A manned, detachable emergency rescue eVTOL aircraft

Abstract

This invention discloses a manned detachable emergency rescue eVTOL aircraft, belonging to the field of low-altitude safety and rescue technology for electric vertical take-off and landing (eVTOL) aircraft. The entire aircraft consists of a jettisonable flight power module and an independent manned rescue capsule, connected by a dual-redundant quick-locking mechanism. Under normal conditions, it operates as a single unit; in emergency situations, it quickly unlocks and separates, discarding the flight module, with only the manned rescue capsule relying on a two-stage parachute for a stable low-altitude descent and rescue. This invention overcomes the limitations of narrowly defined flying cars, is compatible with all types of manned eVTOL aircraft, and has no fixed parameters such as rotor configuration, number, parachute deployment altitude, or weight. It offers broad protection, high redundancy reliability, and strong civilian adaptability, solving the industry pain point of existing integrated low-altitude manned aircraft lacking reliable escape methods in case of failure.

Description

Technical Field

[0001] This invention belongs to the field of low-altitude safety and rescue technology for electric vertical take-off and landing (eVTOL) aircraft, specifically relating to an emergency rescue device for manned eVTOL aircraft that enables rapid separation of the flight power module from the manned rescue capsule and independent parachute escape. Background Technology

[0002] Existing manned eVTOL aircraft generally adopt an integrated rigid structure, with the wings, multi-rotor power system, frame, battery pack and manned cockpit being rigidly connected as one unit, without setting up an independent emergency separation and escape structure for the crew.

[0003] The structure has a fatal safety shortcoming: when the aircraft experiences a power outage, rotor failure, attitude loss, structural damage, battery failure or other emergencies in the air, the occupants have no independent passive escape route and can only fall with the whole aircraft; in the normal low-altitude urban operating environment, there are no reliable emergency landing conditions, and the risk of casualties is extremely high.

[0004] In existing rescue solutions, large aircraft mostly use whole-aircraft parachute emergency landing, which has a large overall load and poor low-altitude response, and is only suitable for high-altitude scenarios; some split-type aircraft can only support ground disassembly and maintenance, and do not have the ability to unlock in the air or actively jettison flight modules; military ejection cockpits have complex structures, large overload, and high costs, and cannot be adapted to civilian low-altitude, low-speed manned scenarios.

[0005] To address the pain points of existing technologies, this invention adopts a brand-new safety architecture: during normal flight, the flight power module and the manned escape capsule are rigidly locked together; in emergency situations, the two modules can be quickly unlocked and separated, actively jettisoning unnecessary loads such as wings, rotors, frames, and power batteries, leaving only the manned escape capsule to independently deploy parachutes for a stable landing, thus fundamentally solving the industry gap of having no reliable rescue means in low-altitude failures of manned eVTOL aircraft. Summary of the Invention

[0006] Purpose of the invention Overcoming the shortcomings of existing integrated manned eVTOL systems, such as lack of independent crew rescue and insufficient redundancy in low-altitude emergency response, this invention provides a detachable emergency rescue device that is structurally reliable, responds quickly, is highly versatile, and adaptable to civilian low-altitude scenarios. In extreme situations such as aircraft loss of control or malfunction, the device can maximize crew safety by jettisoning the flight module and retaining the crew cabin for independent parachute descent. Technical solution

[0007] A manned separable emergency rescue eVTOL aircraft is divided into two independent functional units: a jettisonable flight power module and an independent manned rescue capsule. The two units are equipped with a dual-redundant quick-locking separation mechanism to achieve rigid connection and controllable separation. The jettisonable flight propulsion module includes a fixed wing, a multi-rotor lift propulsion unit, a main flight controller, a main power battery pack, a frame, and a cruise aerodynamic structure. The independent manned rescue capsule includes a sealed crew cabin, an independent emergency controller, a backup emergency power supply, a two-stage parachute rescue system, attitude stabilizing wing surfaces, and a landing cushioning structure. The dual-redundant rapid locking and separation mechanism is fixedly connected to the bottom of the flight power module and the top of the manned escape capsule at its upper and lower ends, respectively, with the docking interface coinciding with the center of gravity axis of the entire aircraft. Under normal flight conditions, the mechanism remains rigidly locked, and the two modules integrate to complete vertical take-off and landing and cruise flight. In the event of an emergency failure, the independent emergency controller issues an unlocking command, and the locking mechanism quickly completes interference-free unlocking and separation. The flight power module detaches and falls on its own, and the manned escape capsule falls stably and automatically deploys the parachute system to achieve a safe landing.

[0008] Furthermore, the multi-rotor lift generator is located in the wing area and only provides lift for vertical takeoff and landing and hovering. During level flight and cruise, the rotor stops working, and the aircraft relies on the aerodynamic lift of the fixed wing to maintain its cruise attitude and trajectory.

[0009] Furthermore, the dual-redundant rapid locking and separation mechanism adopts a dual-redundant configuration of electromagnetic active lock + mechanical emergency lock, supporting three working modes: automatic triggering by the main flight control, manual forced triggering by the crew, and automatic unlocking after power failure; the separation process is free from interference from cables, pipelines, and structural components, ensuring safe and reliable separation action.

[0010] Furthermore, the parachute rescue system adopts a two-stage deployment configuration, which is integrated and arranged at the center of gravity of the top of the manned rescue capsule. After separation, the deceleration and stabilization parachute first deploys to correct the attitude and reduce the descent speed, and then the main load-bearing parachute opens to descend smoothly and slowly, which is suitable for use at civilian low-altitude conventional emergency operating altitudes.

[0011] Furthermore, the independent emergency controller is physically and electrically completely isolated from the main flight controller, and is independently powered by a dedicated backup emergency power supply. It is unaffected by power outages, loss of control, or structural damage to the flight power module, and can still stably execute unlocking and parachute deployment control logic under extreme conditions.

[0012] Furthermore, the manned rescue capsule is equipped with attitude stabilizing wing surfaces on its outer periphery, which automatically suppress the capsule's tumbling and spinning during the separation and descent process, maintain a stable vertical descent attitude, and provide stable flow field conditions for the normal deployment of the parachute. Beneficial effects

[0013] 1. Unique core architecture: Breaking away from the inertia of integrated design, it establishes a core life-saving logic of "sacrificing the flight module and preserving the manned cabin", which fundamentally solves the fatal shortcoming of existing eVTOLs that have no escape route in the air during failure.

[0014] 2. Extremely wide range of applications: Breaking through the limitations of the narrow concept of flying cars, it fully covers civilian manned eVTOL, compound wing aircraft, and low-altitude manned aircraft, and the categories of patent protection have been greatly expanded.

[0015] 3. No rigid parameter lock-in: There are no restrictions on the number of rotors, layout, propeller structure, tilting mechanism, or tail thruster structure. The parachute opening height and overall weight range are not fixed, so others cannot circumvent patent protection by making minor parameter modifications.

[0016] 4. High redundancy and high reliability: Dual redundancy locking mechanism, triple triggering mode, and independent emergency power supply control system eliminate single point of failure risk and can stably adapt to complex low-altitude operating environments in civilian applications.

[0017] 5. High versatility and easy to implement: The structure is simple and there are no complex catapults, rocket thrusters or other high overload mechanisms. It can be directly adapted to various existing compound wing and multi-rotor eVTOL models for retrofitting and application, and the cost of civilian use is low. Detailed Implementation

[0018] This embodiment is a civil manned compound wing eVTOL aircraft, which consists of a jettisonable flight propulsion module and an independent manned escape capsule. The flight propulsion module includes a fixed wing, a multi-rotor lift propulsion unit, a main flight control system, a main power battery pack, and a carbon fiber frame. The manned escape capsule includes a sealed cockpit, an independent emergency controller, a backup emergency power supply, a two-stage parachute system, attitude stabilizing wing surfaces, and a bottom buffer structure.

[0019] The dual-redundant locking mechanism is located on the center of gravity axis of the aircraft. Under normal conditions, the electromagnetic lock and the mechanical lock are doubly locked, and the whole aircraft can complete vertical take-off and landing, hovering and fixed-wing level flight cruise in one unit. During cruise, the rotor stops working and the aircraft relies solely on the aerodynamic lift of the wing to maintain flight.

[0020] When the system detects fatal malfunctions such as rotor failure, power interruption, attitude loss, or abnormal descent rate, or when the crew manually triggers the system or the main system unexpectedly loses power, the independent emergency controller immediately initiates the emergency procedure and quickly unlocks the locking mechanism. After the flight power module and the manned escape capsule separate without interference, the flight module falls autonomously, and the manned escape capsule maintains its attitude through the stabilizing wing surface, sequentially deploys the drag chute and main parachute, descends smoothly and gently, and completes a safe landing through the bottom buffer structure.

Claims

1. A manned detachable emergency life-saving (eVTOL) aircraft, characterized in that, It includes a physically and electrically independent jettisonable flight propulsion module, an independent manned escape capsule, and a dual-redundant quick-locking and separation mechanism connecting the two modules; The jettisonable flight propulsion module includes a fixed wing, a multi-rotor lift propulsion unit, a main flight controller, a main power battery pack, and the entire airframe. The independent manned rescue capsule includes a crew cabin, an independent emergency controller, a backup emergency power supply, a two-stage parachute rescue system, attitude stabilizing wing surfaces, and a landing cushioning structure. Under normal conditions, the dual-redundant rapid locking and separation mechanism rigidly locks the flight power module and the independent manned rescue capsule into a single unit. In an emergency, it receives instructions from the independent emergency controller, quickly and without interference unlocks and separates the flight power module, allowing it to fall autonomously. The independent manned rescue capsule then falls independently and automatically activates the parachute rescue system, enabling the occupants to land safely and gently.

2. The manned detachable emergency rescue eVTOL aircraft according to claim 1, characterized in that, The multi-rotor lift generator is located in the wing area and only provides lift for vertical takeoff and landing and hovering. During level flight and cruise, the rotor stops working and the aircraft relies on the aerodynamic lift of the fixed wing to maintain cruise flight.

3. The manned detachable emergency life-saving eVTOL aircraft of claim 1, wherein, The dual-redundant rapid locking and separation mechanism adopts a dual-redundant structure of electromagnetic active lock and mechanical emergency lock, and has three triggering modes: automatic triggering by the main flight control, manual forced triggering by the crew, and automatic unlocking after power failure.

4. The manned detachable emergency rescue eVTOL aircraft according to claim 1, characterized in that, The two-stage parachute rescue system is located at the center of gravity of the top of the manned rescue capsule. It deploys the deceleration and stabilization parachute and the main load-bearing parachute in sequence, and is suitable for use in civilian low-altitude conventional emergency conditions.

5. The manned detachable emergency life-saving eVTOL aircraft of claim 1, wherein, The independent emergency controller is completely physically and electrically isolated from the main flight controller and is powered by an independent backup emergency power supply, so it is not affected by flight power module failure, power outage, or loss of control.

6. The manned detachable emergency life-saving eVTOL aircraft of claim 1, wherein, The independent manned rescue capsule is equipped with attitude stabilizing wing surfaces to suppress the capsule's roll and spin during separation and descent, thus maintaining a stable descent attitude.