41results about "Supports/holding devices" patented technology

A seat assembly includes a seat pan that is tilted automatically by way of a seat bucket moving up and down relative to a base structure. The seat bucket is pivotably coupled to a carrier. The carrier and the seat bucket each follow respective channels of a base structure. The movement of the seat bucket along the channel of the base structure causes the pivoting of the seat bucket relative to the carrier. The channels are shaped with an angular orientation resulting in the seat pan angle changing as the seat bucket moves up and down.

A seat restraint system holds a user to a seating rig using multiple restraints. These restraints can be released simultaneously using a release actuation system, thereby quickly freeing the user from the seating rig. Certain types of restraints are extendable relative to the seating rig between retracted and extended positions to facilitate freedom of movement of the user. The release actuation system allows the restraints to extend without unintentional actuation of the release mechanism. The release actuation system allows the restraints to be released regardless of the position (e.g., retracted, extended, therebetween) of the extendable restraints.

The invention provides an intelligent early warning system and method for self-adaptive active protection of a helicopter seat, and belongs to the technical field of helicopter anti-crash seats, the system comprises a seat, a sensing system, a seat driving system, a warning system, a safety airbag system, a human body feature recognition system, a test passenger sitting posture data system and a control system; according to the function of actively adjusting the seat to the optimal protection posture through early warning, casualties caused by the fact that the seat is adjusted to the optimal protection position in time due to the fact that no enough response time exists in danger when the seat is manually adjusted in the past can be avoided, meanwhile, the three-way safety air bag is adopted, the buffering performance is better, the damping capacity is higher, safety is higher, and the safety performance is better. Moreover, the complexity of the manual adjustment process is reduced, the adjustment time of the seat is greatly shortened, the comfort of the trail passengers is improved, the seat can meet the riding requirements of the trail passengers with different body types, the trail passengers can realize the lifting adjustment of the seat without getting up, and the riding comfort of the seat is greatly improved.

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 an armor detachable anti-crash seat, which comprises a main framework, a multifunctional back-flipping seat basin, a chair leg lock and a slide rail, the multifunctional back-flipping seat basin is arranged on the main framework, a height adjusting compensation mechanism is connected between the multifunctional back-flipping seat basin and the main framework, the slide rail is arranged below the main framework, and the lower end of the main framework is arranged on the slide rail through the chair leg lock; two detachable side armor assemblies, namely a left side armor assembly and a right side armor assembly, are arranged on the left side and the right side of the multifunctional back-flipping seat basin respectively, and a detachable bottom middle armor assembly is arranged on the lower part of the multifunctional back-flipping seat basin. The application has superior anti-crash protection performance, can meet the height adjusting requirements of the seat with the protective armor and the seat without the protective armor, and can meet the requirements of quick disassembly of all armors.

The kinetic seat assembly includes a primary seat cushion frame, a secondary seat cushion frame movable relative to the primary seat cushion frame, a primary seat back frame, a secondary seat back frame movable relative to the primary seat back frame, a pair of lateral dampers extending between the primary seat back frame and the secondary seat back frame, a pair of vertical dampers extending between the secondary seat back frame and the primary seat cushion frame, a pair of fluid reservoirs providing fluid to the pair of lateral dampers and the pair of vertical dampers, and an electronic control unit configured to control the rate at which fluid is provided to and extracted from each of the dampers to control the damping effect. In an embodiment, the ends of the lateral dampers are allowed to move freely relative to the secondary seat back frame.

According to the invention, a seating device, in particular an aircraft seating device, for mounting in an aircraft, comprises a mounting unit (14a; 14b) having two spaced-apart seat feet (16a, 18a; 16b, 18b), a seat base (30a; 30b) having a seat floor (32a; 32b) and a backrest (34a; 34b), wherein the seat base (30a; 30b) is connected to the two seat feet (16a, 18a; 16b, 18b) in side regions (36a, 38a; 36b, 38b), and a bearing unit (40a; 40b) which pivotably connects the seat base (30a; 30b) to the seat feet (16a, 18a; 16b, 18b) in an upper region. attaches and with which the seat base (30a; 30b) can be pivoted between an upright sitting position and a maximum comfort position, with a locking device (42a; 42b) which is intended to secure the seat base (30a;30b) to lock at least in the upright sitting position and in the comfort position, wherein the locking device (42a; 42b) has at least one actuator (44a; 44b) which is attached below the seat base (32a; 32b) of the seat body (30a; 30b) and is designed to assist an adjustment of the seat body (30a; 30b) towards the comfort position, is proposed.;

An aircraft seat assembly (100) including stanchions (112) defining elongated guide channels (120) and elongated motion sleds (116) nested in the guide channels and affixed to a seat bucket (104). An energy absorber (124) implemented as a wire bender assembly is coupled between the stanchions and the motion sled. In use, the elongated guide channels guide motion of the motion sleds and the wire bender assemblies attenuate energy during a dynamic event exceeding a predetermined threshold load value. The elongated interface between the guide channels and motion sleds serve to transfer excessive loading to the seat frame thereby protecting the seat assembly from damage and the occupant from excessive lumbar spinal loads.

The invention discloses an air bag assembly used for restraining and protecting the head and the neck and an ejection seat, the air bag assembly used for restraining and protecting the head and the neck comprises a headrest plate, two neck restraining devices and a head buffering device, the two neck restraining devices and the head buffering device are arranged on the headrest plate, and the headrest plate is used for being arranged on a seat backrest. The neck restraining devices are located on the two sides of the neck of the human body on the seat, and the head buffering device is located above the head of the human body on the seat. While the requirements for reliable structure, quick response and high adaptability are met, strong constraining force and a high energy absorption effect are actively provided for the head of a pilot, and the injury risk of the head and the neck is reduced.

The utility model discloses an air bag energy absorption protection system which is assembled on an anti-crash seat of a helicopter and comprises cushion air bags arranged on the two sides of a cushion, back cushion air bags arranged on the two sides of a back cushion, a safety belt air bag capable of serving as a safety belt to be installed around the neck and an inflation and deflation device capable of inflating and deflating the air bags. The seat cushion air bag comprises a seat cushion air bag skin positioned on the upper layer and a seat cushion bag body positioned on the lower layer; the back cushion air bag comprises a back cushion air bag skin located on the outer layer and a back cushion bag body located on the inner layer. The safety belt air bag comprises a safety belt air bag skin located on the outer portion and a safety belt bag body located on the inner portion. The system can carry out energy absorption protection on two legs, two sides of an upper body and the head and neck of a passenger during collision, and the riding experience is not affected under the normal flight condition.

The present invention pertains to the field of life-saving equipment having accommodation for passengers and crew, comprising capsules (1), wherein each capsule (1) is impact-resistant, has an oval shape, and comprises a seat (2), wherein said seat (2) is provided with safety belts (4), wherein a sphere (6) is mounted to withstand an initial impact, such that when they undergo said initial impact, the spheres (6) issue a command to the seat, assisting in cushioning the impact inside the capsule (1), which is oval and formed in two parts, and is further provided with a plurality of airbags (7) strategically fastened to the internal walls, as well as apertures (8) to enable oxygen exchange with the environment, and wherein each capsule additionally comprises a manual safety system equipped with an internal battery for use in the event of aircraft failure.

The invention belongs to the technical field of unmanned aerial vehicles, and particularly relates to an eVTOL safety seat system of a heavy-load unmanned aerial vehicle, and the system comprises a sensing layer which is used for firstly measuring data of a safety seat and then collecting the measured data; the decision-making layer is used for performing real-time analysis and decision-making according to the data acquired by the sensing layer, generating a corresponding instruction and diagnosing whether the unmanned aerial vehicle has a fault or not; and the execution layer is used for correspondingly controlling the unmanned aerial vehicle according to the instruction of the decision layer. According to the invention, various sensors work cooperatively, environment information can be captured comprehensively, and the influence of loss or error of a single signal is reduced.

The invention discloses an output control method for separating parachute shooting in an ejection lifesaving seat, which comprises the following steps: separating parachute shooting electric detonators comprise two paths of separating electric detonators and one path of parachute shooting electric detonators, and the method comprises the following steps: detecting the separating electric detonators 1, 2 and the parachute shooting electric detonators in sequence when the ejection lifesaving seat is electrified for self-inspection; the ejection lifesaving seat sends the detection result of each electric detonator to the VMC through the health management data packet; and after the ejection lifesaving seat is judged to meet the releasing condition, the program controller measures the longitude, latitude, flight speed and height of the aircraft according to an inertial measurement module in the program controller, and dynamically controls the separation electric detonators and the parachute ejection electric detonators to output according to a time sequence. The problem that in an existing control mode of the ejection lifesaving seat, due to the fact that the static pressure measurement value cannot correctly reflect the real environment air pressure, the height data obtained based on the static pressure signals have large errors, and effective support cannot be provided for control over an ejection lifesaving system is solved.

The utility model relates to the field of aviation technology, concretely relates to a novel airplane seat with double functions of shock absorption and anti-crash, which comprises a seat back, a seat cushion and an energy absorption structure, the seat back is connected with the seat cushion, the energy absorption structure comprises horizontal wave springs, vertical wave springs and a partition, the horizontal wave springs comprise a plurality of wave spring units stacked together, each wave spring unit is composed of two wave-shaped plate bodies stacked and fixed, and each wave-shaped plate body is a continuous sinusoidal structure, the utility model integrates the functions of shock absorption and anti-crash in the same seat structure, in daily flight, the seat realizes the shock absorption function through the energy absorption structure, effectively buffers the vibration and improves the comfort of passengers, in a crash accident, the energy absorption structure absorbs energy and buffers through deformation, significantly reduces the impact force on passengers and improves the safety performance and applicable scenarios of the seat.

The present application relates to an aerial maneuvering apparatus, a control method thereof, and a computer-readable storage medium. An aerial maneuvering apparatus includes a seat in which a safety airbag and a parachute are stored, and an escape portion configured to support the seat mounted to the escape portion, coupled to the aerial maneuvering apparatus to form a part of the aerial maneuvering apparatus, and configured to enable a passenger to perform an emergency jump with the seat to the outside of the aerial maneuvering apparatus when the escape portion is separated from the aerial maneuvering apparatus.

Provided are a parachute that can be improved in strength as compared with a conventional parachute even though the number of panels is relatively small, and can be increased in size at low cost, a safety device and a flight vehicle provided with the parachute. A parachute 100 includes an umbrella body 11 including an umbrella top portion 14 and an umbrella edge portion 15, and a plurality of lines 12. A portion along a circumferential direction in a range from the umbrella edge portion 14 to a position on the way to the umbrella top portion 15 is folded in a triple fold in the circumferential direction of the umbrella body 11 and fixed by sewing or the like to form a fold portion 17, and one end of one line 12 is connected to the fold portion 17.

An ejection seat 14 comprise a seatback 30, a headrest 42 located at an upper end of the seatback, and a pitot tube 102 rotatably coupled to the headrest. A pitot restraint assembly may be operably co

The invention relates to an aircraft seating device, in particular an aircraft pilot seating device, for mounting in an aircraft, comprising a mounting unit (14a; 14b) having two spaced-apart seat feet (16a, 18a; 16b, 18b), a seat base (30a; 30b) having a seat floor (32a; 32b) and a backrest (34a; 34b), wherein the seat base (30a; 30b) is connected to the two seat feet (16a, 18a; 16b, 18b) in side areas (36a, 38a; 36b, 38b), and a height adjustment device (100a; 100b) by means of which the seat base (30a; 30b) can be adjusted in height on the seat feet (16a, 18a; 16b, 18b). 18a; 16b, 18b) is attached.It is proposed that the height adjustment device (100a; 100b) has a gear unit (102a; 102b) by means of which the seat base (30a; 30b) can be continuously adjusted between a lower position and an upper position, wherein the gear unit (102a; 102b) has at least one adjustment gear (104a, 106a; 104b, 106b) which is functionally arranged between the seat base (30a; 30b) and the stand unit (14a; 14b).

A seat system for use in a crew escape system of a space transport vehicle comprises a seat having a backrest with a supporting surface. The seat is configured to be installed in a cabin area of the crew escape system so it can rotate about a first axis between a first position where the seat faces a first direction, and a second position where faces a second direction that is opposed to the first direction. The seat system further comprises a control unit configured to control a rotation of the seat at least between the first position and the second position in dependence on at least one signal which is indicative of a trajectory of the crew escape system.

The invention relates to a seat, particularly for an aircraft, comprising: - at least one seating structure (22), and - a lower structure (11) comprising at least one guide element (39) including a guide groove (43), - said guide groove (43) comprising a first portion and a second portion, referred to as the inclined portion, - said seat (10) further comprising at least one seat belt attachment (48) and at least one attachment support (50), - said seat belt attachment (48) being rotatably mounted relative to the attachment support (50) by means of an attachment pin, - said attachment support (50) being rotatably mounted relative to the seating structure (22) by means of a support pin, - the head of the attachment pin (55) being disposed inside the inclined portion of the guide groove (43) when the seat (10) is in an upright position. Figure 2b

The invention relates to an inertia-operated unlocking device (21) comprising: - a housing (22), - a support (23) carrying a pin (25), - a weight (26) capable of translational movement under the effect of inertia, - a first shaft (27) rotatably mounted inside an opening in the support (23) and having at least one end with a flat, - a second shaft (30) having a first end with a flat for bearing against the flat of the first shaft (27) and a second end with a weight stop (32), - a first elastic element (35) disposed between the weight (26) and the housing (22), - a second elastic element (36) disposed between the second shaft (30) and the housing (22), and - a third elastic element (37) mounted under compression between the housing (22) and the support (23). Figure 3a

The utility model relates to the technical field of safety belt devices, in particular to a high-strength polypropylene fiber yarn integrated lock safety belt provided with a locking mechanism, which comprises an external shell, a sealing cover plate is assembled on the surface of the external shell, a release port is arranged on the side surface of the external shell, a rotating column is assembled on the surface of the release port, a sunken layer is arranged at one end of the rotating column, and a locking mechanism is arranged at the other end of the rotating column. A sunken layer is arranged on one side of the rotating column, an extending end is assembled in the sunken layer, a return spring is assembled on the surface of the extending end, a vacant layer is arranged at the front end of the other side of the rotating column, a front end is installed on the surface of the rotating column, and a clamping column is assembled on the surface of the front end. The locking mechanism can ensure that the safety belt made of polypropylene fibers inside is clamped and fixed, the stability of the safety belt is ensured in part of working scenes, the phenomenon that the safety belt freely falls off or slips off is avoided, the locking mechanism prevents the safety belt from being released by clamping the middle rotary column inside, and the safety is quite high.

A rescue hoist includes a housing mountable to an airframe, a cable drum rotatably mounted in the housing, a traction sheave rotatably mounted in the housing positioned to one side of the cable drum, a cable, and a hook mounted to one end of the cable. The cable is wrapped around the cable drum in a first direction, over the traction sheave in a second direction opposite the first direction, and exits the housing under the traction sheave. The housing is compact and configured to be mounted to an aircraft under-wing.

Systems and methods for a drone taxi system for ground-level transportation are disclosed. The system includes a multi-rotor drone apparatus capable of carrying individuals at low altitudes, approximately 1-2 feet off the ground. The system includes advanced stabilization and obstacle detection capabilities, a secure harness with a quick-release mechanism, and an inflatable safety vest that activates during emergencies. Controlled via a smartphone application, the system enables users to request drone rides, map routes, and view trip status in real-time. The drone ensures safe and efficient transit over short distances, combining the functionality of ride-sharing platforms with the experience of low-altitude travel. This system addresses urban mobility challenges, offering a safe, efficient, and eco-friendly alternative to traditional ground-based transportation methods while minimizing risks and maximizing convenience for users.

An ejection system is disclosed herein. The ejection system includes a seat having a seat bucket and a seat back, a passive head and neck protection device coupled to the seat back, and an ejection initiation system. The ejection initiation system includes a pull handle coupled to the seat bucket, a first connector having a first end coupled to the pull handle, an ejection sequence initiation device configured to initiate an ejection sequence, a passive head and neck protection mechanism configured to activate the passive head and neck protection device, and an ejection pull connector having a first end and a second end, the second end coupled to the ejection sequence initiation device and to the passive head and neck protection mechanism.

To provide a kinetic seat assembly. [Solution] The kinetic seat assembly includes a primary seat cushion frame, a secondary seat cushion frame movable relative to the primary seat cushion frame, a primary seat back frame, a secondary seat back frame movable relative to the primary seat back frame, a pair of lateral dampers extending between the primary and secondary seat back frames, a pair of vertical dampers extending between the secondary seat back frame and the primary seat cushion frame, a pair of fluid reservoirs that supply fluid to the pair of lateral dampers and the pair of vertical dampers, and an electronic control unit configured to control the rate at which fluid is supplied to and withdrawn from each of the dampers in order to control the damping effect. In the embodiment, the ends of the lateral dampers are made freely movable relative to the secondary seat back frame.

The invention relates to an aircraft seat device, in particular an aircraft pilot seat device, for mounting in an aircraft, comprising a stand unit (14a; 14b), which has two mutually spaced seat feet (16a, 18a; 16b, 18b); a seat main part (30a; 30b), which has a seat base (32a; 32b) and a backrest (34a; 34b), the seat main part (30a; 30b) being connected, in lateral regions (36a, 38a; 36b, 38b), to the two seat feet (16a, 18a; 16b, 18b); and a height adjustment device (100a; 100b), by means of which the seat main part (30a; 30b) is attached to the seat feet (16a, 18a; 16b, 18b) at an adjustable height. According to the invention, the height adjustment device (100a; 100b) has a gear unit (102a; 102b), by means of which the seat main part (30a; 30b) can be continuously adjusted between a lower position and an upper position, the gear unit (102a; 102b) having at least one adjustment gear (104a, 106a; 104b, 106b) which is functionally positioned between the seat main part (30a; 30b) and the stand unit (14a; 14b).

The invention relates to a driver seat and a quick unlocking device of a double-inertia lock structure of the driver seat, and relates to the technical field of aero seats, the quick unlocking device comprises an upper cross beam, and the upper cross beam is used for being installed on a seat body; two inertia winding drums are arranged on the upper cross beam, shoulder straps are arranged on the inertia winding drums, inserting buckles sleeve the shoulder straps, lock tongues are arranged at one ends of the shoulder straps, the inserting buckles are in sliding connection with the shoulder straps, and the inserting buckles are located between the lock tongues and the inertia winding drums in the length direction of the shoulder straps; the number of the synchronous shoulder lock assemblies is two, the synchronous shoulder lock assemblies and the lock tongues are arranged in a one-to-one correspondence mode, and the lock tongues and the corresponding synchronous shoulder lock assemblies are matched in an inserted connection mode; the linkage unlocking assembly is in transmission connection with the two synchronous acromioclavicular assemblies; and the external unlocking assembly is connected with the linkage unlocking assembly. The restraint stability of the safety belt on the driver seat is improved, the unlocking convenience of the safety belt on the driver seat under the emergency working condition is improved, and therefore the safety of a driver is improved.