An Analogy to Bi-Elliptic Transfers Incorporating High and Low-Thrust
نویسندگان
چکیده
g – standard gravitational acceleration, m/s μ gravitational constant, km/s mdry – spacecraft mass without fuel, kg mwet – spacecraft mass with total fuel, kg mhighF – high-thrust system fuel mass, kg mHSTF – hybrid system fuel mass, kg m02 – spacecraft mass after phase 1 of the transfer, kg ∆Vhigh – high-thrust only system ∆V, m/s ∆VH – high-thrust portion of hybrid system ∆V, m/s ∆VL – low-thrust portion of hybrid system ∆V, m/s IspH – high-thrust system specific impulse, s IspL – low-thrust system specific impulse, s Isp HH – Hohmann Vs HST critical specific impulse ratio Isp BH – bi-elliptic Vs HST critical specific impulse ratio
منابع مشابه
Adaptation of Structured Grid for Supersonic and Transonic Flows
Two distinct redistribution grids - adaptation techniques, spring analogy and elliptic grid generator are applied to two-dimensional steady, inviscid, shocked flows, and the ability of each technique is examined and compared. Euler equations are solved base on Roe's Reimann solver approach to simulate supersonic flow around a sphere, transonic flow about an airfoil and supersonic flow in a symm...
متن کاملQuaternion-based Finite-time Sliding Mode Controller Design for Attitude Tracking of a Rigid Spacecraft during High-thrust Orbital Maneuver in the Presence of Disturbance Torques
In this paper, a quaternion-based finite-time sliding mode attitude controller is designed for a spacecraft performing high-thrust orbital maneuvers, with cold gas thrusters as its actuators. The proposed controller results are compared with those of a quaternion feedback controller developed for the linearized spacecraft dynamics, in terms of settling time, steady-state error, number of thrust...
متن کاملLow Thrust Cis-lunar Transfers Using a 40 Kw-class Solar Electric Propulsion Spacecraft
This paper captures trajectory analysis of a representative low thrust, high power Solar Electric Propulsion (SEP) vehicle to move a mass around cislunar space in the range of 20 to 40 kW power to the Electric Propulsion (EP) system. These cislunar transfers depart from a selected Near Rectilinear Halo Orbit (NRHO) and target other cislunar orbits. The NRHO cannot be characterized in the classi...
متن کاملLow-Thrust Optimal Orbit Raising with Plane Change
A new guidance scheme for the problem of Low-thrust transfer between inclined orbits is developed within the framework of optimal control theory. The objective of the guidance scheme is to provide the appropriate thrust steering program that will transfer the vehicle from an inclined low earth orbits to the high earth orbits. The presented guidance scheme is determined using Pontryagin’s princi...
متن کاملOptimal Low-Thrust, Invariant Manifold Trajectories via Attainable Sets
A method to incorporate low-thrust propulsion into the invariant manifolds technique is presented in this paper. The low-thrust propulsion is introduced by means of special attainable sets that are used in conjunction with invariant manifolds to define a first guess solution. This is later optimized in a more refined model where an optimal control formalism is used. Planar low-energy, low-thrus...
متن کامل