Raytheon Company

Ward D Lyman

Frederick B Koehler

Terry M Sanderson

Jeremy C Danforth

James Kendall Villarreal

Anthony O Lee

Jared D Stallings

Kenneth E Schmidt

Thomas Villarreal

Paul E Pontius

Delmar L Barker

Paul A Merems

Matt H Summers

Mark T Langhenry

Brian M Pape

Curtis B Carlsten

Douglas M Beard

Teresa J Clement

Jason E Gaudette

William D Werries

Michael J Birch

A satellite has thrusters that are integral parts of its frame. The frame defines cavities therein where thrusters are located. The thrusters may include an electrically-operated propellant and electrodes to activate combustion in the electrically-operated propellant. The frame may be additively manufactured, and the propellant and/or the electrodes may also be additively manufactured, with the frame and the propellant and/or the electrodes also being manufactured in a single process. In addition the thrusters may have nozzle portions through which combustion gases exit the thrusters. The thrusters may be located at corners and/or along edges of the frame, and may be used to accomplish any of a variety of maneuvers for the satellite. The satellite may be a small satellite, such as a CubeSat satellite, for instance having a volume of about 1 liter, and a mass of no more than about 1.33 kg.

Satellite with integral thrusters

A deployment body for a sensor array includes at least one superelastic spring formed of a shape memory alloy (SMA) material that enables activation of the deployment body. The SMA spring is configured to expand from a stowed position in which the SMA spring is wound around a central hub of the deployment body to a deployed position in which the SMA spring is extended in a radially outward direction relative to the central hub. A stiffness of the SMA spring enables the SMA spring to hold cables of the sensor array and maintain a deployed shape of the sensor array, which may be a volumetric array. Using the SMA material is advantageous in that the material is tuned to maintain superelasticity based on at least one of an intended operating temperature and a desired expansion ratio of stowed to deployed diameter of the deployment body.

Shape memory alloy subsurface array deployment mechanism

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.

Heat-activated triggering device with bi-metal triggering element

Ducting and/or duct couplings can be formed from shape memory polymer material, with the material for example being additively manufactured. The use of shape memory polymer material for one or more of the duct portions may allow for easier installation of the ducting, for example allowing the ducting to be warped and/or bent to fit into or through places that are hard to reach or hard to maneuver through, with the ducting then heated to cause it to return to a predetermined memory shape. The coupling of duct portions together may be accomplished by the duct portions including a shape memory polymer material, with for example ends of the duct portions fitted together, and then heated to use a shape memory property of the material to effect coupling. Heating of the shape memory polymer material also softens the material, allowing it to move to a previously set shape.

Duct with shape memory material, and installation method

A spacecraft, such as a satellite, uses a shape memory polymer actuator to deploy one or more deployable parts. The shape memory polymer actuator may be formed integrally with a deployable part and/or with a fuselage or other structure of the spacecraft, with the shape memory polymer actuator being for example a relatively thin portion of the shape memory polymer material of the integral structure. The shape memory actuator allows deployment of the deployable part(s) upon heating of the shape memory polymer material of the actuator, such as after the satellite has been launched into space. The heating may be caused by a heat source that is part of the spacecraft itself, or may be merely the result of exposing the spacecraft to solar heating after launch. The deployable part of the spacecraft may include any of a wide variety of parts that are used after launch.

Spacecraft with shape memory polymer deployment mechanism

A release mechanism includes a frame with an interior. The release mechanism also includes a prestrained element coupled to the interior of the frame. The prestrained element creates a seal with the frame. The prestrained element is notched in one or more regions. The prestrained element is configured to fracture when heated to a predetermined temperature allowing the interior to open. The fracture is based on the notched regions of the prestrained element such that separation initiates within the notched regions. The remaining regions of the prestrained element unfractured. The shape memory alloy element can include one or more of a nickel-titanium alloy, a titanium-nickel alloy, a copper-zinc-aluminum alloy, a copper aluminum nickel alloy, and a nickel titanium hafnium alloy. Heating of the shape memory alloy element causes a stress in the shape memory alloy that causes fracturing of the prestrained alloy when sufficient heating has been achieved.

Shape memory alloy disc vent cover release

A control system for a missile includes a plurality of control surfaces that can be arrayed across a surface of the missile body, and a controller connected to the control surfaces to selectively move the control surfaces between an aerodynamic stowed position where the control surfaces conform to the surface of the body, and a deployed control position removed from the aerodynamic stowed position where the control surfaces extend from the surface of the body to interact with airflow over the body. The control surfaces are made of a material that includes a shape-memory alloy. Heating the control surfaces causes the shape-memory alloy to move the control surfaces from the aerodynamic stowed position to the deployed control position. By selectively extending and retracting the control surfaces, the control system provides the ability to control the missile's direction of travel or to reduce roll about a longitudinal axis of the body.

Shape memory alloy micro-aero control surfaces

A shape memory circuit breaker includes a shape memory substrate having first and second opposed substrate ends. The shape memory substrate is configured to transition from a strained conductive configuration to a fractured non-conductive configuration. An isolation housing is coupled with the shape memory substrate. The isolation housing includes first and second anchors coupled near the first and second substrate ends. A brace extends between the first and second anchors, and the brace statically positions the first and second anchors and the respective first and second substrate ends. The shape memory substrate is configured to transition from the strained conductive configuration to the fractured non-conductive configuration at or above a specified temperature range corresponding to a specified overload current range or voltage range, and the first substrate end fractures from the second substrate end at or above the specified temperature range resulting in an open circuit.

Shape memory circuit breakers

A mechanical actuator is disclosed. The mechanical actuator can comprise an interface portion configured to interface with an object, a spring configured to exert a force on the interface portion, and a shape memory member coupled to the interface portion. The shape memory member can be configured to fracture at a predetermined temperature range. Upon fracture of the shape memory member, the force of the spring can cause the interface portion to act on the object.

Fracturing shape memory mechanical actuators and systems

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.

Heat-actuated release mechanism

A system includes a structure having a first structural element and a second structural element. The system also includes a latch configured to releasably secure the first structural element to the second structural element. The latch includes first and second portions. The latch also includes a ball lock configured to hold the first and second portions of the latch together when the ball lock is engaged. The ball lock is also configured to allow the first and second portions of the latch to separate when the ball lock is disengaged. The latch further includes a shape memory material member configured to fracture when exposed to an elevated temperature and thereby disengage the ball lock. The shape memory material member could include an elongated structure that is configured to decrease in length when exposed to the elevated temperature. The elongated structure could have at least one notch.

Passive safety mechanism utilizing self-fracturing shape memory material

A robotic finger includes a shape-memory alloy and a shape-memory polymer connected to and adjacent to the shape-memory alloy. Heating the shape-memory polymer causes it to soften, heating the shape-memory alloy causes the alloy to bend in the direction of the shape-memory polymer to press the shape-memory polymer against an object to be grasped, and cooling the shape-memory polymer causes it to stiffen and to retain its shape. An opposing member is positioned to cooperate with the finger to grasp an object positioned between the finger and the opposing member. A selectively controllable heat source is capable of applying heat to the finger.

Robotic grabber and method of use

A shape memory stored energy assembly includes a projectile housing having a projectile lumen. A projectile is within the projectile lumen and the projectile is movable relative to the projectile housing. A shape memory actuator is coupled between the projectile anchored end and the projectile housing. The shape memory actuator is configured to transition from a strained energy stored configuration to a fractured kinetic delivery configuration at a specified temperature range to propel the projectile through the projectile lumen. A method includes storing energy in a shape memory actuator coupled with a projectile. The stored energy in the shape memory actuator is released and propels the projectile. Releasing the stored energy includes heating the shape memory actuator, tensioning the shape memory actuator, and fracturing the tensioned shape memory actuator at a fracture locus to propel the projectile away from the fracture locus.

Shape memory stored energy assemblies and methods for using the same

Embodiments of separating apparatuses are generally described herein. Other embodiments may be described and claimed. In one embodiment, a thermal sensor assembly includes a shape memory substrate anchored within an isolation housing and braced between first and second anchors. The shape memory substrate is configured to transition from the strained configuration to the fractured configuration at a specified temperature range, and the first substrate end fractures from the second substrate end at the specified temperature. In another embodiment, a fracture indicator is coupled with the shape memory substrate, and the fracture indicator is configured to indicate the fractured configuration corresponding to meeting or exceeding of the specified temperature. In one example, the specified temperature range includes a range of temperatures or a single temperature.

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Tucson, AZ, United States of America

Ward D Lyman