cougarnet_Assignment 3 Fall 2023-1

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solve only 'a' part hand written asap

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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]

Motiyo   Add explanation

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.

What are the answers in given problem

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]

please solve quickly and clearly

Find the support reactions (Ax, Ay, By) of the given "L" shaped body depicted below. 5[m] 2[m] Ax B Ay 2[m] + 30[kN] 10[kNm] 5[m] By

Task 3 a. If the Pressure produced by the gas cylinder of the motor of the rocket is governed by the below equation: P = sin* (V)cos³ (V) And the energy is given by: V2 W = PdV Jyi If V2=2V1, Find W. ii. Use Matlab or excel to plot the Energy in the interval [0, 2n] i. What will be W if V2=4V1. ii.

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);…

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

PLEASE solve using the formulas given

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.

Don't Use Chat GPT Will Upvote And Give Handwritten Solution Please

Pls explain in DETAIL the FORMULA and EQUATIONS and how did you come up with the solution. I need to present it in class and I didn't know how

I am trying to find the gross liftoff mass of a 2 stage rocket for different values of n and plot it in MATLAB. I found the total liftoff mass for stage 1 and stage 2. Is the gross liftoff mass equal to m_i1 in the code or do you have to add m_i1 and m_i2? Also, the liftoff seems to be negative for some intial values of n? That is not feasible, right?   % Constants delta_V_ideal = 9800; % m/s f_inert1 = 0.15; f_inert2 = 0.25; Isp_1 = 325; % s Isp_2 = 380; % s g0 = 9.81; % m/s^2 m_PL = 750; n = 0.3:0.01:0.7;   % Initializing variables delta_v1 = zeros(size(n)); delta_v2 = zeros(size(n)); MR_2 = zeros(size(n)); m_prop2 = zeros(size(n)); m_inert2 = zeros(size(n)); m_i2 = zeros(size(n)); MR_1 = zeros(size(n)); m_prop1 = zeros(size(n)); m_inert1 = zeros(size(n)); m_i1 = zeros(size(n));   for i = 1:length(n) delta_v1(i) = n(i)*delta_V_ideal; delta_v2(i) = (1-n(i))*delta_V_ideal;   MR_2(i) = exp(delta_v2(i)/(g0*Isp_2)); m_prop2(i) = (m_PL*(MR_2(i)-1)*(1-f_inert2))/(1-f_inert2*MR_2(i));…

Q2/ For the system shown below, use Newton's method to find the system matrix [M],and [K]

For the following system, find the mass matrix [m] and the stiffness matrix [k] and write the differential equations.

A member of your team gives you the following MATLAB program. Your job is to create the function used in the program. H = 30; % height [cm] V = 50; % volume [cm^3] % calculates the radius [cm] of a cone R2 = RadiusCone(H,V);

Question 12 kana.Full explain this question and text typing work only     We should answer our question within 2 hours takes more time then we will reduce Rating Dont ignore this line

Handwriting Asap. Can u Upload one by one image will write fast once u write one-step then upload will write then step2 again Upload in this question continue understand? It will not take time

Please show all work for c,& d as I cannot solve it for the life of myself A high-altitude skydiver of mass 100kg jumps from an altitude of 25km. Assume a near-standardatmosphere, with the following properties: d) Produce computer-generated plots of the following four quantities experienced by the sky-diver: altitude, temperature, speed, and temperature rate of change (dT /dt|skydiver). Puttime on the horizontal axis for all plots.    Use code if possible, I really need help on this, so the sooner I can be leant a hand the better

For the following system, calculate the mode shapes 3k 2k 2m Select one: O 1 1, [-1 1] [1 1], [1 -0.5]T [1 0.9848], [-1 0.1735]" O-1 1], [-1 1]