The Boeing Company

United States of America as Represented by the Administrator of Nasa

Bruce Lee Drolen

Kevin Scott Callahan

John Rubrecht Lowell

James C Russell

Timothy R North

Thomas P Barrera

Ty Aaby Larsen

Jianmin Liao

William B Barvosa-Carter

John Huntley Belk

Daniel J Murray

Douglas Dean Maben

James Ping Huang

Kelly Thomas Jones

Leslie Momoda

Russell Mistretta Abbott

Frederic Lacaux

Arun Muley

Michael F Stoia

John W Behrens

Daniel F Lewinski

Richard Kevin Johnson

Michael L Trent

Royal E Boggs

Mehdy Barekatein

George A McEachen

Mark E Smith

Jason D Flathom

Douglas H Van Affelen

Gary A Bayles

Nels A Olson

Steven L Rickman

Julie K Plessner

John J Darst

Jonathan M Allison

Michael Worcester

Eric C Dimpault-Darcy

William Q Walker

Kevin J Rooney

David J Nakamura

Geoffrey Orias

Harry H Ayubi

David C Shangraw

Jean-Philippe Belieres

Richard P Lorenz

Alan D Amort

Gary L Duncan

Mohammad M Malik

Matthew J O'Brien

Craig G Robotham

Brian R Foy

Aimen E Shawki

Michael R Madden

Zoran Bilc

Christiaan Khurana

Alfred R Carlo

Natalie N Anderson

Sean Nguyen

David M Bowden

A system for measuring a heat response of a cell during a thermal runaway event includes a housing. An insulation is positioned within the housing. A calorimeter is positioned within the insulation and the housing. The calorimeter is configured to have the cell positioned therein. The calorimeter is configured to measure a temperature increase of the cell, one or more components of the calorimeter, or a combination thereof during the thermal runaway event of the cell. A total energy yield of the thermal runaway event is configured to be determined based at least partially upon the temperature increase. A ratio is configured to be determined based at least partially upon the temperature increase. The ratio includes energy released through a casing of the cell during the thermal runaway event vs. energy released through ejecta material from the cell during the thermal runaway event.

Systems and methods for measuring a heat response of a battery cell in thermal runaway

Systems, methods, and apparatus for dual condenser loop heat pipes for satellites with sun-normal radiators are disclosed. In one or more embodiments, a disclosed method for a satellite thermal management system comprises heating, in an evaporator, a liquid to convert the liquid to a vapor. The method further comprises passively circulating within tubing, from the evaporator, the vapor to a first radiator not illuminated by a sun and to a second radiator illuminated by the sun. Also, the method comprises converting the vapor to the liquid when the vapor is within the first radiator not illuminated by the sun. Further, the method comprises passively circulating within the tubing, from the first radiator not illuminated by the sun, the liquid to the evaporator.

Dual condenser loop heat pipe for satellites with sun-normal radiators

A rechargeable battery comprises a chassis including a lower fixation plate, and a plurality of battery cells on the lower fixation plate. The lower fixation plate includes at least one flow channel positioned to collect condensate from the battery cells and move the collected condensate away from the battery cells.

Chassis for rechargeable battery

A heat pipe comprises a tube and protrusions. The tube has an internal surface, an external surface, and a length running from a first end to a second end. The protrusions are on the internal surface. A first cross-section of the protrusions at a first location of the length of the tube is different from a second cross-section of the protrusions at a second location of the length of the tube. The tube and the protrusions are monolithic.

Heat pipe with non-uniform cross-section

A thermal management system includes a first hydraulic system for circulating a first hydraulic fluid at a first temperature and a second hydraulic system for circulating a second hydraulic fluid at a second temperature that is higher than the first temperature. The thermal management system also includes a sealed heat transfer device coupled between the first hydraulic system and the second hydraulic system. The sealed heat transfer device is not in flow communication with either of the first hydraulic system and the second hydraulic system. The sealed heat transfer device is configured to transfer heat from the second hydraulic fluid to the first hydraulic fluid.

Systems and methods for heat balance and transport for aircraft hydraulic systems

A rechargeable battery comprises a plurality of individual sealed battery cells, and dielectric separators between the battery cells for creating thermal barriers between opposing surfaces of the battery cells. The dielectric separators are made of a fiber composite.

Rechargeable battery including battery cell separators

An aircraft comprises a rechargeable battery including an array of battery cells, and means for mitigating consequences of failure of the rechargeable battery due to aircraft operating cycles.

Aircraft including mitigation system for rechargeable batteries

A thermal management device suitable for use as an electronic chassis includes a monolithic, monocoque body having integrally formed channels for carrying thermal energy away from a heat source, such as electronic components. The device may be fabricated using additive/subtractive manufacturing processes such as ultrasonic consolidation.

Thermal management device and method for making the same

An electrothermal deployment system may be configured for controlled release of various apparatus from their prelaunch stowage positions in small satellites. The deployment system includes a fusible line secured to a structural component of the satellite, as well as to various deployable apparatus secured to, within, or on the satellite. The deployable apparatus may include items such as solar panels and antennas. The deployment system includes an electrically resistive element such as a burn bar formed of a cylinder or tube, including a resistor pad overlying and/or incorporated within an exterior surface of the burn bar. The burn bar may be coupled to an electrical circuit configured to heat the resistor for the purpose of melting the fusible line secured in direct contact therewith, thus causing the fusible line to break to cause deployment. The fusible line is configured to remain in secure contact with the resistor until apparatus deployment.

NANOSAT electrothermal deployment system

An apparatus may have a multilayered support base having a structural section made up of operating components and a function support section. The function support section may have transmission paths and components to supply thermal, power transmission, information and communication paths, along with other functions. At least some of the components may be heat generating and may have a thermal interface surface which may be in operating and heat conductive relationship with a heat conductive substrate/routing section which may have operative connections to the multilayered support base. Some of the components may transmit and receive with one another through the substrate/routing section.

Multi operational system apparatus and method

Growing community of inventors

Altadena, CA, United States of America

Bruce Lee Drolen