Appendix IIIList of Symbols
| A | Transverse inertia moment of the projectile, cross‐section area, linearization coefficient |
|
Matrix of system, rotation matrix |
| a | Acceleration of the mass center of the projectile |
| ap | Axial acceleration of original point o0 of rocket launcher coordinate system ooxoyozo relative to the launching guider |
Bz, 
|
Linearization coefficients |
| C | Polar inertia moment of the projectile, mass center of the rigid body, linearization coefficient |
| C j | Damping coefficient of damper j |
|
Damping coefficient of torsional damper j |
|
Damping matrix |
| D | Action point of exterior forces, interphase drag |
| D1, D3 | Operator |
| Dx , Dy, Dxy | Bending stiffness of the plate |
| dp | Equivalent diameter of the propellant grain |
| Dp | Diameter of the propellant grain |
Dz , 
|
Linearization coefficients |
| d1, d3 | Operator |
| d0 | Rotating band diameter of the projectile |
| E | Young’s modulus |
| Transform matrix | |
| EA | Tensile stiffness |
| EI | Bending stiffness of the beam |
| EX |
Get Transfer Matrix Method for Multibody Systems now with the O’Reilly learning platform.
O’Reilly members experience books, live events, courses curated by job role, and more from O’Reilly and nearly 200 top publishers.
