158results about "Supports/holding devices" patented technology

The invention discloses a vertical take-off and landing fixed-wing aircraft, and relates to the technical field of aircrafts. According to the invention, the conversion from a multi-rotor flight mode to a fixed-wing flight mode and from the fixed-wing flight mode to the multi-rotor flight mode can be easily realized. Due to the structural layout characteristics of the aircraft, the safety of the aircraft is guaranteed, and the aircraft can be safely and reliably landed according to the fault degree and urgency of the aircraft even if the aircraft breaks down seriously and only forced landing can be selected. Through multi-rotor-wing assisting control, the forced landing buffering function of the telescopic empennage assembly and the safety protection measure of a protection sponge lining in the manned cabin, various safety modes and measures such as an internal safety protection air bag, an external safety protection air bag and a forced landing parachute of the manned cabin can be selectively used according to the fault degree and urgency of the aircraft; and safe or low-damage forced landing of the aircraft is realized.

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.

The invention discloses a wearable three-duct power single-person aircraft which comprises a power system, an avionics system, a man-machine interaction system, a safety lifesaving system and a wearable aircraft body. The power system adopts a three-duct pneumatic layout and is arranged in the shape of a Chinese character'pin ', two duct units on the front side are located on the two sides of the wearable machine body at the same height, and the mounting height of the duct unit on the rear side is higher than that of the duct unit on the front side; the man-machine interaction system is located on the left side of the wearable fuselage and the human head and used for manually controlling flight and monitoring the flight state. The safety lifesaving system is located on the upper portion of the wearable machine body and used for guaranteeing personnel safety in emergency. The aircraft has the characteristics of compact structure, high stability, simplicity and convenience in operation, good safety and the like.

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 singular energy absorber and an offset pilot seat including the same. The pilot seat includes a seat base, a seat bucket positioned laterally offset relative to a centerline of the seat base, a singular motion controller movably coupling the seat bucket to the seat base, wherein the singular motion controller is centered relative to the seat bucket and laterally offset relative to the seat base, and the singular energy absorber associated with the singular motion controller, the singular energy absorber operative to maintain relative positions of components of the singular motion controller during normal use of the rotorcraft pilot seat and allow relative motion between the components of the singular motion controller during a dynamic event.

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.

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 relates to the field of aircrafts, in particular to a portable single-person low-altitude vector jet aircraft with a folding wing structure, the portable single-person low-altitude vector jet aircraft comprises a rack part, a power part and a load part, the power part is arranged below the rack part, and the load part is arranged below the power part; according to the portable single-person low-altitude vector jet aircraft with the folding wing structure, through the design of the telescopic framework of a multi-connecting-rod structure, the aircraft can be easily folded when not used, the occupied space is small, carrying and storage are convenient, and the problems that a traditional single-person aircraft is large in size and difficult to carry are solved; the applicability and convenience of the aircraft are improved; meanwhile, the structural strength of the wings in the unfolded state is ensured through the multi-point supporting design of the telescopic framework, the stability and safety of the aircraft are improved, the air resistance of the aircraft is reduced through the design of the wing skin, the protective cover, the conical cover, the wind tunnel and the fairing, the aerodynamic performance is effectively improved, and the aircraft is more efficient in the flight process.

The invention discloses an escape device of a single-person aircraft. The escape device comprises an open type rack, a parachute, a parachute shooting rocket, a bearing device, a separation mechanism and an escape handle. Wherein the open type machine frame is formed by combining a plate, a U-shaped beam, an L-shaped beam, a hoop and a connector assembly, a person is located on the inner side of the U-shaped machine beam, supports on the two sides serve as supporting handrails, the upper portion of the L-shaped beam serves as a placing area of other assemblies, and the connector assembly is locked on a machine body framework through the hoop. In order to solve the problem that an existing parachute is heavy in weight, the invention provides a lifesaving scheme for a single person, the protection function on personnel is emphasized, one-key separation of the personnel and the aircraft is realized through a quick switch when the aircraft breaks down, and the escape personnel stably land under the protection of the parachute. Compared with lifesaving protection for a complete machine system, the escape device only for personnel protection has great advantages in weight and size.

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.

A paragliding harness (14) comprising a seat (16), a backrest (17), two paragliding wing attachment points, and a reserve harness connection device (1) for the harness (14) intended to be connected to a reserve parachute (13), characterized in that the reserve harness connection device (1) comprises: two reserve risers (3) attached to the harness (14) laterally on either side of the seat (16), at or above the paragliding wing attachment points, and an automatic system for righting the pilot upon deployment of the reserve parachute, comprising two righting lines (7), each attached to the backrest (17) or to the lateral periphery of the backrest (17) and to one of the reserve risers (3). Figure for the abstract: 1

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 utility model provides a restraint system for preventing upper limbs from being thrown under the action of airflow, which comprises an elbow guard, a lead, a central pull ring, an upper joint, a lower joint, a power supply, an ejection seat basin and a travel switch, and two ends of the elbow guard are electrically connected with the upper joint through the lead; the lower joint is fixedly connected with the ejection seat basin and is electrically connected with the power supply; one end of the central pull ring is a free end, the other end of the central pull ring is provided with a toggle travel switch structure, the upper connector is electrically connected with the lower connector, and when a pilot pulls the central pull ring, the travel switch is turned on and electrified, so that the artificial muscle wires arranged on the elbow guard contract under the action of current to generate tensioning force, and constraint is provided for the forearm and the upper arm of the pilot. The upper connector and the lower connector are plug-in type connectors, when the pilot separates the body from the chair, the upper connector and the lower connector are separated, the artificial muscle on the elbow guard loses the tensioning force, and the upper limbs of the pilot return to normal. The device is convenient to operate, and the influence of an active constraint mode on a pilot is reduced to the minimum.

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.

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.

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.

The invention relates to a system for measuring the fatigue (11) of a mechanical structure (10), comprising: - a first force sensor (19.1) capable of generating a first signal (S1) representative of a force applied to a first mechanical part (13) of the mechanical structure (10); - a second force sensor (19.2) capable of generating a second signal (S2) representative of a force applied to a second mechanical part (14) of the mechanical structure (10); and - an electronic processing module (21) configured to calculate a correlation coefficient (Corr(S1, S2)) between the first signal (S1) and the second signal (S2), and to indicate a state of fatigue of the mechanical structure (10) as a function of a temporal change in the previously calculated correlation coefficient (Corr(S1, S2)).

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.