The Boeing Company

Gerald F Herndon

Douglas Alan McCarville

David L Banks

Joseph A Marshall, Iv

Robert G Vos

Michael B McGrady

James M Huber

Jerry T Shearer

Isaac R Bakker

Stephen F Sielaff

Kenneth Harlan Griess

David Mitchell Anderson

Joseph A Marshall

Robert Thomas Johnson

David R Gladish

Isaac Ron Bekker

Roger F Yurczyk

Douglas A Mccarville

A conformal, load bearing, phased array antenna system having a plurality of adjacently positioned antenna aperture sections that collectively form a single, enlarged antenna aperture. The aperture sections are each formed by intersecting wall panels that form a honeycomb-like core having a plurality of electromagnetic radiating elements embedded in the wall panels that form the core. The aperture wall panels are assembled onto a single, multi-faceted back skin, bonded thereto, and then machined to produce a desired surface contour. A radome formed by a single piece of composite material is then bonded to the contoured surface. Antenna electronics printed wiring boards are also bonded to an opposite side of the back skin. The contour is selected to match a mold line of a surface into which the antenna system is installed. The antenna is able to form an integral, load bearing portion of the structure into which it is installed.

Design and fabrication methodology for a phased array antenna with integrated feed structure-conformal load-bearing concept

A phased array antenna aperture able to form a structural, load bearing portion of another structure, for example, a portion of a mobile platform. The antenna aperture is formed with a plurality of radiating elements sandwiched between prepreg fabric plies to form independent wall sections having a plurality of electromagnetic radiating elements embedded therein. The wall sections are secured in a honeycomb arrangement to form an array of cells of radiating elements. The manufacturing methods described herein enable arrays of widely varying sizes and shapes to be created and used as structural, load bearing portions of a wing, fuselage, door panel or other area of a mobile platform. The antenna aperture is lightweight because it does not include the weight of parasitic support components typically required in the construction of phased array antenna apertures.

Structurally integrated antenna aperture and fabrication method

An antenna aperture and method of assembling same. The antenna aperture forms a honeycomb-like core structure with dipole radiating elements integrally formed into structural wall portions of the honeycomb-like core. The antenna aperture has sufficient structural strength to form a structural portion of a mobile platform, while still being sufficiently light in weight for weight-critical applications such as with airborne mobile platforms.

Structurally integrated phased array antenna aperture design and fabrication method

A antenna aperture having electromagnetic radiating elements embedded in structural wall portions of a honeycomb-like core. Independent wall sections each having a plurality electromagnetic radiating elements are formed into the honeycomb-like core. Feed portions of each radiating element form teeth that are copper plated before being assembled onto a back skin panel. Each of the teeth are then generally machined flush with a surface of the back skin to present electrical contact pads which enable electrical coupling to each of the radiating elements by an external antenna electronics board.

Design and fabrication methodology for a phased array antenna with shielded/integrated feed structure

A pin connector is provided including a housing having a central orifice and an annular skirt laterally projecting therefrom. The skirt is bondable over a structurally integrated pad with integral wiring array. An array of compliant pins are insertable within holes in the pad. A pin retainer is disposed within the central orifice and includes an array of through holes formed therethrough. The array of compliant pins is disposed within the through holes of the pin retainer. The central orifice is adapted to receive a mating connector such that an array of contacts associated with the mating connector insert within the through holes of the pin retainer to make electrical contact with the array of compliant pins in the pin connector.

Connector interface pad for structurally integrated wiring

A restraint system is provided for restraining a pilot in a safe position during high-acceleration conditions. A stationary harness portion is attached to the pilot's body and haulback straps are connected in a slidable manner to the stationary harness. Under normal conditions, the pilot has some freedom of movement to lean forward or move from side to side. In the event of high acceleration or other emergency conditions, a pair of haulback straps that are slidably attached at the mid-torso position of the pilot are retracted to bring the entire back of the pilot against the back support of his seat. Lateral support pads positioned at the back and side of the pilot are moved to provide support to the sides, ribs and lumbar regions of the mid-torso and to restrain side-to-side movement of the pilot. The position of the lateral support pads is automatically adjusted according to the size of the pilot.

Adaptive torso restraint system

A lateral head restraint system providing support to a pilot's head during ejection or high-acceleration flight maneuvers. The lateral head restraint system includes inflating bladders positioned on opposite sides of a pilot's head. The bladders inflate from a compressed wedge position, sweeping through an arc on each side of the headrest structure. Inflation of the bladders centers the pilot's head into the correct control position and restricts lateral movement. When fully inflated, the bladders permit the pilot to lean forward or turn his head to either side. Further, an unobstructed field of vision is provided. The lateral head restraint system is incorporated into the ejection seat and remains fully operational during the ejection procedure to protect the pilot's head from injury.

Inflatable, lateral head restraint

An ejection seat includes a rigid shell adapted to closely surround the head of a pilot during ejection to restrain lateral movement of the pilot's head. The pilot's head is supported within the shell during ejection at a position that causes it to be aligned with the pilot's spinal column. During normal flight conditions, the pilot's head is supported in a forwardly pivoted position by a front panel. In this forwardly pivoted position, the pilot's head is free to move about to check for other aircraft. In one embodiment, the front panel slides rearwardly into the shell during ejection. In another embodiment, the front panel is divided into two sections, each of which pivots inwardly into the shell during ejection.

Ejection seat having receding headrest for spinal alignment during

A system for assisting a fighter pilot in checking the six-o'clock position. By differentially inflating bladders placed under the seat cushion of the ejection seat of a fighter, the seat cushion can be rotated to the pilot's left or right to aid the pilot in checking the space directly behind the fighter. A system controller, responsive to actions by the pilot, causes the differential inflation of the bladders and controls the rotation of left and right harness straps. The system controller can actuate solenoid valves to control the bladder inflation or can mechanically rotate a fluid valve to control the bladder inflation. The bladders can be fabricated from a resilient material so that they automatically deflate when they are vented to the ambient atmosphere and their size can be limited by placing the bladders inside a resilient casing that has a non-resilient web connecting the opposed surface of the casing.

System for assisting a fighter pilot in checking the six-o'clock position

A G-protective ejection seat assembly for an occupant of the cockpit of an aircraft. The assembly includes a cradle having a rigid, non-articulated upper portion and a rigid lower portion pivotally attached to the upper portion. The upper portion is pivotally attached to the aircraft for selected angular movement within the cockpit between an upright position and a reclined position. The cradle upper portion includes arm rests movable therewith for supporting hand flight controls. Foot flight controls are mounted to the cradle lower portion which is formed by a pair of leg rests. The assembly includes a separable, non-articulated ejection seat removably carried by and stationary with respect to the cradle upper portion during non-ejection use. The seal is moved with the cradle upper portion as the cradle upper portion pivots between the upright and reclined positions. The seat is movable upon ejection independent of the cradle with the cradle and the hand and foot controls remaining in place within the aircraft during ejection. A power actuator is provided for selectively, angularly moving the cradle upper portion between the upright and reclined positions. A controller is provided to control operation of the actuator in response to sensed G-force at the pilot's station and anticipatory aircraft G-force related performance based upon aircraft stick position, angle of attack and other parameters.

Automatic multi-position G-protective ejection seat assembly

A system and method for stabilizing an aircraft ejection seat and crew member after seat ejection and prior to main parachute inflation. The system also providing for delayed opening of the main chute until air speed and altitude have decreased to an acceptable parachute inflation range.

Aircraft ejected seat stabilizing and delayed parachute system

An aircraft ejection seat (10, 120) having a combined catapult (46, 122) and rocket motor (88, 90, 130, 132, 142, 144) in which the amount of rocket thrust is selectable. An outer catapult tube (46, 122) forms a seat support structure. In the outer catapult tube there is a plug (66, 66A) at its upper end before ejection and carries a propellant for ejecting the seat from the aircraft when the propellant is discharged. There is a fixed sleeve (84) in the lower end of the outer catapult having an internal circumferential bearing surface with which the inner catapult tube is engaged before and during ejection. The holding sleeve is positioned to engage the plug (66, 66A) when the ejection has become complete. The plug then seals the outer catapult to receive gas from the rocket gas generators to elevate the seat substantially above the aircraft, as necessary under certain conditions.

Ejection seat having combined catapult/rocket motor providing selectable

Inner catapult tubes (8) of aircraft (2) are pivotably mounted on the upper rear portion of ejection seat (12). When they separate from outer catapult tubes (4), tubes (8) pivot upwardly and rearwardly to form stabilizing booms (8). A drag device (30,30',30') is stowed inside the outer end of each boom (8) and extends axially outwardly therefrom upon deployment to apply a small drag load to the upper portion of seat (12) and counteract a tendency of seat (12) to pitch forward during operation of stabilization control rockets (18,20). The drag surfaces of devices (30,30',30') are folded around a center shaft (32,32',32') when stowed and extend radially outwardly from shaft (32,32',32') when deployed. The drag device may be a ram air inflatable device (30), a split tube/daisy petal device (30'), or a device having spring steel ribbons (40) forming a tuft-like appendage (30'). Ribbons (40) are wound around shaft (32' ) when stowed and spring radially outwardly from shaft (32') upon deployment.

Ejection seat stabilizing apparatus and method

A continuous main strap (10) has a front H-shaped configuration and a rear X-shaped configuration. Strap (10) extends from one side of the waist diagonally up and across the back, down the front, across and under the buttocks, up the front, and diagonally down and across the back to the opposite side of the waist. A chest strap (30) completely encircles the chest and forms the horizontal portion of the 'H'. An integral thigh strap and lap belt (20) is attached to the buttocks portion (16) of strap (10) and extends upwardly and laterally outwardly to side waist fittings (56) on vertical front webs (14) of strap (10), through fittings (56), and inwardly to an adjustable connector (26). Each fitting (56) has a cam lock snubber (66) for releasably securing strap (20) against movement relative to fitting (56).

Ejection seat restraint/parachute harness

Apparatus for adjustably mounting an ejection seat (16) in an aircraft in which outer catapult cylinders (58, 60) support inner catapult cylinders (62, 64) and supply force to the inner cylinders to eject the inner cylinders and the seat from the aircraft, the inner cylinders being connected to an upper rear end of the seat (66, 68). The seat (16) is supported in the aircraft by the inner and outer catapult cylinders (62, 64, 58, 60), by adjusting actuators (40) to raise and lower and to tilt the seat forwardly and rearwardly, by lower anchor links (30) pivotally connected to the aircraft and to lower end (26, 28) of the outer catapult cylinders and to the actuators (40), and by upper links (50). The seat is connected to the catapult cylinders (58, 60) by slipper blocks 82. The slipper blocks (82) are pivotally connected to the seat by pins (84) and are slidably engaged with the outer catapult cylinders.

Growing community of inventors

Bellevue, WA, United States of America

Gerald F Herndon