580results about "Parachutes" patented technology

The invention discloses an ejection device, a control method of the ejection device and electric mobile equipment, and the ejection device comprises a guide structure which is connected to a body; the ejected body is contained in the guide structure and is connected to the body in a releasable manner through a fastener; the parachute is accommodated in the guide structure in a foldable manner and is connected with the ejected body; the gas generator is mounted on the outer wall of the guide structure; wherein the fastener releases the catapulted body when responding to ignition current to be broken, and the gas generator inflates the parachute when responding to the ignition current, so that the parachute is converted into an unfolded state from a folded state, and the catapulted body is driven to fall. The dangerous source or the unit needing to be protected serves as the ejected body to be ejected from the body, damage to the body caused by fire of the dangerous source is effectively reduced, the safety of passengers is greatly improved, and an efficient and practical safety solution is provided for various scenes related to flight safety and equipment protection.

The utility model relates to a model airplane brake parachute mechanism which comprises a brake parachute cabin body, a brake parachute pack, a parachute pack ejection device, a parachute pack cover plate, an unlocking assembly and a steering engine, the brake parachute cabin body is provided with a parachute pack groove for containing the brake parachute pack, the parachute pack ejection device is arranged at the groove bottom of the parachute pack groove, the brake parachute pack is placed on the parachute pack ejection device, and the steering engine is arranged on the brake parachute cabin body. The parachute pack ejection device provides thrust to abut the deceleration parachute pack against the parachute pack cover plate, the parachute pack cover plate capable of opening or closing the parachute pack groove is arranged at an opening of the parachute pack groove, the unlocking assembly is arranged on the deceleration parachute cabin and connected with the parachute pack cover plate in a matched mode, and the steering engine is arranged on the deceleration parachute cabin and connected with the parachute pack cover plate in a matched mode. The steering engine can control the rocker arm to push the unlocking assembly to leave the parachute pack cover plate, so that the parachute pack cover plate opens the parachute pack groove.

The invention belongs to the technical field of aircraft recovery, and provides an aircraft controllable parachute recovery device which comprises a parachute opening motor (1), a motor support (2), a motor rocker arm (3), a connecting rod (4), a recovery parachute cabin (5), a parachute cabin cover (6), a parachute cabin locking block torsional spring (9), a locking block rotating shaft (10), a driving rod (11), an unlocking hook (12), a spring guide rod (13), an initial locking rod (14), a parachute opening shaft (21), a parachute opening compression spring (18), a parachute hanging screw (17), a recovery parachute (19), a tower spring (20) and a tower spring pressing plate (15). According to the technical scheme, the motor drives the connecting rod mechanism to unlock, the tower spring and the pressure spring are combined to open the parachute, and the problems that an initiating explosive device is low in safety, poor in testability, unrepeatable in recovery and the like are solved.

The invention discloses a reusable anti-unmanned aerial vehicle aircraft based on rotary cutting steel blades, and belongs to the technical field of unmanned aerial vehicle countering. The aircraft comprises a seeker cabin, a function cabin, an instrument cabin, a power cabin, a steering engine cabin and a parachute pack cabin. An infrared seeker is arranged in the seeker cabin; the functional cabin comprises a fixed cabin body, a rotating cabin body and a folding and unfolding mechanism, a fixed shaft is arranged at the axis position of the fixed cabin body, N folding steel blades are installed on the rotating cabin body and evenly distributed in the circumferential direction, and the folding and unfolding mechanism drives the folding steel blades to complete unfolding and folding actions. The folding and unfolding mechanism simultaneously drives the rotary cabin to rotate around the axis of the aircraft; a main power supply, an airborne computer, a data chain and an inertial navigation device are arranged in the instrument cabin, and the power cabin provides patrol flight power for the aircraft; a steering engine for controlling the rudder wings to rotate is arranged in the cabin, and a pressurizing device for pressurizing the parachute pack cabin is arranged in the parachute pack cabin. The anti-unmanned aerial vehicle aircraft can be repeatedly used, and the combat time of the aircraft is prolonged to the maximum extent.

The invention discloses an anti-unmanned aerial vehicle aircraft based on folding steel blade rotary cutting, and belongs to the technical field of unmanned aerial vehicle countering. The aircraft comprises a seeker cabin, a function cabin, an instrument cabin, a power cabin, a steering engine cabin and a parachute pack cabin. An infrared seeker is arranged in the seeker cabin; the functional cabin can independently rotate relative to the front cabin section and the rear cabin section under the driving of the motor and release the folding steel blade mounted on the surface of the functional cabin in a folding manner, and the motor drives the functional cabin to rotate at a high speed and drives the folding steel blade to rotate, so that rotary cutting of the target unmanned aerial vehicle is realized; a main power supply, an airborne computer, a data chain and an inertial navigation device are arranged in the instrument cabin, and the power cabin provides patrol flight power for the aircraft; a steering engine for controlling the rudder wings to rotate is arranged in the cabin, and a pressurizing device for pressurizing the parachute pack cabin is arranged in the parachute pack cabin. The anti-unmanned aerial vehicle aircraft is few in component parts, high in reliability, low in cost and high in cost-effectiveness ratio.

The invention discloses a parachute control method and system, and belongs to the field of parachutes, and the parachute control method comprises the following steps: obtaining a map, obstacles, a people flow thermodynamic diagram and wind speed data of a launching area in real time; a low-power-consumption NPU is adopted to operate a lightweight model to recognize obstacles, a reinforcement learning algorithm is combined to predict a crowd movement track, and a putting point is determined; the height, the speed and the material weight of the unmanned aerial vehicle are fused, the optimal parachute opening point of the parachute is calculated, the landing-prohibited area is avoided, and the trajectory of landing to the throwing point is optimized; compared with the prior art, the method has the beneficial effects that after communication is interrupted, the impact acceleration threshold at the grounding moment is set, whether the unmanned aerial vehicle is grounded or not is judged in combination with barometer height change dual verification, and after acceleration and height dual verification is passed, main umbrella connection is directly cut off; the main umbrella can be controlled to be separated without receiving verification of a ground station, and loss caused by non-separation of the main umbrella due to communication interruption is avoided.

An apparatus, including a personal monitoring device and a drone. The personal monitoring device monitors a movement of the individual and detects a deviation from an expected position or location, or detects a deviation from an expected travel route, by the individual, generates a message containing information regarding when the individual deviated from the expected position or location or deviated from the expected travel route, and transmits the message or information contained in the message to the drone. An operation of the drone is activated, the drone travels to the position or location of the personal monitoring device, records video information or video and audio information, and transmits the video information or the video and audio information to a user communication device or to a central processing computer.

The invention relates to an unmanned aerial vehicle for survey based on artificial intelligence in the field of survey equipment, and the unmanned aerial vehicle comprises a survey unmanned aerial vehicle, the survey unmanned aerial vehicle carries a magnetic sheet, an electromagnetic block, a compression spring, a data storage unit and a parachute module, the data storage unit is used for temporarily storing survey data, and when the unmanned aerial vehicle is out of control in the survey process, the data storage unit is used for storing the survey data; through cooperation of a magnetic piece, an electromagnetic block and a compression spring, the storage shell and the parachute module are ejected together, parachute cloth of the parachute module is rapidly unfolded under the action of air resistance, the falling speed of the storage shell is reduced, and then the storage is protected and is not prone to being damaged under landing impact; and after the unmanned aerial vehicle is out of control in the surveying process, a worker can export surveying data before surveying the unmanned aerial vehicle is out of control after recovering the storage shell and the memory, so that the worker is assisted in querying reasons for surveying the accident of the unmanned aerial vehicle, and the influence of surveying progress is reduced.

An ejection seat includes an ejection seat sequencing system. The sequencing system enables time delays to various components of the system, such the drogue parachute, the main parachute, and harness release cartridge. A sequence controller receives data for a parameter, such as airspeed, from at least two sensors. The sequence controller selects a sequence timing delay mode to implement the time delays for the components of the sequencing system. The sequence controller also accesses a lookup table in a database accessible by the sequence controller. The sequence controller uses a delay parameter of the lookup table to modify a time delay within the sequence timing delay mode, as configured by a user.

The invention relates to a multi-sensor fusion and dual-mode control unmanned aerial vehicle parachute ejection system and method, and belongs to the technical field of unmanned aerial vehicle safety. Comprising a sensor module used for collecting acceleration, angular velocity and barometric altitude data of the unmanned aerial vehicle in real time; the control module is used for performing fusion processing on the data acquired by the sensor module based on an extended Kalman filtering algorithm so as to determine the state of the unmanned aerial vehicle, and outputting a parachute opening instruction based on parachute opening decision logic; the parachute opening decision logic comprises air crash detection, manual parachute opening instruction response and normal landing detection; and the execution module responds to the parachute opening instruction and controls the ignition head to trigger the ejection parachute to be opened. The problem that the safety application of the unmanned aerial vehicle is restricted due to insufficient reliability, poor complex environment adaptability and lack of full-flight-cycle safety protection in the prior art is solved.

A system and method are disclosed for softly capturing, protecting, and landing a spacecraft returning from space using a VTOL (vertical takeoff and landing) aircraft including drones and helicopters. The spacecraft is decelerated by a parachute. One or more VTOL drones transport a waterproof pocket that catches and captures the descending spacecraft in the air. In this way, the spacecraft is protected inside the pocket and, after continuing to descend, makes a soft landing in a body of water. In another embodiment, a recovery helicopter, which is a type of VTOL aircraft with heavy-lift capabilities, is used to directly catch the returning spacecraft. One or more VTOL drones are attached to the lower end of a recovery cable suspended from the helicopter. These drones carry a clutch that directly, quickly, and accurately catches the descending spacecraft without interfering with the parachute. In this way, the spacecraft is caught and protected by the helicopter while maintaining the floating function of the parachute.

An electric vertical take-off and landing (eVTOL) aircraft can enhance energy efficiency, safety, and operational range. A deployable wing structure can provide aerodynamic lift during horizontal flight, reducing reliance on energy-intensive propellers. Integrated flexible solar panels capture solar energy, contributing additional power and optimizing energy management. The wing system also includes an emergency descent mode, doubling as a glide-assist device for controlled landings during critical failures. The system offers modular configurations for various missions, ensuring adaptability and improved flight performance. The eVTOL can be implemented with systems and methods for mitigating motion sickness. The systems integrate tactile feedback systems into wearable devices and environmental components. Sensors detect motion and environmental changes, and a computing device can generate corresponding tactile feedback signals. Tactile actuators embedded in the devices or components provide non-visual motion cues, such as pressure, vibration, and haptic feedback, to resolve sensory mismatches between the vestibular and proprioceptive systems.

The invention relates to a method for determining a theoretical deflection angle of a single umbrella in a group umbrella system, which comprises the following steps of: calculating and analyzing the theoretical deflection angle of the axis of the single umbrella relative to the central line of a group umbrella bundle in the group umbrella system consisting of circumferentially and uniformly distributed and adjacently tangent single umbrellas according to a primary design principle of maximizing the resistance performance and the stability performance of the group umbrella system; the method can quantitatively reflect the influence of the number of umbrellas in the group umbrella system and the related design parameters of the single umbrellas on the theoretical deflection angle of the single umbrellas and the comprehensive performance of the system, and can preliminarily lay foundation for formation and gradual improvement of the theoretical design method of the group umbrella system.

The invention discloses a high-temperature-resistant coating for an unmanned aerial vehicle and the unmanned aerial vehicle, and relates to the technical field of unmanned aerial vehicles, the high-temperature-resistant coating comprises a bottom layer, a middle layer and a top layer, the bottom layer comprises a modified polyimide resin and nanometer aluminum oxide compound, and the middle layer comprises hollow ceramic microbeads, boron nitride nanosheets and a phosphate binder; and the top layer comprises a silicon carbide composite ceramic sol layer. According to the invention, the multi-stage thermal barrier layer is constructed to prevent body parts, components and a flight control system of the unmanned aerial vehicle from losing efficacy in a high-temperature environment, so that the unmanned aerial vehicle is ensured to work stably and reliably in the high-temperature environment; a protection structure is arranged, so that the unmanned aerial vehicle body is protected through a parachute when the unmanned aerial vehicle is powered off or other sudden faults occur, and the unmanned aerial vehicle body is prevented from being damaged by high-altitude direct falling; and a release structure is arranged to release transported articles such as fire extinguishing agents, so that the overall weight of the unmanned aerial vehicle is reduced, and the damage to the unmanned aerial vehicle when the unmanned aerial vehicle falls due to overweight is effectively reduced.

The invention relates to a method for intercepting a flying object through aerial high-speed net casting, which is used for solving the technical problem of low interception success rate caused by insufficient maneuverability of an interception means and lack of enough large and reliable interception area when approaching a target in the prior art, and comprises the following steps: controlling an unmanned aerial vehicle to fly to approach the target; an unlocking signal is sent to a locking mechanism arranged on the machine main body, so that the locking mechanism synchronously releases all the power systems; the released power system flies away by means of self-rotation inertia, and the catching net connected with the power system is pulled by the pulling rope, so that the catching net is unfolded to form an intercepting area in the flying-away process. The unmanned aerial vehicle keeps flying at a high speed in the pursuit stage, the unmanned aerial vehicle flies away through inertia of a plurality of power systems in the interception stage, the capture net is unfolded to form an interception area larger than the projection area of the vehicle body, and compared with a traditional interception method, the interception method has the higher interception speed and the higher interception success rate.

The utility model discloses an automatic point explosion type parachute device which comprises a parachute bag, a parachute box, an explosion-proof device and a control device, wherein the parachute bag is internally provided with a parachute; the ignition module is arranged in the parachute bag and is used for quickly unfolding a parachute in the parachute bag; the sensor module is arranged in the parachute bag and is used for detecting the state change of the parachute bag in real time; and the microcontroller is arranged in the parachute bag, is respectively connected with the explosion module and the sensor module, and is used for receiving the sensing data acquired by the sensor module and judging whether an explosion signal is generated or not according to the sensing data and is sent to the explosion module. According to the utility model, the opening time of the traditional parachute is greatly shortened, and the convenience and safety of use are improved.

The invention relates to the technical field of unmanned aerial vehicles, in particular to a parachute protection device suitable for an electric power inspection unmanned aerial vehicle, which comprises an unmanned aerial vehicle main body and further comprises a bottom bracket fixed at the bottom of the unmanned aerial vehicle main body; the protection box is fixed to the top of the unmanned aerial vehicle body; the parachute is arranged in the protection box; the ejection assembly is installed in the protection box and used for being triggered and started when the unmanned aerial vehicle body falls so as to eject the parachute; the protection assembly is mounted on the protection box and used for protecting the unmanned aerial vehicle body and the protection box during falling; according to the device, the protection box can be protected through the protection assembly, and therefore the situation that in the landing process of the unmanned aerial vehicle body, the unmanned aerial vehicle body touches the ground first, and consequently internal parts are still impacted and damaged is avoided.

The invention discloses an unmanned aerial vehicle parachute throwing device, and belongs to the technical field of unmanned aerial vehicle equipment. Comprising a fault detection module, a trigger control module, a dual-power release module, a parachute storage module, a flight control cooperation module and a parachute ejection mechanism which are installed in an unmanned aerial vehicle body. A fault judgment algorithm is built in the trigger control module; the parachute ejection mechanism comprises an ejection shaft, the lower end of the ejection shaft is connected with a force storage assembly, the ejection shaft is sleeved with a limiting protruding ring, and a limiting column is arranged on one side of the limiting protruding ring and matched with the motor driving unit. The three-axis acceleration sensor, the air pressure sensor, the motor rotating speed sensor and the current sensor are integrated, a synchronous acquisition and automatic switching mechanism of the main sensor and the standby sensor is matched, acquisition interruption caused by faults of a single sensor is avoided, and data acquisition continuity is high. Instantaneous impact force is provided through compressed gas driving, the push rod is driven to be accurately unlocked through gear transmission, and the problems that traditional single power thrust is insufficient and release is slow are solved in cooperation with the double-spring force storage assembly.

The invention discloses a turbojet power logistics unmanned aerial vehicle based on a fixed wing structure and a control method. The unmanned aerial vehicle comprises a carbon tube fuselage, cork wood wings, a full-motion horizontal empennage, double vertical empennages, a nose fairing, a storage bin, a turbojet engine, an undercarriage, a flight control system and an emergency parachute. According to the turbojet power logistics unmanned aerial vehicle based on the fixed wing structure and the control method, the fixed wing structure and the turbojet engine are organically combined, short-distance take-off within 50 meters can be achieved, compared with a traditional propeller type fixed wing unmanned aerial vehicle, the take-off distance is shortened by 40% or above, the cruising speed can reach 80 km / h-120 km / h, the unmanned aerial vehicle can be matched with a standard material box of 200 mm * 200 mm * 400 mm, and the unmanned aerial vehicle is suitable for large-scale popularization and application. The flight control system supports two modes of manual remote control and automatic driving, and is equipped with an emergency parachute, so that safe parachute recovery of the unmanned aerial vehicle in an emergency state is realized, and the problem that a traditional unmanned aerial vehicle has obvious limitation when meeting emergency material delivery requirements is effectively solved.

An electronic drogue reefing release system includes a drogue parachute having a canopy, one or more reefing lines coupled to the canopy, one or more reefing line cutters coupled to the canopy, and one or more signal lines configured to deliver an electrical signal. The reefing lines are configured to restrict expansion of the canopy while in a first reefing state. The reefing line cutters are configured to place the at least one reefing line into a second reefing state in response to receiving the electrical signal so as to expand the canopy.

The invention pertains to an autonomous aerial vehicle capable of vertical takeoff and equipped with a parafoil wing, which is used in various fields such as military, civil, agricultural, surveillance, and exploration in the aviation sector. The invention particularly concerns an autonomous aerial vehicle with a parafoil wing, where the entire parafoil wing is folded and stored inside a compartment, and vertical takeoff is achieved with its multiple motor structure; subsequently transitioning to efficient flight by deploying the parafoil wing in the air.

To provide an actuator, a safety device, and a flying body equipped with the safety device in which a moving speed or altitude of a moving body launched during operation is improved compared with conventional techniques.SOLUTION: A safety device 100 includes: a moving body 40 launched in one direction by an actuator 1; an expansion object body 16 that is pulled by the launched moving body 40; and a bottomed cylindrical container 18 that houses the actuator 1, the moving body 40, and the expansion object body 16. The moving body 40 includes: a cylindrical portion 41 that is a bottomed cylindrical member and is disposed so as to cover an outer portion of an upper end of a cylinder 14; a reduction part 42 that is formed in a shape that gradually decreases in size in a reverse direction from a connection portion with the cylindrical portion 41; a hole 43 that is formed inside the cylindrical portion 41; a hole 44 that is formed at a central portion of a bottom portion of the hole 43; and a pair of through holes 46, 47 for connecting cables to which one end of each connecting cable connected to the expansion object body 16 is connected. A gap 80 is formed between the hole 43 and the upper end of the cylinder 14.SELECTED DRAWING: Figure 1

An aerial vehicle includes a communication apparatus, a receiver that obtains a current position, a flight controller that controls flight and can transmit information on the current position with the communication apparatus, a plurality of drive apparatuses that drive respective different ones of a plurality of propulsive mechanisms, a distributor that distributes supplied electric power to each of the plurality of drive apparatuses, a power supply module that supplies electric power from a battery to the communication apparatus, the receiver, and the flight controller through a first power path and supplies electric power to the distributor through a second power path, and a disconnection apparatus that cuts off supply of electric power from the power supply module to the distributor through the second power path when abnormality occurs.

The unmanned aerial vehicle recovery system comprises an unmanned aerial vehicle, and a main control system, a sensor system and a power supply system used for supplying power to the unmanned aerial vehicle are fixedly installed in the unmanned aerial vehicle; the power system comprises a main power supply and an emergency power supply; an airbag component is arranged at the bottom of the body of the unmanned aerial vehicle; a lift assembly is arranged on the top of the unmanned aerial vehicle body. Multiple parachute assemblies are symmetrically arranged on the two sides of a fuselage of the unmanned aerial vehicle. The sensor system monitors operation parameters of the unmanned aerial vehicle and feeds back the operation parameters to the master control system. The master control system receives signals of the sensor system and controls operation of the airbag assembly, the lift assembly and the parachute assembly. The technical problem that an existing unmanned aerial vehicle recycling system cannot meet the high-low-altitude recycling requirement is solved, and the technical effect of being suitable for high-altitude recycling and low-altitude recycling at the same time is achieved.

The utility model discloses a stable self-adaptive meteorological balloon recovery device, which comprises a detection device main body and a positioning assembly, the outer wall of the top of the detection device main body is provided with a storage groove, and the positioning assembly used for preventing the detection device main body from moving is installed in the storage groove. The positioning assembly comprises a baffle, a spiral drill bit, a small motor, a movable plate and sliding groove columns, the spiral drill bit is arranged in the middle of the baffle, the small motor is installed at the top of the spiral drill bit, the movable plate is fixedly installed at the bottom of the small motor, and the sliding groove columns are formed in the two ends of the movable plate; a shaft rod is arranged at the end, close to the detection device body, of the baffle, and the outer wall of the shaft rod is sleeved with a strong torsional spring. The stable self-adaptive meteorological balloon recovery device not only can prevent the device from being moved by external force after landing, but also can reduce the impact force on internal parts after the detection device body lands.

A lighter-than-air airship has an exoskeleton constructed of spokes and hubs to create a set of connected hexagrams comprised of isosceles triangles wherein the spokes flex and vary in length to produce the slope of said airship's surface. In one embodiment, the exoskeleton connects to a nose cone that includes a cockpit cabin for controlling the airship's operation from a single location that can be physically separated from the exoskeleton in response to catastrophic events and for autonomous and / or remotely piloted operation. An improved means is also provided for landing and unloading cargo, and through use of unmanned aerial vehicles in another embodiment, the airship is configured for remote pickup, transport, delivery and return of payloads such as packages. In yet another embodiment, the airship provides a communications platform for beam form transmission and satellite signal relay, including in combination with the foregoing disclosed attributes.

According to the device and method for distributing the traditional Chinese medicine potions through the unmanned aerial vehicle, safe and efficient distribution of the traditional Chinese medicine potions is achieved. The device comprises a safe parachute, a quad-rotor unmanned aerial vehicle, an electronic range finder, a voice prompt system, a high-strength fiber rope, an automatic detacher, a distribution bag, a traditional Chinese medicine liquid packaging bottle and a receiving support. The safety parachute can be automatically opened in emergency to guarantee safe landing of the unmanned aerial vehicle; the electronic range finder measures the distance in real time to ensure accurate landing; the voice prompt system sends distribution information to the user, so that the interactivity is improved; the high-strength fiber rope and the automatic detacher ensure the stability and automation of the distribution process; the distribution bag is made of waterproof and shockproof materials, and medicine safety is protected. The receiving support can be installed on a roof or the ground, and adaptability is high. The distribution method comprises the steps of user ordering, unmanned aerial vehicle takeoff, voice prompt, precise landing, automatic unhooking and the like, and the user can conveniently take medicine. According to the invention, the medicine safety is guaranteed while the distribution efficiency is improved, and the user experience is improved.

This invention discloses a wearable inflatable emergency rescue parachute, belonging to the technical field of emergency rescue equipment for low-altitude manned aircraft. The invention includes a one-piece wearable support vest, a shoulder-mounted accordion-style folding storage bag, an inflatable rescue parachute, an arc-shaped flat high-pressure gas cylinder, high-pressure inflation tubing, a spring-loaded retraction box, an aramid webbing traction rope, an intelligent triggering system, and a manual trigger pull ring. The one-piece wearable support vest is a front-opening integrated structure, with an integrated shoulder-mounted accordion-style folding storage bag on the back for storing the folded inflatable rescue parachute. Arc-shaped flat high-pressure gas cylinders are symmetrically arranged on the outer sides of the left and right thighs, connected to the parachute's inflation frame via high-pressure inflation tubing. The traction rope assembly uses a spring-loaded retraction box and an aramid webbing traction rope structure to achieve opening buffering and automatic retraction. The triggering system integrates an intelligent triggering module and a manual trigger pull ring, forming dual redundant control. This invention can be worn close to the body without affecting the operation of the aircraft. It can achieve rapid inflation and molding at low altitudes without relying on oncoming airflow. It is designed to provide end-point emergency life-saving protection for low-altitude manned aircraft in scenarios of power failure and loss of control in the air. It can also be adapted to high-altitude operations and emergency escape scenarios in high-rise buildings.

The invention relates to the technical field of unmanned aerial vehicles, in particular to a parachute strap fixing and unmanned aerial vehicle hoisting multifunctional device, a hoisting method and a parachute strap fixing method.The parachute strap fixing and unmanned aerial vehicle hoisting multifunctional device comprises a support, a first quick-release pin, a second quick-release pin and a hoisting ring, and the support is of a shell structure with an opening in one side; one end of the first quick-release pin penetrates in from the side wall of the support and then penetrates out from the other side wall of the support; one end of the second quick-release pin penetrates into the support from the side wall of the support, and the lifting ring is arranged on the first quick-release pin and the second quick-release pin in a penetrating mode. According to the invention, a parachute belt fixing point and a fuselage hoisting point share the same space, so that the space in the fuselage is saved, and when the structure is used, conversion and disassembly of a parachute belt fixing function and a fuselage hoisting function can be realized without using a tool; the problems that the cost is high, the structural weight is increased, the space utilization rate is low, and time and labor are wasted during disassembly and assembly due to the fact that a traditional fixed parachute belt structure and a lifting machine body structure are designed separately are solved.