Abstract: Embodiments in accordance with the invention address potential co-orbital threats to a spacecraft through the use of a plurality of evasion pattern maneuvers selected to prevent a rendezvous with a potential co-orbital threat from occurring within a finite horizon. Embodiments in accordance with the invention maintain separation from the potential co-orbital threat while minimizing a defending spacecraft's fuel consumption.

Abstract: The disclosure provides an HAPR apparatus comprising an inflatable frame configured to generate canopy extension based on surrounding atmospheric pressure. The inflatable frame has a first collapse load limit less than the weight of the canopy at a first pressurized state less than 75 kPa and a second collapse load limit greater than the weight of the canopy at a second pressurized state of greater than 95 kPa. The internal pressure of the inflatable frame is typically about 101 kPa. The HAPR apparatus allows ascension with the canopy hanging under its own weight to reduce ascension time, then generates canopy extension prior to release in essentially a zero velocity, zero dynamic pressure condition.

Abstract: A computer-based system and method allows a user to automatically aerially inspect a selected runway/taxiway/tarmac surface for foreign object debris (FOD) using a plurality of UAVs equipped with electro-optical (EO) sensors. Live images of the runway surface captured by the EO sensors are transmitted from the UAVs during an inspection sweep of the runway surface and are compared with FOD-free reference images of the runway surface to determine whether candidate FOD are detected on the runway surface. Information about and images of candidate FOD are displayed to the user allowing the user to determine whether to send a team to remove the FOD from the runway.

Abstract: An aerial payload delivery system uses a cruciform parachute canopy that is connected to base by plurality of suspension lines including an adjustable control line. A control system includes an actuator to selectively adjust the length of the control line. By adjusting the length of the control line, the parachute can be selectively set to glide or descend substantially vertically subject to wind. In an embodiment, the suspension lines also include a short line and a plurality of long lines. The parachute is set to glide by adjusting the control line to be about the same length as the short line and set to vertically descend by adjusting the length of the control line to differ from the short line.

Abstract: Embodiments in accordance with the invention address potential co-orbital threats to a spacecraft through the use of a plurality of evasion pattern maneuvers selected to prevent a rendezvous with a potential co-orbital threat from occurring within a finite horizon. Embodiments in accordance with the invention maintain separation from the potential co-orbital threat while minimizing a defending spacecraft's fuel consumption.

Abstract: The disclosure provides an HAPR apparatus comprising an inflatable frame configured to generate canopy extension based on surrounding atmospheric pressure. The inflatable frame has a first collapse load limit less than the weight of the canopy at a first pressurized state less than 75 kPa and a second collapse load limit greater than the weight of the canopy at a second pressurized state of greater than 95 kPa. The internal pressure of the inflatable frame is typically about 101 kPa. The HAPR apparatus allows ascension with the canopy hanging under its own weight to reduce ascension time, then generates canopy extension prior to release in essentially a zero velocity, zero dynamic pressure condition.

Abstract: A computer-based system and method allows a user to automatically aerially inspect a selected runway/taxiway/tarmac surface for foreign object debris (FOD) using a plurality of UAVs equipped with electro-optical (EO) sensors. Live images of the runway surface captured by the EO sensors are transmitted from the UAVs during an inspection sweep of the runway surface and are compared with FOD-free reference images of the runway surface to determine whether candidate FOD are detected on the runway surface. Information about and images of candidate FOD are displayed to the user allowing the user to determine whether to send a team to remove the FOD from the runway.

Abstract: A method and apparatus for estimating the position and attitude of an aerial vehicle transiting over terrain through a combination of steps combining image registration and the inherent image coordinate system of the camera. The aerial vehicle captures an image of the terrain and extracts features from the camera image and pre-existing aerial imagery, and determines a perspective transform between the images. Image reference points are projected with the 2D perspective transform and an elevation map provides estimated 3D coordinates of the image reference points. Subsequently a camera position and orientation necessary for the camera to obtain the initial camera image is determined by projecting reference points with locations defined by the image coordinate system of the camera to define terrain points, and conducting an optimization to minimize displacements between the estimated coordinates and the terrain coordinates. The estimated camera position provides a location and attitude for the aerial vehicle.

Abstract: An aerial payload delivery system uses a cruciform parachute canopy that is connected to base by plurality of suspension lines including an adjustable control line. A control system includes an actuator to selectively adjust the length of the control line. By adjusting the length of the control line, the parachute can be selectively set to glide or descend substantially vertically subject to wind. In an embodiment, the suspension lines also include a short line and a plurality of long lines. The parachute is set to glide by adjusting the control line to be about the same length as the short line and set to vertically descend by adjusting the length of the control line to differ from the short line.

Abstract: Using battery monitoring and unmanned aerial vehicle (UAV) management, a method and system provide persistent airborne surveillance for intelligence, surveillance, and reconnaissance (ISR) systems supported by UAVs within an airborne surveillance pattern (ASP). In one embodiment, a UAV operating in the ASP with degraded battery charge is autonomously swapped with a UAV having a fully-charged battery to provide persistent aerial surveillance for an extended duration over that of a single UAV.

Abstract: Methods and systems for determining a spin rate of a projectile are provided. A receiving module receives a video of a launch of a projectile in which the projectile having at least one marking disposed thereon. A segmenting module segments a plurality of shapes of the projectile from the video. The segmenting module includes a sensitivity module configured to increase a sensitivity of the video to find the projectile in the video. An extraction module extracts at least one column of pixels of the at least one marking from the shapes. A generating module generates a stripe pixel column history image from the at least one column of pixels. A calculating module calculates a spin rate of the projectile from the stripe pixel column history image.

Abstract: Systems and methods are provided to quantify the pitching and yawing motion of a projectile during ballistic flight using two camera/tracker video systems. Image processing tools are used to segment the shape of the projectile in each frame of a launch video, which allows the location and observed pitch angle to be calculated with sub-pixel accuracy. Subsequent automated analysis uses the history of the projectile location and the pitching behavior to calculate estimates for the epicyclic motion, as well as other ballistic parameters such as aeroballistic coefficients. Using two cameras located at different orthographic views of the line-of-fire (LOF) allows the pitching and yawing motion history of the projectile to be calculated in three dimensions (3D). In addition, input of the camera locations, cannon trunnion location, and the cannon pointing direction allows for automatic correction for camera misalignment.

Abstract: An automated method to quantify the pitching and yawing motion of a projectile during ballistic flight using two camera/tracker video systems. Image processing tools are used to segment the shape of the projectile in each frame of a launch video, which allows the location and observed pitch angle to be calculated with sub-pixel accuracy. Subsequent automated analysis uses the history of the projectile location and the pitching behavior to calculate estimates for the epicyclic motion, as well as other ballistic parameters such as aeroballistic coefficients. Using two cameras located at different orthographic views of the line-of-fire (LOF) allows the pitching and yawing motion history of the projectile to be calculated in three dimensions (3D). In addition, input of the camera locations, cannon trunnion location, and the cannon pointing direction allows for automatic correction for camera misalignment.

Abstract: A new mortar projectile for use to resupply various payloads to distant troops. The mortar projectile has the capability of rapidly and accurately transporting the payloads to forward disposed combatants without interference of terrain or enemy action. The mortar projectile includes a shell body for housing the payload to be delivered, and a GPS-guided parafoil for delivering the payload to the designated remote target location.

Abstract: A method is described that involves establishing a wireless network between a wireless access node of an existing network and a remote location by wirelessly linking a plurality of electronic processing circuits each transported by a respective parafoil. The wirelessly linked processing circuits are to route packets from the wireless access node to the remote location.

Abstract: A method is described that includes performing a), b) and c) below with an electronic control unit of a parafoil: a) after being dropped from an airborne vehicle, wirelessly receiving the parafoil's desired landing location; b) determining a flight path for the parafoil that lands at the desired landing location; and, c) controlling the parafoil's flight path consistently with the determined flight path.

Abstract: Embodiments described herein provide a system and method for persistent high-accuracy payload delivery utilizing a two-phase procedure during the terminal descent phase of aerial payload delivery. In the first phase a small parafoil provides aerial delivery of a payload to within a close proximity of an intended touchdown point, e.g., a target. In the second phase a target designator acquires the target and a trajectory to the target is determined. A harpoon launcher deploys a harpoon connected to the payload by an attachment line, such as a rope. A reel mechanism reels up the attachment line causing the payload to be moved to the target thus providing high accuracy touchdown payload delivery.

Abstract: A method is described that involves establishing a wireless network between a wireless access node of an existing network and a remote location by wirelessly linking a plurality of electronic processing circuits each transported by a respective parafoil. The wirelessly linked processing circuits are to route packets from the wireless access node to the remote location.

Abstract: A method is described that involves performing the following with a parafoil's control unit composed of electronic circuitry while the control unit is being transported with a parafoil: determining a desired exit of a turn; determining a desired time for the turn; determining the parafoil's actual entrance for the turn; determining an arc between the actual entrance and the desired exit; and, incorporating said arc as said parafoil's planned flight trajectory through said turn.

Abstract: A method is described performing the following with a parafoil's control unit composed of electronic circuitry while the control unit is being transported with a parafoil: calculating a desired landing location for a parafoil, the desired landing location corresponding to a moving target, the calculating including using a term representative of the moving target's velocity; determining a flight path to the desired landing location; and, controlling the parafoil's flight path so as to follow the flight path.