The invention discloses a rapid modeling method of a carrier
rocket rigid-elastic-shake
coupling model, which comprises the following steps of: establishing a motion equation of a carrier
rocket: establishing a
mass center motion equation of the carrier
rocket according to a Newton's second law, establishing a motion equation around the
mass center of the carrier rocket according to a moment of
momentum theorem relative to the
mass center, and simplifying the carrier rocket into a one-dimensional beam model; establishing an
elastic vibration equation; solving force, torque and generalized force thereof; solving expressions of gravity, thrust,
control force, engine swing
inertia force,
aerodynamic force, aerodynamic damping force,
wind disturbance force, force, torque and generalized force thereof;
propellant shaking is analyzed by adopting a spring-mass-
damper equivalent model;
propellant shaking equations in the pitching direction and the yawing direction of the carrier rocket are established, and
inertia force,
inertia moment and generalized force generated by
propellant shaking are established; the obtained various forces, moments and
generalized forces and inertia forces, inertia moments and
generalized forces generated by shaking of a propellant are substituted into a motion equation of the carrier rocket to obtain a
mass center motion equation, the motion equation of the rocket is around the
mass center, and a six-degree-of-freedom nonlinear total dynamical model of the carrier rocket is established when the rocket tilts and tilts;
elastic vibration equations in three directions of yawing and rolling are established; and solving the carrier rocket rigid-
missile-shake
coupling model. According to the method, rapid numerical
simulation can be carried out on the carrier rocket rigid-
missile-shake
coupling model, the influence of a solving result on carrier rocket attitude change is analyzed, and a foundation is laid for navigation and
attitude control design of the carrier rocket.