Abstract: A method and system for coordination of a plurality of munitions in a Global Positioning System (GPS) denied attack of a plurality of ground targets. A relative position of each munition is determined relative to the other munitions in the salvo and a distance range is determined of each munition relative to the other munitions in the salvo. A constellation formation is determined for the plurality of munitions in the salvo relative to a target seeker basket such that each munition in the constellation formation is navigated to its respective target seeker basket, whereby a change in navigation for each munition is caused when necessary such that each munition arrives at its determined seeker basket at an approximate same time.

Abstract: A method for collaboration of a plurality of nodes includes determining at each node SLAM data for the node, the SLAM data including estimated position of features and/or targets observed and processed by the node using SLAM algorithms and covariance associated with the estimated positions, communicating at each node the node's SLAM data to the other nodes via each nodes' datalink communication system, receiving at each node SLAM data communicated from the other nodes via each node's datalink communication system, combining at each node the node's SLAM data and the SLAM data received from the other nodes based on features or targets included in SLAM data from the other nodes, refining at each node estimated positions of features and/or targets based on results of the combining, and navigating each node to a target at the target destination as a function of at least one of the refined estimated positions.

Abstract: A method and system for constraining navigational drift in a munition caused by Inertial Measurement Unit (IMU) bias error during flight of the munition in a constellation of a plurality of munitions in a Global Positioning System (GPS) denied attack. Each munition is provided with a datalink communication system to communicate with other munitions in the constellation and a navigation system having an IMU for guiding the munition in flight. An estimated position and covariance of the estimated position is determined for each munition via each munitions' navigation system. A range of each munition relative to at least one other munition in the munition constellation is determined via each munitions' datalink communication system. The estimated position and range to at least one other munition in the munition constellation is shared by each munition via each munitions' datalink communication system.

Abstract: In accordance with at least one aspect of this disclosure, a system includes one or more electronics boards and one or more plates configured to interleave the one or more electronics boards in a stack along an axis. When in the stack, an outer surface of the one or more plates is configured to form an outer mold line of a portion of a moving platform. Each of the one or more plates includes an inner diameter and an outer diameter, where the outer surface has an outer circumference at the outer diameter.

Abstract: A precision guided munition (PGM) system is disclosed. The PGM system comprises a body including a nose portion. The nose portion includes an aperture. A window is attached, secured, or adhered to the body at the nose portion. One or more antenna substrates is attached, secured, or adhered to the window. A plurality of radiating elements is attached, secured, or adhered to the one or more antenna substrates. An image sensor configured to capture an image in front of the body. The image sensor is behind the aperture and is configured to focus at an infinity focus in front of the body. The one or more antenna substrates include unpopulated areas configured to let photons pass through the antenna substrates from the window to the image sensor. The photons are parallel or collimated and the captured image does not include features of the antenna substrates.

Abstract: A method and system for constraining navigational drift in a munition caused by Inertial Measurement Unit (IMU) bias error during flight of the munition in a constellation of a plurality of munitions in a Global Positioning System (GPS) denied attack. Each munition is provided with a datalink communication system to communicate with other munitions in the constellation and a navigation system having an IMU for guiding the munition in flight. An estimated position and covariance of the estimated position is determined for each munition via each munitions’ navigation system. A range of each munition relative to at least one other munition in the munition constellation is determined via each munitions’ datalink communication system. The estimated position and range to at least one other munition in the munition constellation is shared by each munition via each munitions’ datalink communication system.

Abstract: A method and system for coordinating munitions in a salvo to form a constellation in a Global Positioning System (GPS) denied attack of a plurality of targets. Each munition is provided with a datalink communication system to communicate with other munitions and a navigation system for guiding the munition in flight. An estimated position of each munition is determined relative to the other munitions in the salvo via each munitions' datalink communication system. Two-Way Timing and Ranging (TRTW) techniques are utilized to determine positioning of each munition relative to one another. A distance range of each munition relative to the other munitions in the salvo is determined via each munitions' datalink communication system. A constellation formation of the plurality of munitions in the salvo is determined based upon the determined relative position and distance range of each munition relative to one another.

Abstract: A method including obtaining at each of a plurality of nodes navigation data of the node, communicating at each node its navigation data to the other nodes via each node's datalink communication system, receiving at each node navigation data communicated from the other nodes, determining at each node distance range of the node relative to the other nodes for which navigation data was received, determining at each node a constellation of the nodes as a function of the navigation data of the node, the navigation data received from the other nodes, and the distance range of the node relative to the other nodes, accessing formation constraints to form the constellation at each node, calculating at each node first guidance commands to maneuver the node to adjust the constellation to be in compliance with the formation constraints; and navigating each node to execute a maneuver based on the first guidance commands.

Abstract: A method for collaboration of a plurality of nodes includes determining at each node SLAM data for the node, the SLAM data including estimated position of features and/or targets observed and processed by the node using SLAM algorithms and covariance associated with the estimated positions, communicating at each node the node's SLAM data to the other nodes via each nodes' datalink communication system, receiving at each node SLAM data communicated from the other nodes via each node's datalink communication system, combining at each node the node's SLAM data and the SLAM data received from the other nodes based on features or targets included in SLAM data from the other nodes, refining at each node estimated positions of features and/or targets based on results of the combining, and navigating each node to a target at the target destination as a function of at least one of the refined estimated positions.

Abstract: A guided munition system includes a munition body including at least one fluid dynamic control for changing course of the munition body in flight. A seeker onboard the munition body is operatively connected to control the at least one fluid dynamic control. The seeker includes a coded aperture imaging device facing outward from the munition body for image based control for guiding the munition body in flight.

Abstract: A precision guided munition (PGM) system is disclosed. The PGM system comprises a body including a nose portion. The nose portion includes an aperture. A window is attached, secured, or adhered to the body at the nose portion. One or more antenna substrates is attached, secured, or adhered to the window. A plurality of radiating elements is attached, secured, or adhered to the one or more antenna substrates. An image sensor configured to capture an image in front of the body. The image sensor is behind the aperture and is configured to focus at an infinity focus in front of the body. The one or more antenna substrates include unpopulated areas configured to let photons pass through the antenna substrates from the window to the image sensor. The photons are parallel or collimated and the captured image does not include features of the antenna substrates.

Abstract: A course correction system for a projectile can include a pre-steering trajectory determination module. The pre-steering trajectory determination module can be configured to receive a series of possible trajectories from an estimation module including a physical model defining trajectory as a function of gravitational pull and one or more launch variables, and receive a sensor data from one or more on-board sensors of the projectile. The pre-steering trajectory determination module can also be configured to reduce the possible trajectories from the estimation module to one or more refined trajectories using the sensor data, and output the one or more refined trajectories.

Abstract: A guided munition system includes a munition body including at least one fluid dynamic control for changing course of the munition body in flight. A seeker onboard the munition body is operatively connected to control the at least one fluid dynamic control. The seeker includes a coded aperture imaging device facing outward from the munition body for image based control for guiding the munition body in flight.

Abstract: A stacked circuit card assembly includes a power supply having a positive terminal and a negative terminal, a first circuit card having a first via electrically connected to the positive terminal and a second via electrically connected to the negative terminal, and a second circuit card having a third via aligned with the first via and a fourth via aligned with the second via. The assembly further includes a first conductive stand-off disposed between the first circuit card and the second circuit card and structurally supporting the first circuit card with respect to the second circuit card, and a second conductive stand-off disposed between the first circuit card and the second circuit card and structurally supporting the first circuit card with respect to the second circuit card. The first conductive stand-off provides a conductive pathway between the first via and the third via, and the second conductive stand-off provides a conductive pathway between the second via and the fourth via.

Abstract: A canard deployment mechanism includes a canard connected to a shaft that is hingedly attached to a rotatable hub that is moveable between a stowed and deployed position. The mechanism further includes a locking feature on the canard for restraining the canard in the stowed position. In an embodiment the mechanism further includes a pawl rotatably mounted on a drive gear to contact and restrain the canard in the stowed position.

Abstract: A canard deployment mechanism includes a canard connected to a shaft that is hingedly attached to a rotatable hub that is moveable between a stowed and deployed position. The mechanism further includes a locking feature on the canard for restraining the canard in the stowed position. In an embodiment the mechanism further includes a pawl rotatably mounted on a drive gear to contact and restrain the canard in the stowed position.

Abstract: A method of controlling a projectile includes initiating an execution mode if a roll control authority parameter is outside of a pre-determined operating range for a projectile. The execution mode includes bypassing a guidance command and sending a modified command to execute a coning maneuver to improve control response of the projectile. A projectile control system includes a processor operatively connected to a memory. The memory has instructions recorded thereon that, when read by the processor, cause the processor to execute the method operations described above.

Abstract: A method of controlling a projectile includes initiating an execution mode if a roll control authority parameter is outside of a pre-determined operating range for a projectile. The execution mode includes bypassing a guidance command and sending a modified command to execute a coning maneuver to improve control response of the projectile. A projectile control system includes a processor operatively connected to a memory. The memory has instructions recorded thereon that, when read by the processor, cause the processor to execute the method operations described above.