Dual mode active and passive separation and safe landing method for a vehicle cabin and a propeller

Abstract

This invention discloses a dual-mode active and passive disengagement and safe landing method for the spacecraft cabin and thrusters, belonging to the field of emergency rescue technology for aerospace vehicles. Addressing the shortcomings of existing aerospace vehicle technologies, such as delayed rescue response after thruster failure, limited separation methods, weak cabin anti-interference capabilities, low landing fault tolerance, and inability to adapt to all aerospace operating conditions, this invention adopts an integral, non-separable manned / cargo cabin structure design. The manned / cargo cabin has an independent, self-sustaining propulsion system, completely decoupled and independently controlled from the main thruster assembly. This invention constructs a dual-redundant emergency mechanism of active predictive disengagement and passive forced disengagement. Through multi-source sensor nine-dimensional parameter acquisition and a three-level fault threshold algorithm, it achieves early, active, and stable overall disengagement for minor thruster performance failures and millisecond-level forced overall disengagement for sudden, severe, irreversible failures, ensuring the structural integrity and attitude stability of the manned / cargo cabin throughout the process. After the capsule detaches from the thrusters, it can adaptively and optimally switch between three landing modes—pure self-sustaining power landing, pure parachute landing, and powered-parachute hybrid landing—based on flight altitude, wind speed, orbital conditions, and aerospace operational conditions. This adapts to emergency landing needs across low-altitude, high-altitude, suborbital, and near-Earth orbit scenarios. This invention overcomes the limitations of traditional single passive buffering rescue methods, featuring wide adaptability to operational conditions, rapid emergency response, high landing accuracy, and strong anti-interference capabilities. It effectively solves the problems of capsule loss of control, crash, orbital drift, and secondary impact damage after thruster failure, significantly improving the safety and reliability of aerospace vehicle operations. It has extremely high engineering feasibility and industrialization potential.

Description

Technical Field

[0001] This invention belongs to the field of aerospace vehicle safety and rescue technology, specifically involving a method for active and passive dual-mode retreat and autonomous safe landing / return of the crew / cargo cabin and propulsion of an aircraft / space vehicle. It is applicable to emergency rescue scenarios for faults in various modular aerospace vehicles such as multi-rotor aircraft, fixed-wing aircraft, and vertical take-off and landing aircraft, as well as suborbital aircraft, near-Earth orbit space vehicles, and reusable aerospace vehicles. Background Technology

[0002] Currently, modular aircraft and spacecraft generally adopt a fixed connection between the cabin and the thruster or a single passive separation structure. As the core of the aircraft's power, the thruster is prone to failures such as motor failure, oil circuit blockage, structural fracture, and runaway stall under aviation conditions. Under space and suborbital conditions, it is prone to failures such as nozzle distortion, attitude control thrust failure, orbital attitude deviation, thermal protection damage, propellant leakage, and structural stress failure in the vacuum environment. Once the thruster is damaged, the entire spacecraft will lose power and attitude control, and is highly susceptible to safety accidents such as crashes, airbursts, orbital deviations, and cabin damage.

[0003] Existing modular emergency rescue technologies for aerospace vehicles suffer from serious technical shortcomings in both aviation and space operating conditions, with significant deficiencies in engineering implementation and control logic: First, the fault response mechanism is simplistic. Mainstream industry solutions only adapt to passive ejection separation logic in low-altitude atmospheric environments, lacking fault level prediction and active risk avoidance mechanisms suitable for space vacuum, microgravity, and high-speed orbital conditions. Furthermore, most separation solutions are purely passive drop-type buffering without power, lacking autonomous correction and maneuvering capabilities after the crew / cargo capsule detaches, relying solely on parachutes and airbags for passive cushioning. This results in a narrow rescue response window, delayed triggering, and extremely low fault tolerance. Second, an integrated capsule detachment architecture is lacking. Existing technologies mostly employ split capsule coupling structures, which pose risks of asynchronous separation and collision interference. There is no integrated, synchronous detachment architecture for the crew / cargo capsule, making it impossible to achieve single-capsule detachment. Third, there is no autonomous maneuverability after separation. Traditional cabins rely entirely on the main thrusters for power. After the thrusters are damaged, the crew / cargo cabin is in a state of unpowered free fall / orbit drift, unable to avoid the debris of the failed thrusters, high-temperature airflow, and explosive shock waves, making it extremely vulnerable to secondary collision damage and uncontrollable landing point. Fourth, there is a lack of fault resistance. Under aviation conditions, thruster failure will generate residual rotational torque, high-temperature debris, oil leakage and open flame, and residual thrust. Under space conditions, there are propellant leaks, microgravity residual thrust, orbital angular velocity disturbances, and space debris impact interference. Existing separation structures lack multiple isolation designs for electrical, mechanical, thermal, and orbital torque, making them extremely prone to faults such as connection structure jamming, crew / cargo cabin attitude disturbance, secondary damage, and orbital deviation, leading to overall separation failure and landing / return failure.

[0004] In summary, the existing technology system lacks a systematic solution that integrates multi-source sensor fault classification and prediction, active and passive dual redundancy overall separation, decoupled control of manned / cargo cabins, quantitative adaptive landing and return across all airspace and operating conditions in aviation / space, and multi-dimensional fault isolation. There is a significant technological gap, which cannot meet the engineering requirements for emergency self-protection of manned / cargo cabins in aerospace vehicles. There is an urgent need to propose a new technical approach that is feasible, quantifiable, and highly redundant. Summary of the Invention

[0005] Purpose of the invention The purpose of this invention is to address the core pain points of existing modular aerospace and spacecraft thruster failure rescue solutions, such as delayed response, coupled cabin structure, poor adaptability to aerospace conditions, and low engineering reliability. It provides a method for active and passive dual-mode ejection and safe landing of the spacecraft cabin and thruster. This invention constructs a complete technical system encompassing three-level fault assessment, dual-mode redundant overall separation, independent control of the crew / cargo cabin, and quantitative adaptive landing across the entire aerospace / space domain. Through quantifiable fault judgment thresholds, standardized aerospace dual-condition overall separation control logic, and graded adaptive atmospheric landing / space reentry buffer algorithms, it achieves overall, precise, and safe ejection of the crew / cargo cabin after thruster failure. This effectively improves the safety and integrity of spacecraft failure rescue, adapts to atmospheric flight, suborbital, and near-Earth orbit scenarios, and possesses extremely high technological innovation, engineering feasibility, and industrial applicability, fully meeting the novelty, inventiveness, and practicality requirements for invention patent authorization. Technical solution

[0006] To achieve the above objectives, this invention adopts a fully engineering-feasible and systematic technical solution, adaptable to multi-rotor, fixed-wing, and vertical takeoff and landing aircraft, as well as suborbital and near-Earth orbit spacecraft. The modular spacecraft hardware system consists of a manned / cargo capsule, an externally detachable main thruster assembly, a multi-source sensor integrated telemetry and control system, a full-dimensional adaptive safe landing system, and an integrated capsule locking mechanism. The core innovation lies in the fact that the manned / cargo capsule is an integral, non-separable structure with an integrated, self-sustaining propulsion system completely independent of the main thruster assembly, enabling integrated separation of the manned / cargo capsule from the main thruster assembly. The manned / cargo capsule is equipped with a micro-vector propulsion unit, an independent attitude control unit, an independent power supply unit, and an independent landing execution unit. The capsule unlocking, overall separation, attitude adjustment, power maneuvering, and landing / return control links are completely independent, without coupling interference, and can adapt to various operating conditions including conventional atmospheric flight, on-orbit flight in space vacuum, and suborbital transitional flight.

[0007] 1. Proactively predict and exit the process (minor fault prediction and risk avoidance mode) The S100 integrated measurement and control system collects nine operational parameters of the thruster assembly in real time, including rotational speed, power output, structural stress, temperature, attitude deviation, oil circuit status, orbital angular velocity, propellant pressure, and vacuum sealing status. It also performs real-time analysis through a built-in dual-condition fault prediction algorithm to identify mechanical faults and performance degradation hazards under aerospace conditions, as well as potential failure hazards such as propellant leakage, attitude control failure, orbital deviation, and structural thermal deformation under space conditions. S200 When it is determined that the thruster has a potential fault but has not completely failed, and the aircraft still has a short-term stable attitude, the system triggers an active and controllable retreat command to prioritize fault isolation: firstly, the power, oil, and signal linkage paths between the thruster and the crew / cargo cabin are cut off to eliminate residual fault interference from the thruster; S300: Based on the aircraft's operating mode, execute the overall graded separation logic: Regardless of the operating mode, directly execute the core action of the entire crew / cargo cabin detaching from the thruster group, ensuring the integrity of the overall structure of the crew / cargo cabin, and the thruster group remains in place for failure shutdown; During the separation process of the S400 cabin, the self-sustaining power system of the crew / cargo cabin is immediately activated. Through vector power fine-tuning, the cabin pitch, roll, and yaw attitude are corrected in real time. The safe distance between the cabin and the main thruster is actively increased to avoid the fault area and ensure that there is no pulling, no overturning, and no high-speed deviation during the separation process. The cabin relies on its own power to glide smoothly and gradually return to the starting point for landing.

[0008] 2. Passive Fault Handling Procedure (Severe Fault Emergency Backup Mode) When the S500 detects a sudden breakage of the thruster, power failure, uncontrolled dive, fire or explosion under aviation conditions, or a severe irreversible failure such as thruster nozzle failure, propellant leakage, loss of orbital attitude control, thermal protection damage, or severe on-orbit vibration under space conditions, or when the active prediction system fails or the spacecraft's attitude becomes instantly uncontrollable, it immediately triggers a passive forced escape emergency mechanism without human intervention or attitude prediction. The S600 initiates a two-stage forced overall separation action: First stage, it instantly cuts off all connecting circuits, oil lines, and signal links, breaking the electrical binding; Second stage, it unlocks the overall locking mechanism of the crew / cargo compartment, and at the same time, it starts the self-sustaining power system of the crew / cargo compartment at full speed in milliseconds. In conjunction with the micro ejection booster mechanism, it breaks through the overall mechanical latch limit and uses its own power to push away from the faulty main thruster, realizing the rapid forced overall separation of the crew / cargo compartment from the faulty thruster, completely moving away from the faulty power unit and avoiding the risks of collateral damage, explosion impact, and debris collision. During the passive overall disengagement process of the S700, the overall safety of the crew / cargo cabin is the core focus. The cabin structure remains intact and undisassembled throughout the process, shielding it from residual power from the malfunctioning thruster, debris impact, and torque interference, thus ensuring the overall attitude stability and structural integrity of the crew / cargo cabin.

[0009] 3. Post-separation multi-mode selectable safe landing process (self-sustaining power / parachute / hybrid mode adaptive selection) The moment the S800, crew / cargo capsule, and main thruster completely separate, the self-sustaining propulsion system is on standby and activated throughout the entire process. The telemetry and control system collects parameters such as current flight altitude, descent speed, ambient wind speed, capsule attitude, orbital altitude, reentry speed, and atmospheric density in real time. It distinguishes between four operating conditions: low-altitude atmospheric reentry, high-altitude atmospheric reentry, suborbital reentry, and near-Earth orbit return. It adaptively and optimally selects three safe landing methods: pure self-sustaining power landing, pure parachute buffer landing, and power + parachute composite landing, realizing multi-mode selectable adaptive descent control for the crew / cargo capsule. S900, high-altitude standard scenario (height ≥100m): The default landing mode is a hybrid powered landing plus parachute landing mode. It relies on the self-sustaining power of the manned / cargo cabin to complete the initial attitude stabilization, trajectory correction and deceleration gliding. The auxiliary attitude parachute and the main parachute are deployed in stages. The parachute achieves the main deceleration, while the self-sustaining power dynamically balances the falling attitude and speed, eliminates horizontal deviation and tumbling moment, and precisely controls the falling speed within the safety threshold. When approaching the ground, the bottom inflatable cushioning airbag is deployed to complete a highly stable soft landing. Under ideal conditions with no wind and excellent attitude, it can adaptively switch to a pure parachute landing mode, turn off redundant power output, and reduce energy consumption. S1000, low-altitude emergency scenarios (altitude <100m), strong wind disturbance scenarios: If the system determines that the parachute opening range is insufficient or the canopy cannot be fully deployed, the parachute is disabled by default, and a pure self-sustaining power landing mode is adopted. The entire process relies on the self-sustaining vector power of the manned / cargo capsule for reverse braking, attitude locking, and vertical stabilization. Simultaneously, the buffer airbags and shock-absorbing brackets are activated to offset the residual impact force, achieving a stable low-altitude fixed-point landing. For near-Earth orbit derailment and suborbital reentry scenarios, the system prioritizes self-sustaining power to complete attitude stabilization, orbit descent, and reentry correction throughout the entire process. After entering the effective atmospheric altitude, the parachute is selected as needed to assist in deceleration, adapting to the landing needs of all aerospace scenarios and completely eliminating the problems of powerless drift, loss of control during fall, and low-altitude parachute opening failure. S1100 After landing, the system automatically triggers the cabin locking, fault alarm, and location reporting functions, and activates the emergency protection and shockproof locking mechanism for the manned / cargo cabin to ensure the overall safety and structural integrity of the cabin after landing.

[0010] Furthermore, the manned / cargo cabin is an integral, non-separable modular structure, equipped with a dedicated self-sustaining vector power system, attitude control unit, landing buffer unit, and independent power supply unit. It can achieve the independent and complete retraction of the manned / cargo cabin as a whole. After detaching from the main thruster, it can autonomously complete attitude stabilization, gliding, deceleration, and fixed-point landing. The entire process is structurally intact, without disassembly or separation of independent sub-cabins.

[0011] Furthermore, the electromagnetic locking + mechanical buckle composite connection structure, under normal conditions, is double-fixed by electromagnetic lock adsorption and mechanical buckle rigid limit to ensure flight stability; in case of fault separation, the electromagnetic lock is instantly de-energized and unlocked, and the mechanical buckle is elastically released. In active mode, separation is slow and smooth, and in passive mode, separation is forced by a micro ejection mechanism, with no risk of structural jamming.

[0012] Furthermore, the fault prediction algorithm incorporates multi-level thresholds to distinguish between three operating conditions: minor performance degradation, moderate potential faults, and severe irreversible faults. It accurately matches three response modes: active retreat, early warning standby, and passive forced departure, to avoid false triggering or missed triggering.

[0013] Furthermore, the safe landing system includes a multi-stage parachute assembly, an adaptive inflatable buffer airbag, a micro recoil braking unit, attitude correction control surfaces, a space attitude control micro-jet unit, and a reentry thermal protection buffer structure. It can dynamically adjust its working state according to real-time environmental parameters such as aviation atmospheric conditions, space vacuum on-orbit conditions, and suborbital reentry conditions, adapting to all airspace and all operating conditions of fault landing scenarios. Beneficial effects

[0014] Compared with the prior art, this invention has the following core innovations and beneficial effects, while simultaneously meeting the requirements of novelty, inventiveness, and industrial applicability for invention patents:

[0015] 1. This invention pioneers a dual-redundant overall separation mechanism, overcoming the bottleneck of traditional single passive separation technology. It employs a dual-mode system of active predictive risk avoidance and passive forced backup, enabling early detection of potential hazards in the early stages of thruster failure and early, stable overall separation to mitigate the risk of severe malfunctions. Simultaneously, it achieves millisecond-level forced overall separation in the event of sudden irreversible failures, significantly extending the rescue window. This addresses the shortcomings of existing technologies, such as delayed rescue, asynchronous separation, and low reliability, demonstrating significant novelty in its technical solution.

[0016] 2. Pioneering integrated manned / cargo capsule disengagement architecture, offering extremely high safety and uniformity. Unlike traditional split-body coupling and separation structures, this invention adopts a core logic of integrated synchronous disengagement of a single-body manned / cargo capsule. The capsule is designed as a single integrated unit, which cannot be disassembled. In the event of a malfunction, it achieves synchronized disengagement, overall attitude stability, and overall landing, completely eliminating the defects of split-body collisions and asynchronous separation. This maximizes the integrity of emergency operations for the aircraft, demonstrating outstanding innovation.

[0017] 3. A unique multi-mode adaptive landing system, overturning the traditional single-buffer mechanism. This invention addresses the scenario where the main thruster completely fails after the entire crew / cargo capsule detaches. It designs three selectable working modes: pure self-sustaining power landing, pure parachute landing, and a power-parachute hybrid landing. The system can adaptively and optimally switch between these modes based on altitude, wind speed, attitude, and orbital conditions. It retains the advantages of powered landing—precise controllability, strong anti-interference, and controllable landing point—while also preserving the energy-saving, high redundancy, and low-load characteristics of parachute landing. This significantly overcomes the technical shortcomings of traditional rescue solutions, such as a single landing method, poor adaptability to various conditions, and low fault tolerance.

[0018] 4. Multiple fault isolation and anti-interference design ensures strong system stability. Through fault link disconnection, trajectory isolation, and real-time attitude correction design, the residual power, debris, and structural pulling interference from the faulty thruster are completely shielded, eliminating faults such as separation jamming, cabin collision, and overturning. The redundant design is comprehensive and adaptable to various complex flight environments.

[0019] 5. Highly practical and widely applicable. This invention requires no major modifications to existing aircraft structures, is highly modular and adaptable, and can be widely used in various types of aerospace equipment, including civilian manned aircraft, logistics and cargo aircraft, industrial inspection aircraft, emergency rescue aircraft, suborbital sightseeing aircraft, and small near-Earth orbit space shuttles. It features a simple structure, controllable cost, and high reliability, making it extremely valuable for industrialization and promotion. Attached Figure Description

[0020] Figure 1 This is a schematic diagram of the overall structure of the aircraft.

[0021] Attached diagram captions: 1. Manned / cargo compartment; 2. Propulsion unit; 3. Thruster. Detailed Implementation

[0022] The present invention will be further described in detail below with reference to specific embodiments. Example 1: Active back-off and landing scenario for minor flight malfunctions

[0023] During normal flight operations, the telemetry and control system monitored in real time that the single-side motor speed of the thruster was decreasing and the power output deviation exceeded the standard, which was determined to be a minor potential fault. No loss of control, shaking, or fire occurred. The system triggered the active predictive retreat procedure, first cutting off the electrical, fuel, and signal connections between the thruster and the crew / cargo cabin, unlocking the overall composite locking structure of the cabin, and simultaneously activating the crew / cargo cabin's self-sustaining propulsion system. The attitude control system, in conjunction with the self-sustaining propulsion, corrected the overall cabin attitude in real time, actively moving away from the faulty thruster and smoothly gliding away. At this point, the flight altitude was 280m. Relying on the self-sustaining propulsion, the aircraft slowly decelerated and stabilized its attitude, with the parachute providing gradual cushioning. When the aircraft was 5m from the ground, the bottom inflatable airbags were deployed, completing a soft landing of the crew / cargo cabin. Throughout the entire process, the cabin structure remained intact, the attitude was stable, there was no impact, and there was no overturning. The faulty thruster stopped and failed on the spot, with no risk of collateral damage. Example 2: Severe Failure and Passive Forced Departure Landing Scenario

[0024] During flight operations, the main thruster suddenly fractured, causing a complete power failure. The aircraft instantly lost attitude control and rapidly plunged, a severe and irreversible malfunction, which the proactive prediction system could not respond to in time. The system immediately triggered a passive forced escape mechanism, severing all linkage links in milliseconds, unlocking the overall locking structure of the crew / cargo capsule, and instantly activating the crew / cargo capsule's self-sustaining propulsion system at full speed. In conjunction with a miniature ejection mechanism, the system pushed the damaged thruster away from the impact zone, quickly escaping the malfunction zone and actively correcting the plunging attitude. At an altitude of 65 meters, the system skipped the parachute deployment process, relying entirely on its self-sustaining power for reverse braking and vertical descent. With the help of cushioning airbags to offset the residual impact, the crew / cargo capsule made a low-altitude, stable, and precise landing, completely avoiding the risks of traditional split-part crashes and secondary impacts from debris. Example 3: High-risk failure during the space-air transition phase, resulting in overall separation and landing scenario.

[0025] During the space-to-space transition phase of the spacecraft, the main thruster experienced a high-risk malfunction involving propellant leakage and localized thermal deformation. The telemetry and control system simultaneously triggered a combined active and passive emergency mechanism. The system prioritized unlocking the overall locking structure of the crew / cargo capsule, which then instantly activated its self-sustaining propulsion system, using its overall power to push the malfunctioning thruster away, maintaining the capsule's integrity throughout the entire process. At a suborbital altitude of 150km, the crew / cargo capsule relied entirely on its own power to achieve orbital attitude stabilization, controlled and slow descent, reentry thermal protection, and attitude correction. After a smooth transition to an atmospheric altitude of 150m, it used its own power to decelerate and stabilize its attitude, coordinating with a buffer structure to achieve a precise soft landing. Ultimately, the crew / cargo capsule landed intact and smoothly, while the malfunctioning thruster independently fell and was destroyed, achieving autonomous hazard avoidance and a zero-damage return during the space-to-space transition phase.

Claims

1. A method for dual-mode active and passive retreat and safe landing of an aircraft cabin and propulsion system, characterized in that, This method is applied to modular aircraft and modular spacecraft. The modular spacecraft includes a crew / cargo cabin, a detachable main thruster assembly, an integrated telemetry and control system, and a multi-dimensional space-adaptive safe landing system. The crew / cargo cabin is an integral, non-separable structure with a built-in independent self-sustaining power system, completely decoupled from the main thruster assembly. It is modularly docked with the main thruster assembly via an integral electromagnetic locking + mechanical snap-fit ​​composite connection structure. The method includes an active prediction process for overall power disengagement, a passive fault instantaneous overall power disengagement process, and a space-adaptive power safe landing process. The proactive prediction and withdrawal process includes: The S100 integrated measurement and control system collects nine operating parameters of the main thruster group in real time, including rotational speed, power output, structural stress, temperature, attitude deviation, oil circuit status, orbital angular velocity, propellant pressure, and vacuum sealing status. It also identifies potential fault hazards of the main thruster through a built-in dual-condition fault prediction algorithm for space and air. S200: When it is determined that the thruster has a minor fault, potential performance degradation, and the aircraft can maintain a stable attitude for a short period of time, the power, oil, and signal linkage between the thruster and the crew / cargo cabin shall be cut off. S300: According to different operating modes, it uniformly performs the overall withdrawal action of the manned / cargo cabin, realizing the synchronous separation of the manned / cargo cabin and the thruster. During the S400's retreat, the self-sustaining power system of the manned / cargo cabin is activated instantaneously. Through vector power, the cabin's attitude is corrected in real time, actively increasing the safe distance from the malfunctioning main thruster. Relying on its own power, the cabin glides smoothly, achieving a controllable retreat without overturning or deviation. The passive fault recovery process includes: S500: When a severe irreversible failure such as sudden breakage of the thruster, sudden power stoppage, uncontrolled dive, fire and explosion is detected, or when the system failure is actively predicted, a passive forced disengagement mechanism is triggered. S600: Simultaneously disconnect all linkage links, unlock the overall electromagnetic lock and mechanical latch of the manned / cargo cabin, instantly start the self-sustaining power system of the manned / cargo cabin at full speed, and break through the limit with the micro ejection mechanism. Use its own power to push away the faulty main thruster in the opposite direction, and achieve millisecond-level forced power separation of the entire manned / cargo cabin. S700 maintains the attitude and structural integrity of the crew / cargo compartment during the overall disengagement process, avoiding collisions and interference from debris. The space-adaptive dynamic safe return process includes: After the S800 and the cabin separate, the space safety reentry system is activated independently to collect atmospheric altitude, descent speed, wind speed, cabin attitude, orbital altitude, and reentry speed parameters in real time, determine the current space operation condition type, and match the corresponding reentry strategy. In high-altitude scenarios with an altitude of ≥100m, the S900 adaptively selects between a powered parachute hybrid mode or a pure parachute mode. Relying on self-sustaining power and the parachute to stabilize attitude and decelerate, it precisely controls the descent speed and activates the inflatable airbag near the ground to complete a soft landing. S1000, low-altitude operation, and low-Earth orbit separation operation: Parachutes are prohibited in low-altitude scenarios with an altitude of <100m. Pure self-sustaining power is used for reverse braking and stabilization, and buffer airbags are used for smooth landing. In the near-Earth orbit separation operation, the entire process relies on self-sustaining power to complete orbit descent, attitude control, and re-entry correction. After entering the atmosphere, parachutes are used as needed to assist in deceleration, achieving multi-mode selectable controllable aerospace return. S1100 automatically triggers fault alarms and location reports upon landing, activating the manned / cargo cabin landing protection mode to ensure the overall integrity of the cabin.

2. The method according to claim 1, characterized in that, The manned / cargo cabin is an integral, non-separable structure. The cabin has an independent, self-sustaining vector power system, equipped with a dedicated attitude control unit, landing buffer unit, and power supply unit. It is completely physically, control, and power decoupled from the main propulsion group of the aircraft, and can independently complete attitude stabilization, gliding, deceleration, and fixed-point landing without any separation or disassembly.

3. The method according to claim 1, characterized in that, The fault prediction algorithm has a built-in three-level fault threshold, corresponding to three working conditions: slight performance degradation, moderate fault potential, and severe irreversible fault. It accurately matches three response modes: early warning standby, active prediction retreat, and passive forced departure, avoiding false triggering and missed triggering.

4. The method according to claim 1, characterized in that, The multi-dimensional aerospace adaptive safe landing system includes a multi-stage parachute assembly, an adaptive inflatable buffer airbag, a micro recoil braking unit, attitude correction control surfaces, a space micro-jet attitude control unit, and a reentry thermal protection structure. It can dynamically adjust its working state according to real-time environmental parameters of aviation atmosphere, space vacuum, and suborbital reentry, and adapt to all aerospace fault landing scenarios.

5. The method according to claim 1, characterized in that, The passive separation of the cabin adopts the logic of "power priority start, mechanical synchronous unlock". The self-sustaining power system has a higher response priority than all mechanical actuators. This ensures that in the instant the main thruster is damaged and out of control, the starting force is activated first and then the connection is broken. The reverse force is used to offset the impact of the failure, completely avoiding the risks of jamming, collision and rollover. This ensures smooth separation and controllable landing under various working conditions such as aviation atmosphere, space on-orbit and suborbital transition.

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