99results about "Supports/holding devices" patented technology

This invention pertains to aircraft seating, specifically a double-decker semi-reclining airplane seat designed to enhance passenger comfort in economy class. It comprises a front support frame, a rear support frame, a lower seat, and an upper seat. The support frames are positioned parallel and obliquely on a slide rail. The lower seat, situated between the frames, features a movable seatback and a hinged seat base. The upper seat includes a hinged seatback, seat base, and leg support, with a footrest platform hinged to the front support frame. This design optimizes limited cabin space while providing a more ergonomic seating arrangement. Evenly distributing body weight reduces pressure on the waist, hips, and legs, alleviating discomfort from prolonged sitting. Compared to traditional economy seats, this innovation offers improved reclining support, enhancing overall passenger comfort during long flights.

A 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 for providing a fluid into the pair of lateral dampers and the pair of vertical dampers, and an electronic control unit configured to control the rate at which the fluid is provided to and drawn out of each of the dampers to control a damping effect. In embodiments, an end of the lateral dampers is permitted to move freely relative to the secondary seat back frame.

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.

An armored seating assembly for a rotorcraft or other aircraft (e.g., for a pilot or operator) includes a wing armor panel capable of rotational and vertical movement relative to the seat base when adjusted by the operator. For example, a carriage attached to the armor panel translates along a carriage slot in the seat base, stabilized in the carriage slot by orthogonal sets of bearings (e.g., lateral bearings and longitudinal bearings) and allowing the wing armor panel to be vertically adjusted relative to the seat base (e.g., to accommodate pilots of varying heights). The armor panel is coupled to the carriage by hinges allowing the panel to pivot or rotate away from the seat base, in order to facilitate entry to and egress from the seat.

The utility model belongs to the technical field of seats, and particularly relates to a seat energy absorber using a turnup pipe, which comprises an inner sleeve and an outer sleeve sleeved outside the inner sleeve, an inner sleeve connecting lug and an outer sleeve connecting lug are respectively arranged at the outer ends of the inner sleeve and the outer sleeve, the inner sleeve and the outer sleeve are both made of carbon fiber materials, and the turnup pipe is arranged in the outer sleeve. A layer of stainless steel sleeve is arranged on the outer surface of the inner sleeve, one end or two ends of the stainless steel sleeve is / are provided with a turnup pipe which is formed by firstly flanging outwards and then flanging, and the outer surface of the turnup pipe is connected with the inner surface of the outer sleeve in a bonding mode. The energy absorber has no influence on passengers and the environment, is low in manufacturing, mounting and maintaining cost, light in weight and high in strength, and is suitable for aero seats.

The present disclosure discloses a landing aid for a parachutist, in particular for a tandem jump or landing with heavy equipment, having an air bag, which protects the parachutist during landing, wherein the air bag has an inflow opening through which air can flow into the air bag in order to fill it by means of the airstream. It is provided that the landing aid comprises a spring element, by means of which the inflow opening is held in the correct position with respect to the air flow and / or an unpacking process of the air bag is supported.

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 utility model provides a belt tensioning mechanism adjusting device, which is characterized in that a belt winding wheel is matched and connected with a ratchet wheel and a belt, so that the belt winding wheel synchronously moves to wind the belt, one end of a fixed pawl component is fixed on a seat, and the other end of the fixed pawl component is provided with a support, an inclined surface matched with a movable pawl to move and a fixed pawl unidirectionally meshed with the ratchet wheel; the movable pawl assembly comprises a rocker arm and a movable pawl in a one-way meshing structure with the ratchet wheel, the rocker arm and the movable pawl are connected through a fixed shaft and rotate around the fixed shaft, a limiting step is arranged on the support, the ratchet wheel is pushed through the movable pawl, the waistband is rolled, and the tightened waistband is limited and kept tightened through the one-way meshing structure of the fixed pawl and the ratchet wheel. The movable pawl is matched with the inclined face to jack up the fixed pawl, disengage from meshing with the ratchet wheel and move to the limiting step, and after the fixed pawl moves to the limiting position, the movable pawl is pressed up to disengage from meshing with the ratchet wheel through matching of the inclined face, and the restrained waistband is released.

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.

An assembly for an energy attenuation system is described. The assembly offers a lower profile configuration that fits better into tight spaces that exist in the compact seats that are required for military helicopters. The assembly includes a cable (110) that is oriented and positioned to work with the profile. The assembly includes an actuator which ejecting the pins (106) in a multi-stage sequence. The design of the assembly also ensures the pins cannot back drive when the pins are in the ejected position. Additionally, the pins may have part commonality reducing a unique part of the assembly.

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.

A seat assembly includes a seat pan (132) that is tilted automatically by way of a seat bucket (106) moving up and down relative to a base structure (102). The seat bucket is pivotably coupled to a carrier (104). The carrier and the seat bucket each follow respective channels (120, 124) 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 control system for a component of a rescue hoist (210) attached to an aircraft is disclosed. In various embodiments, the control system includes a first bus (270) extending between a control module (252) of the rescue hoist and a control input device (254); a second bus (272) extending between the control module of the rescue hoist and the control input device; and a hardwire extending between the control module of the rescue hoist and the control input device.

A bulkhead-mounted aircraft seat assembly (100) configured for independent vertical and horizontal adjustment includes an aircraft seat (102) (seatback and seat frame / cushion) for supporting a pilot, passenger, or other occupant. Parallel rails (104) attach to the bulkhead (110) and extend along the bulkhead (110) (vertically or near vertically) with opposing slots (104a) set into each rail (104). A sled (202) translates along the rails (104) via paired sliding members (112) set into the slots (104a), each pair of sliding members (112) connected to an axle extending through the sled (202). A four-bar linkage attached to the sled (202) and to the aircraft seat (102); the four-bar linkage extends from a default position to allow the aircraft seat (102) to translate along a horizontal linear rail under the seat while maintaining a stable vertical reference point above the cabin floor. The seat (102) is independently configured for substantially vertical adjustment via a metering plate (106) attached to the bulkhead (110).

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.;

A passenger seat assembly includes a leg, a crushable insert, and a connector assembly. The leg includes an end and a slot extending through the leg proximate to the end, and the slot has a first slot end a second slot end. The crushable insert is retained within the slot, and the connector assembly may connect the leg with a track fitting assembly. The connector assembly includes at least one connector that is at least partially positioned within the slot between the second slot end and the crushable insert such that the connector deforms the crushable insert during a dynamic event.

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.

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.

A passenger seat assembly includes a leg, a crushable insert, and a connector assembly. The leg includes an end and a slot extending through the leg proximate to the end, and the slot has a first slot end a second slot end. The crushable insert is retained within the slot, and the connector assembly may connect the leg with a track fitting assembly. The connector assembly includes at least one connector that is at least partially positioned within the slot between the second slot end and the crushable insert such that the connector deforms the crushable insert during a dynamic event.

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 one-button linkage unlocking device provided by this invention includes an unlocking handle assembly, a steel cable assembly, and a locking assembly. The steel cable assembly includes an active steel cable, a cylindrical cover, a cylindrical body, a pull block, a pull block connecting plate, and a driven steel cable. One end of the active steel cable is connected to the unlocking handle assembly, and the other end passes through the cylindrical cover and connects to one end of the pull block. The other end of the pull block is threadedly connected to the pull block connecting plate, which is located inside the cylindrical cover and has multiple driven steel cables mounted on it, each connected to a multiple locking assembly. Pulling the active steel cable causes the pull block connecting plate to move within the cylindrical body, thereby driving the driven steel cables and simultaneously unlocking multiple locking assemblies. This invention is applied to unlocking aircraft seat parachute packs, reducing the separation time of the backrest parachute from the seat, reducing the number of operation steps during separation, achieving one-button separation of the parachute, and ensuring the stability of the parachute separation state.

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.

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.

A 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 for providing a fluid into the pair of lateral dampers and the pair of vertical dampers, and an electronic control unit configured to control the rate at which the fluid is provided to and drawn out of each of the dampers to control a damping effect. In embodiments, an end of the lateral dampers is permitted to move freely relative to the secondary seat back frame.

An electric vertical take-off and landing aircraft having a disc-shaped blended wing-body that houses power sources and controls. Thrust pod arms are attached to the blended wing-body and each arm has a one of a set of thruster pairs. An ingress / egress hatch is attached to the rear surface. Navigation and strobe lights are located on the outside edge. Front landing gear is attached to the upper surface including pair of parallel motor pod struts. Main landing gear is attached proximate the trailing edge and a set of right and left elevons is attached to the rear surface proximate the main landing gear. A cockpit area including a viewing window is formed on the blended-wing.