Active separation deceleration parachute system and separation method

Abstract

This invention discloses an active separation deceleration parachute system and separation method, including a parachute, a parachute compartment, parachute lines, a mission payload, and a parachute launching mechanism. One end of the parachute lines is connected to the parachute, and the other end is connected to the parachute compartment. The parachute launching mechanism includes a triggering component, a seawater detector, a delay controller, and a separation component. One end of the separation component is connected to the parachute compartment, and the other end is connected to the mission payload. The triggering component is used to trigger the seawater detector and the delay controller to start, and the seawater detector and the delay controller are used to trigger the separation component. The beneficial effects of this invention are: setting up a dual triggering loop of seawater detection and delay timing, which can simultaneously adapt to both land and sea deployment conditions, solving the defects of traditional separation mechanisms that only adapt to a single condition and have poor versatility. The parallel connection of the dual loops forms a redundant fault-tolerant structure, and the parachute launching action can still be completed normally after the failure of a single sensor, effectively avoiding parachute launching failure and greatly improving the reliability of airdrop operations.

Description

Technical Field

[0001] This invention relates to the field of drogues, and more specifically to an active separation drogue system and separation method. Background Technology

[0002] In operational scenarios such as aerial drop, payload recovery, and low-altitude delivery, mission payloads are typically equipped with a drag chute system to perform in-flight deceleration, attitude correction, and steady-state descent, ensuring a smooth landing or sea entry. After the payload has completed its deceleration mission upon landing or at sea, if the drag chute cannot separate from the payload in time, the chute will continue to drag the mission payload under the influence of wind and water currents. In land-based operations, this can easily cause the payload to slip, overturn, or be damaged by impacts; in marine operations, the payload may be dragged by water currents, sink, or experience attitude deviations, severely affecting the accuracy of payload recovery and operational safety.

[0003] Currently, existing separation mechanisms are generally adapted to a single operating condition and cannot meet the needs of both land and sea deployment; they also lack redundant fault-tolerant design, and the failure of a single sensor can easily lead to parachute deployment failure. Therefore, there is an urgent need to design an active separation deceleration parachute system and separation method that requires no load power supply or load command, has adaptive capability for both land and sea operating conditions, and is redundant and reliable. Summary of the Invention

[0004] The purpose of this invention is to overcome the above-mentioned technical deflations and propose an active separation deceleration parachute system and separation method to solve the technical problems of limited adaptability to working conditions and easy failure in complex environments in the prior art.

[0005] Firstly, the active separation deceleration chute system provided in this application adopts the following technical solution: An active separation deceleration parachute system includes a parachute; Parachute cabin; Parachute lines, one end of which is connected to the parachute and the other end of which is connected to the parachute compartment; Mission payload; and, The parachute launching mechanism includes a triggering component, a seawater detector, a delay controller, and a separation component. The triggering component, the seawater detector, and the delay controller are all installed in the parachute compartment. One end of the separation component is connected to the parachute compartment, and the other end of the separation component is connected to the mission payload. The triggering component, the seawater detector, the delay controller, and the separation component are all electrically connected. The triggering component is used to trigger the seawater detector and the delay controller to start, and the seawater detector and the delay controller are used to trigger the separation component.

[0006] In some embodiments, the triggering component includes a pull cord, a pull pin, and a thermal battery. One end of the pull cord is connected to the parachute cord, and the other end of the pull cord is connected to the pull pin. The pull pin is mounted on the thermal battery, which is also electrically connected to the seawater detector and the delay controller. When the parachute opens, the pull cord tauts to trigger the pull pin.

[0007] In some embodiments, the separation assembly includes a flange, an explosive bolt, a fixed cylinder, a movable cylinder, and a connecting strap. The flange is connected to the parachute compartment, the fixed cylinder is connected to the flange, the explosive bolt passes through the fixed cylinder, and the explosive bolt is threadedly connected to the movable cylinder so that the movable cylinder abuts against the fixed cylinder. The seawater detector and the delay controller are both electrically connected to the explosive bolt. Both the seawater detector and the delay controller have built-in ignition capacitors. One end of the connecting strap is connected to the movable cylinder, and the other end of the connecting strap is connected to the mission payload.

[0008] In some embodiments, the parachute launching mechanism further includes a first cable, a second cable, a plug, and a socket. The seawater detector and the delay controller are both electrically connected to the first cable. The first cable is electrically connected to the socket. The plug is electrically connected to the socket. The plug is electrically connected to the second cable. The second cable is electrically connected to the explosion bolt.

[0009] In some embodiments, the separation assembly further includes a nut threadedly connected to the explosion bolt and abutting against the retaining cylinder.

[0010] In some embodiments, the separation component further includes a plurality of reinforcing ribs, all of which are connected to the connecting strip and extend along the length direction of the connecting strip.

[0011] In some embodiments, the deceleration parachute system further includes a buffer mechanism comprising a sleeve, a slide rod, and a spring. The end of the sleeve is hinged to the parachute lines, the slide rod is slidably connected to the sleeve, the end of the slide rod is connected to the pull pin rope, one end of the spring is connected to the sleeve, and the other end of the spring is connected to the slide rod.

[0012] In some embodiments, the explosive bolt includes a bolt body, a separating ring, a connector, an electric detonator, and a propellant charge. The bolt body passes through the fixed cylinder, the separating ring is connected to the middle of the bolt body, and the connector, electric detonator, and propellant charge are sequentially connected to the bolt body along the axial direction of the bolt body. The second cable, connector, and electric detonator are sequentially electrically connected.

[0013] In some embodiments, the buffer mechanism further includes a buffer pad, which is sleeved on the explosive bolt, with its two sides abutting against the nut and the fixing cylinder, respectively.

[0014] Secondly, this application provides a method for separating a catapult, comprising the following steps: Before deployment, the delay time is preset using the delay controller; After the airdrop, the parachute is inflated, the parachute lines pull the pull pin line, and the thermal battery is activated; The thermal battery powers the seawater detector and the delay controller. If it falls into the sea, the seawater detector will be activated, outputting ignition energy to detonate the explosive bolt, thereby separating the mission payload; If it lands on land, the delay controller will output ignition energy to detonate the explosive bolt after a preset time, thus achieving the separation of the mission payload.

[0015] Compared with the prior art, the beneficial effects of the present invention include: setting up a dual trigger circuit for seawater detection and time delay timing, which can simultaneously adapt to both land and sea deployment conditions, solving the defects of traditional separation mechanisms that are only adapted to a single condition and have poor versatility; the parallel connection of the two circuits forms a redundant fault-tolerant structure, and the parachute deployment action can still be completed normally after a single sensor fails, effectively avoiding parachute deployment failure and greatly improving the reliability of airdrop operations. Attached Figure Description

[0016] Figure 1 This is a flowchart of the deceleration parachute separation process provided by the present invention; Figure 2 This is a first-view overall structural diagram of the deceleration parachute provided by the present invention; Figure 3 This is a schematic diagram of the overall structure of the deceleration parachute from a second perspective provided by the present invention; Figure 4 This is a schematic diagram of the overall structure of the umbrella throwing mechanism provided by the present invention; Figure 5 This is a cross-sectional view of the overall structure of the triggering component provided by the present invention; Figure 6 This is a cross-sectional view of the overall structure of the separation component provided by the present invention.

[0017] Explanation of reference numerals in the attached figures: 1. Parachute; 2. Parachute compartment; 3. Parachute lines; 4. Mission payload; 5. Parachute ejection mechanism; 51. Trigger assembly; 511. Pull pin line; 512. Pull pin; 513. Thermal battery; 52. Seawater detector; 53. Time delay controller; 54. Separation assembly; 541. Flange; 542. Explosion bolt; 5421. Bolt body; 5422. Separation ring; 5423. Connector; 5424. Electric detonator; 5425. Explosive charge; 543. Fixed cylinder; 544. Moving cylinder; 545. Connecting strap; 546. Nut; 547. Reinforcing rib; 55. First cable; 56. Second cable; 57. Plug; 58. Socket; 6. Buffer mechanism; 61. Sleeve; 62. Slide rod; 63. Spring; 64. Buffer pad. Detailed Implementation

[0018] To make the objectives, technical solutions, and advantages of this invention clearer, the invention will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative and not intended to limit the invention.

[0019] This invention provides an active separation deceleration chute system, the structure of which is as follows: Figure 1 - Figure 6 As shown, it includes a parachute 1, a parachute compartment 2, parachute lines 3, a mission payload 4, and a parachute ejection mechanism 5.

[0020] One end of the parachute rope 3 is connected to the parachute 1, and the other end is connected to the parachute compartment 2.

[0021] The parachute launching mechanism 5 includes a triggering component 51, a seawater detector 52, a delay controller 53, and a separation component 54. The triggering component 51, the seawater detector 52, and the delay controller 53 are all installed in the parachute compartment 2. One end of the separation component 54 is connected to the parachute compartment 2, and the other end of the separation component 54 is connected to the mission payload 4. The triggering component 51, the seawater detector 52, the delay controller 53, and the separation component 54 are all electrically connected. The triggering component 51 is used to trigger the seawater detector 52 and the delay controller 53 to start. The seawater detector 52 is a SEN-SS01 seawater conductive sensor, and the delay controller 53 is an EDF-2011RY programmable electronic delay module.

[0022] During use, in the airdrop process, parachute 1 opens and straightens, activating trigger component 51, which simultaneously powers on seawater detector 52 and delay controller 53, putting them into standby mode. This invention employs a dual-mode sea-land discrimination logic. In sea-drop conditions, seawater contains a large amount of salt, ionizing Na+. + Cl -Plasma causes a sharp drop in resistance between the electrodes, forming a conductive circuit in the seawater detector 52 and completing the separation. In land-based deployment conditions, the seawater detector 52 remains inactive; instead, the delay controller 53 keeps time according to a pre-set schedule. Upon completion of the timer, the separation component 54 is triggered to deploy the parachute. Simultaneously, the seawater detector 52 and the delay controller 53 form a parallel redundant triggering circuit. Even if a single detection module fails, the other control circuit can still trigger the separation component 54, ensuring reliable parachute disconnection. Ultimately, this achieves autonomous, controllable, and redundant parachute separation under different deployment environments.

[0023] In this invention, a dual-trigger circuit for seawater detection and time delay timing is set up, which can simultaneously adapt to both land and sea deployment conditions. This solves the problem that traditional separation mechanisms are only suitable for a single condition and have poor versatility. The parallel connection of the two circuits forms a redundant fault-tolerant structure, which can still complete the parachute deployment action normally even if a single sensor fails, effectively avoiding parachute deployment failure and greatly improving the reliability of airdrop operations.

[0024] To trigger the seawater detector 52 and the delay controller 53, please refer to... Figure 4 In a preferred embodiment, the triggering component 51 includes a pull cord 511, a pull pin 512, and a thermal battery 513. One end of the pull cord 511 is connected to the parachute cord 3, and the other end of the pull cord 511 is connected to the pull pin 512. The pull pin 512 is mounted on the thermal battery 513. The thermal battery 513 is also electrically connected to the seawater detector 52 and the delay controller 53. When the parachute 1 opens, the pull cord 511 tauts to trigger the pull pin 512.

[0025] In use, when the parachute 1 is inflated and the parachute lines 3 are taut, the parachute lines 3 pull the pull pin 512 axially with the pull pin rope 511, causing the pull pin 512 to detach from the thermal battery 513, thus completing the mechanical activation of the thermal battery 513. After activation, the thermal battery 513 autonomously and continuously supplies power to the back-end seawater detector 52 and delay controller 53, enabling the entire machine to be powered on and started without the need for power supply from the mission payload 4 or external electrical control signals, thus completing the passive trigger activation of the system.

[0026] To achieve the separation of mission payload 4, please refer to Figure 4In a preferred embodiment, the separation assembly 54 includes a flange 541, an explosive bolt 542, a fixed cylinder 543, a movable cylinder 544, and a connecting strap 545. The flange 541 is connected to the parachute compartment 2, the fixed cylinder 543 is connected to the flange 541, the explosive bolt 542 passes through the fixed cylinder 543, and the explosive bolt 542 is threadedly connected to the movable cylinder 544 so that the movable cylinder 544 abuts against the fixed cylinder 543. The seawater detector 52 and the delay controller 53 are both electrically connected to the explosive bolt 542. The seawater detector 52 and the delay controller 53 both have built-in ignition capacitors. One end of the connecting strap 545 is connected to the movable cylinder 544, and the other end of the connecting strap 545 is connected to the mission payload 4.

[0027] In use, flange 541 is fixedly connected to parachute compartment 2, providing an installation reference for separation assembly 54; fixed cylinder 543 is fixed inside flange 541 to limit and support explosive bolt 542; explosive bolt 542 is axially inserted into fixed cylinder 543 and threadedly connected to movable cylinder 544, so that movable cylinder 544 is pressed against the lower end face of fixed cylinder 543, and fixed cylinder 543 and movable cylinder 544 are locked together by the preload of explosive bolt 542. At this time, connecting belt 545 is in a taut state, which can stably transfer the aerodynamic load generated by parachute 1 to mission load 4. When either the seawater detector 52 or the delay controller 53 circuit is activated, the ignition capacitor releases electrical energy to detonate the explosive bolt 542, which breaks along the preset separation surface. After the locking constraint of the explosive bolt 542 is removed, the clamping limit between the fixed cylinder 543 and the movable cylinder 544 is released. The movable cylinder 544 is freed from the constraint of the fixed cylinder 543 and moves downward relative to the mission load 4 along with the connecting belt 545. The parachute compartment 2, flange 541, and fixed cylinder 543 are separated from the mission load 4 along with the deceleration parachute, thus completing the reliable separation of the deceleration parachute from the mission load 4.

[0028] To ensure a reliable connection between the seawater detector 52, the time delay controller 53, and the explosive bolt 542, please refer to... Figure 4 In a preferred embodiment, the parachute launching mechanism 5 further includes a first cable 55, a second cable 56, a plug 57, and a socket 58. The seawater detector 52 and the delay controller 53 are both electrically connected to the first cable 55. The first cable 55 is electrically connected to the socket 58. The plug 57 is electrically connected to the socket 58. The plug 57 is electrically connected to the second cable 56. The second cable 56 is electrically connected to the explosion bolt 542.

[0029] In use, the seawater detector 52 and the time delay controller 53 are connected in parallel to the first cable 55, which aggregates the detected ignition signal and the delayed ignition signal to the socket 58. The plug 57 and the socket 58 are connected by a plug-in sealed connection, which enables rapid circuit conduction and has waterproof and anti-loosening capabilities. The plug 57 is electrically connected to the explosion bolt 542 through the second cable 56. When the system is working, the ignition energy generated by the seawater detector 52 or the time delay controller 53 is accurately transmitted to the explosion bolt 542 in sequence through the first cable 55, the socket 58, the plug 57, and the second cable 56. The segmented cable arrangement with the plug-in electrical connector 5423 not only achieves reliable electrical connection between the control module and the pyrotechnic actuator, but also facilitates modular disassembly and assembly of components.

[0030] To improve the stability of the installation of the 542 explosion bolts, please refer to... Figure 4 In a preferred embodiment, the separation component 54 further includes a nut 546, which is threaded to the explosion bolt 542 and abuts against the fixed cylinder 543.

[0031] During use, under normal airdrop conditions, nut 546 presses against the upper surface of fixed cylinder 543, and in conjunction with the preload of explosive bolt 542, restricts the axial movement of fixed cylinder 543 and movable cylinder 544, improving the overall structure's resistance to vibration and impact, and preventing loosening of threads and excessive connection gaps due to vibration during airdrop flight. Simultaneously, nut 546 can adjust the preload of explosive bolt 542, ensuring a tight fit and uniform force distribution between fixed cylinder 543 and movable cylinder 544. When explosive bolt 542 breaks upon receiving ignition energy, nut 546 loses its bolt constraint and releases its locking limit along with fixed cylinder 543, without interfering with the separation of movable cylinder 544 and connecting belt 545, ensuring smooth and reliable separation of the parachute.

[0032] To improve the strength of the 545 connecting strip, please refer to... Figure 4 In a preferred embodiment, the separation component 54 further includes a plurality of reinforcing ribs 547, all of which are connected to the connecting strip 545 and extend along the length of the connecting strip 545.

[0033] During use, at the moment of parachute opening and during steady-state descent, the reinforcing rib 547 can provide overall tensile reinforcement and rigid constraint to the connecting belt 545, disperse the impact tension of parachute opening, and prevent local stress concentration, tensile deformation, tearing or excessive bending of the connecting belt 545. At the same time, the reinforcing rib 547 is arranged along the length direction, which can limit the lateral swing and twisting of the connecting belt 545, maintain smooth and stable force flow transmission, improve the load-bearing strength and fatigue resistance of the connecting belt 545, and ensure reliable parachute load transmission throughout the airdrop process.

[0034] To reduce the possibility of damage to paracord 3 and pull pin rope 511, please refer to Figure 4In a preferred embodiment, the deceleration parachute system further includes a buffer mechanism 6, which includes a sleeve 61, a slide rod 62, and a spring 63. The end of the sleeve 61 is hinged to the parachute rope 3, the slide rod 62 is slidably connected to the sleeve 61, the end of the slide rod 62 is connected to the pull pin rope 511, one end of the spring 63 is connected to the sleeve 61, and the other end of the spring 63 is connected to the slide rod 62.

[0035] During use, the moment the parachute 1 opens, it generates an instantaneous impact force. When this impact load acts on the buffer mechanism 6, the slide bar 62 slides axially relative to the sleeve 61, stretching the spring 63. The elastic deformation of the spring 63 absorbs and attenuates the instantaneous impact load during parachute opening, preventing the pull pin rope 511 from being subjected to excessive tension and breaking or failing due to overload. After the parachute opening force stabilizes, the spring 63 rebounds, causing the slide bar 62 to return to its original position, ensuring that the pull pin rope 511 receives a stable and uniform traction force, accurately completing the pull pin 512 pulling action. This effectively improves the activation stability of the trigger component 51 and reduces the probability of false triggering or failure to trigger under harsh airdrop conditions.

[0036] To improve the reliability of the 542 explosion bolt, please refer to... Figure 6 In a preferred embodiment, the explosive bolt 542 includes a bolt body 5421, a separating ring 5422, a connector 5423, an electric detonator 5424, and a propellant charge 5425. The bolt body 5421 passes through the fixed cylinder 543. The separating ring 5422 is connected to the middle of the bolt body 5421. The connector 5423, the electric detonator 5424, and the propellant charge 5425 are sequentially connected to the bolt body 5421 along the axial direction of the bolt body 5421. The second cable 56, the connector 5423, and the electric detonator 5424 are sequentially electrically connected.

[0037] In use, the bolt body 5421 is inserted inside the fixed cylinder 543 as the main load-bearing base. A separation ring 5422 is set in the middle of the bolt body 5421 to form a preset weak separation section, which facilitates directional breakage. The connector 5423, electric detonator 5424 and explosive charge 5425 are installed in sequence along the axial direction of the bolt body 5421. The second cable 56 is electrically connected to the connector 5423 to introduce external ignition energy into the explosive bolt 542. Under normal airdrop conditions, the breechblock 5421 withstands the parachute deployment force thanks to its own structural strength, while the separation ring 5422 maintains structural integrity, ensuring a reliable connection between the parachute and the mission payload 4. When a firing command is received, the firing energy is transmitted to the electric detonator 5424 via the second cable 56 and connector 5423. The electric detonator 5424 detonates and ignites the explosive charge 5425. The explosive charge 5425 instantly explodes, generating a high-pressure impact force. The stress is concentrated on the weak section of the separation ring 5422, causing the breechblock 5421 to break precisely along the separation ring 5422, releasing the axial locking constraint of the explosive bolt 542. This provides the unlocking conditions for the separation assembly 54, enabling the rapid and reliable separation of the deceleration parachute from the mission payload 4.

[0038] To further improve the stability of the 542 explosive bolt, please refer to... Figure 6 In a preferred embodiment, the buffer mechanism 6 further includes a buffer pad 64, which is sleeved on the explosion bolt 542, and the two sides of the buffer pad 64 abut against the nut 546 and the fixing cylinder 543 respectively.

[0039] During use, the tension of the parachute ropes 3, aerodynamic vibration, and impact loads are transmitted to the contact surfaces of the nut 546 and the fixing cylinder 543 during airdrop descent and parachute deployment, which can easily lead to rigid impacts, gap movement, and thread loosening. The buffer pad 64 utilizes its flexible deformation characteristics to absorb and attenuate axial impacts and vibrations, preventing direct rigid collisions between the nut 546 and the fixing cylinder 543, thus reducing structural vibration noise and stress concentration. At the same time, the buffer pad 64 can fill the assembly gap between the nut 546 and the fixing cylinder 543, playing a role in axial limiting, anti-loosening, and vibration damping, thereby improving the connection stability of the overall structure under vibration and overload conditions.

[0040] This application also discloses a method for separating a catapult, such as... Figure 1 As shown, it includes the following steps: Before deployment, the delay time is preset using the delay controller 53; After the airdrop, parachute 1 is inflated, parachute rope 3 pulls pull pin rope 511, and thermal battery 513 is activated; The thermal battery 513 powers the seawater detector 52 and the delay controller 53; If it falls into the sea, the seawater detector 52 will be activated, outputting ignition energy to detonate the explosive bolt 542, thus achieving the separation of the mission payload 4; If it lands on land, the delay controller 53 will reach the preset time and output ignition energy to detonate the explosive bolt 542, thus achieving the separation of the mission payload 4.

[0041] Before deployment, a preset delay time is pre-set via the delay controller 53. After airdrop, the parachute 1 inflates and opens in the air, the parachute lines 3 are straightened, and the pull pin 511 is pulled, triggering the pull pin 512 to activate the thermal battery 513. Once operational, the thermal battery 513 continuously supplies power to the seawater detector 52 and the delay controller 53, putting both control circuits into standby mode. When the mission payload 4 falls into the seawater environment, the seawater detector 52 senses the seawater and immediately activates, outputting ignition energy to detonate the explosive bolt 542, achieving rapid separation of the deceleration parachute and the mission payload 4. When the mission payload 4 falls onto land, the seawater detector 52 does not activate; instead, the delay controller 53 times the preset time. Upon the timeout, it automatically outputs ignition energy to detonate the explosive bolt 542, similarly achieving autonomous separation of the deceleration parachute and the mission payload 4.

[0042] To better understand this invention, the following is combined with... Figure 1 - Figure 6 The working principle of an active separation deceleration parachute system according to the present invention is described in detail below: During the airdrop process, the parachute 1 opens and straightens, which activates the trigger component 51, causing the seawater detector 52 and the delay controller 53 to be powered on synchronously and enter the standby working state. The present invention adopts a dual-mode sea-land discrimination logic. Under the sea-drop condition, the seawater contains a large amount of salt and ionizes Na+. + Cl - Plasma causes a sharp drop in resistance between the electrodes, forming a conductive circuit in the seawater detector 52 and completing the separation. In land-based deployment conditions, the seawater detector 52 remains inactive; instead, the delay controller 53 keeps time according to a pre-set schedule. Upon completion of the timer, the separation component 54 is triggered to deploy the parachute. Simultaneously, the seawater detector 52 and the delay controller 53 form a parallel redundant triggering circuit. Even if a single detection module fails, the other control circuit can still trigger the separation component 54, ensuring reliable parachute disconnection. Ultimately, this achieves autonomous, controllable, and redundant parachute separation under different deployment environments.

[0043] The specific embodiments of the present invention described above do not constitute a limitation on the scope of protection of the present invention. Any other corresponding changes and modifications made in accordance with the technical concept of the present invention should be included within the scope of protection of the claims of the present invention.

Claims

1. An active separation decelerating parachute system, characterized by include: parachute; Parachute cabin; Parachute lines, one end of which is connected to the parachute and the other end of which is connected to the parachute compartment; Mission payload; as well as, The parachute launching mechanism includes a triggering component, a seawater detector, a delay controller, and a separation component. The triggering component, the seawater detector, and the delay controller are all installed in the parachute compartment. One end of the separation component is connected to the parachute compartment, and the other end of the separation component is connected to the mission payload. The triggering component, the seawater detector, the delay controller, and the separation component are all electrically connected. The triggering component is used to trigger the seawater detector and the delay controller to start, and the seawater detector and the delay controller are used to trigger the separation component.

2. The active separation deceleration chute system according to claim 1, characterized in that, The triggering component includes a pull cord, a pull pin, and a thermal battery. One end of the pull cord is connected to the parachute cord, and the other end of the pull cord is connected to the pull pin. The pull pin is installed on the thermal battery, which is also electrically connected to the seawater detector and the delay controller. When the parachute opens, the pull cord tauts to trigger the pull pin.

3. The active separation deceleration chute system according to claim 2, characterized in that, The separation assembly includes a flange, an explosive bolt, a fixed cylinder, a movable cylinder, and a connecting strap. The flange is connected to the parachute compartment, the fixed cylinder is connected to the flange, the explosive bolt passes through the fixed cylinder, and the explosive bolt is threadedly connected to the movable cylinder so that the movable cylinder abuts against the fixed cylinder. The seawater detector and the delay controller are both electrically connected to the explosive bolt. Both the seawater detector and the delay controller have built-in ignition capacitors. One end of the connecting strap is connected to the movable cylinder, and the other end of the connecting strap is connected to the mission payload.

4. The active separation deceleration chute system according to claim 3, characterized in that, The parachute launching mechanism also includes a first cable, a second cable, a plug, and a socket. The seawater detector and the delay controller are both electrically connected to the first cable. The first cable is electrically connected to the socket. The plug is electrically connected to the socket. The plug is electrically connected to the second cable. The second cable is electrically connected to the explosive bolt.

5. The active separation deceleration chute system according to claim 3, characterized in that, The separation assembly also includes a nut, which is threaded onto the explosive bolt and abuts against the fixed cylinder.

6. The active separation deceleration chute system according to claim 3, characterized in that, The separation component also includes a plurality of reinforcing ribs, all of which are connected to the connecting strip and extend along the length of the connecting strip.

7. The active separation deceleration chute system according to claim 3, characterized in that, The deceleration parachute system also includes a buffer mechanism, which includes a sleeve, a slide rod, and a spring. The end of the sleeve is hinged to the parachute lines, the slide rod is slidably connected to the sleeve, the end of the slide rod is connected to the pull pin rope, one end of the spring is connected to the sleeve, and the other end of the spring is connected to the slide rod.

8. The active separation deceleration chute system according to claim 4, characterized in that, The explosive bolt includes a bolt body, a separating ring, a connector, an electric detonator, and a propellant charge. The bolt body is inserted into the fixed cylinder, the separating ring is connected to the middle of the bolt body, and the connector, electric detonator, and propellant charge are sequentially connected to the bolt body along the axial direction of the bolt body. The second cable, connector, and electric detonator are sequentially electrically connected.

9. The active separation deceleration chute system according to claim 7, characterized in that, The buffer mechanism also includes a buffer pad, which is sleeved on the explosive bolt, and the two sides of the buffer pad abut against the nut and the fixing cylinder, respectively.

10. A method for separating a deceleration chute, characterized in that, The active separation deceleration parachute system according to any one of claims 1 to 9 comprises the following steps: Before deployment, the delay time is preset using the delay controller; After the airdrop, the parachute is inflated, the parachute lines pull the pull pin line, and the thermal battery is activated; The thermal battery powers the seawater detector and the delay controller. If it falls into the sea, the seawater detector will be activated, outputting ignition energy to detonate the explosive bolt, thereby separating the mission payload; If it lands on land, the delay controller will output ignition energy to detonate the explosive bolt after a preset time, thus achieving the separation of the mission payload.

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