781results about "Parachutes" patented technology

Embodiments relate generally to systems and VTOL aerial vehicles. An example central server system comprises: at least one central server system processor; and central server system memory storing central server system program instructions accessible by the at least one central server system processor, and configured to cause the at least one central server system processor to: receive vehicle registration data associated with a manned VTOL aerial vehicle; and determine that the vehicle registration data is associated with a manned VTOL aerial vehicle that is authorized to communicate with the central server system. Some embodiments include VTOL aerial vehicles in communication or communicable with a central server system.

The invention relates to the technical field of parachute separation, and discloses an automatic parachute falling mechanism and an aircraft. The automatic parachute falling-off mechanism comprises a cylinder used for being connected with an aircraft; the cylinder body is provided with a channel penetrating in the axial direction of the cylinder body; the pull rod is connected with a parachute; the pull rod is positioned in the channel; the first limiting piece is arranged on the barrel close to the top of the channel and can move in the radial direction of the barrel; the first limiting piece abuts against the pull rod for limiting the top of the pull rod to move towards the bottom of the barrel; the bottom, close to the channel, of the second limiting piece is arranged on the barrel and can move in the radial direction of the barrel; the second limiting piece abuts against the pull rod and is used for limiting the bottom of the pull rod to move towards the top of the barrel. The aircraft comprises the automatic parachute falling mechanism. By means of the scheme, the technical problem that in the prior art, a limiting mechanism between the connecting pull rod and the barrel cannot be repeatedly used can be solved.

An emergency aircraft parachute-balloon system for assisting landings during abnormalities. Integrated modular enclosures house inflatable balloon-like apparatuses made of parachute materials along the fuselage. A sliding door seals each enclosure. A control system allows the pilot to remotely deploy balloons. Multiple balloons provide redundancy. Once deployed, the balloons gently bring down the aircraft to avoid crashes. Spacing prevents tangling. The customizability and aircraft integration distinguishes this invention from prior individual ejection / parachuting systems. Overall, this parachute-balloon system enables safe emergency landings to save lives.

The utility model relates to an automatic parachute opening device based on cam unlocking, and belongs to the technical field of parachutes. The automatic parachute opening device based on cam unlocking comprises a main parachute, a guide parachute, a parachute cabin and an action mechanism. Wherein the parachute bay comprises a bay body, a parachute bay cover and a parachute folding seat and is used for accommodating the main parachute and the guide parachute; the cabin body is hinged to the parachute cabin cover, the cabin body is fixedly connected with the parachute folding base, the main parachute is installed on the parachute folding base, and the guide parachute is contained above the main parachute; the action mechanism is installed at the end, close to the parachute cabin cover, of the cabin body, movably connected with the parachute cabin cover and used for controlling opening or closing of the parachute cabin cover. The action mechanism comprises a rotary lock catch mounted on the cabin body and a fixed lock catch mounted on the parachute cabin cover; and when the action mechanism is unlocked, the rotary lock catch is separated from the fixed lock catch, so that the main umbrella and the guide umbrella are opened. According to the automatic parachute opening device based on cam unlocking, the parachute cabin cover is controlled to be opened or closed through the action mechanism, and a more efficient, safer and more economical solution is provided for air-drop laying of ocean observation and detection equipment.

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 invention discloses an opening device of a drag parachute cabin door of a lower parachute cabin and a using method. The opening device comprises the cabin door, a driving mechanism and a door bolt mechanism. The cabin door is installed at the opening position of the drag parachute containing groove and used for sealing the opening position of the drag parachute containing groove, the driving mechanism is installed on a front wall plate of the drag parachute containing groove through an inner support of the driving mechanism, the door bolt mechanism is installed in the cabin door in a penetrating mode in the course direction, and one end of the door bolt mechanism is associated with the driving mechanism. The door bolt mechanism is controlled by the driving mechanism 3 to open and close the cabin door; the front lock seat and the rear lock seat are correspondingly installed on the inner sides of a front wall plate and a rear wall plate of the drag parachute containing groove, the lock pin assembly penetrates through the cabin door in the course direction, a front lock pin in the lock pin assembly penetrates through a front side plate of a box-shaped piece in the cabin door and then is inserted into the front lock seat, and a rear lock pin in the lock pin assembly penetrates through a rear side plate of the box-shaped piece in the cabin door and then is inserted into the rear lock seat. The front lock pin and the rear lock pin are hinged to the middle crank through hinged connecting rods respectively, the front lock pin is sleeved with a compressed spring, one end of the compressed spring is fixedly connected with the axial designated position of the front lock pin, the other end of the compressed spring is fixed to the designated position of the cabin door through a support, and pressing force is provided for the front lock pin and the rear lock pin through the compressed spring so that the front lock pin can be pushed into the front lock seat. And the rear lock pin is pushed into the rear lock seat, so that a locking state when the cabin door is closed is realized. The drag parachute cabin door opening device solves the problems that an existing drag parachute cabin door opening device is mostly in a hydraulic mode, a pneumatic mode and the like and is complex in structure, large in occupied space, low in reliability and the like.

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.

An unmanned aerial vehicle system including an unmanned aerial vehicle (UAV); a tether having a first end positioned in a winch system of the UAV and a second end secured to a payload coupling apparatus; a payload coupling apparatus receptacle positioned in the UAV; a payload having a handle, wherein the handle of the payload is positioned within a slot in the payload coupling apparatus; wherein the UAV has a recessed restraint slot for receiving a top portion of the payload.

Disclosed herein are parachute canopies and sliders for use with parachutes. The parachute canopies can include one or more deformable vent panels that can be used to control an inflation rate of the canopies based on an internal pressure within the canopies. The sliders can include strips that form through holes that have a width that distributes a radial load on suspension lines and allow for the use of lower weight, high modulus suspension lines.

A method is disclosed herein. The method includes receiving, by a processor, an ejection command for ejecting an ejection seat from an aircraft; determining, by the processor, an airspeed and an altitude of the ejection seat; responsive to the altitude of the ejection seat indicating a second mode of operation, determining, by the processor, whether the airspeed of the ejection seat is at or above a first threshold and below a second threshold; and responsive to the airspeed of the ejection seat being at or above the first threshold and below the second threshold: sending, by the processor, a command to deploy a drogue parachute; and, responsive to a first predetermined time period expiring, sending, by the processor, a command to deploy a main parachute and sever the drogue parachute based on a variable drogue severance delay.

A method is disclosed herein. The method includes receiving, by a processor, an ejection command for ejecting an ejection seat from an aircraft; determining, by the processor, an equivalent airspeed and an equivalent altitude of the ejection seat; and, responsive to the airspeed and the altitude indicating a second mode of operation: sending, by the processor, a command to deploy a drogue parachute; determining, by the processor, a variable drogue severance delay; and responsive to the variable drogue severance delay expiring, sending, by the processor, a command to sever the drogue parachute and deploy a main parachute.

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.

Rescue parachute deployment systems (RPDSs) and related techniques are provided to improve the safety and operational flexibility of unmanned aerial vehicles (UAVs). An RPDS includes a canopy assembly, a rotor guard disposed at least partially about the canopy assembly and configured to protect the canopy assembly from rotor strike damage as the canopy assembly is launched through a rotor plane of the UAV, and an ejector assembly configured to deploy the rotor guard into and the canopy assembly through a rotor plane of the UAV. The RPDS may also include a logic device coupled to and / or integrated with the ejector assembly and / or the UAV that is configured to determine a rescue parachute launch condition is active and to control the ejector assembly to deploy the canopy assembly through the rotor plane of the UAV.

The invention relates to the technical field of aircrafts, in particular to an aircraft and a landing method of the aircraft. The aircraft provided by the invention comprises a cabin, a parachute and a jet device, the cabin is in butt joint with the flight mechanism; the parachute is arranged in the cabin; the spraying device comprises a spraying opening, and the spraying opening faces the parachute; when the cabin is separated from the flight mechanism, the jet orifice jets high-pressure airflow to rush out the parachute, so that the parachute can be normally opened under the condition that the low altitude is not enough, the landing speed of the cabin can be slowed down after the parachute is jetted upwards, and the safety during landing is improved.

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.

A payload delivery device is an apparatus designed to facilitate the delivery of emergency items to a target location via aerial vehicles. The apparatus includes a base strap, a plurality of holder straps, and a plurality of cargo straps. The base strap serves as the central structure of the apparatus that supports the plurality of holder straps and the plurality of cargo straps. The plurality of holder straps includes several straps designed to retain a parachute and the devices necessary to facilitate the deployment of the parachute. The plurality of holder straps is also designed to facilitate the operation of the parachute while securing the parachute to the base strap. The plurality of cargo straps include several straps that secure the payload to the apparatus. The plurality of cargo straps can also be arranged to accommodate the shape and size of the payload to be delivered using the apparatus.

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.

An emergency landing apparatus (100) for an aircraft and an associated method are provided. The emergency landing apparatus comprises: a housing (10) for ejection from the aircraft; a parachute (20), arranged for deployment from the housing, comprising a canopy (22); a rocket motor (30), positioned in the housing, arranged to provide upwards thrust to control descent of the aircraft during emergency landing of the aircraft; a rocket motor initiator (38), positioned in the housing, arranged to initiate the rocket motor; and one or more sensors for sensing ejection of the housing from the aircraft and for arming the rocket motor initiator in response to sensing ejection of the housing from the aircraft.

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.

A system enabling safe manned and unmanned operations at extremely high altitudes (above 70,000 feet). The system utilizes a balloon launch system and parachute and / or parafoil recovery.

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 parachute control system based on an unmanned aerial vehicle and an unmanned aerial vehicle system. The parachute control system based on the unmanned aerial vehicle comprises an airborne module used for receiving a starting instruction of a parachute control module to activate a flight control module; the flight control module is used for controlling the flight operation of the unmanned aerial vehicle, monitoring the flight state of the unmanned aerial vehicle and sending the data of the flight state to the parachute control module; the parachute control module is used for receiving data of the flight control module to judge whether the unmanned aerial vehicle needs to open a parachute or not and sending a parachute control signal to the parachute driving circuit module when the parachute needs to be opened; and the parachute driving circuit module is used for receiving the parachute control signal and controlling the parachute to unfold according to the parachute control signal. Whether the parachute needs to be opened or not is evaluated through the parachute control module. And when the requirement is confirmed, a control signal is sent to the parachute driving circuit module, so that the parachute is unfolded, and the safe landing of the unmanned aerial vehicle is ensured in an emergency.

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.

A fall protection system and method, particularly for attenuating shocks transmitted to a person's body by a safety line, such as a rope or cable, after a fall or while being deliberately lowered from an overhead anchor point. A shock absorber assembly is incorporated in or on the safety line, deployed between the person and the safety line anchor point.