Abstract: A deployment module according to the present application enables both compact stowage of a sensor array and expansion of the sensor array into a three-dimensional volumetric array shape that enables improved directionality of the sensors during operation. The deployment module includes a support shell that is configured to retain a cable of the sensor array separately from sensors of the sensor array and an expandable deployment body formed of a superelastic shape memory alloy that uses superelasticity and stored energy for deployment of the sensor array. During deployment, the deployment body is removed from the support shell and the sensors are subsequently pulled out of the support shell. The deployment body then expands and holds the cable to retain the three-dimensional volumetric shape of the deployed array.

Abstract: A solid rocket motor uses at least one thermally conductive wire or at least one pair of electrically conductive wires to increase a burn surface area of a propellant grain and thus a thrust of the rocket motor. The rocket motor includes a pulse chamber containing a burnable propellant grain, a propellant inhibited center bore bonded to surfaces of the burnable propellant grain, and at least one conductive wire coupled to the burnable propellant grain and arranged in variable regions along the propellant inhibited center bore. The conductive wire is configured for passive or active activation to ignite the propellant inhibited center bore that subsequently burns in the variable regions. The thermally conductive wire is formed of a refractory metal or refractory alloy material that enables the entire length of the wire to be heated simultaneously or nearly simultaneously when the wire is passively activated.

Abstract: A rocket motor has an electrically operated propellant initiator for a propellant grain that includes an electrode arrangement configured to concentrate an electric field at an ignition electrode for igniting an electrically operated propellant. The rocket motor includes a combustion chamber containing at least one propellant grain and an electrically operated propellant initiator operatively coupled to the propellant grain to initiate combustion of the propellant grain. The electrically operated propellant initiator includes the electrically operated propellant and at least one pair of electrodes configured to ignite the electrically operated propellant. The pair of electrodes includes a ground plane electrode and an ignition electrode. When an electrical input is applied to the electrically operated propellant initiator, the electric field is concentrated at the ignition electrode to ignite the electrically operated propellant at the location where the ignition electrode is arranged.

Abstract: A rocket motor has an electrically operated propellant initiator for a propellant grain that includes an electrode arrangement configured to concentrate an electric field at an ignition electrode for igniting an electrically operated propellant. The rocket motor includes a combustion chamber containing at least one propellant grain and an electrically operated propellant initiator operatively coupled to the propellant grain to initiate combustion of the propellant grain. The electrically operated propellant initiator includes the electrically operated propellant and at least one pair of electrodes configured to ignite the electrically operated propellant. The pair of electrodes includes a ground plane electrode and an ignition electrode. When an electrical input is applied to the electrically operated propellant initiator, the electric field is concentrated at the ignition electrode to ignite the electrically operated propellant at the location where the ignition electrode is arranged.

Abstract: A solid rocket motor uses at least one thermally conductive wire or at least one pair of electrically conductive wires to increase a burn surface area of a propellant grain and thus a thrust of the rocket motor. The rocket motor includes a pulse chamber containing a burnable propellant grain, a propellant inhibited center bore bonded to surfaces of the burnable propellant grain, and at least one conductive wire coupled to the burnable propellant grain and arranged in variable regions along the propellant inhibited center bore. The conductive wire is configured for passive or active activation to ignite the propellant inhibited center bore that subsequently burns in the variable regions. The thermally conductive wire is formed of a refractory metal or refractory alloy material that enables the entire length of the wire to be heated simultaneously or nearly simultaneously when the wire is passively activated.

Abstract: An electrically operated propellant includes an electrolyte source. The electrolyte source is an ionic liquid, a polyelectrolyte, or a combination thereof. The electrically operated propellant also includes a polymeric binder. The electrically operated propellant is substantially waterless with a water content of less than 10 wt. % water based on total weight of the electrically operated propellant.

Abstract: An electrically operated propellant includes a perchlorate oxidizer and a water insoluble polymeric binder with a water solubility of less than 0.1 grams (g) per 100 grams water at 25° Celsius (° C.). The electrically operated propellant is substantially waterless with a water content of less than 10 weight % (wt. %) water based on total weight of the electrically operated propellant.

Abstract: A deployment module according to the present application enables both compact stowage of a sensor array and expansion of the sensor array into a three-dimensional volumetric array shape that enables improved directionality of the sensors during operation. The deployment module includes a support shell that is configured to retain a cable of the sensor array separately from sensors of the sensor array and an expandable deployment body formed of a superelastic shape memory alloy that uses superelasticity and stored energy for deployment of the sensor array. During deployment, the deployment body is removed from the support shell and the sensors are subsequently pulled out of the support shell. The deployment body then expands and holds the cable to retain the three-dimensional volumetric shape of the deployed array.

Abstract: 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.

Abstract: 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.

Abstract: A heat-activated triggering device, such as for a missile or munition, includes a firing pin that is driven into a primer, to initiate a detonation and/or combustion reaction. The firing pin may be mechanically coupled to a linkage that prevents egress of output from the primer if the firing pin has not been moved. The linkage may include, for example, a cylindrical valve element with a through hole, the through hole being alignable with an output channel from the primer when the firing pin has been moved sufficiently. The movement of the firing pin slides a dowel pin that is attached to the firing pin. This in turn translates a cam element that turns the cylindrical element. Partial movement of the firing pin still may leave the valve closed. Preventing the primer from prematurely operating to trigger explosion, for example preventing full operation due to a primer being heated.

Abstract: A heat-activated triggering device, such as for a missile or munition, includes a firing pin that is driven into a primer, to initiate a detonation and/or combustion reaction. The firing pin may be mechanically coupled to a linkage that prevents egress of output from the primer if the firing pin has not been moved. The linkage may include, for example, a cylindrical valve element with a through hole, the through hole being alignable with an output channel from the primer when the firing pin has been moved sufficiently. The movement of the firing pin slides a dowel pin that is attached to the firing pin. This in turn translates a cam element that turns the cylindrical element. Partial movement of the firing pin still may leave the valve closed. Preventing the primer from prematurely operating to trigger explosion, for example preventing full operation due to a primer being heated.

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: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: A device is provided. The device includes at least one SMM component fabricated from an SMM. The SMM component is configured to change shape in response to receiving a stimulus. The SMM component is also configured to deploy from a device body of the device allowing the device to change shape in an advantageous way. A method implemented by a device is also provided. The method includes changing a shape of an SMM component of the device in response to receiving a stimulus. The SMM component is fabricated from an SMM. The method also includes deploying the SMM component from a device body of the device allowing the device to change shape in an advantageous way.