379results about "Launching/towing gear" patented technology

An unmanned aerial vehicle (UAV) 1 of the vertical take-off and landing (VTOL)-type that can be launched from a launcher tube 2 is provided. A launcher 2 for launching the UAV 1 is also provided. The UAV 1 comprises a housing 10 and a transition mechanism 100 for transitioning the UAV 1 between a collapsed configuration for stowing the UAV 1 in a launcher tube 21 and a flight configuration. The housing 10 and the transition mechanism 100 are configured so that one or more rotors 12a-d that, in use, are connected to the transition mechanism 100 are located substantially within the housing 10 in the collapsed configuration and outside the housing 10 in the flight configuration. The launcher 2 comprises a hollow tube 21 for receiving a UAV 1 in a collapsed configuration and a trigger mechanism 26 for triggering a propulsion mechanism for propelling the UAV 1 out of an end of the hollow tube 21. A system comprising both the UAV 1 and the launcher 2, and a kit of part which, when assembled, provide the UAV 1 are also provided.

The invention discloses a rocket-boosted warplane ultra-short-distance launching take-off system and method. The system comprises a chassis, a high-precision track, a hydraulic lifting mechanism and a rocket sled. The rear end of the high-precision track is connected with the top of the chassis in a vertically swinging mode, the front end of the high-precision track is driven by a hydraulic lifting mechanism to ascend and descend, and the rear portion of the high-precision track is provided with a check block. The bottom of the rocket sled is provided with a sliding block used for being in sliding fit with the high-precision track. The mounting interface is used for being connected with a warplane undercarriage through an electronic lock, and the electronic lock is used for timing when a rocket engine is started, unlocking when the rocket engine reaches the working time and sending a separation success signal after being separated from a warplane. Small-overload ultra-short-distance take-off of the fighter is achieved, the volume of ground take-off facilities of the fighter is effectively reduced, the requirement for ground conditions is lowered, the flexibility and convenience of deployment are effectively improved, and the structure or a power system of the fighter is not greatly changed.

The invention discloses an aircraft nozzle protection device and an aircraft, and relates to the technical field of aircraft nozzle protection.The aircraft nozzle protection device comprises an annular shell and a cover plate, the annular shell is arranged outside an aircraft engine in a sleeving mode, and the cover plate is arranged on the outer side of the annular shell; the first side of the cover plate is rotationally connected with the annular shell, the second side of the cover plate is connected with the annular shell and the engine jet pipe in an unlocking mode, when the aircraft is ejected out of the barrel, the engine jet pipe is static, the second side of the cover plate is locked with the annular shell, and when the aircraft is ejected out of the barrel, the engine jet pipe swings, the second side of the cover plate is unlocked from the annular shell. The first side of the cover plate rotates around the annular shell by the preset angle and then is separated from the annular shell, the cover plate bears huge airflow impact force generated by fuel gas when the aircraft is ejected out of the barrel, the situation that an engine jet pipe is damaged by high-temperature and high-pressure fuel gas is avoided, an ejection bottom plate in the launching barrel does not need to be used, and space is saved; and the mass and cost of the launch canister and the aircraft are reduced.

The disclosed inventions include personal Unmanned Aerial Vehicles (UAV's) and UAV universal docking ports “docking ports” to be incorporated into and / or attached to headwear, including helmets, hard hats and hats and face masks, as well as footwear including boots and shoes, clothing and outerwear, devices, gear and equipment, land, air, water and space vehicles, buildings, wireless towers and other mobile or stationary objects and surfaces referred to collectively as “docking stations”. A docking station may have one or more docking ports for docking, networking and charging or refueling compact personal UAVs, and for providing data communications between said UAVs and other electronic devices that remain with the person while the UAV is in flight or driving or landed on terrain. Said docking ports may also incorporate wireless power transmission for remote wireless charging of one or more UAV's. Supplemental power for recharging said UAVs when docked may be supplied by integrated battery(s) in said docking port or me be provided directly from the docking station or other connected power source.

A device for launching a drone using spring thrust, in which the means that control the unlocking of an ejection assembly from its armed position include a release housing containing a release chamber, at least one release element which, with the housing, delimits the chamber and is able to move, under the action of the pressure of a gas introduced into the chamber, from a position of rest to a release position in which the at least one release element unlocks the ejection assembly, and return means for returning the at least one release element to the position of rest. The invention also relates to a method for launching drones using the device and to a tool for implementing this method.

The present disclosure provides a deployment mechanism for arms of a drone. This mechanism is particularly of relevance to a drone that is housed in a container and is configured to be launched therefrom, and therefore is required to have an efficient deployment mechanism for its arms to be deployed immediately after the launch. The deployment mechanism is biased to its deployed state and is retained in its non-deployed state by external forces, such as the normal forces that are applied by the walls of the container on the arms while the drone is housed within the container. After the launch from the container, the above-mentioned forces are no longer applied to the arms of the drone and the deployment mechanism, causing a transition of the arms from their non-deployed state to their deployed state, in which they are in a position suitable for flying, i.e. activation of the rotors mounted on the arms.

An embodiment vertiport includes a main body portion having a lower space, a take-off and landing zone disposed in the lower space and spaced apart from the main body portion by a predetermined gap, a door portion disposed in the gap and configured to open or close the gap, a plurality of elevating portions disposed to surround the take-off and landing zone in the lower space, a ring-shaped portion surrounding the take-off and landing zone and connected to the plurality of elevating portions, wherein the ring-shaped portion is configured to be elevated by the plurality of elevating portions, and a plurality of generators disposed on the ring-shaped portion in a fixed position.

An embodiment vertiport includes a main body portion having a lower space, a take-off and landing zone disposed in the lower space and spaced apart from the main body portion by a predetermined gap, a door portion disposed in the gap and configured to open or close the gap, a plurality of elevating portions disposed to surround the take-off and landing zone in the lower space, a ring-shaped portion surrounding the take-off and landing zone and connected to the plurality of elevating portions, wherein the ring-shaped portion is configured to be elevated by the plurality of elevating portions, and a plurality of generators disposed on the ring-shaped portion in a fixed position.

The invention provides an aircraft launching opportunity determination method, device, system, equipment and medium, and the method comprises the steps: responding to an aircraft launching instruction, and obtaining criterion parameters in real time, the criterion parameters comprising meteorological data, aircraft attitude data and platform actual attitude data, the aircraft attitude data comprises an aircraft pitch angle, an aircraft roll angle and an aircraft yaw angle; obtaining platform prediction attitude data at a pre-execution moment according to the platform actual attitude data at the historical moment, and judging whether the launching platform is in a stable state or not according to the platform prediction attitude data and the platform actual attitude data at the pre-execution moment when the pre-execution moment arrives; and in a stable state, if each item in the criterion parameters meets a preset launching condition and is in an automatic launching mode, determining the target launching opportunity of the aircraft according to the criterion parameters. The method solves the problems that in the prior art, the reliability of the transmitting opportunity is low, and hysteresis exists.

Aircraft system and launching method and apparatus A method of controlling the altitude and / or velocity of a tethered aircraft, the method comprising the steps of: a charging phase, in which the energy of the aircraft is increased, a conversion phase following the charging phase, in which the increased energy is utilised to increase the altitude and / or velocity of the aircraft; a gliding phase, in which the aircraft is positioned for a further charging phase and conversion phase; and repeating the charging phase and conversion phase at least once.

The present invention belongs to the technical field of drone launch platforms, and in particular to a launch platform for a drone launch vehicle, which includes a launch frame, the bottom of which is rotatably provided with a rear support and two front support mechanisms, a through hole and a groove are provided on the launch frame, an ejection mechanism is provided in the groove, an ejection slider is slidably installed in the through hole, the ejection slider is connected to the ejection mechanism, a cavity is provided on the ejection slider, an elastic plate is slidably installed in the cavity, a force-bearing mechanism is connected to the elastic plate, a drone fixing mechanism is provided on the top of the ejection slider, the drone fixing mechanism includes a placement bar and two clamps, and the placement bar is connected to the top of the ejection slider. The present invention is easy to fix and operate, and only needs to place the drone, and then push the two clamps to clamp it. When the launch stroke is reached, the fixation can be automatically released by mechanical transmission, avoiding additional operations by the staff, and reducing the difficulty of operation.

An air vehicle assembly initialization and ejection system includes a canister configured to contain an air vehicle assembly, where the air vehicle assembly includes an onboard electronic system and at least one squib for ejecting the air vehicle assembly from the canister. The system further includes a magazine having a canister position configured to contain the canister. The system further includes a first signal path providing electrical communication of a first control signal between the canister position and the canister, the first control signal for causing the onboard electronic system to power up, and a second signal path providing electrical communication of a second control signal between the canister position and the canister, the second control signal for causing the at least one squib to detonate.

The invention provides an aircraft follow-up rotation supporting device, and relates to the technical field of aircraft launching, the aircraft follow-up rotation supporting device comprises an aircraft, a launching cylinder, a supporting seat, a tension spring, a fixing seat, a connecting rod, an adapter block and a guide seat, the supporting seat is arranged in the launching cylinder, a positioning pin is arranged on the supporting seat, and a positioning pin hole matched with the supporting seat is formed in an aircraft projectile body; the connecting block is fixedly connected with the guide seat and then connected with the supporting seat through the two connecting rods, and the supporting seat is fixedly connected to the launching cylinder. The aircraft moves to drive the supporting seat to slide for a certain stroke in the launching cylinder, and drives the connecting rod to complete the rotation action together after impacting the guide seat. Omni-directional supporting of the aircraft in the launch canister in the storage and transportation environment can be achieved through the follow-up rotation supporting device, the aircraft can synchronously move along with the aircraft during launch and rapidly rotate to be out of an aircraft canister outlet channel, and it is ensured that the aircraft safely and reliably exits from the canister.

The present invention relates to a method for constructing a launch / landing arrangement (101) for unmanned aerial vehicles (100) comprising a plurality of rail modules (102, 103), wherein a plurality of longitudinal rail modules (102), at least one transverse rail module (103), and at least one receiving carriage (104) are provided, wherein the plurality of longitudinal rail modules (102) are mechanically fixed to form a longitudinal rail (102A) and the transverse rail modules (103) are mechanically fixed to form a transverse rail (103A), and wherein the receiving carriage (104) is configured and designed to interact mechanically, at least temporarily, with an unmanned aerial vehicle (100) to be received therein.wherein a plurality of subsets of the plurality of longitudinal rail modules (102) are each assigned to a land transport means (106) and the land transport means (106) are arranged spaced apart from each other along a longitudinal direction (L) of a runway (107) to be formed from the longitudinal rail modules (102) on a substrate (U), the plurality of longitudinal rail modules (102) of the subsets of one of the land transport means (106) each forming a section (108) of the runway (107) is moved towards at least one adjacent land transport means (106) with at least one longitudinal rail module (102) of the adjacent land transport means (106), at least one free end of a longitudinal rail module (102) of the land transport means (106) is mechanically coupled to a free end of a longitudinal rail module (102) of the adjacent land transport means (106), wherein the continuous rail module (102) is formed from the longitudinal rail modules,The present invention relates to a device for carrying out the method.

The fragile cover comprises structural layers, a functional layer and a pressing plate, the structural layers are in the form of honeycomb layers and skin, the functional layer is arranged between the honeycomb layers of the two structural layers, by means of the structural advantages of the honeycomb layers, the structural weight is reduced, meanwhile, the functional layer is designed to increase rigidity, the stability of the fragile cover is improved, and the service life of the fragile cover is prolonged. In addition, the functional layer has the advantages of being neat in fracture, small in residue and the like, the function layer is beneficial to avoiding an object barrel outlet channel, and interference is prevented. The manufacturing process can be simplified, and the method is suitable for mass production and has the advantages of controllable quality, high reliability and the like.

The invention relates to the technical field of aircraft catapult-assisted take-off, and discloses a lodging avoidance mechanism for an aircraft catapult-assisted take-off device, comprising an avoidance frame mechanism mounted on the aircraft catapult-assisted take-off device; the receding frame mechanism comprises linkage arms and a supporting base, the linkage arms comprise the first linkage arm, the second linkage arm and the third linkage arm, the first linkage arm, the second linkage arm and the third linkage arm are sequentially hinged, and the ends, away from the second linkage arm, of the first linkage arm and the third linkage arm are hinged to the supporting base. An aircraft clamp for fixing an aircraft is arranged at one end, close to the second linkage arm, of the first linkage arm; the length of the first linkage arm is larger than that of the third linkage arm, and the aircraft takes off in a catapult-assisted mode in the direction from the first linkage arm to the third linkage arm. The problems that an existing aircraft catapult-assisted take-off device cannot ensure the fixing stability in the aircraft catapult-up process, and an aircraft clamp cannot be prevented from colliding with the tail of an aircraft are solved.

An embodiment vertiport includes a body portion, a take-off and landing portion disposed in the body portion and spaced apart from the body portion by a predetermined gap, a door portion disposed in the gap between the take-off and landing portion and the body portion and configured to be opened and closed, an elevation portion disposed in the body portion and configured to be raised and lowered with respect to the body portion, and a power generating unit slidably coupled to the elevation portion, wherein the power generating unit is configured to produce electrical energy using a downdraft generated by a take-off and landing operation of an aircraft on the take-off and landing portion.

A device for launching a drone using spring thrust, in which the means that control the unlocking of an ejection assembly from its armed position include a release housing containing a release chamber, at least one release element which, with the housing, delimits the chamber and is able to move, under the action of the pressure of a gas introduced into the chamber, from a position of rest to a release position in which the at least one release element unlocks the ejection assembly, and return means for returning the at least one release element to the position of rest. The invention also relates to a method for launching drones using the device and to a tool for implementing this method.

The air pressure ejection air cylinder piston of the unmanned aerial vehicle comprises a piston sleeve, the piston sleeve is of a cylindrical structure with one end closed and the other end open, a pull rope shaft is connected to the piston sleeve, and an air bleed hole is formed in the closed end of the piston sleeve; and the piston sleeve is sleeved outside the piston sleeve. The hydraulic cylinder is simple in structure, connection between the pull rope and the piston is facilitated, high-pressure gas in the piston is released through the vent hole formed in the piston sleeve, the internal temperature of the piston and the internal temperature of the cylinder barrel are prevented from being too high, and therefore damage to the pull rope is reduced; and through the arrangement of the vent hole, the stability of the pressure in the launching process is ensured while the gas is released.

The present invention discloses a split-type reconnaissance and detection robot and method. The split-type reconnaissance and detection robot includes a quadruped robot and a drone module; the drone module includes a stacked-wing drone carrying platform and a stacked-wing drone; the stacked-wing drone is installed in a launch tube, and a gas ejection device for launching the stacked-wing drone is provided in the launch tube; a lifting device is provided at the bottom of the stacked-wing drone carrying platform, and the lifting device is installed on the robot body. The split-type reconnaissance and detection robot provided by the embodiment of the present invention enables the quadruped robot to carry out aerial reconnaissance and detection of the area to be detected through the stacked-wing drone, and the quadruped robot performs land detection, and has the ability to realize two detection modes, land and air, and can adapt to a variety of complex working environments.

The present invention discloses an aircraft locking device, which belongs to the field of aircraft locking technology. The device includes a base and two limiting fastening frames. The base is provided with a through hole A and a notch, and the notch is connected to the through hole A. An eccentric locking mechanism is provided in the notch. The two limiting fastening frames are symmetrically arranged on the inner side of the through hole A and are movably connected to the base respectively. By utilizing the characteristic of the eccentric wheel to automatically find a stable center of gravity, the aircraft is automatically locked and unlocked, thereby improving the reliability of the locking device. The locking device does not need to be driven by a related driving mechanism, which simplifies the structure of the locking device and reduces the external dimensions of the locking device. It can be installed in a limited space, which helps to increase the number of locking devices installed on the launch device and improve the number of aircraft carrying capacity and application efficiency of the launch device.

The application belongs to the field of aircraft auxiliary take-off equipment, and particularly relates to an aircraft launching system and an aircraft. The aircraft launching system comprises a driving part I and a fixed releasing mechanism. The output end of the driving part I has a circular circumferential rotation stroke or a linear movement stroke. The fixed releasing mechanism comprises a support, a fixed releasing rod and two connecting rods, and the support, the fixed releasing rod and the two connecting rods form a parallelogram mechanism. The support is arranged opposite to the fixed releasing rod. The support is connected with the output end of the driving part I. The fixed releasing rod is provided with a fixed releasing structure for fixing and releasing the aircraft. The fixed releasing mechanism formed by the parallelogram mechanism can lower the fixed releasing rod to leave a flight space when the aircraft takes off, so that the aircraft can be prevented from colliding with the fixed releasing mechanism when taking off, and the use safety of the launching system is improved.

An aircraft assist system described herein includes an aircraft coupling counterpart attached to a strut of a landing gear of an aircraft, and an assist vehicle. The assist vehicle includes a frame, ground-engaging wheels mounted to the frame, a power source for driving one or more of the ground-engaging wheels, and a vehicle coupling counterpart for engagement with the aircraft coupling counterpart. The aircraft coupling counterpart and the vehicle coupling counterpart define a swivel connection for transferring a propulsive force from the takeoff assist vehicle to the aircraft. The aircraft coupling counterpart is disengageable from the vehicle coupling counterpart by upward movement of the aircraft coupling counterpart relative to the vehicle coupling counterpart.

A catapulting assembly comprises a catapulting guide rail, a first catapulting device and a catapulting carrier, the catapulting guide rail comprises a first end and a second end opposite to the first end, the catapulting carrier is used for loading a machine body to be catapulted, and the catapulting carrier can slide between the first end of the catapulting guide rail and the second end of the catapulting guide rail. The first ejection device is arranged at the first end of the ejection guide rail, the first ejection device can drive the ejection carrier to slide from the first end of the ejection guide rail to the second end of the ejection guide rail through elastic force, and the ejection carrier can release the machine body to be ejected when sliding to the second end of the ejection guide rail.

An aircraft assist system (38) described herein includes an aircraft coupling counterpart attached to a strut (26) of a landing gear (22) of an aircraft (10), and an assist vehicle (12). The assist vehicle (12) includes a frame, ground-engaging wheels (34, 36) mounted to the frame, a power source for driving one or more of the ground-engaging wheels (34, 36), and a vehicle coupling counterpart for engagement with the aircraft coupling counterpart. The aircraft coupling counterpart and the vehicle coupling counterpart define a swivel connection for transferring a propulsive force from the takeoff assist vehicle (12) to the aircraft (10). The aircraft coupling counterpart is disengageable from the vehicle coupling counterpart by upward movement of the aircraft coupling counterpart relative to the vehicle coupling counterpart.

The invention provides an aircraft pushing and punching device. The aircraft pushing and punching device comprises a cylinder assembly, at least one actuator cylinder, at least one fire pushing and punching device and a tray. A lifting rod and a piston are arranged in the actuating cylinder, one end of the lifting rod penetrates out of the actuating cylinder and extends to be fixedly connected with the tray, the other end of the lifting rod is fixedly connected with the piston, the outer ring face of the piston is attached to the inner side face of the actuating cylinder and can slide in the axial direction of the actuating cylinder, and the hot work pushing and punching device is fixed in an end cover at the end, penetrating out of the lifting rod, of the actuating cylinder. The tail end of the aircraft is arranged on the tray; a central long blind hole is formed in the lifting rod, the central long blind hole penetrates through the lifting rod and is communicated with an inner cavity of the actuating cylinder, and a drainage hole communicated with the central long blind hole is formed in the lifting rod; the hot work pushing and punching device works to generate gas, the gas enters the rod cavity and pushes the piston to move in the first direction, the piston drives the lifting rod to move in the first direction, and when the drainage hole in the lifting rod is communicated with the rod cavity, the gas in the rod cavity enters the rodless cavity through the central long blind hole.