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adaptive optimization method of multiple firing for determining optimal trajectories of spacecraft
adaptive optimization method of multiple firing for determining optimal trajectories of spacecraft
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机译：多次发射的自适应优化确定航天器最优轨迹的方法
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摘要
Method for determining a path for a transfer of a spacecraft from a space body starting up a space objective body about a central space given body, where the given path is optimal regarding a requirement since a space mission It must be performed by the transfer of the spacecraft; wherein the method includes: providing, according to the maximum principle of Pontryagin, a physical-mathematical model that relates quantities model and physical quantities representing the transfer of the spacecraft relative to the central space given body, wherein the amounts of model include a first amount vector model (λv) and a second amount vector model (λr), wherein the first amount vector model (λv) has a first module that changes over time and a first spatial orientation changing over time and is defined by a first angle length (Φv) that changes over time and a first angle of elevation (& thetasym; v) which changes over time, wherein the first amount vector model (λv) represents, moment by moment, a respective optimum direction of momentum of the spacecraft relative to the requirement given space mission, wherein the second vector quantity l model (λr) has a second module that changes over time and a second spatial orientation which changes over time, and is defined by a second angle length (& thetasym; r) that changes over time and a second elevation angle (& thetasym; r) which changes over time, where the second amount vector model (λr) represents, moment by moment, an evolution over time of the first amount vector model (λv); * Fit the mathematical physical model conditions boundary initial and end where the initial boundary conditions are such that at an initial time (t0) of the transfer position (r) and speed (V) of spacecraft are near the position (rtierra) and speed (Vtierra), respectively, the spatial starting body, where the final boundary conditions are such that, in a final time (tf) of the transfer position (r ) and speed (V) of the spacecraft are near the position (rmarte) and speed (Vmarte) respectively of the target space body; * Adjustment in the physical-mathematical model of the first conditions such that the second module associated with the first module via a speed related to the angular amount which depends the central space given body; * Fit the mathematical physical model of the second conditions such that a specific longitude angle between the first angle length (Φ v) and the second angle length (Φ r), and a specific elevation angle, between the first elevation angle (& thetasym; v) and the second angle of elevation (& thetasym; r), are independent of each other; * Consideration of the first initial time (t0) included in a given time range, the first length values of the specific angle of length included in a given length range and the first elevation values specific elevation angle included in an range given elevation; and * determining a path for transferring the spacecraft based on the physical-mathematical model of the first initial time (t0) considered, the first length values considered and the first elevation values considered.
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