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978-1118870983 Chapter 1 Part 1
BRIAN L. STEVENS FRANK L. LEWIS ERIC N. JOHNSON AIRCRAFT CONTROL AND SIMULATION DYNAMICS, CONTROLS DESIGN, AND AUTONOMOUS SYSTEMS THIRD EDITION Instructor’s Solution Manual to Accompany Aircraft Control and Simulation Third Edition, John Wiley & Sons, 2015 by Brian L. […]
978-1118870983 Chapter 1 Part 2
Problem 1.6-5: Conditions for geostationary orbit. An orbit with constant angular rate, matching that of the Earth (i.e. geostationary), must be circular. The forces can only remain balanced if the center of the orbit is at the Earth’s cm (i.e. […]
978-1118870983 Chapter 2
Therefore, if ωb/aω, the corresponding quaternion is: —————— Problem 1.8-4: Reproduce the results of Example 1.8-3. (a) Subroutine for the 6-DoF equations of motion (b) Driver program and reproduction of results. This problem is self-checking. —————— Chapter 2 Problem 2.2-1: […]
978-1118870983 Chapter 3 Part 1
CHAPTER 3 Problem 3.2-1: State equations for the system in Fig. P3.2-1. The extensions of the two springs and velocities of the two masses determine the stored energy, and none of these variables can be related to some linear combination […]
978-1118870983 Chapter 3 Part 2
Problem 3.4-2. Simulation of the Lorenz equations. For second-order systems (e.g. Van der Pol, Example 3.4-1), the possible autonomous (response to initial conditions) trajec- tories in the two-dimensional phase space have been completely classified. Particular trajectories can be identified by […]
978-1118870983 Chapter 3 Part 3
is about 0.9 ft. Therefore, the short-period involves essentially only changes in alpha, theta, and pitch-rate, with very little change in flight path angle as theta and alpha vary together. ————————- Problem 3.8-2: Transport A/C; Throttle step-input time-history simulation: and […]
978-1118870983 Chapter 3 Part 4
%PROBLEM 3.9-3. Antenna azimuth control for tracking clear all z= 2.5; K= 7.6; a=[0 1 0; -10*K -10 10; -z*K 0 0]; b= [0 10*K z*K]’; c= 57.3*[-1 0 0]; % Error in degrees d= 57.3*[1]; t=[0:.005:10]; t0= 5; u= […]
978-1118870983 Chapter 4 Part 1
CHAPTER 4 Problem 4.2-1: Program to calculate longitudinal modes from stability derivatives. The following program calculates the longitudinal modes exactly as described in Section 4.2 in connection with Table 4.2-1. It requires a trim file, made with program TRIM, for […]
978-1118870983 Chapter 4 Part 2
0.0021499,0,0,0,0,0,-0.00025384,-1.0189,0,0.90506,0,0,0,0; 0,0,0,0,0,0,0,0,0,1,0,0,0,0; 0.17555,0,0,0,0,0,2.9465e-012,0.82225,0,-1.0774,0,0,0,0; command if i==0 Cp= [zeros(1,12),57.29578,0]; % roll-rate Cq= [zeros(1,9),57.29578,0,0,0,0]; % pitch-rate Cy= [zeros(1,12),0,57.29578]; % yaw-rate Cvt=[zeros(1,6), 1, zeros(1,7)]; % speed Cay=[0,0,0,-0.0046043,-0.012571,… 0,0,0,0,0,-5.0249,0,-0.0081179,0.11932]; [z,p,k]=ss2zp(A,B(:,1),Cvt,0) end x0=[.7588 2.114787 .92798296 0 0 0 502 .03691 .03691 0 0 0 0 […]
978-1118870983 Chapter 5 Part 1
978-1118870983 Chapter 5 Part 2
978-1118870983 Chapter 6
978-1118870983 Chapter 8
CHAPTER 8 Problem 8.1-1: Difference between a propeller and a rotor: Both are similar, in that they are a set of angled blades that are spun to Problem 8.1-2: Multirotor configurations with three rotors: Appropriate differential thrust between the three […]
978-1118870983 Chapter 9 Part 1
CHAPTER 9 Problem 9.2-1: (a) An appropriate reference model: (b) An appropriate linear feedback: 𝐾𝑒. The single gain parameter K here could be different value that used for the reference model. (c) A nominal dynamic inverse: 𝑢 = 𝑣 −sin𝑥. […]
978-1118870983 Chapter 9 Part 2
points = tfinal/dt + 1; t = zeros(points,1); r = zeros(points,1); for i=1:points, t(i)=(i-1)*dt; % external input if mod(t(i),2*tswitch)<tswitch, externalInput = 1; else externalInput = -1; end; % reference model vrm = -K*( externalInput – r(i,1) ); % error signals […]