AircraftStateElementConverter Properties

Gets or sets the weights to be applied to the state elements when computing the error which determines how to adapt the step size during integration. This is in addition to any weights used in the integration algorithm itself. The weights are initialized to default values of one based on the Order and Dimension of the state element. The order of the motion is one less than the Order and each array is of length Dimension.

Gets the number of parameters (per Order) within this element.

Gets the ellipsoidal shape to be used in converting the propagation state elements.

Gets the string identifying this instance in the overall output.

Gets the initial values of this element of the state and their derivatives. The size of the initial state is its Dimension and the order of the motion is one less than the Order of the differential equation defining the derivative of this element.

Gets a value indicating whether the methods on this instance are safe to call from multiple threads simultaneously.

Gets the order of the differential equation corresponding to this element. This corresponds to one greater than the Order of the InitialState.

Gets the indices locating each variable of this element within the overall state. The motion represents the value of this state element and its derivatives up to but not including the Order of the differential equation defining the state's derivative. The indices will be set by the NumericalPropagatorDefinition when this element is added.

Gets the type associated with the output of this instance.