Abstract: An ultrasonic air data system can include a pole having a length longer than a boundary layer thickness of a boundary layer flow such that at least a distal end of the pole is configured to extend outwardly from an aircraft surface to be at least partially outside of the boundary layer flow. The system can include a transmitter disposed on or in the pole at or near the distal end of the pole such that the transmitter is located at least partially outside of the boundary layer flow when in use, wherein the transmitter is configured to output a transmitter signal. The system can include one or more receivers disposed downstream of the pole as defined by the boundary layer flow and configured to receive the transmitter signal.

Abstract: An acoustic air data system includes first and second acoustic transmitters, an array of acoustic receivers, and control circuitry. The array is positioned to receive first and second acoustic signals. The control circuitry determines time difference of arrival (TDOA) of the first and second acoustic signals. The control circuitry determines, for each of a first and second set of acoustic receiver pairs, a signal velocity of the first and second acoustic signals, respectively, based on a distance between an inner acoustic receiver and an outer acoustic receiver and a corresponding TDOA for each pair of acoustic receivers. The control circuitry estimates one or more of wind angle, speed of sound, Mach number, and true airspeed of the airflow about the exterior of the vehicle based on parameters of a best fit circle.

Abstract: An acoustic airspeed sensor system can include at least one acoustic transmitter configured to provide an acoustic pulse, a plurality of acoustic receivers including at least a first acoustic receiver, a second acoustic, receiver, and a third acoustic receiver, each positioned at a first radial distance from the at least one acoustic transmitter. The first acoustic receiver, the second acoustic receiver, and the third acoustic receiver are each configured to receive the acoustic pulse at a first time, a second time, and a third time, respectively, and output a first receiver signal, a second receiver signal, and a third receiver signal respectively. The system can include a computation unit operatively connected to the acoustic receivers and configured to generate a propagation function. The computation unit is further configured to determine true air speed based upon a receiver signals and the propagation function.

Abstract: An acoustic airspeed sensor system can include at least one acoustic transmitter configured to provide an acoustic pulse, a plurality of acoustic receivers including at least a first acoustic receiver, a second acoustic, receiver, and a third acoustic receiver, each positioned at a first radial distance from the at least one acoustic transmitter. The first acoustic receiver, the second acoustic receiver, and the third acoustic receiver are each configured to receive the acoustic pulse at a first time, a second time, and a third time, respectively, and output a first receiver signal, a second receiver signal, and a third receiver signal respectively. The system can include a computation unit operatively connected to the acoustic receivers and configured to generate a propagation function. The computation unit is further configured to determine true air speed based upon a receiver signals and the propagation function.

Abstract: An acoustic air data system includes first and second acoustic transmitters, an array of acoustic receivers, and control circuitry. The array is positioned to receive first and second acoustic signals. The control circuitry determines time difference of arrival (TDOA) of the first and second acoustic signals. The control circuitry determines, for each of a first and second set of acoustic receiver pairs, a signal velocity of the first and second acoustic signals, respectively, based on a distance between an inner acoustic receiver and an outer acoustic receiver and a corresponding TDOA for each pair of acoustic receivers. The control circuitry estimates one or more of wind angle, speed of sound, Mach number, and true airspeed of the airflow about the exterior of the vehicle based on parameters of a best fit circle.

Abstract: An air data computer senses acceleration and rotational rate of an aircraft with an inertial sensor assembly of the air data computer. The air data computer determines first attitude information of the aircraft based on the acceleration and rotational rate sensed with the inertial sensor assembly. The air data computer receives second attitude information of the aircraft from a source external to the air data computer, and determines attitude correction values based on the first attitude information and the second attitude information. The air data computer applies the attitude correction values to the first attitude information to produce error-corrected attitude information that is output from the air data computer.

Abstract: A system includes a first smart sensor, a second smart sensor, and at least one image processor. The first smart sensor is configured to sense light in a forward direction and to capture an image during a first time period. The second sensor is configured to sense light in the forward direction and to capture a second image during the first time period. The at least one image processor is configured to identify at least one object in the first and second image, to determine a first size of the at least one object in the first image and a second size of the at least one object in the second image, and to determine a distance of the at least one object from the aircraft based upon the first size and the second size.

Abstract: An angle-of-attack sensor includes at least one acoustic transmitter is configured to provide an acoustic pulse. The first acoustic receiver is positioned at a radial distance from the at least one acoustic transmitter. The first acoustic receiver is configured to receive the acoustic pulse at a first time and provide a first receiver signal. The second acoustic receiver is positioned at the radial distance from the at least one acoustic transmitter aligned with an axis that extends through the at least one acoustic transmitter and the first acoustic receiver. The second acoustic receiver is configured to receive the acoustic pulse at a second time and provide a second receiver signal. The angle-of-attack circuitry is configured to determine a delay difference between the first and second receiver signals representative of a difference between the first time and the second time and determine an angle-of-attack based upon the delay difference.

Abstract: Apparatus and associated methods relate to determining a course-correction signal for a spin-stabilized projectile based on a time sequence of images of a scene aligned with and obtained by a forward-looking imager coupled to the projectile. As the projectile rotates, the aligned scenes captured in the images obtained by the forward-looking imager are rotated. The rotation angle of each of the captured scenes corresponds to the spin angle of the projectile at the time of image exposure. Objects in the captured scenes will circle about a rotation center of the time-sequence images. The distances from a rotation center to the objects in the captured scenes, as well as the rotation angles of the captured scenes can be used to generate a course-correction signal so that the projectile can be guided to a target selected from the objects in the captured scene.

Abstract: Apparatus and associated methods relate to ranging an object nearby an aircraft by triangulation using two simultaneously-captured images of the object. The two images are simultaneously captured from two distinct vantage points on the aircraft. Because the two images are captured from distinct vantage points, the object can be imaged at different pixel-coordinate locations in the two images. The two images are correlated with one another so as to determine the pixel-coordinate locations corresponding to the object. Range to the object is calculated based on the determined pixel-coordinate locations and the two vantage points from which the two images are captured. Only a subset of each image is used for the correlation. The subset used for correlation includes pixel data from pixels upon which spatially-patterned light that is projected onto the object by a light projector and reflected by the object.

Abstract: An ultrasonic air data system can include a pole having a length longer than a boundary layer thickness of a boundary layer flow such that at least a distal end of the pole is configured to extend outwardly from an aircraft surface to be at least partially outside of the boundary layer flow. The system can include a transmitter disposed on or in the pole at or near the distal end of the pole such that the transmitter is located at least partially outside of the boundary layer flow when in use, wherein the transmitter is configured to output a transmitter signal. The system can include one or more receivers disposed downstream of the pole as defined by the boundary layer flow and configured to receive the transmitter signal.

Abstract: An acoustic air data sensing system includes an acoustic transmitter and a plurality of acoustic receivers. The acoustic transmitter is located to transmit an acoustic signal into airflow about an exterior of a vehicle. Each of the acoustic receivers is located at a respective angle from a wind angle reference line and a respective distance from the acoustic transmitter. Planar components of a velocity of the airflow are determined based on signal velocities of the acoustic signal to each of the plurality of acoustic receivers and the respective angles of the acoustic receivers from the wind angle reference line. Based on the planar components, the acoustic transmitter determines one or more of true airspeed and relative wind angle of the airflow about the exterior of the vehicle. The acoustic transmitter outputs the one or more of the true airspeed and the relative wind angle for operational control of the vehicle.

Abstract: Apparatus and associated methods relate to ranging object(s) nearby an aircraft using triangulation of pulses of linearly-patterned light projected upon and reflected by the object(s). A light projector projects the pulses of linearly-patterned light in a controllable direction onto the scene external to the aircraft. A reflected portion of the projected pulses is focused onto a selected row or column of light-sensitive pixels of a two-dimensional array, thereby forming a row or column of image data. The direction of projected light and the row or column of pixels selected are coordinated so that the portion of the projected pulses reflected by the scene is received by the camera and focused on the selected one of the rows or columns of light-sensitive pixels. Location(s) and/or range(s) of object(s) in the scene are calculated, based on a projector location, a camera location, and the row or column of image data.

Abstract: Apparatus and associated methods relate to forming images for a terminal-imaging seeker using software defined optics. An optically-neutral lens with a ballistic-ogive-shaped front surface receives light from a scene aligned along an optical axis. The optically-neutral lens transmits the light received at the ballistic-ogive-shaped front surface to a planar rear surface, which is then transmitted to a coded-aperture plate aligned with the optical axis. The coded-aperture plate includes a plurality of pinhole-like apertures, each of which is configured to perform pinhole-like lensing of the scene. The plurality of pinhole-like apertures form a multiplex of overlapping images on a focal plane array aligned with the optical axis. An image processor reconstructs, based on a configuration of the plurality of pinhole-like apertures and the multiplex of overlapping images, a single image of the scene.

Abstract: An air data computer configured to be installed on an aircraft includes an inertial sensor assembly having a plurality of accelerometers and a plurality of rate gyroscopes. The air data computer is configured to: determine a pressure altitude of the aircraft based on measured pressure of the airflow about the exterior of the aircraft; determine an estimated attitude of the aircraft based on rotational rate sensed by the plurality of rate gyroscopes; and determine a vertical acceleration of the aircraft based on the estimated attitude of the aircraft and the acceleration sensed by the plurality of accelerometers. The air data computer is further configured to blend the vertical acceleration and the pressure altitude using a complementary filter to produce a blended altitude rate that is output to consuming systems.

Abstract: A real-time compensation system of a projectile includes at least one flight controller, at least one imager device, at least one gyroscope, and at least one processor. The at least one flight controller is configured to rotate the projectile about an axis between a first orientation and a second orientation. The at least one imager device is configured to capture a first image at the first orientation and a second image at the second orientation. The at least one gyroscope is configured to sense a first angular rate of the projectile as the projectile rotates from the first orientation to the second orientation. The at least one processor is configured to determine a first rotation angle based upon the first and second images and a second rotation angle based upon the angular rate sensed by the at least one gyroscope, and determine a gyroscope compensation parameter.

Abstract: Apparatus and associated methods relate to ranging object(s) nearby an aircraft using triangulation of pulses of spatially-patterned light projected upon and reflected by the object(s). The projected pulses provide rapidly-changing illumination of a spatially patterned portion of the scene. A camera receives a reflected portion of the projected pulse and focuses the received portion onto a plurality of light-sensitive pixels, thereby forming a pulse image. The pulse image includes pixel data indicative of a rate of change of light intensity focused thereon exceeding a predetermined threshold. Pixel coordinates, corresponding to a subset of the plurality of light-sensitive pixels that are indicative of the rate of change of light intensity exceeding a predetermined threshold, are identified. Trajectory and/or range data of object(s) in the scene are calculated, based on a projector location, a camera location, and the identified pixel coordinates.

Abstract: A system includes a first smart sensor, a second smart sensor, and at least one image processor. The first smart sensor is configured to sense light in a forward direction and to capture an image during a first time period. The second sensor is configured to sense light in the forward direction and to capture a second image during the first time period. The at least one image processor is configured to identify at least one object in the first and second image, to determine a first size of the at least one object in the first image and a second size of the at least one object in the second image, and to determine a distance of the at least one object from the aircraft based upon the first size and the second size.

Abstract: A seeker imaging system and method includes at least one imager, a plurality of optical elements, and control electronics. The at least one imager is configured to output image frame data. The plurality of optical elements are configured to receive light and direct the light to the at least one imager. The control electronics are configured to receive the image frame data from the at least one imager. The control electronics is configured to obtain a plurality of initial images from each frame of the image frame data, and wherein the control electronics is configured to generate a single output image based upon the plurality of initial images.

Abstract: Apparatus and associated methods relate to ranging an object in a scene external to an aircraft. A light projector and two cameras are mounted on the aircraft, the cameras at two locations distinct from one another. The light projector and the two cameras are coordinated so that the light projector projects a linear-patterned beam of light while the cameras simultaneously capture a row or column of image data corresponding to an active row or column of pixels upon which a linear-patterned beam of light projected by the light projector and reflected by the scene is focused. Range to the object is calculated using triangulation based on the captured rows or columns of image data and the distinct locations of the two cameras from which the image data are simultaneously captured.