Power-limited low-thrust trajectory optimization with operation point detection

The power-limited solar electric propulsion system is considered more practical in mission design. An accurate mathematical model of the propulsion system, based on experimental data of the power generation system, is used in this paper. An indirect method is used to deal with the time-optimal and fuel-optimal control problems, in which the solar electric propulsion system is described using a finite number of operation points, which are characterized by different pairs of thruster input power. In order to guarantee the integral accuracy for the discrete power-limited problem, a power operation detection technique is embedded in the fourth-order Runge-Kutta algorithm with fixed step. Moreover, the logarithmic homotopy method and normalization technique are employed to overcome the difficulties caused by using indirect methods. Three numerical simulations with actual propulsion systems are given to substantiate the feasibility and efficiency of the proposed method.

[1]  John R. Brophy,et al.  Electric Propulsion for Solar System Exploration , 1998 .

[2]  Joseph E. Riedel,et al.  The Deep Space 1 autonomous navigation system - A post-flight analysis , 2000 .

[3]  R. Epenoy,et al.  New smoothing techniques for solving bang–bang optimal control problems—numerical results and statistical interpretation , 2002 .

[4]  Marc D. Rayman,et al.  Design of the First Interplanetary Solar Electric Propulsion Mission , 2002 .

[5]  M. Patterson,et al.  Wear Test Results for the NEXT Ion Engine , 2003 .

[6]  C. A. Kluever,et al.  Engine-switching strategies for interplanetary solar-electric-propulsion spacecraft , 2005 .

[7]  John W. Hartmann,et al.  Trajectory and System Analysis For Outer-Planet Solar-Electric Propulsion Missions , 2005 .

[8]  Cesar A. Ocampo,et al.  Low-Thrust Variable-Specific-Impulse Transfers and Guidance to Unstable Periodic Orbits , 2005 .

[9]  Alessandro Antonio Quarta,et al.  Fuel-optimal, power-limited rendezvous with variable thruster efficiency , 2005 .

[10]  Ryan P. Russell,et al.  Primer Vector Theory Applied to Global Low-Thrust Trade Studies , 2006 .

[11]  Michael Cupples,et al.  Application of Solar Electric Propulsion to a Comet Surface Sample Return Mission , 2006 .

[12]  Pierre Martinon,et al.  Using switching detection and variational equations for the shooting method , 2007 .

[13]  John W. Dankanich.  Low-Thrust Mission Design and Application , 2010 .

[14]  Damon Landau,et al.  Electric Propulsion System Selection Process for Interplanetary Missions , 2011 .

[15]  Alessandro Antonio Quarta,et al.  Minimum-time space missions with solar electric propulsion , 2011 .

[16]  Hexi Baoyin,et al.  Practical Techniques for Low-Thrust Trajectory Optimization with Homotopic Approach , 2012 .

[17]  D. Izzo,et al.  Time-optimal trajectories to circumsolar space using solar electric propulsion , 2013 .

[18]  Hexi Baoyin,et al.  A low-thrust transfer between the Earth–Moon and Sun–Earth systems based on invariant manifolds , 2013 .

[19]  D. Jewitt,et al.  EPISODIC EJECTION FROM ACTIVE ASTEROID 311P/PANSTARRS , 2014, The Astrophysical Journal.

[20]  Peng Zhang,et al.  Fuel-optimal trajectory design using solar electric propulsion under power constraints and performance degradation , 2014 .

[21]  Hongwei Yang,et al.  Fuel-optimal control for soft landing on an irregular asteroid , 2015, IEEE Transactions on Aerospace and Electronic Systems.

[22]  Francesco Topputo,et al.  Low-Thrust Minimum-Fuel Optimization in the Circular Restricted Three-Body Problem , 2015 .

[23]  Hexi Baoyin,et al.  Low-cost transfer between asteroids with distant orbits using multiple gravity assists , 2015 .

[24]  Stefano Campagnola,et al.  Global search for low-thrust transfers to the Moon in the planar circular restricted three-body problem , 2017 .

[25]  R. de la Fuente Marcos,et al.  Asteroid (469219) 2016 HO3, the smallest and closest Earth quasi-satellite , 2016, 1608.01518.

[26]  Hongwei Yang,et al.  Rapid Generation of Time-Optimal Trajectories for Asteroid Landing via Convex Optimization , 2017 .

[27]  Zhemin Chi,et al.  Homotopy method for optimization of variable-specific-impulse low-thrust trajectories , 2017 .

[28]  Hexi Baoyin,et al.  J2-Perturbed Multitarget Rendezvous Optimization with Low Thrust , 2017 .

[29]  Fanghua Jiang,et al.  Improving Low-Thrust Trajectory Optimization by Adjoint Estimation with Shape-Based Path , 2017 .

[30]  Ping Lu,et al.  Celebrating Four Decades of Dedication and Excellence , 2018 .