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- W2164685324 abstract "A = axial location of the solid rocket booster (SRB) reference point in Space Shuttle main engine (SSME) plume coordinate system, ft ax, ay, az = acceleration components along body axes (excluding components due to gravity), ft=s CA = isolated (freestream) axial force coefficient Cm = isolated (freestream) pitching moment coefficient CN = isolated (freestream) normal force coefficient Cn = isolated (freestream) yawing moment coefficient CY = isolated (freestream) side force coefficient Cl = isolated (freestream) rolling moment coefficient eA, eB = unit vectors in body A and body B, respectively Fp = plume impingement force, lb Fx, Fy, Fz = aerodynamic forces in axial, lateral, and normal directions, lb F CON A , F CON B = joint constraint force vector for body A and body B" @default.
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- W2164685324 date "2013-01-01" @default.
- W2164685324 modified "2023-09-27" @default.
- W2164685324 title "Application of Constraint Force Equation Methodology for Launch Vehicle Stage Separation" @default.
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- W2164685324 doi "https://doi.org/10.2514/1.a32048" @default.
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