rope, and assisting in its recovery; the middle parachute rope is the key part connected to the parachute cloth, and by contracting the middle parachute rope first, the unfolding volume of the entire parachute can be effectively reduced, making the recovery process more stable and controllable.

[0016] Before landing, the battery pack is tightly attached to four limit locks on the left and right sides, connected to the parachute pack body on the top, and close to the aluminum alloy lower bracket on the bottom; when the aircraft is in flight, it is connected to the positive and negative poles of the battery pack through the conductive contact points on the slide rail to provide the aircraft with the required power; two symmetrical propeller brackets are respectively provided on the front and rear sides of the battery protection frame; when the battery pack is detached from the aircraft, the slider slides on the slide rail, guiding the battery protection frame to slide smoothly and safely out of the aluminum alloy bracket along the track of the slide rail in the predetermined direction, thereby achieving the smooth release and separation of the battery pack and other components, ensuring stability and safety during the detachment process.

[0017] The height sensor is tightly connected to the battery protection frame through an embedded fixed structure. The height sensor integrates a barometer and an optical flow sensor, and can simultaneously detect the air pressure height of the battery pack and the movement information relative to the ground.

[0018] The front end face of the battery protection frame is provided with a central control panel and an inspection cover. The central control panel consists of an embedded display screen, a control knob and an internal connection module, and integrates the automated operation and monitoring functions of all key controllers after the battery pack is separated from the aircraft; the control knob is arranged on the right side of the display screen, and each control knob corresponds to an independent control loop. The user can pre-set and adjust the operating parameters and operations of each controller through the control knob; these settings include the opening of the parachute rope, the operation timing of the dual-axis motor during parachute recovery, the operating parameters of the main parachute retracting and discharging motor and the recovery motor, the brushless DC motor for starting the folding propeller, and the deployment of the propeller bracket; the internal connection module is integrated in the central control panel and connected to the electrical channel arranged inside the battery protection frame to realize the connection between the central control panel and each controller, sensor and circuit; the inspection cover is located on the right side of the control knob, and is connected to the battery protection frame through a simple fixing device. The necessary inspection, maintenance or replacement of components can be carried out by opening the inspection cover.

[0019] The lower part of the buffer rod is also connected to a spring rod and a rubber foot pad, the spring rod and the rubber foot pad are closely connected, and the rubber foot pad is located at the end of the spring rod; when the battery pack and other components are separated from the aircraft, the spring rod and the rubber foot pad reduce the impact force of the battery pack during landing, and increase friction after landing to prevent the battery pack from sliding on the ground; this design effectively reduces shock and absorbs energy, while enhancing the stability and safety of the battery pack.

[0020] The battery safety separation and recovery device for an electric aircraft with replaceable batteries of the present invention has the following advantages:

[0021] 1. By setting a rotating device on the aluminum alloy bracket, the battery can select the best escape trajectory and slide out of the aircraft in a safe direction, reducing the potential risk of collision; the hydraulic push rod on the opening and closing mechanism is pushed when working, acting on the front of the rotating device, causing the upper and lower hydraulic rods to push forward so that the hydraulic rods open to form a certain angle, thereby generating a certain angle difference between the upper and lower brackets, so that the battery can slide down along the slide rail of the bracket and leave the aircraft when released;

[0022] 2. After the battery pack and other components are separated from the aircraft, the descent process is slowed down by parachutes first, and then the propellers are started. This way of landing is adopted because the parachute can provide a stable landing trajectory for the entire system after opening. The use of parachutes helps to maintain the vertical posture of the system, reduce the rotation or shaking of the battery during the descent process, and improve the overall stability; the parachute has the advantage of rapid response and can be opened quickly when the battery system needs emergency deceleration, providing a strong deceleration effect; in addition, the phased design enables the system to better adapt to different landing environments; the parachute plays a role in rapid deceleration and emergency situations, while the propeller provides more precise speed control after stable descent to adapt to different descent needs;

[0023] 3. Before the battery touches the ground, the recovery process of the parachute takes the following steps: First, the parachute rope connected to the recovery ratchet is controlled to be de-energized from bottom to top by the internal coil. At this time, the parachute rope is softened from bottom to top by the magnetorheological fluid arranged inside, so that the middle parachute rope is contracted section by section; by first recovering the middle parachute rope, a balanced recovery of the entire parachute system can be achieved to prevent instability caused by the lack of synchronization between the two sides; the parachute rope is composed of the internal magnetorheological fluid fluid and segmented multi-segment coils; the conduction of the current in each coil section is controlled separately by the controller; the structure of magnetorheological fluid fluid and segmented multi-segment coils is adopted to achieve segment-by-segment demagnetization and segment-by-segment contraction, which can more accurately control the length change of the parachute rope and finely adjust the recovery of the parachute The speed and mode of contraction are controlled; at the same time, the opening of the parachute is opened by controlling the opening and closing ratchet, and the parachute cloth around the opening is tightened and the parachute cloth on both sides is loosened, so that the parachute surface is folded upward in a V shape, and the folding of the parachute surface is completed with the help of aerodynamic force; finally, the parachute rope connected to the retracting and releasing ratchet and the opening and closing ratchet is controlled in coordination, and the power is cut off from bottom to top in sequence by the internal coil, and the parachute rope is softened from bottom to top in sequence by the magnetorheological fluid set inside; the parachute rope is recovered section by section until the parachute is completely recovered into a storage device to prevent the parachute from being entangled with the propeller; by recovering the parachute in advance, the impact force in the landing stage can be reduced, and the possibility of damage can be reduced; in addition, by recovering the parachute into a storage device, the maintenance and recovery process can be simplified, and labor costs and resource investment can be reduced;

[0024] 4. By connecting a parachute bag above the battery pack and setting propellers around it, the battery pack can be landed at a fixed point. The gradual contraction of the parachute rope makes the parachute form a paraglider structure. The propeller on the rear side increases the thrust, so that the entire system tilts forward and generates forward momentum. Under the action of the parachute, the system glides in the air. After flying to the predetermined target point in the air, the lift of the four propellers is adjusted to restore the normal flight state. After reaching the target point, the landing process is executed. The parachute gradually contracts into a storage device and is placed above the battery. The battery pack and other components slowly land to achieve a fixed-point landing. The landing method using propellers and parachutes makes the battery more flexible and safe during the landing process, and can achieve a more accurate landing.

[0025] 5. A spring rod and rubber foot pad are set under the propeller bracket, so that when the battery lands, the spring rod can absorb part of the impact force, thereby protecting the battery from excessive impact and vibration; the rubber foot pad is located at the end of the spring rod, mainly used to provide additional cushioning and anti-slip effects to absorb energy and reduce shock, which can further reduce the degree of impact transmitted to the battery, and at the same time increase friction after the battery lands, which helps prevent the battery from sliding on the ground. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] Figure 1 It is the aircraft position diagram of the present invention.

[0027] Figure 2 This is a rear view of the battery pack of the present invention in the installed state.

[0028] Figure 3 This is an axonometric diagram of the battery pack of the present invention in the installed state.

[0029] Figure 4 It is a schematic diagram of the battery pack of the present invention in the un-opened state.

[0030] Figure 5 This is a schematic diagram of the parachute opening and landing state of the present invention.

[0031] Figure 6 An internal view of the parachute cord of the present invention.

[0032] Figure 7 It is a top view of the internal structure of the parachute rope of the present invention.

[0033] Figure 8 It is an axonometric diagram of the parachute-opening landing state of the present invention.

[0034] Fig. 9 This is an illustration of the bottom of the battery pack of the present invention.

[0035] In the figure: parachute rope 1, coil 2, aircraft body 3, aluminum alloy bracket 4, limit lock 5, battery pack 6, parachute bag body 7, rotating device 8, opening and closing mechanism 9, propeller 10, propeller bracket 11, spring rod 12, rubber foot pad 13, buffer rod 14, slide rail 15, slider 16, battery protection frame 17, retractable ratchet 18, opening and closing ratchet 19, recovery ratchet 20, parachute mouth 21, opening and closing assembly 22, height sensor 23, brushless DC motor 24, central control panel 25, control knob 26, inspection cover 27, retractable motor 28, recovery motor 29, opening and closing motor 30, protective layer 101, shielding layer 102, inner layer 103, hollow cavity 104. DETAILED DESCRIPTION

[0036] Embodiment 1: A battery safety separation and recovery device for an electric aircraft with replaceable batteries, installed in the aircraft body, comprises an aluminum alloy bracket, a battery pack, a parachute pack body, a battery protection frame, and the aluminum alloy bracket is arranged at the battery hatch near the bottom of the tail of the electric aircraft body, the battery protection frame is arranged in the aluminum alloy bracket, the battery pack is arranged in the battery protection frame, and the parachute pack body is fixed on the top of the battery protection frame, wherein:

[0037] The aluminum alloy bracket includes an upper bracket, a lower bracket, a limit lock, a slider, an opening and closing mechanism and a rotating shaft. The upper bracket is attached to the upper surface of the battery hatch, and the lower bracket is attached to the lower surface of the battery hatch. The upper bracket and the lower bracket are connected by a rotating shaft. The opening and closing mechanism is arranged between the upper bracket and the lower bracket, and is connected to the rotating shaft, the upper bracket and the lower bracket. Several sliders are symmetrically installed on the upper and lower sides of the lower bracket on the left and right sides, respectively contacting the top and bottom of the battery protection frame; eight limit locks are symmetrically fixed on both sides of the lower bracket and located on the outside of the sliders;

[0038] The battery protection frame includes a slide rail, a propeller bracket, a propeller, a buffer rod, an electrical channel and a height sensor. The battery protection frame is a rectangular parallelepiped structure, the frame is an internal hollow structure, and the interior of the frame is set as an electrical channel; four slide rails are respectively arranged at the four long edges of the upper surface and the lower bottom surface of the battery protection frame; there are four propeller brackets, which are symmetrically arranged on both sides of the front end and the rear end of the battery protection frame, the propeller is installed on the propeller bracket, and the buffer rod is fixed to the bottom of the propeller bracket; a height sensor is respectively arranged on the four bottom corners of the battery protection frame; the battery protection frame is provided with conductive contacts, which are in contact with the positive and negative poles of the battery pack, and the electrical channel is energized through the conductive contacts;

[0039] The parachute bag main body includes a parachute cloth, a parachute rope, a retractable assembly, an opening and closing assembly, and a recovery assembly. The parachute cloth is arranged on the top of the battery protection frame. The retractable assembly, the opening and closing assembly, and the recovery assembly are all fixedly installed on the top of the battery protection frame. The parachute cloth is connected to the retractable assembly, the opening and closing assembly, and the recovery assembly through the parachute rope.

[0040] The opening and closing mechanism includes a hydraulic push rod, a knob and a hinge. The hydraulic push rod is divided into an upper push rod and a lower push rod. The upper push rod and the lower push rod respectively pass through the inside of the connecting frame on the knob, and their tails pass through the inside of the hinge and are fixed on the hinge; there are two hinges, one with an opening facing downward and fixed under the upper bracket, and the other with an opening facing upward and fixed on the lower bracket; the hydraulic push rod is connected to the hydraulic system of the electric aircraft through a hydraulic oil pipe. When working, the hydraulic push rod of the opening and closing mechanism is pushed and acts on the front of the rotating shaft, causing the upper push rod and the lower push rod to be pushed forward and opened to form a certain angle, so that a certain angle difference is generated between the upper bracket and the lower bracket, so that the battery protection frame can slide down along the slide rail when released, thereby achieving a smooth release and landing action.

[0041] The propeller bracket is installed on the side wall of the battery protection frame through a rotating rod. The propeller bracket rotates around the rotating rod. A brushless DC motor is arranged at the bottom of the propeller bracket. The brushless DC motor is fixed on the battery protection frame and connected to the electrical channel through a wire. The brushless DC motor is connected to the propeller through a transmission gear and a transmission belt to drive the propeller to rotate; the propeller is a foldable blade, which is convenient for folding and retracting when not working. When the battery pack reaches a relatively stable descent state, the brushless DC motor is started, and the propeller bracket is rotated outward 135° along the rotating rod to the unfolded position; driven by the brushless DC motor, the foldable propeller transmits rotation through internal gears and starts to rotate to provide the necessary lift.

[0042] The retractable and retractable assembly includes a retractable and retractable motor, the opening and closing assembly includes an opening and closing ratchet and an opening and closing motor, and the recovery assembly includes a recovery ratchet and a recovery motor. There are eight retractable ratchets divided into two groups, which are symmetrically installed on the left and right edges of the battery protection frame, and the sides of the retractable and retractable ratchets are connected to the retractable and retractable motors through connecting shafts; there are four opening and closing ratchets divided into two groups, which are symmetrically installed on the front and rear ends of the battery protection frame, and the opening and closing motor is arranged between the two opening and closing ratchets, and the two ends of the opening and closing motor are respectively linked to the two opening and closing ratchets through transmission shafts; two recovery ratchets are installed in the middle of the battery protection frame, and the recovery motor is arranged next to the recovery ratchet, and is linked to the recovery ratchet through a transmission shaft; the retractable and retractable ratchet, the opening and closing ratchet and the recovery ratchet are connected to the umbrella cloth through umbrella ropes.

[0043] There are two parachute openings symmetrically arranged on both sides of the parachute cloth, and the parachute openings are connected to the opening and closing components through parachute ropes. When the parachute is unfolded, the opening and closing motor drives the opening and closing ratchet to drive the parachute ropes to pull the parachute surface inward, thereby opening or closing the parachute opening. By adjusting the size of the parachute opening, the descent speed of the parachute can be effectively controlled.

[0044] The parachute rope adopts a three-layer structure design. The outer layer is a protective layer made of high-strength polymer; the middle layer is a shielding layer, which is composed of a copper braided mesh or metal foil, used to shield external electromagnetic interference and ensure the stability of internal current control; the inner layer contains a hollow cavity filled with magnetorheological fluid, around which are arranged multiple segmented coils; the conduction of current in each coil is controlled separately by a controller; the controller consists of a single-chip microcomputer chip, an OA port and a current control module, which is used to control the conduction and disconnection of the current in the multiple coils in the parachute rope, and adjust the hardening and softening of the magnetorheological fluid in the hollow cavity inside the parachute rope; after the battery pack and other components are separated from the aircraft, the parachute opening mechanism is activated, and at the same time, all the parachute ropes on the parachute are connected in sequence from top to bottom by the internal coils. When current is input, the parachute rope is hardened from top to bottom by the magnetorheological fluid arranged inside, so that the parachute is opened and a support structure is provided for the parachute cloth, the descending speed of components such as the battery pack is effectively controlled, and a smooth landing is ensured. When the parachute starts to be recovered, the parachute rope connected to the recovery ratchet is firstly de-energized from bottom to top by the internal coil. At this time, the parachute rope is softened from bottom to top by the magnetorheological fluid arranged inside, so that the middle parachute rope is contracted section by section, and the recovery motor is immediately started, driving the recovery ratchet to rotate synchronously, gradually winding the softened parachute rope, and assisting its recovery. The middle parachute rope is the key part connected to the parachute cloth. By contracting the middle parachute rope first, the unfolded volume of the entire parachute can be effectively reduced, making the recovery process more stable and controllable.

[0045] Before landing, the battery pack is tightly attached to four limit locks on the left and right sides, connected to the parachute pack body on the top, and close to the aluminum alloy lower bracket on the bottom; when the aircraft is in flight, it is connected to the positive and negative poles of the battery pack through the conductive contact points on the slide rail to provide the aircraft with the required power; two symmetrical propeller brackets are respectively provided on the front and rear sides of the battery protection frame; when the battery pack is detached from the aircraft, the slider slides on the slide rail, guiding the battery protection frame to slide smoothly and safely out of the aluminum alloy bracket along the track of the slide rail in the predetermined direction, thereby achieving the smooth release and separation of the battery pack and other components, ensuring stability and safety during the detachment process.

[0046] The altitude sensor is tightly connected to the battery protection frame through an embedded fixed structure. The altitude sensor integrates a barometer and an optical flow sensor, and can simultaneously detect the air pressure altitude of the battery pack and the motion information relative to the ground.

[0047] A central control panel and an inspection cover are provided on the front face of the battery protection frame. The central control panel consists of an embedded display screen, a control knob and an internal connection module, and integrates the automated operation and monitoring functions of all key controllers after the battery pack is separated from the aircraft. The control knob is arranged on the right side of the display screen, and each control knob corresponds to an independent control circuit. The user can pre-set and adjust the operating parameters and operations of each controller through the control knob. These settings include the opening of the parachute rope, the operating timing of the dual-axis motor during parachute recovery, the operating parameters of the main parachute retracting and discharging motor and the recovery motor, the brushless DC motor for starting the folding propeller, and the deployment of the propeller bracket. The internal connection module is integrated in the central control panel and connected to the electrical channel arranged inside the battery protection frame to realize the connection between the central control panel and each controller, sensor and circuit. The inspection cover is located on the right side of the control knob and is connected to the battery protection frame through a simple fixing device. The necessary inspection, maintenance or replacement of components can be carried out by opening the inspection cover.

[0048] The lower part of the buffer rod is also connected to a spring rod and a rubber foot pad, which are tightly connected and located at the end of the spring rod. When the battery pack and other components are detached from the aircraft, the spring rod and the rubber foot pad reduce the impact force of the battery pack during landing, and increase friction after landing to prevent the battery pack from sliding on the ground. This design effectively reduces shock and absorbs energy while enhancing the stability and safety of the battery pack.

Claims

1. A battery safety separation and recovery device for an electric aircraft with replaceable batteries, characterized in that The separation and recovery device is installed in the aircraft body, including an aluminum alloy bracket, a battery pack, a parachute pack body, a battery protection frame, and the aluminum alloy bracket is arranged at the battery hatch near the bottom of the tail of the electric aircraft body, the battery protection frame is arranged in the aluminum alloy bracket, the battery pack is arranged in the battery protection frame, and the parachute pack body is fixed on the top of the battery protection frame, wherein: The aluminum alloy bracket includes an upper bracket, a lower bracket, a limit lock, a slider, an opening and closing mechanism and a rotating shaft. The upper bracket is attached to the upper surface of the battery hatch, and the lower bracket is attached to the lower surface of the battery hatch. The upper bracket and the lower bracket are connected by a rotating shaft. The opening and closing mechanism is arranged between the upper bracket and the lower bracket, and is connected to the rotating shaft, the upper bracket and the lower bracket. Several sliders are symmetrically installed on the upper and lower sides of the lower bracket on the left and right sides, respectively contacting the top and bottom of the battery protection frame; eight limit locks are symmetrically fixed on both sides of the lower bracket and located on the outside of the sliders; The battery protection frame includes a slide rail, a propeller bracket, a propeller, a buffer rod, an electrical channel and a height sensor. The battery protection frame is a rectangular parallelepiped structure, the frame is an internal hollow structure, and the interior of the frame is set as an electrical channel; four slide rails are respectively arranged at the four long edges of the upper surface and the lower bottom surface of the battery protection frame; there are four propeller brackets, which are symmetrically arranged on both sides of the front end and the rear end of the battery protection frame, the propeller is installed on the propeller bracket, and the buffer rod is fixed to the bottom of the propeller bracket; a height sensor is respectively arranged on the four bottom corners of the battery protection frame; the battery protection frame is provided with conductive contacts, which are in contact with the positive and negative poles of the battery pack, and the electrical channel is energized through the conductive contacts; The parachute bag main body includes a parachute cloth, a parachute rope, a retractable assembly, an opening and closing assembly, and a recovery assembly. The parachute cloth is arranged on the top of the battery protection frame. The retractable assembly, the opening and closing assembly, and the recovery assembly are all fixedly installed on the top of the battery protection frame. The parachute cloth is connected to the retractable assembly, the opening and closing assembly, and the recovery assembly through the parachute rope.

2. The battery safety separation and recovery device for an electric aircraft with replaceable batteries as claimed in claim 1, characterized in that The opening and closing mechanism includes a hydraulic push rod, a knob and a hinge. The hydraulic push rod is divided into an upper push rod and a lower push rod. The upper push rod and the lower push rod respectively pass through the inside of the connecting frame on the knob, and their tails pass through the inside of the hinge and are fixed on the hinge; there are two hinges, one with an opening facing downward and fixed under the upper bracket, and the other with an opening facing upward and fixed on the lower bracket; the hydraulic push rod is connected to the hydraulic system of the electric aircraft through a hydraulic oil pipe.

3. The battery safety separation and recovery device for an electric aircraft with replaceable batteries as claimed in claim 1, characterized in that The propeller bracket is installed on the side wall of the battery protection frame through a rotating rod. The propeller bracket rotates around the rotating rod. A brushless DC motor is arranged at the bottom of the propeller bracket. The brushless DC motor is fixed on the battery protection frame and connected to the electrical channel through a wire. The brushless DC motor is connected to the propeller through a transmission gear and a transmission belt to drive the propeller to rotate; the propeller is a foldable blade.

4. The battery safety separation and recovery device for an electric aircraft with replaceable batteries as claimed in claim 1, characterized in that The retractable and deployable assembly includes a retractable and deployable ratchet and a retractable and discharge motor, the opening and closing assembly includes an opening and closing ratchet and an opening and closing motor, and the recovery assembly includes a recovery ratchet and a recovery motor. There are eight retractable and deployable ratchets divided into two groups, which are symmetrically installed on the left and right edges of the battery protection frame, and the side surfaces of the retractable and deployable ratchets are connected to the retractable and discharge motors through connecting shafts; there are four opening and closing ratchets divided into two groups, which are symmetrically installed on the front and rear ends of the battery protection frame, and the opening and closing motor is arranged between the two opening and closing ratchets, and the two ends of the opening and closing motor are respectively linked to the two opening and closing ratchets through transmission shafts; the two recovery ratchets are installed in the middle of the battery protection frame, and the recovery motor is arranged next to the recovery ratchet, and is linked to the recovery ratchet through a transmission shaft; the retractable and deployable ratchet, the opening and closing ratchet, and the recovery ratchet are connected to the umbrella cloth through umbrella ropes.

5. The battery safety separation and recovery device for an electric aircraft with replaceable batteries as claimed in claim 1, characterized in that Two umbrella openings are symmetrically arranged on both sides of the umbrella cloth, and the umbrella openings are connected to the opening and closing components through umbrella ropes.

6. The battery safety separation and recovery device for an electric aircraft with replaceable batteries as claimed in claim 1, characterized in that The parachute rope adopts a three-layer structural design, the outer layer is a protective layer made of high-strength polymer; the middle layer is a shielding layer, which is composed of a copper braided mesh or a metal foil, and is used to shield external electromagnetic interference and ensure the stability of internal current control; the inner layer contains a hollow cavity filled with magnetorheological fluid, and a plurality of segmented coils are arranged around the cavity; the conduction of the current in each coil is controlled separately by a controller; the controller is composed of a single-chip microcomputer chip, an OA port and a current control module, and is used to control the conduction and disconnection of the current of the plurality of coils in the parachute rope, and adjust the hardening and softening of the magnetorheological fluid in the hollow cavity inside the parachute rope.

7. The battery safety separation and recovery device for an electric aircraft with replaceable batteries as claimed in claim 1, characterized in that The height sensor is tightly connected to the battery protection frame through an embedded fixing structure. The height sensor integrates a barometer and an optical flow sensor, and can simultaneously detect the air pressure height of the battery pack and the movement information relative to the ground.

8. The battery safety separation and recovery device for an electric aircraft with replaceable batteries as claimed in claim 1, characterized in that The front end face of the battery protection frame is provided with a central control panel and an inspection cover. The central control panel consists of an embedded display screen, a control knob and an internal connection module, and integrates the automated operation and monitoring functions of all key controllers after the battery pack is separated from the aircraft; the control knob is arranged on the right side of the display screen, and each control knob corresponds to an independent control circuit. The user can pre-set and adjust the operating parameters and operations of each controller through the control knob; these settings include the opening of the parachute rope, the operation timing of the dual-axis motor during parachute recovery, the operating parameters of the main parachute retracting and discharging motor and the recovery motor, the brushless DC motor for starting the folding propeller, and the deployment of the propeller bracket; the internal connection module is integrated in the central control panel and connected to the electrical channel arranged inside the battery protection frame to realize the connection between the central control panel and each controller, sensor and circuit; the inspection cover is located on the right side of the control knob, and is connected to the battery protection frame through a simple fixing device. The necessary inspection, maintenance or replacement of components can be carried out by opening the inspection cover.

9. The battery safety separation and recovery device for an electric aircraft with replaceable batteries as claimed in claim 1, characterized in that The lower part of the buffer rod is also connected with a spring rod and a rubber foot pad, the spring rod and the rubber foot pad are closely connected, and the rubber foot pad is located at the end of the spring rod.

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