401results about "Parachutes" patented technology

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.

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 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.

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 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 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.

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 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.

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.

The invention relates to the technical field of aviation safety, in particular to a parachute type slow descent and tail end buffering emergency lifesaving system and method for an ultra-low-altitude aircraft. The system comprises an umbrella-shaped slow descent module, a tail end buffer module, a detection and control module and an emergency energy discarding module. When the detection and control module judges that the aircraft is out of control, the emergency energy discarding module is triggered to throw away the battery pack, meanwhile, the umbrella-shaped slow descent module is triggered to pop out of the canopy, and the canopy is rapidly inflated through high-pressure gas, so that the aircraft is stably and slowly descended; before touching the ground, the gas generator of the tail end buffering module enables the buffering air bag to expand rapidly, impact energy is absorbed through compression deformation and controllable pressure relief, and safe landing is achieved. The problem that traditional lifesaving equipment cannot effectively work in the ultra-low-altitude environment is solved, the system has the advantages of being rapid in response, high in reliability and good in buffering effect, and the safety of the ultra-low-altitude aircraft is remarkably improved.

The invention relates to the technical field of engine recovery, in particular to a turbojet engine ejection recovery system and method in an aircraft fault state, and the system comprises an ejection mechanism which is arranged between a turbojet engine and an aircraft and used for disconnecting the turbojet engine from the aircraft. The turbojet engine is ejected out of the aircraft; the cut-off mechanism is arranged in the aircraft and used for cutting off an oil way and a circuit of the turbojet engine. The protection mechanism comprises a parachute assembly and an air bag assembly, the parachute assembly is connected with the turbojet engine, and a parachute is automatically opened in the landing process of the turbojet engine; the air bag assembly is folded and contracted outside the turbojet engine and automatically expands to wrap the turbojet engine in the landing process. The recycling device is compact in structure and flexible and convenient to use, recycling of the turbojet engine can be efficiently and safely completed when the fixedly-mounted turbojet engine is in an emergency, and the technical requirement for recycling of the turbojet engine in the field is met.

The utility model relates to the technical field of controllable parachutes, in particular to an in-parachute wind resistance controllable parachute which comprises a parachute cover, an exhaust hole is formed in the parachute cover, an annular air bag is arranged in the exhaust hole, a connecting plate is arranged below the annular air bag, a containing frame is arranged below the connecting plate, and a winch is arranged in the containing frame. Firstly, the annular air bag is inflated, the area of the exhaust hole is reduced, the wind resistance in the umbrella is controlled to be increased, then the winch is controlled to enable the pull rope to drive the connecting plate to ascend or descend, the connecting rope pulls the bottom of the umbrella cover to expand or gather, and therefore the wind resistance in the umbrella is controlled to be reduced or increased.

The invention relates to an interceptor drone (1) comprising a drone main body (2) and comprising a plurality of drive devices (3) arranged around the circumference of the drone main body (2). The drive devices (3) are arranged and oriented on the drone main body (2) such that the interceptor drone (1) can be driven and steered by the drive devices (3) in a flight direction (5) along a flight trajectory. The interceptor drone (1) comprises a capture net. The capture net is arranged in or on the drone main body (2) in a drone portion (6) of the drone main body (2), which drone portion is at the front in the flight direction (5). The capture net is fixed to the drone main body (2) by an elongate, flexible fixing means of the capture net. The capture net comprises drive means, by means of which the capture net can be accelerated away from the drone main body (2) in the flight direction (5).

This invention discloses a cone-shaped sealing and release mechanism, comprising a cone (1), a connecting belt (2), a cone protective sleeve (3), and a safety pin (4). The connecting belt (2) passes through the cone (1) and is fixed by a cone fixing pin (6) and a cone fixing pin screw (7). A safety pin (4) is provided on the connecting belt (2), and the sealing is performed using the safety pin (4) on the connecting belt. This invention can solve the problem of umbrella-pack integration and improve system reliability.

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.

The invention discloses a manned aircraft, and belongs to the technical field of aircrafts, the manned aircraft comprises a rack, the rack is provided with a human body fixing device and at least two turbofan assemblies, and the human body fixing device is used for fixing a human body on the rack; the turbofan assembly is connected to the tilting shaft in a tilting mode through a turbofan tilting shaft, the rotating shaft is connected to the rack, the rack drives the turbofan tilting shaft to rotate with the tilting shaft as the axis through a rotating motor, and the turbofan assembly is driven by a tilting motor to tilt with the turbofan tilting shaft as the axis. According to the invention, the rotatable and tiltable rim fan is matched with the telescopic wings for driving, so that the utilization efficiency of energy and the space efficiency of flight are improved. The driving force of the rim fan is applied to the peripheral rim, and a traditional middle motor driving mode is omitted. Due to the fact that no middle driving motor hinders airflow and wake flow distortion, thrust can be improved through a smooth and continuous flow channel in the whole duct, the motor in the center is eliminated, an important noise source is removed, and noise of the whole fan is reduced.

The application discloses a closing control structure and method of a parachute, and relates to the field of parachutes. The closing control structure of the parachute comprises a canopy support arranged at the bottom opening of a main canopy, N radial closing ropes arranged along the circumference of the canopy support, at least one circumferential closing rope sleeved on the outer wall of the bottom of the main canopy, and a delay actuator for timing cutting of the circumferential closing rope. The bottom of the main canopy is connected with a plurality of closing rings arranged along the circumference of the bottom of the main canopy. Both ends of each radial closing rope are connected to the edge of the canopy support, the middle part of each radial closing rope passes through a closing ring of the bottom of the main canopy, the middle part of the last radial closing rope passes through the closing ring and the main canopy, and is then sleeved on the circumferential closing rope. The middle part of the Nth radial closing rope passes through the closing ring, and is then sleeved on the middle part of the (N-1)th adjacent radial closing rope passing through the closing ring. N is a positive integer greater than or equal to 2. The closing control structure and method of the parachute provided by the application can reduce the opening time of the canopy, reduce the hovering height, guarantee the opening consistency of the parachute, and significantly improve the opening performance.

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.

The application relates to a device and method for improving the opening reliability of a rescue parachute of an ejection seat, and relates to the field of air dropping. The device for improving the opening reliability of the rescue parachute of the ejection seat comprises a rescue parachute box and a deceleration parachute box which are installed on the ejection seat and are connected with each other, the deceleration parachute box is configured to be separable from the rescue parachute box, the rescue parachute box is internally provided with a rescue parachute, the deceleration parachute box is internally provided with a connecting belt, a deceleration parachute and a constant force breaking rope, one end of the connecting belt is connected with a parachute rope of the deceleration parachute, the other end of the connecting belt is connected with the top of the rescue parachute box, one end of the constant force breaking rope is connected with the top of a canopy of the deceleration parachute, the other end of the constant force breaking rope is connected with the top of the deceleration parachute box. The device and method for improving the opening reliability of the rescue parachute of the ejection seat solve the bending phenomenon of the parachute rope and the canopy during the high-speed ejection of the ejection seat, avoid the problems of early inflation of the rescue parachute, serious damage and local parachute turning, avoid the safety hazards caused by the interference after the separation of the parachute box and the rescue parachute, and improve the high-speed working reliability of the rescue parachute matched with the ejection seat.

To provide a convenient and safe vehicle.SOLUTION: An airbag extending to the outside of a vehicle body is inflated by igniting a gas generator when a monitor with a speed measuring instrument detects danger. Furthermore, solar power generation by a solar panel provided on a roof of the vehicle body, self-generated power by driving of propellers and tires, and hydrogen fuel are utilized to address energy issues and CO2 emission issues. In addition, even if one blade of a propeller encounters an abnormality, the other propeller can continue driving in a form of four-propeller-driving and in which the propeller has double blades in one set. A parachute for an escape in the event of an accident is provided.SELECTED DRAWING: Figure 1

The application discloses a ram-air parachute with adjustable deployment time and a parachute opening method, and relates to the field of ram-air parachutes. The ram-air parachute with adjustable deployment time comprises a parachute body, a plurality of parachute ropes connected to the parachute body, and a slide cloth connected to the parachute ropes. The slide cloth comprises four annular rings sleeved on the four parachute ropes, two longitudinal deployment reinforcing belts, two transverse chord reinforcing belts, and a canopy with four edges connected to the four annular rings. The four edges of the canopy are connected to the two longitudinal deployment reinforcing belts and the two transverse chord reinforcing belts. The two ends of the deployment reinforcing belts and the chord reinforcing belts are connected to two adjacent annular rings. A plurality of interval arranged hooks are arranged on the deployment reinforcing belts and the chord reinforcing belts. One end of the deployment reinforcing belts and the chord reinforcing belts is connected to a retractable spring hook connected to a corresponding hook. The ram-air parachute with adjustable deployment time and the parachute opening method can adjust the length of the four edges of the canopy and the size of the slide cloth to adapt to the resistance requirement of different ram-air parachutes.

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.

A ballistic projectile recovery system includes a forward opening in an ogive of the projectile, selectively opened to deploy a portion of the recovery system. A parachute is deployable through the opening, connected to the projectile by riser line(s). A rotational bearing assembly makes the riser line(s) rotationally decoupled from the projectile. A bidirectional drag inducing element extends externally of an ogive of the projectile. A spacer, between a setback plate and the rotational bearing assembly, is deformable in at least the longitudinal direction of the projectile. The setback plate is movable between a first position to a second position made available by the compression of the spacer. In the second position, the setback plate is in contact with the projectile, providing a load path that avoids the rotational bearing assembly to take up strain applied to the projectile in at least the longitudinal direction.

The invention provides a canopy sleeve top-pulling releasing mechanism of a parachute recovery device and an unmanned aerial vehicle, the canopy sleeve top-pulling releasing mechanism of the parachute recovery device comprises an outer parachute bag, a canopy sleeve, a main parachute top-pulling rope, a bag sealing ring, a first ring sleeve, a second ring sleeve, a third ring sleeve, a cleat rope, a hair pulling rope and a fixing pin, and the canopy sleeve top-pulling releasing mechanism of the parachute recovery device is linked with multiple components through cooperation of a three-ring mechanism; reliable unlocking after straightening of the canopy sleeve is ensured, the main parachute smoothly slides out for inflation, the problems that a traditional canopy sleeve type recovery parachute is stacked in parachute opening and unsmooth in procedure are solved, and the canopy sleeve type recovery parachute is simple in structure, high in reliability and suitable for various unmanned aerial vehicle recovery systems.