Copy of 5AL Pre-Lab 4 Submission Template - F23

USE MATLAB (Convolutional Code) The vector representation of a convolutional code is g1=[1 1]and g2=[1 0]. If the received sequence is 11 11 01 10, please use Viterbi Algorithm todecode it. Please show the full trellis diagram, including the updated trellis statemetrics.

3

Help me with this ENGINEERING GRAPHICS problem.

For the Following question Graph all 4 : [I just need all 4 graphs and please explain and make clean solution] Position vs time Velocity vs time Acceleration vs time Force vs time [For your convenience, I have solved the numerical solutions for the problem] (Please Look at the picture since it is much cleaner) Question : A 550 kilogram mass initially at rest acted upon by a force of F(t) = 50et Newtons. What are the acceleration, speed, and displacement of the mass at  t = 4 second ? a =(50 e^t)/(550 ) [N/kg] v = ∫_0^t▒(50 e^t )dt/(550 )= v_0  +(50 e^t-50)/550=((e^t- 1))/11 x = ∫_0^t▒(e^t- 1)dt/(11 )= x_0  +(e^t- t - 1)/(11 ) a(4s)=(50*54.6)/550= 4.96[m/s^2 ] v(4s)=((e^4-1))/11= 4.87[m/s] x(4s)=((e^4- 4 - 1))/11= 4.51 [m]

Given: Mass = M, Radius = R, Moment of Inertia = I, Distance =  H, Gravity = g, Initial timing = 0 Unknown =  How long will the [delta t] process take? (time) Please keep in mind that almost every variable is unknown! We are given no numbers and are instructed to generate a solution using the variables [ "R, M, g, I and H." ]  Target =  Find an equation that, if we could substitute numbers, would determine how long the process would take.  Newton's second law and torque seem to be relevant based on how the problem is written. * Also please show drawing based on what we are calculating

Please assist with this question. I reviewed the lecture notes that was given and do not understand. Please answer with a detailed explanation. Thank you. I believe there is an easier way to solve this using matlab apparently but I dont know. I will have an image of the reference slide.

I need actual data for the international space station (ISS) position vector so I can create the orbit. I tried to copy the SGP4 propagator in the Space Track website in MATLAB, but I could not manage to run it. Can you give me the data or the code to run the propagator?

I need help with my MATLAB code. There is an error in the following code. The error says my orbitaldynamics function must return a column vector. Can you help me fix it? I tried changing the semi colon to a comma in dstate_dt = [v, a_total]; but it still gives me error   mu_earth = 398600.4418; % Earth's gravitational parameter (km^3/s^2) R_earth = 6378.137; % Earth's radius (km) C_d = 0.3; % Drag coefficient (assumed) A = 0.023; % Cross-sectional area of ISS (km^2) m = 420000; % Mass of ISS (kg)       % Initial conditions: position and velocity (ISS state vector) % ISS initial state vector (km and km/s) - sample data state_ISS =[-2.1195e+03, 3.9866e+03, 5.0692e+03, -5.3489, -5.1772, 1.8324];   % Time span for 10 revolutions T_orbit = 2 * pi * sqrt((norm(state_ISS(1:3))^3) / mu_earth); time_span = [0, 10 * T_orbit];     % Step 3: Numerical integration using ODE solver options = odeset('RelTol', 1e-12, 'AbsTol', 1e-12); [t, state] = ode45(@orbitalDynamics, time_span, state_ISS,…

I created an orbit of the ISS in MATLAB. I want to validate my data. How and where can I get actual data of the ISS orbit? I would need the time history of the position vectors?

AutoSave STATICS - Protected View• Saved to this PC - O Search (Alt+Q) Off ERIKA JOY DAILEG EJ File Home Insert Draw Design Layout References Mailings Review View Help Acrobat O Comments E Share PROTECTED VIEW Be careful-files from the Internet can contain viruses. Unless you need to edit, it's safer to stay in Protected View. Enable Editing Situation 9 - A 6-m long ladder weighing 600 N is shown in the Figure. It is required to determine the horizontal for P that must be exerted at point C to prevent the ladder from sliding. The coefficient of friction between the ladder and the surface at A and B is 0.20. 25. Determine the reaction at A. 26. Determine the reaction at B. 27. Determine the required force P. 4.5 m 1.5 m H=0.2 30° Page 5 of 5 671 words D. Focus 100% C ЕPIC GAMES ENG 7:24 pm w US 16/02/2022 IZ

Use matlab to solve the question

HW_5_01P.pdf PDF File | C:/Users/Esther/Downloads/HW_5_01P.pdf 2 Would you like to set Microsoft Edge as your default browser? Set as default To be most productive with Microsoft Edge, finish setting up your Complete setup Maybe later browser. (D Page view A Read aloud V Draw 7 Highlight 2 of 3 Erase 5. Two cables are tied to the 2.0 kg ball shown below. The ball revolves in a horizontal circle at constant speed. (Hint: You will need to use some geometry and properties of triangles and their angles!) 60° 1.0 m 60° © 2013 Pearson Education, Inc. (a) For what speed is the tension the same in both cables? (b) What is the tension? 2. 2:04 PM O Type here to search C A 2/9/2021 (8)

Can you write me a program manuscript using geometric definition on FAPT language. The starting point is P1 and starts where the blue dot is. P1 = 0,0

I created a MATLAB code to plot the orbit of a satellite at an altitude of 300 km (LEO). I wanted to propagate my code for 2 revolutions but instead I used (180*60) because it takes 90 minutes to make a full rotation around the earth in LEO. Is that correct? Also, if I wanted to use revolutions how would I propagate it for 2 revs? Would my t = [0 4*pi].

I am trying to plot an orbit in MATLAB. There is something wrong with my code because the final values I get are incorrect. The code is shown below. The correct values are in the image.     mu = 3.986*10^5; % Earth's gravitational parameter [km^3/s^2] % Transforming orbital elements to cartesian coordinate system for LEOa_1 = 6782.99;e_1 = 0.000685539;inc_1 = 51.64;v_1 = 5;argp_1 = 30;raan_1 = 10; [x_1, y_1, z_1, vx_1, vy_1, vz_1] = kep2cart(a_1, e_1, inc_1, raan_1, ...                                            argp_1, v_1); Y_1 = [x_1, y_1, z_1, vx_1, vy_1, vz_1];   % time_span for two revolutions (depends on the orbit)t1 = [0 (180*60)];  % Setting tolerancesoptions = odeset('RelTol',1e-12,'AbsTol',1e-12); % Using ODE45 to numerically integrate for LEO[t_1, state_1] = ode45(@OrbitProp, t1, Y_1, options);       function dYdt = OrbitProp(t, Y)     mu = 3.986*10^5; % Earth's gravitational parameter [km^3/s^2]   % State Vector x = Y(1); % [km] y = Y(2); % [km] z = Y(3); % [km] vx = Y(4);…

Please answer all three subparts. I will really upvote. Thanks

T5

MULTIPLE CHOICE -The answer is one of the options below please solve carefully and circle the correct option Please write clear .

ihài 25 Q3) Let vector A = 5i +2j, Vector B = -3i %3D -5j, and vector C = A+ B. (a) Write %3D vector C in component form. (b) Draw a coordinate system and on it show the all vectors. (c) What are the ?magnitude and direction of vector C