Introduction We started with one frame (B) rotating and accelerating with respect to another(), and obtained the following expression for the absolute acceleration

Spring 2003 Example Given: Catapult rotating at a constant rate(frictionless, in the horizontal plane) Find the eom of the particle as it leaves the tube

Spring 2003 Derivation of lagrangian equations Basic Concept: Virtual Work Consider system of N particles located at(, x2, x,,.x3N )with 3 forces per particle(f. f, f..fn). each in the positive direction

美国麻省理工大学：《Aerospace Dynamics（航空动力学）》英文版 lecture 11

Spring 2003 1661AC22 Longitudinal Dynamics For notational simplicity, let X=Fn, Y= Fu, and Z= F aF Longitudinal equations(1-15 )can be rewritten as mi=X+X2- mg cos(0+△X

FURTHER BASICS 5-1 · LINEAR MOMENTUM m NEWTON'S LAW ∴F=P ow TAKE THE MOMENT OF MDMENTUM ANGULAR MOMENTUM MUST EXPLICITLY OEFINE

Aircraft Lateral Dynamics Using a procedure similar to the longitudinal case, we can develop the equa tions of motion for the lateral dynamics

美国麻省理工大学：《Aerospace Dynamics（航空动力学）》英文版 Lecture 15

NEWTONs L丹WS ① BoDY CoNTINUES玉 N TTS STATE OF MOT(0N DR REST UNLESS FORCED DI RECTIoNs IMPoRTA. 儿L M5T3 E AN NIERT升L ACELERATION

ATTITUDE MOTION -TORQVE FeEE MANE 0ISCUSSED THE ROTATIONAL MOTION FRDn 1 ERSPECTvE。FE”6o0 FRAME 一NE0T0F1A0 A WAy TO CONNECT THE MOTION To THE INEATIAL FRAME So WE CAN DESCRI BE THE ACTUAL MOTION TYPICALLY DoNE 6y DESC RI BING MOTION oF NEHICLE ABoVT THE