72results about "Parachutes" patented technology

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.

According to at least one example a launch system is provided, including a carrier vehicle and at least one payload vehicle. The payload vehicle includes a payload propulsion system and aerodynamic lift surfaces designed for providing the payload vehicle with aerodynamic powered flight at a design subsonic cruise speed at a desired altitude. The carrier vehicle is configured for carrying the at least one payload vehicle at least up to the desired altitude, and further includes a solid rocket propulsion system for propelling the launch system to the desired altitude. The carrier vehicle is configured for providing a predetermined forward speed at the desired altitude, correlated to the design subsonic cruise speed. The carrier vehicle is configured for releasing the payload vehicle with respect to the carrier vehicle at the desired altitude and the predetermined forward speed. The design subsonic cruise speed is less than 0.7 Mach number, and, the desired altitude is greater than 3km.

This invention relates to the field of underwater vehicle technology, specifically to an airdrop-type underwater glider. The airdrop-type underwater glider includes an attitude adjustment cabin, a bow mounting frame, a cushioning elastic component, a mobile battery pack, and a pitch drive mechanism. The pitch drive mechanism is drive-connected to the mobile battery pack. The bow mounting frame is mounted at the front end of the attitude adjustment cabin. The cushioning elastic component includes a first cushioning elastic element disposed on the front surface of the mobile battery pack. The bow mounting frame has a cushioning mating surface for cooperating with the first cushioning elastic element. The cushioning elastic component also includes a second cushioning elastic element disposed between the mobile battery pack and the pitch drive mechanism. When the airdrop-type underwater glider is subjected to an impact load, the first cushioning elastic element at the front end of the mobile battery pack and the bow mounting frame cushion the impact force transmitted from the water surface, while the second cushioning elastic element absorbs the impact force transmitted by the mobile battery pack, significantly reducing the impact force transmitted to the pitch drive mechanism.

Rotor assemblies for a rotor-based aerial vehicles are described. An example rotor assembly (100) comprises an electric motor (102) including a stator, a rotor (108), and an open central region. The rotor is configured to rotate relative to the stator. The open central region is located radially inward relative to the stator. The example rotor assembly further comprises a plurality of rotor blades (104) operatively coupled to the rotor. The example rotor assembly further comprises a device (106) deployable from a stowed position relative to the electric motor into a deployed position relative to the electric motor. At least a portion of the device is located within the open central region when the device is in the stowed position. The at least a portion of the device is located above the electric motor and above the plurality of rotor blades when the device is in the deployed position.

The application discloses a kind of eVTOL aircraft parachute safety systems with active trigger mechanism, it is related to flight landing equipment technical field, the system includes umbrella package module, quick release module, umbrella opening trigger module, deployment induction module, impact slow-release module and attitude stability and tension control module;For electric vertical take-off and landing aircraft in emergency or emergency state Safety slow descent protection, with artificial command control and automatic fault recognition dual trigger mechanism as the core of parachute, can be triggered by artificial or system automatic trigger to complete umbrella body deployment in the critical situation such as aircraft out of control, power interruption, significantly reduce the impact load in the early stage of deployment and maintain the attitude stability during descent process.The system has the characteristics of fast response, compact structure, slow-release adjustable, strong adaptability, etc., and is suitable for the safe landing requirements of eVTOL aircraft in low-altitude operation in emergency situations such as loss of control or power failure.

The present disclosure discloses a control method based on an unmanned aerial vehicle system and an unmanned aerial vehicle system. The unmanned aerial vehicle system includes an unmanned aerial vehicle, a remote controller, a second control apparatus and a first control apparatus. The second control apparatus is disposed on the unmanned aerial vehicle. The first control apparatus is disposed on the remote controller. The unmanned aerial vehicle includes a first battery. The control method based on the unmanned aerial vehicle system includes: The first control apparatus outputs a first control signal. The second control apparatus receives the first control signal, and outputs a second control signal to the first battery when receiving the first control signal. The first battery stops outputting voltage when receiving the second control signal. This approach reduces the risk of UAV damage and effectively enhances flight safety.

The goal is to obtain an actuator, safety device, and aircraft that are simpler in configuration and lighter than conventional designs. [Solution] The actuator 1 comprises an igniter 2, a piston 3 extending in one axis direction, a cylindrical housing 5 that restricts the direction of propulsion of the piston 3, a holder 6 that holds the igniter 2, a lid 7 provided at one end of the housing 5, a coil spring 8 provided inside the piston 3, and a locking member 9 provided between the lid 7 and the coil spring 8. The locking member 9 is provided between the lid 7 and the coil spring 8 and has a locking portion on the side wall that, in the initial state, is pushed toward the lid 7 by the coil spring 8 which is biased or compressed in the axial direction of the housing 5, and locks into a hole 5b formed in the side wall of the housing 5. The locking portion has a cantilevered beam portion 9a and a projection 9b provided on the outer surface side of the cantilevered beam portion 9a, which tapers radially from one end to the other.

This invention discloses a structure and method for recovering parachute lines for unmanned aerial vehicle (UAV) cargo transport. The structure includes an internal cabin structure, a power drive unit, a front support, a steel wire rope, parachute lines, and a rear support. The front support is mounted on the internal cabin structure, and the power drive unit is mounted on the front support. The rear support is mounted at the tail of the internal cabin structure, and a pulley is installed on the rear support. The power drive unit is connected to a chain and a control unit. One end of the steel wire rope is fixed to the chain, and the other end of the steel wire rope passes around the pulley and extends along the flight direction of the internal cabin structure. A buckle is fixed to the surface of the steel wire rope. The parachute lines are draped over the surface of the steel wire rope, and the end of the parachute lines is connected to the buckle. This design achieves stable transmission in the parachute line recovery system, improving its reliability and safety.

This invention relates to the field of engine recovery technology, and in particular to a system and method for the ejection and recovery of a turbojet engine in the event of an aircraft malfunction. The system includes an ejection mechanism positioned between the turbojet engine and the aircraft, used to disconnect the turbojet engine from the aircraft and eject the engine outside the aircraft; a cutting mechanism located inside the aircraft, used to cut off the turbojet engine's oil and electrical circuits; and a protective mechanism including a parachute assembly and an airbag assembly. The parachute assembly is connected to the turbojet engine and automatically deploys during the engine's descent; the airbag assembly folds and retracts outside the turbojet engine and automatically expands to enclose the engine during descent. This invention has a compact structure, is flexible and convenient to use, and can efficiently and safely recover a fixed-mounted turbojet engine in an emergency, meeting the technical requirements for turbojet engine recovery in this field.

This invention discloses a ramjet parachute deployment and load reduction system, comprising a restraint ring, a sliding sheet (3), a release belt (4), a second connecting belt (5), a first connecting belt (6), a deceleration chute (7), a release mechanism (8), a load-bearing belt (9), and a restraint rope (10). This system can extend the ramjet parachute's inflation and deployment time. Compared to the current two-stage deployment method, it reduces the impact of the deceleration chute (7) on the ramjet parachute's gliding performance, and does not lose the deceleration chute (7). Compared to the current sliding sheet closing method, it has a better load reduction effect.

The application discloses a parachute opening data generation method and system, a terminal and a computer readable storage medium. The method comprises the following steps: when a sampling signal is received, a barometric pressure sensor is controlled to enter a full-speed mode to acquire a barometric pressure sensor value in real time, and a first height value is generated according to the barometric pressure sensor value; it is judged whether an IMU enters a measurement mode, if yes, the IMU is calibrated, IMU data is acquired in real time, and first acceleration and attitude data are calculated; according to the first height value, the first acceleration and the attitude data, a fusion algorithm is adopted to obtain parachute opening data. The data acquired by the barometric pressure sensor and the IMU is fused, and accurate parachute opening data for parachute opening judgment can be obtained.

An electric VTOL aircraft has a fuselage having a nacelle that is flexibly connected to a power plant assembly that includes a plurality of electric rotors and arms. The power plant assembly may pitch and roll relative to and independently of the nacelle to produce efficient forward, rearward, and lateral thrust while the nacelle attitude remains unchanged. This provides a stable passenger experience as well as enhanced performance and controllability, while reducing cost and complexity. In some embodiments, the fuselage is vertically elongated, and the power plant assembly is mounted above the fuselage such that a person can walk fully upright below the rotors. Also disclosed is a VTOL docking station configured to allow an aircraft to land without the use of landing gears. The docking station also includes an electronic component configured to automatically provide charging to the aircraft when the aircraft is docked with the docking station.

A stabilizing parachute system with entanglement prevention capabilities for safely deploying a load from a high-altitude craft. The system includes an expandable container component coupled to the load, a strap coupled to the expandable container component, and a stabilizing parachute disposed within the expandable container component and coupled to the strap. The system further includes an actuation component coupled to the stabilizing parachute, configured to deploy the stabilizing parachute from the expandable container component upon actuation. Upon deployment, the stabilizing parachute is configured to apply tension to the strap that is transferred to the expandable container component. Upon receiving tension from the strap, the expandable container component is configured to expand into a rigid support component configured to surround the strap.

The utility model discloses a community patrol unmanned device, including main part, the top fixed mounting of main part has installation box and the all rotation installation of drive paddle of four around of main part, the fixed mounting of camera on main part and the fixed mounting of installation box on the bottom of main part, the fixed mounting of rotation motor on installation box and rotation installation have round bar in installation box, the fixed sleeve joint of reciprocating screw rod has on the output shaft of rotation motor, and the screw joint of reciprocating rack has on reciprocating screw rod, the fixed sleeve joint of reciprocating gear has on round bar and the cleaning brush of the screw installation of one end of round bar, the fixed mounting of main power supply has in main part. The utility model provides a community patrol unmanned device through flight and patrol, camera cleaning mechanism, emergency landing protection mechanism, has realized the efficient, safe, reliable community patrol task.

This utility model discloses a parachute cover and a parachute landing device. The parachute cover includes: a parachute pouch with a cavity for storing the parachute canopy; and a parachute fabric connected to the outside of the pouch. An inflation cavity is formed between the fabric and the pouch, allowing external airflow to enter. When airflow enters the inflation cavity, at least a portion of its kinetic energy is converted into upward lift force acting on the fabric, thus generating upward buoyancy for the parachute cover. In this utility model, the parachute cover, through the inflation cavity formed between the fabric and the pouch, allows external airflow to enter when the cover is deployed. The airflow flows within the inflation cavity and converts part of its kinetic energy into upward lift force acting on the fabric. This lift force causes the entire parachute cover to experience upward buoyancy, altering the trajectory and position of the parachute canopy inside, enabling it to move upward after release and smoothly pass over the vertical stabilizer or tail propeller area, avoiding collision or entanglement.

A ram-air parachute system is presented. The system may include upper and lower airfoil surface members and one or more proximal wall members, distal wall members, interior wall members, and proximal-facing air inlets. The proximal-facing air inlets may be defined between the interior wall members and the upper and lower airfoil surface members. One or more edge airfoils may be defined between the proximal wall members and at least a portion of the upper airfoil surface member, the lower airfoil surface member and the distal wall member(s). The edge airfoils may be in fluidic communication with the proximal-facing air inlet such that air may flow into the edge airfoils via the proximal-facing air inlet and inflate the edge airfoils. Inflation of the edge airfoils may vertically expand the parachute system, increasing a vertical distance between the upper and lower airfoil surface members.

This invention discloses an airdrop landing device, an airdrop parachute deployment method, and an airdrop system. The airdrop landing device includes a parachute hook, a parachute pull cord system, a guide parachute system, a main parachute system, and tethering accessories. The parachute pull cord system is connected to the parachute hook via a third connection method, and the parachute hook is used to connect to a drone. The parachute pull cord system is used to control the airdrop landing device to deploy the parachute in a set state. The guide parachute system is used to deploy the main parachute, and the main parachute system is used to provide aerodynamic drag. The tethering accessories include a tether net and a tether cloth for securing the airdrop. The airdrop landing device of this invention can be used for parachute deployment and release from a drone during airdrop, and is equipped with corresponding parachute pull cords so that when the drone drops the airdrop, the length of the parachute pull cord after breakage is insufficient to affect the closure of the drone's door, thereby increasing the safety of the drone airdrop.

This application relates to the field of unmanned aerial vehicle (UAV) accessory technology. It provides a UAV parachute device and a UAV, comprising a cabin with a receiving cavity and an opening at the top communicating with the receiving cavity; a parachute body disposed within the receiving cavity, with parachute lines connected to the parachute body; an airbag assembly disposed at the bottom of the receiving cavity for inflating to push the parachute body towards the opening; a guide plate movably disposed within the receiving cavity and located between the airbag assembly and the parachute body, the airbag assembly pushing against the guide plate when inflated; and a buffer assembly disposed within the receiving cavity, the guide plate surrounding the buffer assembly, one end of the buffer assembly connected to the parachute lines and the other end fixed to the cabin. By setting the movable guide plate between the airbag assembly and the parachute body, parachute body jamming is effectively reduced, and the buffer assembly effectively reduces the impact of parachute opening, protecting the aircraft's fuselage structure.

This utility model discloses a parachute fixing device for a fixed-wing unmanned aerial vehicle (UAV). The UAV includes a fuselage with a cabin on its upper part. The parachute fixing device includes a square shell housed within the cabin and limiting devices arranged around the perimeter of the shell. The limiting devices include a U-shaped slide rail, a T-shaped perforated lug, and a bearing. The T-shaped perforated lug is slidably mounted on the U-shaped slide rail via the bearing. The U-shaped slide rail is vertically positioned within the shell. This utility model ensures that the parachute is completely retracted within the shell during normal flight, preventing aerodynamic interference. In emergency deployment, the tension of the parachute lines causes the T-shaped perforated lug to move rapidly upward along the slide rail, evenly transferring the impact load to the fuselage. This ensures the reliability of the parachute's instantaneous deployment and achieves the effect of evenly transmitting the parachute's impact force axially to the main load-bearing structure of the fuselage. This effectively prevents the fixing device from loosening or shifting due to turbulence, airflow, or other factors during flight, ensuring the stability of the parachute upon deployment.

A balloon system, preferably including a balloon and a payload. A balloon, preferably including a plurality of gores, a plurality of load members, and an apex fitting. A method of balloon system operation, preferably including deflating a balloon, and optionally including operating the balloon system in flight and / or landing the balloon system.

The application discloses a kind of auxiliary guide umbrella's opening umbrella transverse unloading and stabilizing mechanism.The mechanism is the umbrella top tear strip of side branch auxiliary guide umbrella, for pulling the umbrella top of umbrella cloth of side branch auxiliary guide umbrella when umbrella cloth is inflated;Umbrella top tear strip is formed by folding and sewing, 2 layers of tear strip, one end of which is cut into two halves and sewn together, the other end is cut open when folding, and the two ends are fixed respectively;One end is fixed on the umbrella top of side branch auxiliary guide umbrella, and the other end is fixed on the connection of long and short sections of connecting rope.The application solves the stability problem of multiple auxiliary guide umbrellas, so that auxiliary guide umbrellas can be used in the form of multiple umbrella parallel combination, and solves the instability of side umbrella of multiple auxiliary guide umbrella parallel system and the problem of excessive opening umbrella dynamic load.

An apparatus, including a personal monitoring device and a drone. The personal monitoring device 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 application discloses a kind of separation devices, belong to electromechanical field.The device includes mounting body, connecting body and carrier, one end of the carrier is detachably connected with one end of mounting body by connecting body, electromagnetic separation mechanism and electric explosion separation mechanism are equipped in the mounting body, the electromagnetic separation mechanism is used to control mounting body and connecting body separation, the electric explosion separation mechanism is used to separate mounting body and connecting body when electromagnetic separation mechanism fails.Integrated mechanical, electromagnetic and electric explosion separation function, high separation reliability, and in the case of electromagnetic separation normal action, electric explosion separation only acts as backup and does not act, only in the case of electromagnetic separation failure, electric explosion separation will act, because electric detonation tube is consumable, it needs to be replaced after use, therefore, the separation device realizes electric explosion separation as backup function, reduces consumables and saves product cost.

To provide a safety device for an air vehicle which achieves desired operation without fail while achieving reduction of the weight and making assembly work easy.SOLUTION: A safety device 1 for an air vehicle includes: a housing including a top plate part, a bottom plate part, and a peripheral wall part 12; a deployed body; an ejection device 30 which ejects the deployed body; a first member and a second member 50 having strength higher than that of the bottom plate part 21; fastening members 90; and connection members 80. The first member includes: an attachment part 40 which attaches the safety device 1 for the air vehicle to an air vehicle including a propulsion mechanism; and a first fastened part 31a3. The second member 50 includes a second fastened part 51. The fastened members 90 fasten the first fastened part 31a3, the second fastened part 51, and the bottom plate part 21 in a state that the bottom plate part 21 is sandwiched between the first fastened part 31a3 and the second fastened part 51 to fix the bottom plate part 21, the first member, and the second member 50 to each other. Each connection member 80 is connected at one end to the second member 50 and at the other end to the deployed body.SELECTED DRAWING: Figure 5

The application provides an automatic separation device, and relates to the technical field of parachutes. The automatic separation device comprises a separation claw and a lock slot shell, the separation claw and the lock slot shell are slidably connected along a first preset direction, the separation claw is provided with a first connecting end, the lock slot shell is provided with a second connecting end, the first connecting end and the second connecting end are oppositely arranged along the first preset direction, and the separation claw and the lock slot shell are in a first relative position under the condition that the first connecting end and the second connecting end are simultaneously subjected to a pulling force. A first elastic component is arranged on the lock slot shell and acts on the separation claw, and the first elastic component has a tendency to make the separation claw and the lock slot shell slide from the first relative position to a second relative position to be unlocked. The automatic separation device can realize automatic unlocking between a parachute and a load.