A star tracker has an electronically steerable point of view, without requiring a precision aiming mechanism. The star tracker can be strapped down, thereby avoiding problems associated with precision aiming of mechanical devices. The star tracker images selectable narrow portions of a scene, such as the sky. Each stellar sighting can image a different portion of the sky, depending on which navigational star or group of navigational stars is of interest. The selectability of the portion of the sky imaged enables the star tracker to avoid unwanted light, such as from the sun.

Techniques for placing a satellite into a highly inclined elliptical operational orbit (HIEO) having an argument of perigee of 90 or 270 include executing an orbit transfer strategy that transfers the satellite from a launch vehicle deployment orbit to the operational orbit. The launch vehicle deployment orbit is selected to have an argument of perigee of approximately 90 greater than the argument of perigee of the operational orbit, and to be substantially lower than the operational orbit. The orbit transfer strategy includes (i) an apsidal rotation of approximately 90, at least a substantial part of the apsidal rotation being attained without expenditure of any satellite propellant; and (ii) an electric orbit raising maneuver to attain an apogee altitude and a perigee altitude required by the HIEO.

A modular satellite system is provided comprising a main body member, one or more controllers, a communication system, a datastore, a power unit, and one or more orbital cameras. The controller(s) may be operable to perform a mission instruction. The communication system may be in communication with the controller(s) and with a client terminal. The datastore may store data accessible by the controller(s). The orbital camera(s) may be operable to capture one or more image(s) associated with the mission instruction, which may be defined as captured image(s). The controller(s) may be operable to detect and identify one or more predetermined object(s) in the one or more captured image(s). The controller(s) may generate a mission analytics packet, and the controller(s) may be operable to transmit the mission analytics packet to the client terminal.

Enclosures for facilitating activities in space, and associated systems and methods, are disclosed. A representative system includes a spacecraft having an enclosed interior volume (which can be formed by an inflatable membrane) and one or more unmanned aerial vehicles (UAVs) carried by the spacecraft and positioned to deploy into the enclosed interior volume. The system can include a remote-control system to control the one or more UAVs from a terrestrial location while the spacecraft is in space. A wireless charging system can provide electrical power to the one or more UAVs. A representative method includes configuring one or more controllers to launch a first spacecraft to a first orbit, launch a second spacecraft to a second orbit, move the first spacecraft to the second orbit, dock the first spacecraft with the second spacecraft, and broadcast an event within an interior volume of the first spacecraft to a terrestrial location.

A space vehicle system includes a first star tracker disposed at a first location on or near the space vehicle, the first star tracker configured to obtain first images of a space object and stars and a second star tracker disposed at a second location on or near the space vehicle, at a distance D from the first location. The second star tracker is configured to obtain second images of the space object and the stars and the first images and the second images being stereoscopic images. The system also includes a processor configured to determine an estimate of a range from the space vehicle to the space object based on the first images and the second images.

Spacecrafts are disclosed herein. The spacecraft can include a primary payload sensor, the primary payload sensor being aligned to capture images in a direction of a first axis, and at least one secondary imaging system for determining a position of the spacecraft, the at least one secondary imaging system being aligned to capture images in the direction of a second axis. The at least one secondary imaging system can include a housing, the housing including a first end and a second end, wherein the first end includes an opening into an internal portion of the housing, an image sensor positioned within the internal portion of the housing, and an optical element positioned within the internal portion of the housing, wherein the optical element has a length parameter and a width parameter, wherein one of the length parameter and the width parameter is larger than the other parameter.

A debris removal satellite includes a capture device, a thruster of a chemical propulsion method, and a propellant tank to store chemical fuel. A solar array wing is operable in an orbit at an orbital altitude higher than a congested orbit region congested with satellites forming a satellite constellation. The debris removal satellite is built in advance for future use as a satellite to be launched, and when a debris intrusion alarm to give a warning about intrusion of debris into the congested orbit region is issued, propellant is loaded into the propellant tank and the debris removal satellite is launched by a rocket built in advance for future use as a launch rocket. The debris removal satellite captures capture-target debris at an orbital altitude higher than the congested orbit region, and operates a propulsion device with the capture-target debris being captured.

A method for determining the position of a spacecraft in space includes receiving image data from a plurality of differently oriented optics modules, processing the received image data and computing a position, a rate of rotation and/or direction of rotation from the processed image data. The method may be carried out with the aid of at least one image processing module, a device for carrying out such a method, and a computer program for carrying out such a method on such a device.

A debris removal satellite includes a capture device, a thruster of a chemical propulsion method, and a propellant tank to store chemical fuel. A solar array wing is operable in an orbit at an orbital altitude higher than a congested orbit region congested with satellites forming a satellite constellation. The debris removal satellite is built in advance for future use as a satellite to be launched, and when a debris intrusion alarm to give a warning about intrusion of debris into the congested orbit region is issued, propellant is loaded into the propellant tank and the debris removal satellite is launched by a rocket built in advance for future use as a launch rocket. The debris removal satellite captures capture-target debris at an orbital altitude higher than the congested orbit region, and operates a propulsion device with the capture-target debris being captured.