LOW-THRUST PROPULSION VEHICLE WITH TRAJECTORY OPTIMIZATION USING MINIMUM PROPELLANT TRANSFER
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.
1 . A vehicle capable of operating in space, the vehicle comprising:
a memory that stores computer-executable instructions; and
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.
2 . The vehicle of claim 1 , wherein the computer-executable instructions, when executed by the processor, further cause the processor to determine the initial guess of the first value of the costate of the vehicle as corresponding to trajectory boundary conditions of the vehicle.
3 . The vehicle of claim 1 , wherein the computer-executable instructions, when executed by the processor, further cause the processor to determine the second value of the costate in the full-state orbit dynamics using the first value of the costate and the single shooting technique by applying multivariate root solvers to solve for a set of variables that minimize a set of constraints defined within a constraints vector.
4 . The vehicle of claim 1 , wherein the computer-executable instructions, when executed by the processor, further cause the processor to generate the instructions for causing the vehicle to travel along the optimal transfer in the full-state orbit dynamics including a path between an initial position and a final position for the vehicle to follow, wherein the path corresponds to the vehicle using minimum propellant to reach the final position.
5 . A non-transitory, computer-readable medium comprising computer-executable instructions, wherein the computer-executable instructions, when executed by a computer system, cause the computer system to:
derive an equation of motion for an 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;
generate instructions for causing the vehicle to travel along an optimal transfer in full-state orbit dynamics; and
adjust a path of the vehicle to cause the vehicle to travel along an optimal transfer in full-state orbit dynamics.
6 . The non-transitory, computer-readable medium of claim 5 , wherein the computer-executable instructions further include instructions, when executed by a computer system, cause the computer system to determine the initial guess of the first value of the costate of the vehicle as corresponding to trajectory boundary conditions of the vehicle.
7 . The non-transitory, computer-readable medium of claim 5 , wherein the computer-executable instructions further include instructions, when executed by a computer system, cause the computer system to determine the second value of the costate in the full-state orbit dynamics using the first value of the costate and the single shooting technique by applying multivariate root solvers to solve for a set of variables that minimize a set of constraints defined within a constraints vector.
8 . The non-transitory, computer-readable medium of claim 5 , wherein the computer-executable instructions further include instructions, when executed by a computer system, cause the computer system to generate the instructions for causing the vehicle to travel along the optimal transfer in the full-state orbit dynamics including a path between an initial position and a final position for the vehicle to follow, wherein the path corresponds to the vehicle using minimum propellant to reach the final position.
9 . The non-transitory, computer-readable medium of claim 5 , wherein the computer-executable instructions further include instructions, when executed by a computer system, cause the computer system to determine a user-specified transfer time when the averaged orbit dynamics derives in response to minimizing propellant usage for the vehicle.
10 . The non-transitory, computer-readable medium of claim 9 , wherein the computer-executable instructions further include instructions, when executed by a computer system, cause the computer system to determine the first value of the costate in the averaged orbit dynamics using the equation of motion, the initial guess, the single shooting, and the user-specified transfer time.
11 . The non-transitory, computer-readable medium of claim 5 , wherein the computer-executable instructions further include instructions, when executed by a computer system, cause the computer system to determine the first value of the costate in the averaged orbit dynamics by solving a two-point boundary value problem with the equation of motion and the initial guess as inputs, wherein the two-point boundary value problem is solved with the single shooting technique.
12 . The non-transitory, computer-readable medium of claim 5 , wherein the computer-executable instructions further include instructions, when executed by a computer system, cause the computer system to determine the first value of the costate for the minimum propellant transfer over a fixed-transfer time in the averaged orbit dynamics using the equation of motion, the initial guess, and the single shooting technique.
13 . A computer-implemented method for determining a trajectory for an vehicle, the method comprising:
deriving an equation of motion for the vehicle;
determining an initial guess of a first value of a costate of the vehicle;
determining 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;
determining 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;
generating instructions for causing the vehicle to travel along an optimal transfer in full-state orbit dynamics; and
adjusting a path of the vehicle to cause the vehicle to travel along an optimal transfer in full-state orbit dynamics.
14 . The method of claim 13 , wherein determining the initial guess of the first value of the costate comprises determining the initial guess of the first value of the costate of the vehicle as corresponding to trajectory boundary conditions of the vehicle.
15 . The method of claim 13 , wherein determining the second value of the costate in the full-state orbit dynamics using the first value of the costate and the single shooting technique comprises determining the second value of the costate in the full-state orbit dynamics using the first value of the costate and the single shooting technique by applying multivariate root solvers to solve for a set of variables that minimize a set of constraints defined within a constraints vector.
16 . The method of claim 13 , wherein generating instructions for causing the vehicle to travel along the optimal transfer in the full-state orbit dynamics comprises generating the instructions for causing the vehicle to travel along the optimal transfer in the full-state orbit dynamics including a path between an initial position and a final position for the vehicle to follow, wherein the path corresponds to the vehicle using minimum propellant to reach the final position.
17 . The method of claim 13 , further comprising determining a user-specified transfer time when the averaged orbit dynamics derives in response to minimizing propellant usage for the vehicle.
18 . The method of claim 17 , further comprising determining the first value of the costate in the averaged orbit dynamics using the equation of motion, the initial guess, the single shooting, and the user-specified transfer time.
19 . The method of claim 13 , wherein determining the first value of the costate in the averaged orbit dynamics using the equation of motion, the initial guess, and the single shooting comprises determine the first value of the costate in the averaged orbit dynamics by solving a two-point boundary value problem with the equation of motion and the initial guess as inputs, wherein the two-point boundary value problem is solved with the single shooting technique.
20 . The method of claim 13 , wherein determining the first value of the costate for the minimum propellant transfer in the averaged orbit dynamics using the equation of motion, the initial guess, and the single shooting technique comprises determining the first value of the costate for the minimum propellant transfer over a fixed-transfer time in the averaged orbit dynamics using the equation of motion, the initial guess, and the single shooting technique.