A dual band infrared imaging system self-contained to fit within a small spacecraft is provided. The imaging system uses a detector array cooled by a mini cryocooler, and includes telescope optics and two bandpass filters for fire detection and thermal and evapotranspiration Earth science.

A method of controlling a satellite and a computer-readable recording medium are provided. The method is for controlling a satellite moving along an orbit having an inclination angle from the equatorial plane to capture due-north images. The method includes: determining a position of the satellite; calculating a roll angle and a pitch angle of the satellite for pointing a line-of-sight vector of the satellite to a first ground surface being a photographing point; determining a compensation angle by considering effects of the inclination angle and rotation of the Earth so as to capture images in the due north direction of the photographing point; calculating a yaw angle based on the compensation angle; and rotating the satellite according to the calculated roll angle, pitch angle, and yaw angle.

A device for deploying and pointing an equipment item is disclosed including a mobile platform for receiving the equipment item, a carrier integrally secured to a wall of a spacecraft, and three identical linear actuators which connect the carrier to the mobile platform and are suitable for moving the platform in translation along one axis and for orienting the platform in rotation about two axes. Each linear actuator including a first portion connected to the platform by a universal joint, a second portion connected to the carrier by a pivot connection, a motor, and a screw/nut joint interconnecting the two portions, each universal joint being suitable for preventing the screw/nut joint from rotating about the axis, such that driving the motor causes a translational movement between the first and the second portion.

A spacecraft control system and method for determining the necessary delta-V and timing for impulsive maneuvers to change the plane of an orbit or the size of the orbit of a secondary spacecraft that is in an orbit around a primary spacecraft. The system and method uses an apocentral coordinate system for the relative orbital motion and geometric relative orbital elements to determine the required impulsive velocity change and time to maneuver, for relative orbital changes in which only one of slant or colatitude of the sinilaterating node changes.

For generating a points-of-interest plan, a method generates communication graph nodes for at least one satellite. The method calculates communication graph edges from the communication graph nodes, wherein the communication graph nodes and the communication graph edges comprise a communication graph. The method solves the communication graph to yield a communication plan. The method generates a points-of-interest plan from the communication plan.

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.

Space system comprising a structure formed by structure components, an on-board equipment carried by the structure, and a passive device designed to facilitate demise of the space system during re-entry into the Earth's atmosphere. The passive device comprises connecting members designed to stably connect the structure components. The connecting members comprise at least a portion made of a primer material with characteristics such as to decay at re-entry altitudes higher than those at which the current connecting members melt so as to make unstable the connection created by the connecting members to such an extent as to early triggering demise of the structure of the space system during re-entry into the Earth's atmosphere.

A satellite with a paraboloid mirror fabricated while in space is described. The mirror is formed by solidifying liquid precursor material after its surface assumes a paraboloid shape as a result of compound rotation of the satellite. The mirror is preferably formed from a photopolymer which creates a rigid paraboloid mirror surface upon exposure to a cross-linking radiation source. Optical coating(s) deposition system is described. Several deployable satellite structures, including mirror support are executed in shape memory materials and are deployed by application of heat.

A satellite in orbit around a planetary body includes a bus and a drag flap coupled to the bus. The drag flap is used to increase the drag torque applied to the satellite. The bus may house sensors and actuators, such as a star tracker, a gyroscope, a reaction wheel, and a global position system (GPS) receiver to monitor the attitude of the satellite in response to the applied drag torque. The measurements from the sensors and actuators may be used to determine the drag torque applied to the satellite. An estimate of the atmospheric density may be then be determined based on the drag torque. Compared to conventional approaches, the satellite and methods described herein estimates the atmospheric density at comparable, if not better, resolution and bandwidth. The atmospheric density estimates may also be acquired in real-time using a cheaper, lighter, and smaller satellite.

In one embodiment, an optical system includes: a first lens configured to receive incoming light from an object; a first mirror comprising a central aperture, the first mirror configured to refract the light from the first lens, reflect the light, and refract the light reflected from the first mirror; a second mirror configured to receive the light from the first mirror, wherein the light is refracted towards a first surface of the second mirror where the light is reflected back and refracted upon exiting the second mirror; a negative corrector lens configured to refract the light from the second mirror through the central aperture of the first mirror; and a positive corrector lens configured to receive the light through the central aperture of the first mirror and refract the light to an imaging surface.