A satellite with deployable optics is provided. The satellite has a frame, an optical axis, and a deployable optical system. The optical system has a mechanical aperture perpendicular to the optical axis, where light collected travels substantially parallel to the optical axis. The optical system has a stored configuration in which it remains within the frame and a deployed configuration in which it extends outside the frame. In some configurations, the light-collecting area of the deployed configuration is larger than the possible light-collecting area of the stored configuration. In a partially deployed configuration, all of the primary mirror segments remain substantially within the frame, and the light-collecting area is smaller than that in the deployed configuration. A method of using the satellite includes setting the satellite to the deployed configuration, detecting whether there is a deployment malfunction, and, if so, setting the satellite to a partially deployed configuration.

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 space vehicle comprising an optical system having a field of view, the optical system comprising at least two optical elements spaced from one another along an optical axis, thereby defining an interior cavity; at least one control system comprising at least one physical element configured for performing function(s) for enabling operation of the vehicle; and at least one holding assembly for holding the at least one control system and comprising a folding mechanism configured to move between a folded position corresponding to an inoperative mode of the optical system, and a deployed position corresponding to an operative mode of the optical system, such that in the folded position, the control system is at least partially located in the interior cavity for stowage, and in the deployed position, the control system is located outside the interior cavity and outside the field of view of the optical system, allowing operation of the optical system.

One variation of a method for identifying stressors in crops based on fluorescence of sensor plants includes: accessing a set of spectral images of a sensor plant sown in a crop, the sensor plant of a sensor plant type including a set of promoters and a set of reporters configured to signal a set of stressors present at the sensor plant, the set of promoters and set of reporters forming a set of promoter-reporter pairs; accessing a reporter model linking characteristics extracted from the set of spectral images of the sensor plant to the set of stressors based on signals generated by the set of promoter-reporter pairs in the sensor plant type; and identifying a first stressor, in the set of stressors, present at the sensor plant based on the reporter model and characteristics extracted from the set of spectral images.

Computer systems (100) for satellite image acquisition and mission-plan calculation devices (120) for satellite and also Earth observation satellites (110). Based on the observation that the uncertainty connected with meteorological conditions can lead to the development of mission plans, for satellites, with low effectiveness, the uncertainty is characterized and used to improve the preparation of mission plans for satellite. A model of the uncertainties is built upon observations and/or past meteorological forecasts. Next, at the time of planning, the model is used by presenting the observations and/or the current forecast as input to the model. In that way, the acquisition zones for which it is unlikely to get acceptable images on the preferred acquisition date may be identified.

A device for determining an attitude of a satellite is disclosed, the satellite having an attitude control system comprising a gyroscopic actuator including a flywheel mounted so as to be rotatable around an axis of rotation and carried by a gimbal articulated to rotate around an axis of rotation. The device includes an attitude sensor configured to measure the attitude of the satellite, a position sensor configured to measure the angular position of the gimbal around its axis of rotation, a speed sensor configured to measure the rotational speed of the flywheel, and a processing circuit configured to determine the attitude of the satellite by using the measurement of the angular position of the gimbal, the measurement of the rotational speed of the flywheel, and the measurement of the attitude of the satellite.

Techniques for improving the quality of images captured by a remote sensing overhead platform such as a satellite. Sensor shifting is employed in an open-loop fashion to compensate for relative motion of the remote sensing overhead platform to the Earth. Control signals are generated for the sensor shift mechanism by an orbital motion compensation calculation that uses the predicted ephemeris (including orbit dynamics) and image geometry (overhead platform to target). Optionally, the calculation may use attitude and rate errors that are determined from on-board sensors.

The present technology relates to an artificial satellite and a control method thereof that enable to ensure quality of a captured image while suppressing battery consumption. An artificial satellite includes: an imaging device configured to perform imaging of a predetermined region on the ground; and a management unit configured to change accuracy of attitude control in accordance with a remaining battery amount at an instructed imaging time, and configured to change an imaging condition in accordance with accuracy of the attitude control. The present technology can be applied to, for example, an artificial satellite or the like that performs satellite remote sensing by formation flight.

Method, apparatus, and computer program product are provided for estimating crop type and/or sowing date. In some embodiments, a historical crop growth time series and a plurality of simulated crop growth time series are determined, and the historical time series is matched against each simulated time series to determine an estimated crop type and/or sowing date. For example, one simulated time series may be determined for each crop type/sowing date combination within a set of one or more crop types and one or more sowing dates based on historical crop data. Each time series represents crop growth in an area of interest and comprises element(s) including crop-specific parameter(s), such as leaf area index (LAI). The historical time series may be determined based on remote sensor data. Each simulated time series may be determined using a crop growth simulation model and based on historical crop data, geospatial data, and weather data.

The purpose of the present invention is to provide an observation control device, an observation system, a spacecraft, an observation control method, and an observation control program which enable stable observation. An observation control device 60 applicable to a plurality of sensor systems (#1 to #n) mounted on a spacecraft for the purpose of observation is provided with: a determination unit that determines whether each of the sensor systems (#1 to #n) is in a normal observable state; and an adjustment unit that, when at least one of the sensor systems (#1 to #n) is determined not to be in a normal observable state, adjusts the allocation state of a target searching and/or tracking function in sensors, among the sensor systems (#1 to #n), determined to be in the normal observable state.