The Boeing Company

Michael John Langmack

Richard William Aston

Anna Maria Tomzynska

Nicole M Hastings

Matthew J Herrmann

Emily Colleen Woods

Jazzmin P Martinez

Martin William Bieti

Nicole Diane Schoenborn

Rachel Elizabeth Zilz

Sumit K Purohit

Steven Fulton Griffin

James J Peterka, Iii

Russell W Cochran

Christopher R Shurilla

Brett T Cope

Philip R Munoz

Torger J Totusek

Nicole Marie Hastings

Matthew Joseph Herrmann

James Peterka

A satellite apparatus is disclosed, including a housing having first and second opposing walls, and a support structure inside the housing spanning the first and second walls. The support structure is structurally connected to the housing only at the first and second walls, and an end portion of the support structure is configured for connection to a launch vehicle by a separation system.

Stacked satellite assemblies and related methods

An additively manufactured heat transfer device is disclosed, including an enclosure portion with outer walls. The outer walls contain an inner channel configured to direct a flow of coolant fluid. The heat transfer device further includes a fluid intake port and a fluid outtake port, each connected to the first inner channel. The fluid intake port is configured to direct a flow of coolant fluid through an outer wall of the enclosure portion into the inner channel, and the fluid outtake port is configured to direct a flow of coolant fluid through an outer wall of the enclosure portion out of the inner channel. The inner channel is defined by internal walls, and the enclosure portion and the internal walls form a single additively manufactured unit.

Additively manufactured heat transfer device

A satellite assembly is disclosed, including a satellite and a shroud. The satellite is stowed in a launch vehicle and the shroud includes a frame supporting a flexible thermal blanket enclosing the satellite.

Satellite thermal enclosure

An additively manufactured antenna device is disclosed, including a base portion and a body portion. The body portion is attached to the base portion and includes a lattice stiffening structure configured to eliminate secondary printing support.

Additively manufactured antenna

An isolation coupler for coupling a functional element to a support structure includes a first bracket. The first bracket includes a number of first-bracket sides. The number of first-bracket sides forms a closed polygonal shape, in plan view. The isolation coupler further includes a number of isolators coupled to each one of the first-bracket sides. The isolation coupler also includes a second bracket. The second bracket includes a number of second-bracket sides. The second bracket sides are coupled to the isolators. The number of second-bracket sides is equal to the number of first-bracket sides and forms the closed polygonal shape, in plan view. The isolators separate each one of the first-bracket sides from a corresponding one of the second-bracket sides to attenuate a load transferred from the first bracket to the second bracket.

Isolation coupler for a structural assembly and method for attenuating a load

A drive train linkage includes a drive arm having a drive arm pivot axis, a driven arm having a driven arm pivot axis, at least one first coupling member extending between and being rotatably coupled to each of the drive arm and driven arm, and at least one second coupling member extending between and being rotatably coupled to each of the drive arm and driven arm so that the at least one second coupling member opposes the at least one first coupling member, where the at least one first coupling member and the at least one second coupling member are coupled to both the drive arm and the driven arm so to form a substantially zero mechanical deadband coupling between the drive arm and the driven arm.

Drive train linkage and method therefor

An apparatus for damping a first member relative to a second member. The apparatus includes a receiving member that includes a flange, an axial elastomeric member, and a radial elastomeric member. The axial elastomeric member is positionable between a surface of the first member and the flange of the receiving member, and the radial elastomeric member is positionable between the first member and the receiving member.

Damping apparatus and associated systems and methods for damping a first member relative to a second member

A mounting device is disclosed, including a first torsion bar structure having an elongated axis and opposing end portions connected by a middle portion. The mounting device further includes a second torsion bar structure having an elongated axis and opposing end portions connected by a middle portion. The middle portions of the first and second torsion bar structures are connected. The end portions of the first torsion bar structure are configured for attachment to a vehicle, and the end portions of the second torsion bar structure are configured for attachment to an accessory. The first and second torsion bar structures are configured to decrease transmission of vibration frequencies between the vehicle and the accessory.

Torsion bar mounting device

A method of manufacturing a vehicle control surface includes generating, using an electronic controller, a three-dimensional plan for the vehicle control surface. The three-dimensional plan includes, at least, non-vehicular support structure dimensions, for a non-vehicular support structure, and skin dimensions for a skin. The method further includes configuring the dimensions of the non-vehicular support structure based on build environment characteristics associated with an additive manufacturing process of the control surface. The additive manufacturing process is based on the three-dimensional plan. The method further includes fabricating the vehicle control surface, using the additive manufacturing process, based on the three-dimensional plan.

Single piece vehicle control surface and associated systems and methods of manufacture

Systems and methods for interconnecting dual manifested spacecraft for launch by a launch vehicle are disclosed. Different motive forces are utilized to couple a first spacecraft to a second spacecraft and to restrict demating of the second spacecraft from the first spacecraft. Some systems and methods utilize pneumatic pressure to permit mating of a first spacecraft to a second spacecraft and utilize spring force to restrict demating of the second spacecraft from the first spacecraft.

Systems for interconnecting dual manifested spacecraft

A satellite is disclosed comprising an anti-nadir panel having a first side and a second side. In one or more embodiments, the first side of the anti-nadir panel is mounted to an anti-nadir side of the main body of the satellite. The satellite further comprises at least one battery pack mounted to the second side of the anti-nadir panel, where at least one battery pack comprises at least one battery cell.

Spacecraft with anti nadir battery radiator

Systems and methods for dampening dynamic loading between two bodies are described. An example dampening system includes a non-ferrous metal body attached to a second body and a stack of magnets attached to a third body. The stack of magnets is movably disposed within or around the non-ferrous metal body, and adjacent magnets are arranged in an opposed polar relationship, whereby relative movement of said second and third bodies is damped. An example method of dampening dynamic loading includes arranging a plurality of magnets along an axis to form at least one pair of magnets having an opposed polar relationship along the axis. The method further includes axially moving the at least one pair of magnets relative to a non-ferrous metal body, so as to dampen dynamic loading of a payload attached to a vehicle.

Growing community of inventors

Huntington Beach, CA, United States of America

Michael John Langmack