Bachelor of Engineering The State University of Buffalo, 2002 Submitted to the Department of Aeronautics and Astronautics in partial fulfillment of the requirements for the degree of Master of Science in Aeronautics and Astronautics

USuALLY WE NOT KNOw THE \ACTUAL SYSTE\ So How WE ESTABLISH IF OUR MODEL Is Goo0? VARIOUS TPES OF TESTS CAN BE PERFORMEO PREDICTION ANO SIMULATIONJ ERRORS FRERUENCY RESPONSE FIT >MAKE SVRE YOU USE O1FFERENT 4TA To

Lateral Autopilots We can stabilize/modify the lateral dynamics using a variety of dif- ferent feedback architectures

Analysis to date has assumed that the atmosphere is calm and fixed -Rarely true since we must contend with gusts and winds -Need to understand how these air motions impact our modeling of the aircraft. Must modify aircraft equations of motion since the aerodynamic forces and moments are functions of the relative motion between the aircraft and the atmosphere, and not of the inertial velocities

INERTIAL SENSoRS MoST, IF NoT ALL, INETIAL SEN SORS MEASURE RATES LINE4R R ANGULAR) 6R ACCELERATIONS WHILE THE RATE INFORMATION IS TYPLCALLY VALIO VER LONG PERIODS of TIME) IT MUST BE INTEGRATED To CET

Altitude Controller In linearized form, we know from 1-5 that the change of altitude h can be written as the flight path angle times the velocity, so that

Complementary Filter(CF) Often, there are cases where you have two different measurement sources for estimating one variable and the noise properties of the two measurements are such that one source gives good information only in low frequency region while the other is good only in high frequency region

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

Goal: analyze aircraft longitudinal dynamics to determine if the be- havior is acceptable, and if not, then modify it using feed back control Note that we could (and will)work with the full dynamics model but for now, let's focus on the short period approximate model from

Recall from 6-2 that the derivative stability derivative terms zai, and Mi ended up on the lhs as modifications to the normal mass and Inertia terms displaced air is \entrained\and moves with the aircraf rounding These are the apparent mass effects- some of the sur Acceleration derivatives quantify this effect Significant for blimps, less so for aircraft e Main effect: rate of change of the normal velocity w causes a transient