Category: Aerospace Engineering

I’m working on Aerospace Industry Studies assignment and need help in certain time ( APR 22 2024 at 10:00 A.M. UTC ). Questions will be same or similar to the attachment.

hello there is a paper, here is the topic of it:- conduct an in-depth study of the company or organization at which they would like to be employed. This may be a company that might hire you immediately upon graduation, or one that you will aspire to be at a later point in your career. in my case it is an airline company called Flyadeal and it is a low cost Saudi airline company. attached to you the instructions. please no more than 5 % Turnitin and read the instructions carefully especially the references part. tell me if you need anything!
Note: DON’T USE AI OR CHAT GPT in any way.

attached are 2 files
1- REQUIREMENTS + the data to use in the project
2- an example (DONT COPY AND PASTE FROM THE EXAMPLE)
the example doesnt have purpose included so make sure to add the purpose and all required topics

the assignment is attached to the zip file but here is some of it so u have an ideaSV Basic Properties:
– SV has same 3 reaction wheels (RWs) as & MOI as HW4
– Body-mount radiator normal: -?2 (point away from sun and Earth for max efficiency)
– Solar panel normal: ― ?3 (point towards sun whenever possible)
– Payload boresight: ?3 (point this axis towards targets when asked to)
– Sun direction: ― ?2
– Control Law: ? = ?? ??(1:3) + ??? + ?? ∑? ― 4
? ??(1:3)∆??
o Control law units: rad
?2
o Gains: ?? = 70 ?? = 1200 ?? = 30
SV Thruster Properties:
– 8x 1 N thrusters (See
properties sheet on
CANVAS)
– Nominal thrust is 0.9 N
at beginning of life (BOL)
– Tank filled with 5.5 kg
of propellant (LMP-103S)
– Assume each pulse
consumes 6.93E-05
kg/pulse where each
pulse is 100 ms in
duration (same as
controller frequency)
CASE 1 (1 pt) – Thruster Detumble to Sun Safe Mode
Goal: Detumble SV only using thrusters and point solar panels
directly at sun (see fig.)
Requirements:
Use thrusters in model as shown above (turn RWs off)
Initial quaternion: ?(0) = [ ―0.3062 0.1768 0.362 0.839]?
Final quaternion: see image on right
SV initial angular rates: ??(0) = ?
180[2 2 2]? rad/s
SV final angular rates: ?? = ?
180[0 0 0 ]? rad/s
Initial & final RW spin rates: ?(0) = 2?
60[1,000 1,000 1,000]? [rad
s ]
Analysis time period: 0 – 1,000 s
Deliverables:
a. Explain which thruster pairs need to be fired for control about each SV axis, both
+ and – torque needed to attain 3-DOF control. For example, “thrusters 5 & 1 fire
together for torque about the ― ?2 axis”
b. Explain how much torque is applied when thrusters are firing in the pairs as
described in part a. of this problems – both positive and negative torques?
c. Provide graphical screenshots showing the initial and final SV orientations
d. Write 2-3 sentences explaining “bang-bang” control and show evidence in the
plots where you see this type of control in effect
e. How much propellant did the thrusters consume (kg & percentage of total)?
CASE 2 (1 pt) – Thruster & RW Detumble to Sun Safe
Goal: Detumble SV using thrusters and RWs and point solar panels
at sun
Requirements:
Use thrusters and RWs, but never at the same time
Initial quaternion: ?(0) = [ ―0.3062 0.1768 0.362 0.839]?
Final quaternion: see image on right
SV initial angular rates: ??(0) = ?
180[2 2 2]? rad/s
SV final angular rates: ?? = ?
180[0 0 0 ]? rad/s
Initial RW spin rates: ?(0) = 2?
60[1,000 1,000 1,000]? [rad
s ]
Analysis time period: 0 – 1,000 s
Commanded Attitude with
constraints applied
Commanded Attitude with
constraints applied
Deliverables:
a. Provide graphical screenshots (main screen w/values showing) showing the initial
and final SV orientation
b. Write 2-3 sentences explaining when thrusters are used and when RWs are used
– show they are not used at the same time
c. How much propellant did the thrusters consume to detumble and compare to
Case 1? Was it less?
CASE 3 (1 pt) – Disturbance Torque
Goal: Use RWs and thrusters to fight a gravity gradient disturbance torque
Requirements:
Initial quaternion: ?(0) = [0 0 0 1]?
Final attitude: ?3 axis pointed at ? = 1
3[1 1 1]
Final attitude: ― ?2 axis pointed from sun ( ― ?2) as well as
you can
SV initial and final angular rate: ??(0) = ?
180[0 0 0]? rad/s
Initial RW spin rates: ?(0) = 2?
60[0 0 0]? [rad
s ]
Dist. Torque: M_b_ext = [ 0.001 0.001 0.001 ]? [Nm]
Analysis time period: 0 – 2,600 s (may be greater to see RW saturation)
Deliverables:
a. Provide graphical screenshots (main screen with values) showing starting and
final SV orientations and values
b. Plot the total SV angular momentum ?? in the inertial frame and RW speeds –
explain in 2 sentences what is occurring (1 sentence per topic)
c. Did RW rates change or saturate? Provide a plot and 2 sentences of explanation
BONUS QUESTIONS:
a. (1 POINT) Your boss said Case 2 uses too much propellant. Figure out how to
reduce propellant by half. Your boss said to turn in evidence to prove it and 2
sentences explaining how you did it.
b. (1 POINT) Your boss told you to add a thruster control law to unload the
RWs when they get above 3,500 rpm for Case 3. Your boss also said the
thrusters shall fire long enough to unload the RW below 1,000 rpm and
the RWs must be on when the thrusters are firing. Your boss also said
that you will likely have to extend the final time period to > 5-7,000 s to
see when the RWs get saturated. Your boss said to turn in evidence to
prove it and 2 sentences explaining how you did it.
Commanded Attitude with

the assignment is attached to the zip file but here is some of it so u have an ideaSV Basic Properties:
– SV has same 3 reaction wheels (RWs) as & MOI as HW4
– Body-mount radiator normal: -?2 (point away from sun and Earth for max efficiency)
– Solar panel normal: ― ?3 (point towards sun whenever possible)
– Payload boresight: ?3 (point this axis towards targets when asked to)
– Sun direction: ― ?2
– Control Law: ? = ?? ??(1:3) + ??? + ?? ∑? ― 4
? ??(1:3)∆??
o Control law units: rad
?2
o Gains: ?? = 70 ?? = 1200 ?? = 30
SV Thruster Properties:
– 8x 1 N thrusters (See
properties sheet on
CANVAS)
– Nominal thrust is 0.9 N
at beginning of life (BOL)
– Tank filled with 5.5 kg
of propellant (LMP-103S)
– Assume each pulse
consumes 6.93E-05
kg/pulse where each
pulse is 100 ms in
duration (same as
controller frequency)
CASE 1 (1 pt) – Thruster Detumble to Sun Safe Mode
Goal: Detumble SV only using thrusters and point solar panels
directly at sun (see fig.)
Requirements:
Use thrusters in model as shown above (turn RWs off)
Initial quaternion: ?(0) = [ ―0.3062 0.1768 0.362 0.839]?
Final quaternion: see image on right
SV initial angular rates: ??(0) = ?
180[2 2 2]? rad/s
SV final angular rates: ?? = ?
180[0 0 0 ]? rad/s
Initial & final RW spin rates: ?(0) = 2?
60[1,000 1,000 1,000]? [rad
s ]
Analysis time period: 0 – 1,000 s
Deliverables:
a. Explain which thruster pairs need to be fired for control about each SV axis, both
+ and – torque needed to attain 3-DOF control. For example, “thrusters 5 & 1 fire
together for torque about the ― ?2 axis”
b. Explain how much torque is applied when thrusters are firing in the pairs as
described in part a. of this problems – both positive and negative torques?
c. Provide graphical screenshots showing the initial and final SV orientations
d. Write 2-3 sentences explaining “bang-bang” control and show evidence in the
plots where you see this type of control in effect
e. How much propellant did the thrusters consume (kg & percentage of total)?
CASE 2 (1 pt) – Thruster & RW Detumble to Sun Safe
Goal: Detumble SV using thrusters and RWs and point solar panels
at sun
Requirements:
Use thrusters and RWs, but never at the same time
Initial quaternion: ?(0) = [ ―0.3062 0.1768 0.362 0.839]?
Final quaternion: see image on right
SV initial angular rates: ??(0) = ?
180[2 2 2]? rad/s
SV final angular rates: ?? = ?
180[0 0 0 ]? rad/s
Initial RW spin rates: ?(0) = 2?
60[1,000 1,000 1,000]? [rad
s ]
Analysis time period: 0 – 1,000 s
Commanded Attitude with
constraints applied
Commanded Attitude with
constraints applied
Deliverables:
a. Provide graphical screenshots (main screen w/values showing) showing the initial
and final SV orientation
b. Write 2-3 sentences explaining when thrusters are used and when RWs are used
– show they are not used at the same time
c. How much propellant did the thrusters consume to detumble and compare to
Case 1? Was it less?
CASE 3 (1 pt) – Disturbance Torque
Goal: Use RWs and thrusters to fight a gravity gradient disturbance torque
Requirements:
Initial quaternion: ?(0) = [0 0 0 1]?
Final attitude: ?3 axis pointed at ? = 1
3[1 1 1]
Final attitude: ― ?2 axis pointed from sun ( ― ?2) as well as
you can
SV initial and final angular rate: ??(0) = ?
180[0 0 0]? rad/s
Initial RW spin rates: ?(0) = 2?
60[0 0 0]? [rad
s ]
Dist. Torque: M_b_ext = [ 0.001 0.001 0.001 ]? [Nm]
Analysis time period: 0 – 2,600 s (may be greater to see RW saturation)
Deliverables:
a. Provide graphical screenshots (main screen with values) showing starting and
final SV orientations and values
b. Plot the total SV angular momentum ?? in the inertial frame and RW speeds –
explain in 2 sentences what is occurring (1 sentence per topic)
c. Did RW rates change or saturate? Provide a plot and 2 sentences of explanation
BONUS QUESTIONS:
a. (1 POINT) Your boss said Case 2 uses too much propellant. Figure out how to
reduce propellant by half. Your boss said to turn in evidence to prove it and 2
sentences explaining how you did it.
b. (1 POINT) Your boss told you to add a thruster control law to unload the
RWs when they get above 3,500 rpm for Case 3. Your boss also said the
thrusters shall fire long enough to unload the RW below 1,000 rpm and
the RWs must be on when the thrusters are firing. Your boss also said
that you will likely have to extend the final time period to > 5-7,000 s to
see when the RWs get saturated. Your boss said to turn in evidence to
prove it and 2 sentences explaining how you did it.
Commanded Attitude with

my topic is Delta 191
Each student will conduct an in-depth case study of a specific aircraft accident. The
particular accident to be examined will be assigned by the instructor. Students will be
expected to write an in-depth analysis of the accident, addressing the timeline of the
accident (including the events leading up to the accident) and the probable cause (as
determined by the NTSB). Additionally, the paper should expound upon the role of any
airline and airport managers, flight dispatchers, air traffic controllers, pilots, aircraft
manufacturers, mechanics, weather forecasts, weather conditions, etc., in the accident.
The paper should address the various lessons learned and what measures (procedural,
technological, etc.) should be adopted to prevent a similar accident from occurring in the
future. The style required for formatting the paper is American Psychological
Association (APA), 7th edition, guidelines. The paper will be graded on accuracy and
completeness of information, cohesiveness, spelling and grammar, and number and
quality of references. The paper should be a minimum of 5 pages of content. A
minimum of 5 quality references, appropriately cited in the text and appropriately listed
on a reference page, should be used. In addition to the 5 pages of content, a title page and
a reference list are also required. Paper topics will be assigned approximately the 3rd
week of class, and the paper (in Word) must be submitted to the class D2L Dropbox no
later than 9:00 pm on Monday 11/6. No paper will be accepted late.

the full detaled question is in the word file attached.
1)Create your own version of Q2R. Look at R2Q (provided on CANVAS) as an example – code should be about the same length.
Your script shall be called “your last name_HW2_4807_Q2R.m”  please replace “your last name” with your actual last name.
MATLAB Function Name
Input Format
Output Format
function [a,phi,R,q] = Q2R(q)
Q2R(q)
q is a 4×1 quaternion
[a,phi,R,q]
phi is in radians
a is a unit vector
a)Show that your Q2R code works for the following cases by comparing with the output of the R2Q that uses the output of Q2R as the input.
Case #1:
Case #2:
Case #3:
b)Your script must verify all constraints, such as magnitude, before returning results.
c)Compute by hand and compare with your MATLAB results
d)Produce a picture (by hand or MATLAB) of the two coordinate systems where one is the identity matrix.
2)First, perform the following tasks in this provided code on CANVAS:
“AEE_4807_HW2_2023_Student_Code.m”:
a. Ensure this code calls your Q2R function (same directory)
b. Code “x_dot” function for kinematics only (should be around line 54 in provided code). HINT: See slide entitled “(4) Quaternions – relationship between quaternion derivative and SV angular rate ” in Lecture 04 Attitude Kinematics slides.
Run simulations for the following initial conditions:
Case #1:
Case #2:
Case #3:
Case #4: 3-2-1 Euler Angle Sequence:
Case #5:
For each case, the satellite’s angular velocity is . Simulation time is 10 seconds for every case.
Provide 2 screenshots of the satellite’s attitude at the beginning and end of the 10 second simulation in your PDF results. Each screenshot should look like what is provided below which is the correct answer for Case 5 at 0 and 5 seconds.
BONUS (1 pt):

Assume the b- and i-frames are currently aligned (q = [ 0 0 0 1])
The sun vector in the i-frame is currently: sun_i = [ 1 1 1 ]/sqrt(3) (see green vector in picture below)
The SV solar panel normal vector is -b_3 (see red “solar_panel” vector in picture below)
GOAL: Align the red “solar panel” and “sun_i“ vectors as shown below taking the following steps:
Step 1) Computing the cross product of these 2 vectors to determine the rotation axis
Step 2) Compute the dot product to determine the rotation angle
Step 3) Create the Euler axis and angle
Step 4) Create the quaternion
Step 5) Create the graphic below by setting the initial quaternion computed in
The previous step, and set the rotation rate omega_b = [ 0 0 0] so the SV does not rotate. NOTE: There is no need to add the vectors as shown in the graphic below, but you do have to show the final values of the R, q, a, and Euler angles (as typically shown in the simulation). If you want to add the vectors, place the code below inside the t_ctr loop after “clf”

I need a 2 page paper about the air crash at Tenerife, agreeing with the crash report’s findings. Please feel free to reach out with any questions! This was a major crash, so they should be easy to come across. Thank you!

Discuss which SMS component you feel is most important in an aviation safety program, and why. What are some of the economic impacts of that component?

Im using an eppler 423 airfoil, 18ft wingspan, 2.27ft root chord to .91ft tip chord. I understand that its because of viscous errors and the airfoil polars don’t extend to that region but I don’t understand how to fix it, I have extended the range of the polars and they still don’t extend, how do I fix this.