A linearized model of a vertical takeoff and landing (VTOL) aircraft is [24] where and The state vector components are (i) x1 is the horizontal velocity (knots), (ii) x2 is the vertical velocity (knots), (iii) .x3 is the pitch rale (degrees/second), and (iv) ,v4 is

In an effort to open up the far side of the Moon to exploration, studies have been conducted to determine the feasibility of operating a communication satellite around the translunar equilibrium point in the Earth-Sun-Moon system. The desired satellite orbit, known as a halo orbit.

Consider the system y (t) = [1 0 0]x(t). Suppose that we are given three observations y(t1), i – 1,2,3, as follows: y(t1) = 1 at t1 = 0 y(t2) = -0.0256 at t2 = 2 y(t3) = -0.2522 at t3 = 4. (a) Using

A system is described by a single-input state equation with Using the method of Section 11.7 (Equation 11.40) and a negative unity feedback, determine the optimal system when xT(0) = [1 0].

A first-order system is given by with the initial condition x(0) = .v0. We want to design a feedback controller u = -kx such that the performance index is minimized. (a) Let A = 1. Develop a formula for / in terms of k, valid

NASA has identified the need for large deployable space structures, which will be constructed of lightweight materials and will contain large numbers of joints or structural connections. This need is evident for programs such as the space station. These deployable space structures may have precision

A simplified version of the attitude rate control for the F-94 or X-15 type aircraft is shown in Figure PI0.3. When the vehicle is flying at four times the speed of sound (Mach 4) at an altitude of 100,000 ft, the parameters are [26] Design

An automated guided vehicle (AGV) can be considered as an automated mobile conveyor designed to transport materials. Most AGVs require some type of guide path. The steering stability of the guidance control system has not been fully solved. The slight “snaking” of the AGV about

For the system of Problem PI0.30, use a phase-lag compensator and attempt to achieve a phase margin of approximately 50°. Determine the actual overshoot and peak time for the compensated system.

When a motor drives a flexible structure, the structure’s natural frequencies, as compared to the bandwidth of the servo drive, determine the contribution of the structural flexibility to the errors of the resulting motion. In current industrial robots, the drives are often relatively slow, and