Abstract: Disclosed herein is a flow control device. The flow control device comprises a sheet made from a shape memory alloy. The flow control device also comprises at least one slit through the sheet. At least the one slit defines at least one flap in the sheet. The flow control device further comprises at least one electrically-resistive trace printed on the sheet at least one of on or adjacent at least the one flap. Upon receipt of an electrical current, at least the one electrically-resistive trace configured to generate heat for deforming at least the one flap relative to the sheet and opening an aperture formed in the sheet.

Abstract: Described herein is a heater for space equipment that includes a heat pipe. The heater also includes a first layer applied to the heat pipe. The first layer may be made from an electrically non-conductive material. The heater additionally includes a resistance heater printed onto the first layer after the first layer is applied to the heat pipe. The heater includes a second layer adjacent the resistance heater. The resistance heater may be positioned between the first layer and the second layer, and the second layer may be made from an electrically non-conductive material.

Abstract: Described herein is a composite panel that includes a first layer made from an electrically non-conductive material. The composite panel also includes a resistance heater printed onto the first layer and a capacitive sensor applied onto the first layer. The capacitive sensor is operably coupled with the resistance heater. The composite panel additionally includes a second layer adjacent the resistance heater and the capacitive sensor. The resistance heater and the capacitive sensor are positioned between the first layer and the second layer. Furthermore, the second layer is made from an electrically non-conductive material. The resistance heater is configured to generate heat at least partially in response to input sensed by the capacitive sensor.

Abstract: Disclosed herein is an actuator for effectuating a shape memory alloy (SMA). The actuator includes a body including shape memory alloy. The body includes a plurality of segments. The actuator also includes a plurality of heaters that are each configured to maintain a predetermined temperature based on a predetermined resistance of the heater when a voltage is applied to the heater. Each heater of the plurality of heaters is associated with a different segment of the plurality of segments. A segment of the plurality of segments is effectuated in response to increasing a temperature of the heater associated with the segment.

Abstract: Disclosed herein is a flow control device. The flow control device comprises a sheet made from a shape memory alloy. The flow control device also comprises at least one slit through the sheet. At least the one slit defines at least one flap in the sheet. The flow control device further comprises at least one electrically-resistive trace printed on the sheet at least one of on or adjacent at least the one flap. Upon receipt of an electrical current, at least the one electrically-resistive trace configured to generate heat for deforming at least the one flap relative to the sheet and opening an aperture formed in the sheet.

Abstract: Disclosed herein is an actuator for effectuating a shape memory alloy (SMA). The actuator includes a body including shape memory alloy. The body includes a plurality of segments. The actuator also includes a plurality of heaters that are each configured to maintain a predetermined temperature based on a predetermined resistance of the heater when a voltage is applied to the heater. Each heater of the plurality of heaters is associated with a different segment of the plurality of segments. A segment of the plurality of segments is effectuated in response to increasing a temperature of the heater associated with the segment.

Abstract: Described herein is a heater for space equipment that includes a heat pipe. The heater also includes a first layer applied to the heat pipe. The first layer may be made from an electrically non-conductive material. The heater additionally includes a resistance heater printed onto the first layer after the first layer is applied to the heat pipe. The heater includes a second layer adjacent the resistance heater. The resistance heater may be positioned between the first layer and the second layer, and the second layer may be made from an electrically non-conductive material.

Abstract: Described herein is a composite panel that includes a first layer made from an electrically non-conductive material. The composite panel also includes a resistance heater printed onto the first layer. Further, the composite panel includes a second layer adjacent the resistance heater, the resistance heater being positioned between the first layer and the second layer. The second layer is made from an electrically non-conductive material.

Abstract: Described herein is a composite panel that includes a first layer made from an electrically non-conductive material. The composite panel also includes a resistance heater printed onto the first layer and a capacitive sensor applied onto the first layer. The capacitive sensor is operably coupled with the resistance heater. The composite panel additionally includes a second layer adjacent the resistance heater and the capacitive sensor. The resistance heater and the capacitive sensor are positioned between the first layer and the second layer. Furthermore, the second layer is made from an electrically non-conductive material. The resistance heater is configured to generate heat at least partially in response to input sensed by the capacitive sensor.

Abstract: Described herein is a composite panel that includes a first layer made from an electrically non-conductive material. The composite panel also includes a resistance heater printed onto the first layer. Further, the composite panel includes a second layer adjacent the resistance heater, the resistance heater being positioned between the first layer and the second layer. The second layer is made from an electrically non-conductive material.

Abstract: A damage-detection apparatus for an aircraft may include a composite structure comprising embedded conductive traces. The embedded conductive traces may be for transmitting a damage-detection signal to indicate if the composite structure has been damaged.

Abstract: An aircraft includes a composite structure and a plurality of small lightweight pollable communication devices for providing lightning strike detection coverage of a region of the structure. Each device is rendered inoperative if at least proximate to lightning current.

Abstract: A twisted-pair cable and methods are disclosed. The twisted-pair cable comprises a first layer comprising a first non-conductive. A second layer is coupled to the first layer, and comprises a printed circuit patterned with first diagonal conductor segments. A third layer is coupled to the second layer, and comprises a non-conductive strip. A fourth layer is coupled to the third layer, and comprises a printed circuit patterned with second diagonal conductor segments. The first diagonal conductor segments and the second diagonal conductor segments are coupled at respective segment ends such that at least two wires are formed around the non-conductive strip. A fifth layer is coupled to the fourth layer, and comprises a second non-conductive.

Abstract: A twisted-pair cable and methods are disclosed. The twisted-pair cable comprises a first layer comprising a first non-conductive. A second layer is coupled to the first layer, and comprises a printed circuit patterned with first diagonal conductor segments. A third layer is coupled to the second layer, and comprises a non-conductive strip. A fourth layer is coupled to the third layer, and comprises a printed circuit patterned with second diagonal conductor segments. The first diagonal conductor segments and the second diagonal conductor segments are coupled at respective segment ends such that at least two wires are formed around the non-conductive strip. A fifth layer is coupled to the fourth layer, and comprises a second non-conductive.

Abstract: A damage-detection apparatus for an aircraft may include a composite structure comprising embedded conductive traces. The embedded conductive traces may be for transmitting a damage-detection signal to indicate if the composite structure has been damaged.

Abstract: An aircraft includes a composite structure and a plurality of small lightweight pollable communication devices for providing lightning strike detection coverage of a region of the structure. Each device is rendered inoperative if at least proximate to lightning current.

Abstract: Nondestructive examination is performed on a composite aircraft component including a composite body and a conductive medium. The conductive medium is substantially more conductive than the composite body. The nondestructive examination includes applying an electromagnetic field that penetrates the composite body and heats the conductive medium, and creating a thermal image of the conductive medium to reveal conductivity information about the conductive medium.