Questions related to Aeronautics
In recent, I am done compiling my teaching materials for the Fundamentals of Aircraft Manufacturing Management Process. I've studied some materials and currently doing theoretical research on Aircraft Manufacturing Management Process.
If anyone is interested to review my syllabus, lecture notes and PowerPoint slides then you can contact me.
I will be sharing my material and expecting/ requesting suggestions, comments, recommendations and your ideas to improve my lecture materials. Thanks in Advance.
I’m currently working on a project related to the resilience of Air Navigation Service Providers (ANSP) to the outbreak of the COVID-19. The purpose of this research is to propose solutions for a sustainable way out of this global pandemic.
The main source of income of many ANSPs is the aeronautical charges, also known as ANSP charges, that are collected from airspace users in return for the services they received.
The COVID-19 has taught us that ANSPs cannot continue relying on Aeronautical charges only. Due to airspace restrictions since 2020, many airlines suspended their flights. This situation resulted in a lack of aircrafts in the airspace. ANSP charges depends on the traffic flow in the airspace. The more airlines fly, the more ANSPs can charge the airspace users. Therefore, in order to be resilient and be able to face future crisis, ANSPs should compulsorily find new business model that will strengthen the current one based on ANSP Charges.
What kind of new business model can we propose to ANSPs in order to diversify their sources of income?
This Network is the perfect place to ask this question and I hope that some specialists or experts will share their opinions.
Is there a group of crucial and important UAV's parameters/features regardless of kind of mission (search missing people, disaster, evacuation, emergency deliveries, monitoring, fight a fire, training, saving trapped people, contamination, flying rescue cushion)? Or maybe every kind of mission has their own crucial parameters/features?
Aerospace industry is based on innovative and path breaking technologies specifically in the field of Aeronautical design, development, materials, manufacturing processes, and quality. Most of the new technologies are developed and introduced in this industry due to its major role in fighters, drones, Satellite, etc.
The startups in high tech area take very high risks as the gestation period of investment is long and returns on investment are low. In addition, a few rejections of the design or product may lead to closure of startup. Despite of huge risk, entrepreneurs start startups.
This phenomenon is quite interesting but I find very less literature on it. I like to get the answers to my question "What is the motivation for startups in Aerospace industry?" despite of huge risk from the scholars of motivation, startup and aerospace fields.
Hi. Can anyone could recommend an aeronautical / aviation conferences to attend in 2020 in Europe; particularly for fluid mechanics and applied aerodynamics. Thanks!
Dear collegues, i'm looking for informations about a topic that i must presente in our class, it's about hybrid propulsion in aeronautics, if you have ideas, documents, web sites, PDF documents that can help me .
Thank you very much.
Karpp RR. Prog Astronaut Aeronaut 1993;155:223.
Above is the information shown in the reference part in the paper I am reading now. I even couldn't find the name of this reference. The content in it should include a table or something else that introduce parameters in Mie-Gruneisen EOS model.
Thanks a lot.
How is your day? I hope you are very well.
Health and Peace!
My name is Marizene Nonato da Silva. Nice to meet you.
I am a master student at the Institute of Aeronautical Technology (ITA) - São José dos Campos in Brazil.
I research this my theme of study now: Space Elevator.
Thank you for taking your time in to answer my ask.
Marizene Nonato da Silva -
Master's student in the Space Science and Technology Program at ITA
Research Line: Engineering and Space Technology Management
A student of materials engineering & structures, I would like to have some guidance in finding interesting master thesis topics in the mentioned field! Something that can be done with motorcycle OEMs? Something similar in Aeronautical industry would also be interesting. Kindly help.
I would love to know what human factors you are considering for this research project and where you currently stand in the research of this topic. I believe that this topic would be beneficial to the study that I am working to complete as part of my capstone project from my Bachelors Degree in Aeronautics through Embry-Riddle Aeronautical University.
a) flying rescue cushion/net - NetGuard: https://www.youtube.com/watch?v=4KRqKnKERC0, https://bgr.com/2018/11/07/net-guard-drone-concept-china/
b) start from mobile platform - in Poland: http://s4t.com.pl/#
https://media.landrover.com/news/2018/10/life-saving-land-rover-discovery-joins-red-cross-emergency-fleet , https://dronelife.com/2017/03/08/new-land-rover-suv-features-rescue-drone/
c) Delivery of medicines, blood, defibrillators - in Poland: https://www.airvein.io/, https://www.linkedin.com/company/airvein-sp.-z-o.o.?originalSubdomain=pl,
TU Delft - Ambulance Drone https://www.youtube.com/watch?v=y-rEI4bezWc
d) Delivery of life jacket, pod, raft
Blueskimmer Drones - ORANGE RESCUER https://www.facebook.com/blueskimmerdrone/videos/353042375255581/
Flying Rescuer https://www.thenational.ae/uae/the-flying-rescuer-meet-dubai-s-new-life-saving-drone-1.779153, https://thelittleripper.com.au/
e) fire fighting/extinguishing fires on the floors of buildings - https://www.youtube.com/watch?v=Bm2BVTTir4c, https://www.aerones.com/eng/firefighting_drone/ , https://www.youtube.com/watch?v=Bm2BVTTir4c
f) spraying anti fire chemical compounds
h) New Futuristic Massive Firefighting Drones, https://www.youtube.com/watch?v=GL8L2Y2RtWY
i) Morphing, foldable retract propeller arms drones, https://www.uasvision.com/2018/12/19/morphing-drone-solution-for-search-and-rescue/
j) Detecting Wifi signals from smartphones of trapped people, https://www.youtube.com/watch?v=7ysg-m7kV14
k) Dropping a fire-blanket???
l) Fire ignitions
FlamethrowersTF-19 WASP Flamethrower Drone Attachment , https://throwflame.com/products/flamethrower-drone-kit/
m) Claws, robotic arms, https://techcrunch.com/2019/03/13/tiny-claws-let-drones-perch-like-birds-and-bats/?guccounter=1&guce_referrer_us=aHR0cHM6Ly93d3cuZ29vZ2xlLmNvbS8&guce_referrer_cs=lota9OexAiq6d17kKBwHIg, https://www.youtube.com/watch?v=3KeBKEdeUKU ,
n) Launches Autonomous Drone,
https://www.youtube.com/watch?v=j6cdTSIDOSA&feature=youtu.be , https://percepto.co/ , https://irlock.com/ , http://www.airobotics.co.il/ ,
http://www.edronic.com/ , https://fotokite.com/?fbclid=IwAR2zuI1gpC6B72EKHcg6ILA-Nj2QGPfk8zk5wRxOuyhZPBGznyc7tf9cN5I , https://www.youtube.com/watch?v=ZmSo3unQ5As , https://patents.google.com/patent/US20190023416A1/en
o) Charging Pad
p) Wireless charging
Is it correct to use a term "drone/UAV special for fire service/fire brigades"? Or are there only a adaptations/modifications of available models (like adaptations of Matrice - see https://www.dslrpros.com/inspire-1-first-responder-thermal-kit.html https://www.rmus.com/collections/police-fire-search-and-rescue-drones)?
Am in final stages of my Phd in Supersonic Aerodynamics . I would like to apply for post doctoral position in the field of Aeronautical in reputed universities. Can anyone pls guide me
I need to calculate the forces caused by vortex shedding(or vortex induced vibrations) on a tapered cantilever structure under wind loading.
I did some reading and some researchers suggests to calculate the response using some empirical equations to include the motion induced forces due to lock in and negative damping as I understood.
Your advice and suggestions will be appreciated.
I am trying to find metals/alloys apart from titanium which are not harmful for the jet engine cooling systems. I know that jet engine lubrication oils are usually "neopentyl plyol esters", but I have not been able to find any information on materials apart from titanium that can withstand such lubrication oils. Any book or article sources that gives information will be helpful. I have not been able to find much information probably because my background is in mechanical/aeronautical engineering and the searches are limited to general terminology. In addition to this, my current project is fairly interdisclipinary and requires intermediate to advanced knowledge of chemistry.
As usually the trend is a Courant number (CFL no) can only be used for a Transient( Unsteady) flow condition.
Thank you in Advance.
Recently, a friend of mine working on a different project has waved me into his office. It turned out that he wanted to visualise the orbit of one of space probes, and the orbital elements he had were not pretty: in fact, they resembled a sawtooth in one of the axes (and were seemed normal in the other two). He asked for my suggestion regarding fixing the flight path for the presentation purposes; I typed up a quick and dirty implementation of a moving average smoothing algorithm that was enough for a last-minute fix.
After walking home from my work I first spent a couple of minutes thinking whether I should have applied a different approach (such as fitting polynomials or local regression, or whatever jumped to my mind at the moment), but moments later I realised I have no idea why do the data look that way. Any explanation for such a sawtooth for being there? It is too regular to look like constant engine corrections. Do any of you have a clue?
This works has been made within a project with the CNES (French National Center for Space Studies, during my studies in aeronautic engineer high school), within the project for the study of the sizing of the lauching pad of Ariane 5 project sattelite launcher.
I have made a lot of research to find if this theroem was known or not ?
I had never never found a reference ? May you help me please.
Before the theorem statement, just few recall :
1/ The aerodynamic drag is given (within special domain) traditionaly by : 1/2 Cx ro S v^2
(ro being the air density, v the velocity (relative to air flow), and Cx the so called penetration coefficient)
The term of interest in the problem is the S, which is called the "master couple, french traduction of the term used in french" which represents the projection surface of the body on a plan perpendicular to it's trajectory vector.
2/ The theorem I have demonstrated is the following statement :
" The average master couple for any convex body over all orientations (then integrated over unit sphere, for projection axis) is equal to the "Exterior Surface of the body" divided by 4. "
[this is an evidence for the particular case of the sphere : 4 pi R2 / 4 = pi R2 projected surface equal everywhere]
I know that at the epoch, these formula was used by persons as an heurisic ?
3/ But my definitive questions are :
Is this theorem relevant or not ?
Is it an obvious corollary of convex mathematics ?
(which is from my point of view certainly the case) ?
PS = I have also demonstrated the exact formula for only one particular non convex body (in fact a surface, but this is just a question of factor 2) which is an angular part of a section of a cylinder). This is not really difficult but hardly analysis computational !
and an approximation formula for non convex body (but I do not realy know the quality)
and other few relative theorems (like the result for the union of two convex body creating another convex body)
Thx in advance for any kind of answer ?
What Knowledge Management System Software is being used by major Aeronautics Industries of the world ?
Would anyone be able to explain to me how I can calculate the Reynolds number for a HAWT when I have the freestream velocity, power coefficient and tip speed ratio values. I'm trying to figure out the axial and tangential induction factors.
I'm conducting a literature review on Formation Flying. While there are numerous studies and surveys on the subject, I have not been able to find a well-structured concept map on the general FF research framework. Any recommendation is greatly appreciated.
I have a project about finding Cd and Cl for NACA 2415 for different angle of atacks.
I have a problem. The flow appears to be reverse and i hhave negatives coefficients of drag. Why this happens?
Boundary conditions at outlet is zero pressure, and I change the direction of the flow. Re 600000.
When designing the control systems, I always confused about how to get the bandwidth of the systems. Nearly all the textbooks says like :"In the systems where the low-frequency magnitude is 0 dB on the Bode diagram, the bandwidth is measured at -3dB frequency." But almost all of the systems I meet in practice do not satisfy the conditions that the low-frequency magnitude is 0 dB on the Bode diagram. The low-frequency is always above or lower than 0 dB. What's more, the open-loop cut-off frequency on the Bode diagram is always connected with the bandwidth of close-loop. In this situations, if there is a cut-off frequency, the low-frequency will not be 0dB.
In wiki, it says the bandwidth is the range of frequency which is less than 3dB below the maximum value. While in a ppt created by Dr Grant Covic for paper: Systems & Control 1988: Document 3 of 3, it says:"Some type 0 systems do not have 0dB low frequency gains, hence the bandwidth is normally taken over the frequency range that has gain > –3dB above the designed passband gain." So more confused. So I want to ask your opinions of how to calculate the bandwidth when the low-frequency is above or lower than 0 dB? And if there are some books or articles talking about this? Thank you very much for your help.
Is there a new cognitive task analysis in Phases of flight for pilot?
Please, send me.
Thanks, for your attention
“Phases of flight” means: Pre-flight, Pre-departure, Gate Departure, Taxi-out, Take-off, Terminal Area Departure, Climb, Cruise, Descent, Terminal Area Arrival, Final Approach, Landing and Rollout, Taxi-in, Parking and Post-flight.
I need this data for my thesis, but I can not find it anywhere. There are still some books to order, but I am rather a pessimist.
This postion looks intresting but I can not find it anywhere. Maybe somebody is able to tell me if required data is there?
Althaus, D., 'ProfilePolaren Fur den Modellflug (Windkanalmessungen an
Profile im Kritischen Reynoldszahlbereich)', [Model airfoil polars
(Wind tunnel measurements of airfoils at critical Reynolds numbers)],
Institut Fur Aerodynamik u. Gasdynamik der Universitat Stuttgart.
Neckar-Verlag, Postfach 1820, 7730 Villingen-Schwenningen, Germany, 1980.
Hello, im trying to simulate the flow around the Ahmed body and i want to plot the velocity profiles graphs that many papers have but i can't understand how to do that. Can anyone guide me into that? I should mention that i am using Fluent for my simulation.
i have an ODB of some thousand elements. i want to copy some elements to new empty odb and run it again to get results for that elements. is that possible ?
Real aircraft is too large and when i use similar parameters then, i can't simulate the flow for large velocities in wind tunnel. Is there a way to simulate high velocities in wind tunnel.
When no of impact on the laminate increases, saturation in water absorption of composite laminate will come earlier or take long time?
Do you know of any unstable aircrfat used for commercial operation including cargo?
Do you think it is a good idea to use such aircraft for commercial operation? Provided the higher payload it provides. The idea could be more feasible for cargo operation.
Suppose, a simplified model of the roll dynamics of an aircraft, which is represented by xdot(t) = A x(t) + B u(t), where the states are (phi, p) and the u is the aileron command **(neglecting the dutch-roll mode).
Due the fact that, the controller contains an integral term, the system dynamics is augmented to contain the state related to the integral of the error signal. Let's call it of Tau(t). Then, we have [xdot Tau_dot] = A_aug x_aug(t) + B_aug u(t).
So, the control law is given by u(t) = - K x_aug + K(1) Phi(ref), where K is the static gain of the controller. Which we can "interpreted" as K = [Kp Kd Ki] = [Proportional, Derivative , Integral] (I have all states to feedback).
As the output of actuator is limited and the controller has an integral term, I should implement an Anti-windup scheme to avoid the windup of integral term. So, what type of anti-windup do you suggest?
Thanks in advance.
see attachment please.
I have successfully come up with a new helicopter design that I call the NOTA MRH (NO TAil Mono Rotor Helicopter). The picture shows it's basic design. This helicopter does not need a tail rotor for torque reaction. The person flying this helicopter will only mind about the single main rotor cause that's the only rotor on the helicopter. It can work well for stealth helicopters. It is not a Mono copter or Coaxial helicopter nor Tandem helicopter and can easily be fitted in a space capsule if required for future landing.
I am interested in using a small/miniature biofuels/diesel powered engine to both charge the batteries (while the solar cells are not producing enough power) and to directly power the 4 electric motors of a small drone (which is used as an aerial platform for cameras and remote sensing equipment, like LIDAR). Which would be the better engine to use, a conventional reciprocating-piston engine, or a turbine? Both have rather high "costs" in terms of start-up current draws from the batteries, but I am thinking this factor would about equal-out for each type, and thus could be disregarded. However, how should fuel-consumption compare for the same amount of power produced from each type? Any thoughts on which maker/model (combination with generator/starter ?) is the best?
I am not a specialist of transonic aerodynamics and I try to understand the difference between buffet and buzz phenomenon.
1) I wonder if the buffet is the periodic variation of lift due to shock wave oscillation and buzz is the name of the aeroelastic answer of the buffet excitation. Is that right ?
2) What is the link beetween the shock wave oscillation and the boundary layer.
3 Is it possible to have buffet without boundaly layer ?
I am working on a Systems Engineering project. As a team, we have to find the reliability, availability and maintainability figures or values for different components in an aircraft. For example: powerplant, avionics, airframe structure, fuel system, flight control and electrical systems. Since, the data on these systems are hard to find in a public domain; any amount of help on how or where to find these values would be greatly appreciated. Looking forward to some positive response.
Have a good day.
My name is Mykolas. I live in Lithuania and currently I am studying for my pilots license and Aerospace engineering masters degree VGTU (Vilnius Gediminas Technical University).
My final paper is about an importance of English language in aviation. So I would like to ask for help:
1. Information about techniques of evaluating English knowledge (especially for evaluating professional requirements).
2. Any article about incidents because of miscommunication or recordings would help.
3. Expert opinion on the subject would really help.
4. Information on where I could find statistics about the traffic in airports would help.
5. Any ideas to make the subject more useful or interesting would also be very appreciated.
I will mention and give credit to anyone who will help me on my Master's dissertation.
Of the current systems that exist onboard an aircraft, which if any are able to transmit location data to a ground receiver station?
I am in need to validate the codes for aeroacoutics computational simulation. What are the standard test cases in computational simulation of Aeroacoustics, whose experimental data will be available?
I am working on an Aeroacoustics Competency Development Program.
As I don't have much solid experience on Aeroacoustics and its allied processes, I would like to know which will be the best way to start with.
I have simulated a system using pure simulink blocks. Later I substituted some of the subsystems by commands in a matlab embedded function. The results are completely different. What could cause such diverge results?
Warp field generation using metamaterials and sub-nanoscale casimir cavities architecture (e.g. optimising multiscallar geometry of warp propultion).
I am working on improving cockpit automation interfaces and will be using a PC based simulation as part of that effort. I am considering using Microsoft’s FSX, Flight Gear, X-Plane or Prepar3D. I’m leaning toward Flight Gear as it is open source and may be easier to develop interfaces with it using custom software. I wanted to ask other researchers what opinion they have regarding the suitability of these platforms for academic research especially when failure simulations will be created?
Is the derivative of the error the rotation between the derivative of the desired and the derivative of the actual angle or simply the derivative of the error equation?
I need a transient aero-thermal test case for the validation of numerous procedures. I have one very good test case of x-15 but I need one or two more test cases.
X-15 transient aero-thermal test case contains complete detail of free-stream conditions, material thickness, temperature measurement instruments locations, and skin temperatures.
If anyone knows some other test cases which have these all data available for study please inform me.
I have a control volume as attached. Left is inlet, right is outlet, top is symmetry and bottom is axis (it is a 2d axisymmetric analysis). What you see is a vehicle and there is a piston-cylinder mechanism inside it. The piston moves and creates pulses. There is no flow from the inlet, so the velocity of the inlet set to "0". When I initialize the case, it gives a warning as "turbulent viscosity ratio is limited to 1e+5 in xxx cells". When I plot turbulent k contours, I see that every turbulent k is over the limited value. What might be the problem?
I set inlet and outlet turbulent parameters to 0. The warning disappeared, but then it did not solve the case. I changed the boundary inlet to wall and the turbulent viscosity ratio warning still appears. I am really confused. Do you have any ideas?
We know that the path of a point on a Bezier curve can be controlled through the control points of the curve. This parametric curve ranges from t=0 to t=1. This means the velocity is uniform for fixed control points. Is there any research where the possibilities of a non uniform (assigned) velocity for a point on a Bezier curve has been discussed?
Can anybody guide me on how to analyse the Impeller of the Centrifugal pump in Ansys-CFX/Fluent/Solid Works, or provide a related tutorial?
I am trying to write a project proposal and I am having a problem referencing my proposal. Thing is I know things like dust etc can cause some damage to propellers which might lead to dents and cracks and etc, but what I need is research papers that prove this Where can I find them?
I just read a paper from Antony Jameson published in Progress in Aerospace Sciences 47 (2011) 308–318, http://www.sciencedirect.com/science/article/pii/S0376042111000029
He discussed CFD simulations of the Korn airfoil, and stated that some numerical methods failed to give a shock free solution. I am really impressed by Jameson's work, he did a mesh convergence study of this problem (Mach=0.75, CL=0.629) and give a new shock-free cruising condition (Mach=0.751, CL=0.625).
I tested this case with my own codes and failed. I would like to know from other CFDers, whether your code can produce the shock-free solution. Is there some important factors I need to pay attention? e.g. accurate treatment of the solid boundary condition? point-vortex at the far field? etc.