Rocket control is a difficult and unpredictable task in environments with inclement weather. As a result, launch missions are often strictly limited based on weather conditions. The present invention provides a method for controlling a rocket to account for environmental uncertainties and maintain optimal mission performance. First, sensors collect data about the rocket's environment, passing the information to storage in the rocket's database. Second, the rocket's processor manipulates the database with an optimization algorithm producing instructions. Third, the instructions command the rocket's control system for an optimal end-to-end trajectory and to enable the rocket to perform a safe landing.

The invention relates to a system and method for autonomous navigation of a host satellite equipped with moving and orienting means, a unit for controlling these means, and at least one on-board image-acquisition camera, said method comprising the following steps: acquiring (E1) a plurality of images; default processing of said images, referred to as long-range processing (E2), configured to detect and identify space objects and to calculate their relative orbits; conditional processing of said acquired images, referred to as short-range processing (E3), configured to estimate the attitude of at least one of said space objects, referred to as target object, detected during the long-range processing, this step being implemented when said long-range step detects at least one space object located at a distance estimated to be less than a predetermined threshold distance; determining (E4) a possible rendezvous between at least said target object and the host satellite; preparing and transmitting instructions (E5) to said control unit of said moving means based on at least one rendezvous and/or risk of collision determined in the previous step.

A vehicle is described herein that is capable of operating in space. The vehicle comprises a memory that stores computer-executable instructions. The vehicle further comprises a processor in communication with the memory, wherein the computer-executable instructions, when executed by the processor, cause the processor to: derive an equation of motion for the vehicle; determine an initial guess of a first value of a costate of the vehicle; determine the first value of the costate for a minimum propellant transfer in averaged orbit dynamics using the equation of motion, the initial guess, and a single shooting technique; determine a second value of the costate for the minimum propellant transfer in full-state orbit dynamics using the first value of the costate and the single shooting technique; and adjust a path of the vehicle to cause the vehicle to travel along an optimal transfer in full-state orbit dynamics.

A terrestrial-based system for is described herein that can determine a minimum time transfer for an extraterrestrial vehicle. The terrestrial-based system comprises a memory that stores computer-executable instructions. The terrestrial-based system further comprises a processor in communication with the memory, wherein the computer-executable instructions, when executed by the processor, cause the processor to: derive an averaged equation of motion for the extraterrestrial vehicle; determine an initial guess of a first value of a costate of the extraterrestrial vehicle; determine the first value of the costate for the minimum time transfer in averaged orbit dynamics; determine a second value of the costate for the minimum time transfer in full-state orbit dynamics; generate instructions for causing the extraterrestrial vehicle to travel along an optimal transfer in full-state orbit dynamics; and cause the extraterrestrial vehicle to adjust trajectory based on the generated instructions.

A vehicle is described herein that is capable of operating in space. The vehicle comprises a memory that stores computer-executable instructions. The vehicle further comprises a processor in communication with the memory, wherein the computer-executable instructions, when executed by the processor, cause the processor to: derive an equation of motion for the vehicle; determine an initial guess of a first value of a costate of the vehicle; determine the first value of the costate for a minimum time transfer in averaged orbit dynamics using the equation of motion, the initial guess, and a single shooting technique; determine a second value of the costate for the minimum time transfer in full-state orbit dynamics using the first value of the costate and the single shooting technique; and adjust a path of the vehicle to cause the vehicle to travel along an optimal transfer in full-state orbit dynamics.

A terrestrial-based system for is described herein that can determine a minimum propellant transfer for an extraterrestrial vehicle. The terrestrial-based system comprises a memory that stores computer-executable instructions. The terrestrial-based system further comprises a processor in communication with the memory, wherein the computer-executable instructions, when executed by the processor, cause the processor to: derive an averaged equation of motion for the extraterrestrial vehicle; determine an initial guess of a first value of a costate of the extraterrestrial vehicle; determine the first value of the costate for the minimum propellant transfer in averaged orbit dynamics; determine a second value of the costate for the minimum propellant transfer in full-state orbit dynamics; generate instructions for causing the extraterrestrial vehicle to travel along an optimal transfer in full-state orbit dynamics; and cause the extraterrestrial vehicle to adjust trajectory based on the generated instructions.

An optimal rescue orbital elements online decision-making method based on RBFNN for launch vehicles under thrust drop fault includes establishing the flight dynamic equations of launch vehicles in the second-stage ascending phase in the geocentric inertial coordinate system, to construct a series of optimization problems of maximum semi-major axis of circular orbit under the thrust drop fault. The method further includes using the adaptive pseudo-spectrum method to solve the optimization problems of maximum semi-major, and using the maximum and minimum method to normalize the sample data to [1, 1], using the orthogonal least square method to select the data center of the radial basis function neural network (RBFNN), where the Gaussian function is selected as the radial basis function, and the RBFNN is trained offline to establish a nonlinear mapping relationship from the fault states to the optimal rescue orbital elements.

A space-based circuit-replacing robotic system and method include a satellite grasper configured to grasp the satellite having a printed circuit onto which an integrated circuit is soldered and the integrated circuit is to be replaced; an access mechanism configured to remove the printed circuit and/or to provide access to the printed circuit; a printed circuit orientation device configured to orient a printed circuit such that sunlight is incident on the printed circuit; one or more temperature sensors configured to measure a temperature of the solder on the printed circuit; a processor configured to adjust a rate of heating to match a desired heating rate; a circuit grasping device configured to position the circuit for replacement; and an optical shield that is configured to be adjusted to allow light to pass substantially only to a desired area of the printed circuit.

Systems and methods for describing, simulating and/or optimizing spaceborne systems and missions. Configurations for spaceborne systems are generated and validated based on simulation output.

A method and satellite for capture-less management of orbital debris objects, include controlling a satellite having opposing thrusters to be maintained at a predetermined distance from an orbital debris object to be managed, i.e., paired with the orbital debris object. Management may include fine tracking of the orbital debris object and/or operating the opposing thrusters to apply force to the orbital debris object to generate a model of the orbital debris object, to change the attitude of the orbital debris object, to deorbit the orbital debris object, and/or breakup the orbital debris object.