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With the increasing size of space vehicles and their larger diameters which lower the natural frequencies of the propellants, the effects of propellant sloshing especially since at launch a very large amount of the total weight is in the form of liquid propellant. With increasing diameters the eigenfrequencies of the propellant become smaller and shift closer to the control frequency of the space vehicle. Furthermore, the oscillating propellant masses and the corresponding forces increase considerably. A relatively simple means of avoiding strong dynamic coupling can be achieved by subdivision of the container by radial or circular walls. This results in smaller sloshing masses and higher eigenfrequencies. Another possibility is the clustering of tanks with small diameters which has the disadvantage of a weight penalty. For stability investigations the influence of the oscillating propellant has to be known. For this reason forces and moments of the propellant with a free fluid surface in a container of circular ring sector cross section performing forced oscillations must be determined. This will be performed with the assumption of irrotational, frictionless, and incompressible liquid. Linear equivalent damping is introduced with the help of a mechanical model describing the fluid motion. It has to be determined by experiments.
With the increasing size of space vehicles and their larger diameters which lower the natural frequencies of the propellants, the effects of propellant sloshing especially since at launch a very large amount of the total weight is in the form of liquid propellant. With increasing diameters the eigenfrequencies of the propellant become smaller and shift closer to the control frequency of the space vehicle. Furthermore, the oscillating propellant masses and the corresponding forces increase considerably. A relatively simple means of avoiding strong dynamic coupling can be achieved by subdivision of the container by radial or circular walls. This results in smaller sloshing masses and higher eigenfrequencies. Another possibility is the clustering of tanks with small diameters which has the disadvantage of a weight penalty. For stability investigations the influence of the oscillating propellant has to be known. For this reason forces and moments of the propellant with a free fluid surface in a container of circular ring sector cross section performing forced oscillations must be determined. This will be performed with the assumption of irrotational, frictionless, and incompressible liquid. Linear equivalent damping is introduced with the help of a mechanical model describing the fluid motion. It has to be determined by experiments.
Dynamics and Simulation of Flexible Rockets provides a full state, multiaxis treatment of launch vehicle flight mechanics and provides the state equations in a format that can be readily coded into a simulation environment. Various forms of the mass matrix for the vehicle dynamics are presented. The book also discusses important forms of coupling, such as between the nozzle motions and the flexible body.This book is designed to help practicing aerospace engineers create simulations that can accurately verify that a space launch vehicle will successfully perform its mission. Much of the open literature on rocket dynamics is based on analysis techniques developed during the Apollo program of the 1960s. Since that time, large-scale computational analysis techniques and improved methods for generating Finite Element Models (FEMs) have been developed. The art of the problem is to combine the FEM with dynamic models of separate elements such as sloshing fuel and moveable engine nozzles. The pitfalls that may occur when making this marriage are examined in detail. - Covers everything the dynamics and control engineer needs to analyze or improve the design of flexible launch vehicles - Provides derivations using Lagrange's equation and Newton/Euler approaches, allowing the reader to assess the importance of nonlinear terms - Details the development of linear models and introduces frequency-domain stability analysis techniques - Presents practical methods for transitioning between finite element models, incorporating actuator dynamics, and developing a preliminary flight control design
In a microgravity experiment, the conditions prevalent in fluid phases can be substantially different from those on the ground and can be exploited to improve different processes. Fluid physics research in microgravity is important for the advancement of all microgravity scients: life, material, and engineering. Space flight provides a uniqu