Abstract: A heat-activated triggering device, such as for a missile or munition, includes a bi-metal trigger element, with a breakable pin of a first metal surrounded by a sleeve made of a second metal that is different than the first metal. The sleeve may be made of a shape memory alloy, such as a single-crystal shape memory alloy, that is pre-compresses around part of the pin. The sleeve may be configured to put a tension force on the pin as the sleeve passes a predetermined temperature, for instance a temperature at which the shape memory feature of the sleeve is activated. The pin may have a weakened portion, such as a notched portion, at which the pin breaks. The breaking of the pin may be used to drive a firing pin into a primer, to initiate a detonation and/or combustion reaction.

Abstract: A heat-activated triggering device, such as for a missile or munition, includes a bi-metal trigger element, with a breakable pin of a first metal surrounded by a sleeve made of a second metal that is different than the first metal. The sleeve may be made of a shape memory alloy, such as a single-crystal shape memory alloy, that is pre-compresses around part of the pin. The sleeve may be configured to put a tension force on the pin as the sleeve passes a predetermined temperature, for instance a temperature at which the shape memory feature of the sleeve is activated. The pin may have a weakened portion, such as a notched portion, at which the pin breaks. The breaking of the pin may be used to drive a firing pin into a primer, to initiate a detonation and/or combustion reaction.

Abstract: A control system of a flight vehicle automatically varies the relationship between the center of gravity and the center of pressure of the flight vehicle. The control system automatically adjusts a center of pressure of the flight vehicle depending on a varying payload or payload type that is removably couplable to the flight vehicle. The control system automatically limits translational movement of the one or more wings of the flight vehicle in response to coupling of a payload to a fuselage of the flight vehicle.

Abstract: A control system of a flight vehicle automatically varies the relationship between the center of gravity and the center of pressure of the flight vehicle. The control system automatically adjusts a center of pressure of the flight vehicle depending on a varying payload or payload type that is removably couplable to the flight vehicle. The control system automatically limits translational movement of the one or more wings of the flight vehicle in response to coupling of a payload to a fuselage of the flight vehicle.

Abstract: A release mechanism passively releases a mechanical coupling as a result of a temperature rise. The release mechanism includes a breakable element, such as a shape memory alloy (SMA) element, that is configured to break when the element is heated to a predetermined temperature. The breakage of the breakable element releases a mechanical coupling, such as a coupling holding a lid onto a container. The release mechanism may be part of a handle or other device to close the container. The release mechanism may have a mechanical load on it prior to release, a load that in part passes through the breakable element. Most of the load may pass through one or more other members of the release mechanism, providing the force for separation after the release mechanism is triggered. The release mechanism may be used to provide a passive way of releasing a mechanical coupling in response to heating.

Abstract: A release mechanism passively releases a mechanically coupling as a result of a temperature rise. The release mechanism includes a breakable element, such as a shape memory alloy (SMA) element, that is configured to break when the element is heated to a predetermined temperature. The breakage of the breakable element releases a mechanical coupling, such as a coupling holding a lid onto a container. The release mechanism may be part of a handle or other device to close the container. The release mechanism may have a mechanical load on it prior to release, a load that in part passes through the breakable element. Most of the load may pass through one or more other members of the release mechanism, providing the force for separation after the release mechanism is triggered. The release mechanism may be used to provide a passive way of releasing a mechanical coupling in response to heating.

Abstract: A method of adjusting an optical system includes placing the optical system in a controlled environment enclosure, and adjusting an optical mount of the optical system while the optical system is in the controlled environment enclosure.

Abstract: An adjustable optical mounting includes a mounting support or frame, and multiple adjusters to provide a six-degree-of-freedom adjustment of the support relative to a base. The adjusters include cams with cam surfaces that bear against and engage slots in the support or frame, to translate the support in directions parallel to the base. In addition, threaded devices and resilient (compliant) devices such as springs are utilized to adjust the height of the support relative to the base, at multiple locations. The cams and the threaded devices of the adjusters may be independently adjusted to translate the support relative to the base, and/or to change the height and/or tilt angle of the support.