cougarnet_Assignment 3 Fall 2023-1

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хоос» 0 Python 3 (p Define a python function to determine the 2nd moment of area I, under the parabola, with respect to the centroidal-axis. The parabolic curve is defined as z = ky2, where k = b/h². The centroidal axis has a given distance d with respect to z axis. Hints: Use the parallel axis theorem. Find the 2nd moment of area against z axis first and then use the formula I₂ = I₁ + d²A to calculate I, where d is a given value (no need to derive). Note that this question requires you to derive the equation first. $ 4 l) | Idle Mem: 260.77/12288.00 MB Q F4 R y 1 1 0 do 5 [ ]: # Complete the function given the variables b,h,d and return the value as "Area","Iz" and "Ic" # This is not about numerical integration, we only need the analytical solution. # Don't change the predefined content, only fill your code in the region "YOUR CODE" Mode: Command % 9 F5 0 T . Markdown v z = ky² 2 6 C F6 Validate Y & 7 8: F7 U * 8 DII F8 I 19 F9 b O ) Ln 1, Col 1 English (United States)…

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,…

Using a value of k/m = 270, write state-space equations for the undamped two-story building system. Using that result fill in blanks to identify A, B, C and D matrices. [A] = 0 0 [B] = 0 0 [C] = 1 [D] = |0 1 10 0 0 0 0 10 -270 0 0 1 0 0 0

How would you solve for the equation of motion using Lagrange equations ?

1 Please answer the best you can.

Please Solve correctly [ Mechanical- Dynamics]

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A bar is pinned to ground at its O with the bar rotating clock-wise at a constant rate of Ω=8.9[rad/s]. Block P is traveling to the left along a straight path towards with a constant speed of vp=9.7 [ft/s]. Given that h=4.7[ft] and rA/O=1.2[ft], solve the following: What is the J^ component of v¯A? What is the J^ component of (v¯P/A)rel? What is the I^ component of (v¯P/A)rel? What is the ω of the local coordinate system (this is the ω in the relative velocity and acceleration equations.

I need help with a MATLAB code. I am trying to implement algorithm 3 and 4 as shown in the image. I am getting some size errors. Can you help me fix the code. clc; clear all;     % Define initial conditions and parameters r0 = [1000, 0, 0]; % Initial position in meters v0 = [0, 10, 0]; % Initial velocity in m/s m0 = 1000; % Initial mass in kg z0 = log(m0); % Initial mass logarithm   a0 = [0, 0, 1]; % Initial thrust direction in m/s^2 (thrust in z-direction) sigma0 = 0.1; % Initial thrust magnitude divided by mass   % Initial state vector x0 = [r0, v0, z0] x0 = [r0, v0, z0];   % Initial control input u0 = [a0, sigma0] u0 = [a0, sigma0];   % Time span for integration t0 = 0; % Initial time tf = 10; % Final time N = 100; % Number of time steps dt = (tf - t0) / N; % Time step size t_span = linspace(t0, tf, N); % Discretized time vector   % Solve the system of equations using ode45 [t, Y] = ode45(@(t, Y) EoMwithDiscreteMatrix(t, Y, u0, x0, t0, tf), t_span, x0);   % Compute the matrices A_k,…

Solve the problem correctly in a handwritten format. Strictly chatgpt not allowed Mechanical engineering

Description: The Autonomous Underwater Vehicle (AUV) is a small submersible that is intended to provide scientists with low cost and appropriate time response capability in order to collect environmental data. Moreover, the motion of AUV can be described using 6 DOF differential equations of motion. These equations are developed using two coordinate frames: 1. The velocity components are 6: [u, v, w, p, q, r] (surge, sway, heave, roll, pitch, yaw) are defined in body-fixed frame. 2. The earth-fixed frame defines the corresponding positions and attitudes [x, y, z, q, 0, v). You have to adopt a dual loop control with an inner pitch control loop and an outer depth control loop in order to design the heading and depth Attitude controller (regulator system to control the depth and pitch) W, r Body-fixed frame и, р Earth-fixed frame Part 1: 1- Find the dynamic equations of motion for the sukmarine in order latain ite transfer function. ces) 2- Draw une schematic of the closed-loop system…

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]

(Repost) Can you assist with a detailed solution for the dynamic force analysis of the linkage mechanism aswell.

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);…

help!Options:1: Roller at D / Pulley2: Zero / two / multi3: Force / Direction4: B / F / E

Read and solve carefully please write clearly and box the final answer (remember to make the block diagram)

2.1.28. [Level 2] In the year 2137 a hovering spacecraft releases a probe in the atmosphere far above the surface of New Earth, a planet orbiting Alpha Proximi. The gravita- tional acceleration g1 is constant and equal to 7.5 m/s?. How far will the probe have traveled when it has reached 98% of its terminal speed? The probe's speed is governed by ÿ = -g1 + cy where y is the probe's position above the planet's surface (expressed in m). c = 1.2 × 10-4 m-1.

. I am planning to perform some volume-flow rate measurements in the Fluid Mechanics Laboratory. For this, I need a volumetric measuring tank (graduated cylinder) and a stopwatch. I considered the volume of the measured tank as 15 gallons and a stopwatch with reaction time as 1/10th of a second (though resolution of 1/1000th of a second). What is the volume flow rate if it takes 5 minutes to fill a 15-gallon of tank? Determine the smallest division to be on the tank in order to estimate the volume flow rate within an accuracy of ± 0.05 gpm.

weight = 60 air resistance = 5.5 initial speed = 2.5

Q: Find the steady-state response of the system shown in the figure below. Pulley, mass moment of inertia Jo 寻 k2 00000 For the following data: Fo sin of m 00000 uu x(t) w FO JO r m C k2 [Rad/s] [N] kg-m [cm] [Kg] [N.s/m] [N/m] kl [N/m] 28 58 1.8 13 18 540 540 1080

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