A general formulation of the dynamical problems associated with powered flight of a two stage flexible, variable-mass missile with internal flow, discrete masses, and aerodynamic forces is presented. The formulation comprises six ordinary differential equations for the rigid body motion, 3n ordinary differential equations for the n discrete masses and three partial differential equations with the appropriate boundary conditions for the elastic motion. This set of equations is modified to represent a single stage flexible, variable-mass missile with internal flow and aerodynamic forces. The rigid-body motion consists then of three translations and three rotations, whereas the elastic motion is defined by one longitudinal and two flexural dis...
The dynamics of multibody systems with deformable components has been a subject of interest in many ...
A dynamic derivative sensitivity study was conducted to demonstrate the importance of dynamic deriva...
In order to provide accurate launching pitching angular velocity (LPAV) for the exterior trajectory ...
A general formulation of the dynamical problems associated with powered flight of a two stage flexib...
The general motion of a variable mass flexible missile with internal flow and aerodynamic forces is ...
The dynamic characteristics of two-stage slender elastic body were investigated. The first stage, co...
Differential equations of motion for determining dynamic characteristics of variable mass slender el...
AbstractThe transverse vibration, dynamic stability and flutter characteristics of a flexible missil...
Dynamic motion characteristics of variable-mass flexible rocket with internal flo
The development and computer simulation is presented for a bending flexible missile with a rigid-bod...
Abstract: Approaches to the mathematical description of different types of flexible vehicles in view...
A mechanics based linear analysis of the problem of dynamic instabilities in slender space launch ve...
A mechanics based linear analysis of the problem of dynamic instabilities in slender space launch ve...
Aircrafts and missiles for efficient nanoeuverability should have adequate stability and control cha...
A relatively general formulation for the governing equations of motion, applicable to a large class ...
The dynamics of multibody systems with deformable components has been a subject of interest in many ...
A dynamic derivative sensitivity study was conducted to demonstrate the importance of dynamic deriva...
In order to provide accurate launching pitching angular velocity (LPAV) for the exterior trajectory ...
A general formulation of the dynamical problems associated with powered flight of a two stage flexib...
The general motion of a variable mass flexible missile with internal flow and aerodynamic forces is ...
The dynamic characteristics of two-stage slender elastic body were investigated. The first stage, co...
Differential equations of motion for determining dynamic characteristics of variable mass slender el...
AbstractThe transverse vibration, dynamic stability and flutter characteristics of a flexible missil...
Dynamic motion characteristics of variable-mass flexible rocket with internal flo
The development and computer simulation is presented for a bending flexible missile with a rigid-bod...
Abstract: Approaches to the mathematical description of different types of flexible vehicles in view...
A mechanics based linear analysis of the problem of dynamic instabilities in slender space launch ve...
A mechanics based linear analysis of the problem of dynamic instabilities in slender space launch ve...
Aircrafts and missiles for efficient nanoeuverability should have adequate stability and control cha...
A relatively general formulation for the governing equations of motion, applicable to a large class ...
The dynamics of multibody systems with deformable components has been a subject of interest in many ...
A dynamic derivative sensitivity study was conducted to demonstrate the importance of dynamic deriva...
In order to provide accurate launching pitching angular velocity (LPAV) for the exterior trajectory ...