1159results about "Parachutes" patented technology

A system for protecting occupants of a vehicle during aa catastrophic event includes at least one safety pod that encloses one or more seats within the vehicle. The pod is constructed of a material that is fire proof, waterproof, bomb proof, crash proof, and / or capable of withstanding any other physical or environmental hazards that might be expected during the catastrophic event, and includes a sliding, electrically powered doors that seals the pod when closed. The pod may be configured to be ejected from the vehicle when the catastrophic event occurs or is imminent. When the vehicle is a passenger airplane, pods may be provided for each row of passenger seats, the pods being mounted to tracks by brackets and latched in a stationary position until an emergency occurs. When an emergency that requires ejection from the airplane occurs, the pods are propelled towards the rear of the airplane, and at least a portion of the rear section of the airplane is detachable to provide a space through which the pods are ejected. Sealing of the pods protects the occupants from hazards such as fire and smoke, and provides a waterproof flotation chamber in case of ejection over water.

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.

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.

An aerial vehicle safety apparatus includes a safety mechanism, a drive mechanism, an ejection mechanism, and a control mechanism. The safety mechanism is used for securing safety of at least one of an aerial vehicle and an object outside the aerial vehicle. The drive mechanism includes at least one drive unit serving as a drive source of the safety mechanism. The ejection mechanism ejects the drive mechanism together with the safety mechanism. The control mechanism controls operations of the drive mechanism for the drive mechanism to drive the safety mechanism after the ejection mechanism starts ejection of the safety mechanism.

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 invention relates to the technical field of unmanned aerial vehicles, in particular to an emergency slow descent device for an unmanned aerial vehicle. According to the emergency slow descent device for the unmanned aerial vehicle, emergency slow descent can be conducted on the unmanned aerial vehicle under the condition that the unmanned aerial vehicle is powered off, meanwhile, multiple falling protection is conducted on the unmanned aerial vehicle, and damage to the unmanned aerial vehicle is effectively reduced. An emergency slow descent device for an unmanned aerial vehicle comprises a vehicle body, vehicle arms, motors and the like. Four machine arms are evenly arranged on the machine body at intervals, and a motor is arranged on each machine arm. The arc-shaped electromagnet loses magnetism through power failure of the unmanned aerial vehicle, the parachute pops up and is opened, the parachute is opened to reduce the descending speed of the fuselage through air resistance, excessive damage caused by too high descending speed of the unmanned aerial vehicle is avoided, and therefore the unmanned aerial vehicle can be subjected to emergency slow descending when the unmanned aerial vehicle breaks down in the air; potential safety hazards are reduced by reducing the landing speed of the unmanned aerial vehicle.

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.

The invention relates to a flight state system (20) for ascertaining a flight state of a paraglider (50, 50′) which comprises a canopy (51) with two canopy ends (52) and which carries a load (53) during intended use. Thereby, the flight state system comprises a sensor arrangement (S1, S2, S3) for ascertaining a first distance (d1) between the canopy ends (52) and / or at least a second distance (d2, d3) between a canopy end (52) and the load (53). Furthermore, the flight state system comprises an evaluation unit (37) which ascertains the flight state using the first distance (d1) and / or the second distances (d2, d3). The invention further relates to an evaluation system and / or control system (40), a paraglider (50, 50′) and a method for ascertaining a flight state of a paraglider (50, 50′).

The invention discloses a vertical take-off and landing fixed-wing aircraft, and relates to the technical field of aircrafts. According to the invention, the conversion from a multi-rotor flight mode to a fixed-wing flight mode and from the fixed-wing flight mode to the multi-rotor flight mode can be easily realized. Due to the structural layout characteristics of the aircraft, the safety of the aircraft is guaranteed, and the aircraft can be safely and reliably landed according to the fault degree and urgency of the aircraft even if the aircraft breaks down seriously and only forced landing can be selected. Through multi-rotor-wing assisting control, the forced landing buffering function of the telescopic empennage assembly and the safety protection measure of a protection sponge lining in the manned cabin, various safety modes and measures such as an internal safety protection air bag, an external safety protection air bag and a forced landing parachute of the manned cabin can be selectively used according to the fault degree and urgency of the aircraft; and safe or low-damage forced landing of the aircraft is realized.

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.

The invention discloses a cargo-parachute separation mechanism after airdrop equipment enters water, which solves the problems of slow cargo-parachute separation speed and low cargo-parachute separation success rate existing in the existing separation mechanism. A spring (1) is arranged between the piston (13) and the cylinder cover (11), a thermal battery starting pin sleeve (16) is arranged in the piston cylinder (10) below the piston (13), a compressed compression spring (18) is arranged on the thermal battery starting pin (6), a safety pin (2) is fixedly arranged on the bottom end surface of the piston (13), a thermal battery (3) is arranged in the piston cylinder (10) below the thermal battery starting pin sleeve, an explosive bolt control circuit board (7) is connected to the insulation pad (4), an explosive bolt (9) is fixedly arranged on the bottom end plate of the piston cylinder (10), the explosive bolt is electrically connected to the explosive bolt control circuit board, and an airdrop equipment connection seat (5) is fixedly connected to the lower end of the explosive bolt. The equipment can be quickly deployed in place after entering the water, and the cargo-parachute separation is fast.

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 discloses a device and method for controlling load shedding of a ram-type parafoil through multiple sliding cloths, and relates to the field of parachutes. The device comprises at least two pieces of sliding cloth which are sequentially arranged from top to bottom, each piece of sliding cloth comprises four circular rings, two spanwise reinforcing bands arranged in the longitudinal direction, two chordwise reinforcing bands arranged in the transverse direction, covering cloth with the four corners connected with the four circular rings respectively, and a connecting ring connected to the middle of the covering cloth. The two ends of the two spanwise reinforcing bands are connected with the two pairs of circular rings arranged in the longitudinal direction of the covering cloth respectively, the two ends of the two chordwise reinforcing bands are connected with the two pairs of circular rings arranged in the transverse direction of the covering cloth respectively, the connecting rings of the two pieces of adjacent sliding cloth are connected through a connecting rope, and the area of the covering cloth in each piece of sliding cloth is sequentially reduced from top to bottom. According to the device and method for controlling the load shedding of the ram parafoil through the multiple pieces of sliding cloth, one-time inflation and fullness of the ram parafoil can be controlled to be multiple times of inflation according to the time sequence through linkage cooperation of the multiple pieces of sliding cloth, and instant fullness and parachute opening impact of the ram parafoil can be effectively controlled.

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 wearable three-duct power single-person aircraft which comprises a power system, an avionics system, a man-machine interaction system, a safety lifesaving system and a wearable aircraft body. The power system adopts a three-duct pneumatic layout and is arranged in the shape of a Chinese character'pin ', two duct units on the front side are located on the two sides of the wearable machine body at the same height, and the mounting height of the duct unit on the rear side is higher than that of the duct unit on the front side; the man-machine interaction system is located on the left side of the wearable fuselage and the human head and used for manually controlling flight and monitoring the flight state. The safety lifesaving system is located on the upper portion of the wearable machine body and used for guaranteeing personnel safety in emergency. The aircraft has the characteristics of compact structure, high stability, simplicity and convenience in operation, good safety and the like.

The jettisonable gas sensor comprises a jettisonable unmanned aerial vehicle and a controller, the bottom of the controller is fixedly connected with a jettisonable device, the jettisonable device comprises a fixing plate and a rotating shaft rotationally connected to the fixing plate, and the fixing plate is rotationally connected with the controller through the rotating shaft; two limiting holes are formed in the bottom of the fixing plate, electric push rods are arranged in the two limiting holes, and connecting mechanisms are fixedly connected to the bottoms of the two limiting holes; the effect of accurately detecting gas information is achieved through the buffering mechanism, when the damping mechanism falls to the ground, the buffering air bag absorbs impact energy, a movable rod in the buffering air bag moves to drive related parts to eject the parachute, an air inlet or a sensing part of the detection mechanism is prevented from being covered, and effective contact between a sensor and external gas is guaranteed; therefore, gas information is accurately converted into electric signals, accurate detection is realized after processing, and reliable data is provided for mastering on-site gas conditions.

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.

The invention provides a parachute opening control method, an aircraft, electronic equipment and a storage medium. The parachute opening control method is applied to a falling detection unit in the aircraft. The method comprises the following steps: acquiring current state data, acquired by an air-ground state sensor, of an aircraft, current height, acquired by a height sensor, of the aircraft, and current acceleration, acquired by an acceleration sensor, of the aircraft; acquiring current attitude data of the aircraft by a gyroscope sensor and acquiring a current image of the aircraft by a visual sensor; determining whether the aircraft is in an out-of-control falling state or not according to the current state data, the current height, the current acceleration, the current attitude data and the current image; if yes, an ignition instruction is sent to an ignition triggering device, so that the ignition triggering device responds to the ignition instruction, and the umbrella body is opened through the gas generator. Parachute opening control of the whole parachute is automatically and rapidly triggered, and the survival rate of air crash of the multi-rotor manned aircraft is effectively increased.

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.

The invention discloses a cover shooting and parachute guiding assembly and an unmanned aerial vehicle, and relates to the technical field of aircrafts, the cover shooting and parachute guiding assembly comprises a shell mechanism and a trigger mechanism, the shell mechanism comprises a shell and a cabin cover, the shell is provided with a parachute cabin, and the cabin cover covers the parachute cabin. The triggering mechanism comprises a rotating part, an elastic part and a control switch, the rotating part is rotationally connected with the machine shell through the elastic part, the rotating part is slidably connected with the hatch cover, and the control switch is arranged on the machine shell and detachably connected to the hatch cover. When the control switch is connected with the cabin cover, the cabin cover covers the parachute cabin, and the elastic piece accumulates elastic force. When the control switch is separated from the cabin cover, the elastic piece can release elastic force to drive the rotating piece to rotate, so that the cabin cover is separated from the rotating piece through inertia sliding and drives the guiding parachute to be separated from the parachute cabin. The cover shooting and parachute guiding assembly only comprises light-weight parts such as the cabin cover, the rotating piece, the elastic piece and the control switch, the weight proportion of the cover shooting and parachute guiding assembly to the whole unmanned aerial vehicle is small, and the mounting space of effective loads such as fuel equipment of the unmanned aerial vehicle cannot be excessively occupied.