Closed form optimal continuous guidance scheme for new dynamic of electrical propulsion plane change transfers

Abstract

New guidance policies for the problem of low-thrust transfer between inclined orbits are developed within the framework of optimal control theory. The objectives of this guidance schemes are to provide appropriate thrust steering programmes that will transfer the vehicle from inclined low earth orbits to high earth orbits. The presented guidance schemes are determined by using optimal control theory such that two optimal performance measures are minimized. In this work, the independent variable is changed from time to thrust angle and some properties of autonomous system equations are considered to obtain the exact closed form solutions. Three states are considered, orbital inclination, velocity, and ascending node, to establish this dynamic system. Finally, two performances are investigated for new class of electrical propulsion plane change manoeuvres.

Minimum-time open-loop and closed-loop optimal guidance with GA-PSO and neural fuzzy for Samarai MAV flight

“…Therefore, it would let users choose their missions with expandability upon targets. The current research increases the previous studies [18][19][20] to achieve closed-loop guidance policies regarding TS fuzzy logic based on minimum time performance index for MAVs (Samarai). The resulting optimal guidance law would be composed of the …”

Introducing a novel algorithm for minimum-time low-thrust orbital transfers with free initial condition

“…Procedures of obtaining the pertinent equations have been discussed in ShaEeenejad and Novinzadeh. 38,39 Dynamics equations are considered for a variable-mass spacecraft. In the initial time, spacecraft is on the circular orbit a 0 , i 0 , which is indicative of the orbital inclination and orbital radius and moves with a constant magnitude of the thrust that constitutes the control angle (t).…”