Systems and methods of calibrating a sensor using an in-path optic capable of remaining in the sensor's optical path of view for both nominal imaging and for solar calibration collects are described. The optic is reversibly switchable between a transparent state and a diffuse state. An electric field aligns a plurality of liquid crystals dispersed in a polymer between two conductive layers is created to enable the transparent state. Incident light is transmitted through the aligned liquid crystals. The electric field between the two conductive layers is removed, misaligning the plurality of liquid crystals dispersed in the polymer between the two conductive layers. Light dispersed by the misaligned liquid crystals is received, and the sensor is calibrated based on the light dispersed by the misaligned liquid crystals.

Systems and methods are provided for scheduling objects having pair-wise and cumulative constraints. The systems and methods presented can utilize a directed acyclic graph to increase or maximize a utilization function. The objects can comprise satellites in a constellation of satellites. In some implementations, the satellites are imaging satellites, and the systems and methods for scheduling can use human collaboration to determine events of interest for acquisition of images. In some implementations, dominant edges are removed from the directed acyclic graph. In some implementations, dynamic weights are assigned to nodes associated with downlink events in the directed acyclic graph.

The present technology relates to a display control device, a display control method, and a program enabling images to be checked in real time.

A display control device includes: a receiving unit that receives small volume data that is information on current imaging by an artificial satellite; and a control unit that displays a live view image based on the small volume data on a display unit, wherein the receiving unit receives a satellite image corresponding to the live view image as large volume data at a timing different from that of the small volume data. The present technology can be applied to, for example, a satellite image processing system that processes satellite images captured by artificial satellites.

Systems, apparatuses, and methods provide for technology that locates one or more masses of a thunderstorm system, as the thunderstorm system starts to organize and before the thunderstorm system spawns a tornado, and controls a transmission of electromagnetic radiation from the space platform to the one or more masses, wherein the transmitted electromagnetic radiation tracks the one or more masses as the thunderstorm system is starting to organize and rotate, and wherein the transmitted electromagnetic radiation prevents the thunderstorm system from rotating and spawning the tornado.

A spectrographic system includes a space-borne spectrometer in communication with a ground-based processor. The space-borne spectrometer may include an interferometer, a detector array downstream from the interferometer, and a spectrometer controller configured to cooperate with the detector array to collect Fourier Transform Spectral (FTS) data, generate Principle Component Analysis (PCA) scores from the collected FTS data, generate an approximate interferogram based upon the PCA scores and the collected FTS data, generate residuals based upon the approximate interferogram, and generate compressed FTS data based upon the PCA scores and residuals to be sent to the ground-based processor.

A satellite with a primary imaging mirror fabricated while in space is described. The primary mirror is formed by solidifying liquid precursor material which assumes a paraboloid shape upon certain rotational maneuvers of the satellite. The primary mirror is preferably formed from a molten metal which creates a rigid paraboloid primary mirror upon solidification. The mirror material can be pre-melted prior to launch and carried to orbit while liquid, or it can be stored as a solid and melted in space to create the mirror.

A satellite observation system and method of deploying a satellite system are disclosed. The system includes a plurality of observation satellites comprising one or more sensors, each of the plurality of observation satellites configured with at least a solar array and a mechanical stabilization element. Each of the plurality of observation satellites is constructed without positioning components. The plurality of observation satellites is positioned in a dawn/dusk sun-synchronous orbital plane about a celestial body such that the one or more observation sensors are oriented toward the celestial body. The system further includes one or more servicing vehicles configured to engage each of the plurality observational satellites to configure at least the solar array and mechanical stabilization element

A method (100) for referencing an optical image (19) including: obtaining (110, 120) a stereoscopic image pair (19, 23) of the optical image (19) and a SAR image (35), the surface areas covered by the images (19, 23, 35) on the ground having an overlapping area (39); selecting (130) an area of interest (42) in the overlapping area (39); from the area of interest (42): obtaining (140) a 3D model (40); calculating (150) a simulated radar image (44); estimating (160) an offset (di, dj) between the simulated image (44) and the radar image (35); selecting (170) a reference point (46); projecting (180) and shifting (di, dj) the reference point (46) in the radar image (35) to correct the radar connection point (46′″); determining (175) a pair of connection points (46′, 46″) in the image pair; and referencing the optical image (19) based on the connection points (46′, 46″, 46′″).

An SSA business device (47) is a business device (40) with which an SSA business operator manages space object information. The SSA business device (47) includes a space traffic management device (200) that is compatible with space traffic management devices (200) respectively included in business devices (40) that manage space objects. The SSA business device (47) is connected, through the space traffic management device (200), to a space traffic management system (800) in which the space traffic management devices (200) respectively included in the business devices (40) are mutually connected with a communication line.

A satellite thruster increases satellite efficiency. The Linear Actuated μCAT has a stepper motor to move the ablative electrode forward. A LabVIEW program and Arduino microcontroller are used to analyze the Linear Actuated μCAT to determine how many steps are required for re-ignition, arc current, and the validity of the feed system. Results from testing show that micro-stepping the stepper motor is an effective way to replenish the cannibalized electrode for propellant.