Abstract: A method, apparatus and system for controlling an attitude of a spacecraft, the spacecraft including an attitude control system operatively associated with a ground-based spacecraft control system. According to an exemplary embodiment, the spacecraft attitude control system uses a B-spline interpolator for commanding the spacecraft and a Kalman filtering process is used to estimate B-spline interpolator coefficients. The methods and systems disclosed herein can be implemented in, for example, executable machine code and/or integrated circuit hardware.

Abstract: A method, apparatus and system for controlling an attitude of a spacecraft, the spacecraft including an attitude control system operatively associated with a ground-based spacecraft control system. According to an exemplary embodiment, the spacecraft attitude control system uses a B-spline interpolator for commanding the spacecraft. The methods and systems disclosed herein can be implemented in, for example, executable machine code and/or integrated circuit hardware.

Abstract: A method, apparatus and system including the execution of an accelerated optimization method. According to an exemplary embodiment, the accelerated optimization method includes: first-order optimality conditions for a generic nonlinear optimization problem are generated as part of the terminal transversality conditions of an optimal control problem. It is shown that the Lagrangian of the optimization problem is connected to the Hamiltonian of the optimal control problem via a zero-Hamiltonian, infinite-order, singular arc. The necessary conditions for the singular optimal control problem are used to produce an auxiliary controllable dynamical system whose trajectories generate algorithm primitives for the optimization problem. A three-step iterative map for a generic algorithm is designed by a semi-discretization step. Neither the feedback control law nor the differential equation governing the algorithm need be derived explicitly.

Abstract: A method and system for generating an optimal trajectory path tasking for an unmanned aerial vehicle (UAV) for collection of data on one or more collection targets by a sensor on the UAV.

Abstract: The invention relates to route planning and optimization. In some embodiments, the invention includes obtaining vertex data describing target attributes, including at least one target location, and process dynamics data describing system constraints of a process; defining vertex functionals, describing attribute requirements, and edge functionals, which use the system constraints to determine cost requirements, for cost objectives; and using the data, the functionals, and the cost objectives to construct a T-graph that includes a label space representing the target attributes. Next, the T-graph is solved to construct a label space trajectory by determining waypoints such that the process (1) travels through all target locations and (2) satisfies the attribute requirements, dynamically calculating travel cost by applying the cost requirements to each intervening edge, and minimizing the travel cost according to the cost objectives.

Abstract: A method and system for generating an optimal trajectory path tasking for an unmanned aerial vehicle (UAV) for collection of data on one or more collection targets by a sensor on the UAV.

Abstract: A mission planning system for scheduling the operations of one or more ground stations in order to optimize overall system communications with a plurality of satellites. The mission planning system comprises a digital processor in communication with each ground station, with the digital processor acting to assess the benefits and penalties acting in the system as a whole over a given time horizon. A system-wide cost function evaluated by the processor generally compares resultant SNR and slewing penalties for achievable communications, and provides a control vector uj(t) for each ground station determined through an optimization process, in order that various physical constraints and weighting factors pertinent to an individual ground station may be incorporated and accommodated as the digital processor optimizes overall system communications.

Abstract: The disclosure provides a closed-loop controller for a controlled system comprising a comparison element generating an error e, a compensator generating a control uN value based on the error e, and a control allocator determining a manipulated parameter uM value based on the control uN. The control allocator typically utilizes a control effectiveness function and determines uM value by selecting one or more specific system x0 signals from the system state xi or system input yj values or system parameters values pk reported, defining a plurality of distributed xD around each specific system x0 signal, and minimizing an error function E(zi), where the error function E(zi) is based on errors which arise from use of the plurality of distributed xD in the control effectiveness function rather than one or more specific system x0 signals.

Abstract: The disclosure provides a robotic arm controller which determines a control parameter for at least one actuator comprising the robotic arm using a control equation having the general form Ax=b, where A is a transformation matrix A based on the geometry and Jacobian of the robotic arm, x is the control parameter x such as a torque vector at a specific joint, and b is the end effector parameter b which specifies a desired corrective state of the end effector. The methodology, by way of constructing and solving an unscented optimization problem, provides a solution to the Ax=b problem by perturbing at least one joint angle appearing in the Jacobian to generate a plurality of distributed joint angles, determining a control parameter x which minimizes an error function.

Abstract: The disclosure provides a method and apparatus for determination of a control policy for a rigid body system, where the rigid body system comprises a sensor and a plurality of actuators designed to maneuver the rigid body system and orient the sensor toward a plurality of defined vertices, such as geographic points on the earth surface. A processor receives input data describing an initial state of the rigid body system and further receives a plurality of candidate vertices for potential targeting by the sensor. The processor additionally receives an intrinsic value for each vertex, reflecting the relative desirability of respective vertices in the plurality of vertices. The processor determines an appropriate control policy based on the vertices, the intrinsic values, and the rigid body system through a formulation of the determination process as an optimization problem which actively considers various constraints during the optimization, such as maneuvering and observation constraints.

Abstract: Methods, systems and computer readable media are presented for computing a guidance control policy to transition an uncertain dynamical system from an initial state to a final state, in which a set of points are computed to provide discreet and accurate representation of uncertainty, and in which a guidance control policy is computed based on a set of equations involving the initial state, the final state, state variables, control variables, and parameters, as well as designated parameters of interest, a set of constraints corresponding to state and control variables, a performance metric, statistical distribution types corresponding to the parameters of interest, statistical moments individually corresponding to the parameters of interest, and weighting values corresponding to the parameters of interest.

Abstract: Unscented optimal control combines the unscented transform with optimal control to produce a new approach to directly manage navigational and other uncertainties in an open-loop framework. The sigma points of the unscented transform are treated as controllable particles that are all driven by the same open-loop controller. A system-of-systems dynamical model is constructed where each system is a copy of the other. Pseudo-spectral optimal control techniques may be applied to this system-of-systems to produce a computationally viable approach for solving the large-scale optimal control problem.

Abstract: A method, apparatus and system is provided for reducing an amount of information transmitted to a vehicle in order to implement attitude control of the vehicle. In accordance with the present invention, data corresponding to at least one time-varying attitude command trajectory defining an attitude of the vehicle is reduced, for example, into a vector of polynomial coefficients. The vector of polynomial coefficients then are transmitted to the vehicle, where they are used to reconstruct the at least one time-varying attitude command trajectory via a polynomial interpolation operation.

Abstract: Methods and apparatus are presented for spacecraft operation using non-Eigen axis attitude transitions via control momentum gyroscopes (CMGs) to avoid or mitigate singularities by providing a time-varying attitude command vector including a plurality of time-varying attitude command signals or values representing a plurality of spacecraft states and control trajectories as a guidance command input to an attitude controller of the spacecraft without modifying the spacecraft feedback control law.

Abstract: A method, apparatus and system is provided for reducing an amount of information transmitted to a vehicle in order to implement attitude control of the vehicle. In accordance with the present invention, data corresponding to at least one time-varying attitude command trajectory defining an attitude of the vehicle is reduced, for example, into a vector of polynomial coefficients. The vector of polynomial coefficients then are transmitted to the vehicle, where they are used to reconstruct the at least one time-varying attitude command trajectory via a polynomial interpolation operation.

Abstract: Methods and apparatus are presented for spacecraft operation in which a control problem is formulated using a control law or steering law as a path constraint or as a dynamic constraint, and the control problem is solved to provide a guidance command trajectory for use in operating spacecraft control momentum gyroscopes to guide the spacecraft from an initial state to a desired final state.