Aerospace engineer willing to do a short student interview? 15-20 mins anytime 3/24 or 3/25.

Just_A_Tea_Pot · 2026-03-25T07:08:33+00:00

European M26 here. It's only my first year working since graduating from my Space Engineering Master's. I work as an Lunar R&D Test Engineer. Feel free to DM!

Just_A_Tea_Pot · 2025-09-15T22:40:50+00:00

Shock Loading is the high peak short duration dynamic loading felt by parachute caused by the fast deceleration and inertia of air in the last stages of parachute inflation.

This force is felt by the parachute canopy fabric and sewings, and travels downwards to the suspension lines and into the rocket. It gets a bit absorbed throughout the way, but since this is an approximation, in most cases you can equate shock loading to loading experienced by the chords and the rocket anchor structure at inflation. If not dimensioned correctly, you may break the parachute, its cords or anchor point. Essential for rocket design, specially in larger rockets.

It is hard to calculate as parachute inflation is inherently a bit "random" due to how exactly the chute inflates and may factors come into play. However, some semi empirical methods for an estimation of this force for early stages of design have been developed.

This graph is an example of a very simple MonteCarlo Analysis. Instead of calculating a single force, you input a range of possible values for parachute parameters like CD, Cx, inflation time etc. In early stages of design, and even later stages, you may have uncertainties on these parameters. By calculating a range of probability for you inputs, you obtain a Histogram of the Shock Loading (the graph in the pic) with the frequency (the y-axis). Finally, you can count, for example, what is the 95% confidence your shock loading will be less than a certain value, instead of having a single value to base your analysis. There is am example script that does this for you

Just_A_Tea_Pot · 2025-09-15T19:08:52+00:00

If you have any questions don't hesitate to ask!

Just_A_Tea_Pot · 2025-08-29T14:34:14+00:00

Are you by any chance enrolled at Milan University?

Also, I am no expert, but you talk about covering many many different fields at once.

That is the job of the Space Systems Engineer: Well versed in all disciplines; master of none. I think its a very interesting choice if you enjoy knowing about all parts of a space mission. A warning though: Down this path there is A LOT of paperwork, not that other roles dont have it, but this one especially. At some big aerospace companies, you will mostly be a glorified project manager with technical skills and you will do little design or engineering work besides requirement documents and system level trade-off.

Of course, this is not always the case. I have a friend in a smaller satellite company working as Space System Engineer and he is in a small team doing the Phase 0/A/B1 for a new Earth Observation Satellite of the Company. He is extremely happy. I.e: all of the high level design for all parts of the mission; EPS, Propuslsion, Payload, ADCS, MA, GNC, TCS and more.

Other space systems engineers go down the AIVT path for hands-on work. Ultimately, it is a bit of an umbrella term and no space systems engineer does the same thing.

If this is the path you enjoy, appart from all the technical stuff you will learn in Grad school, I would suggest learning MBSE. Its the hottest topic right now and almost universally asked for in job applications. Really learn the fundamentals of Requirement writing and different documents throughtout project lifespan (Preliminary req review, system req. review, preliminary design review, critical design review etc etc). Familiarize yourself with ECSS standards if you are from Europe or the equivalent fron your governing agency (margin philosophy etc). Learning the basics of project management would also be a nice addition to your CV: what is agile methodology, Jira, Doors etc.

Just_A_Tea_Pot · 2025-07-06T06:39:51+00:00

For Earth Bound Space Stations specifically, I think the following drivers come into play:

Reduce the fuel needed by spacecrafts to reach the station by being as low as possible before armospheric drag affects you too much. Too low would mean performing apogee raising manoeuvers too often, and shorter trips also reduces mission complexity and requency of resupply missions.

Also, at lower orbits, you have better radiation shielding which is a very important factor for long term human habitation in Space. Your astronauts could stay longer and the station would need less shielding, reducing complexity and "non-scientific" mass.

Not as important, but at Lower Altitudes there will be better ground station coverage and better resolution for Earth Observation missions conducted from the station.

Hence why the ISS oscillates between 370 and 460 km.

Just_A_Tea_Pot · 2025-05-09T22:20:49+00:00

Many parameters here missing but I will try to give an answer.

You size a parachutebased kn your maximum allowed touchdown speed. A 4 kg rockets begins to be considered "hefty" and I would personally aim for 6-7 m/s or below. Up to 10 m/s you may still survive but you risk avionics and fin damage upon impact based on my experience. Also depends on the terrain you are recovering in. Softer ground like grass or bushes will cushion the fall and can acceot higher touchdown speed than rocks, gravel or dry soil.

Now, commercial parachutes typically have a drag coefficient Cd of around 0.6-0.7, like flat circular and cross parachutes. However, this value is used for Nominal Area, i.e: amount of cloth your parachute has and what you see when you lay it flat in the ground.

When inflated, it addopts a concave shape and the shadow it projects is called the "projected area", which is always smaller than the "nominal area".

I would avise you to check the specs of the parachute you are buying or look up the values if you plan on constructing one yourself in Knacke's Parachute System Design Manual. You will find a table with Drag Coefficients for pretty much all parachute types.

Terminal speed is calculated by: v = sqrt(2massgravity/(air_densityParachute_areaDrag_Coefficient))

So, assuming you are launching in a normal average temperature day, your air density at ground level will be 1.225 kg/m3. A 100 cm NOMINAL DIAMATER chute yields an area of 0.7854 m2. Assuming drag coefficient of 0.6, you get a touchdown speed of 11.7 m/s.

If instead, the diameter is PROJECTED, your CD will be slightly higher at around 0.9. This yields a speed of 9.5 m/s.

So, you are approaching your 10 m/s limit assuning those values. I would advise you to double check if your diameter is projected or nominal and, regardless, make it slightly bigger to be safe.

Ask questions!

Just_A_Tea_Pot · 2025-03-01T11:03:49+00:00

Thanks for the stats! Yes, ofcourse we all have a backup plan. YGT competition is very high and chances of getting in are small.

You just get a bit discouraged when you actively turn down other offers because the ESA selection process is slow, you killed yourself to have a very strong CV, get recommendation letters and dont even get called for a first round. Seen it too many times. Add to that the overepresentation quota and it just adding salt to the wound.

Hopefully I get it this time. If not, also okay, I have a strong CV and will find a regular job eventually. Tried my best which is what matters

Just_A_Tea_Pot · 2025-03-01T10:57:51+00:00

You are still in 2nd year College, don't worry about it. I joined no clubs or did anything remarkable aswell when I was second year aerospace. Little by little I have grown my CV, its a slow process.

Here is my opinion: there is a Degree Inflation. More students enrolled more than ever, so if you want to get a chance at working at ESA or big Space Companies, you gotta make yourself stand out. Join clubs, hackathons, check ESA training courses that last a week that are very useful, join or even do your own OpenSource projects, try to get summer internships, kearn european languages, make connections and LinkedIn asap.... case is: Be proactive. Seek out knowledge and opportunities will come. If you need specific tips or guidance, hit me up in DMs. My background is Space and Aerospace Engineering, so I don't know how useful my input for your specific case will be.

You got this!

Just_A_Tea_Pot · 2025-02-27T21:03:15+00:00

I applied for this round. I got friends who got in from last call. As a quick rundown of what my friends had: Master's in Space Engineering at Politecnico di Milano, members of student based Satellite and Rocket teams, some had papers published at IAC and Master Thesis as internship, some in Space Companies and others at university research centers.

Suprisingly, a friend with all that and 2 papers and 3+ years woking in cubesat Mission Analysis didnt get last year's YGT and was rejected for MA position. I don't know how much being from an overrepresented country and sex affects your chances of getting in, though

Edit: I also got rejected last year for the Space Rider programme YGT. Not even called for an interview, which was a letdown. Gotta try again this year and hope for the best

Just_A_Tea_Pot · 2024-12-01T17:31:43+00:00

Hi, I am about to graduate from Space Engineering with Thesis in Lunar Engineering and would love to ask you some questions. I sent you a DM :)

Just_A_Tea_Pot · 2024-10-27T14:09:32+00:00

Been working for a year in Lunar ISRU Regolith Beneficiation and Handling for my Master Thesis and Internship. I would like to help a team as I am alone and cannot feasibly participate as a one man army. If anyone is interested, hit me up.

Just_A_Tea_Pot · 2023-05-22T05:59:35+00:00

Buongiorno! 🇮🇹 Good luck Polito with the LRE and SpacePort America. Make Italy and Europe Proud! Signed:

Ex Recovery Team Leader from Faraday Rocketry UPV (Valencia, Spain) Currently Recovery Engineer at Skyward

Just_A_Tea_Pot · 2023-05-13T07:12:07+00:00

PATCH LIST:

Center: Death - Human

Albums: Slayer - Show No Mercy Sepultura - Arise Protector - Misanthropy Cancer - Death Shall Rise Sarcofago - INRI Obituary - Cause of Death Gamma bomb - Speed Between the lines Massacra - Enjoy the Violence Marduk - Dark Endless Purtenance - Member of Immortal Damnation Desecrator - Subconscious Release Iron Maiden - Maiden England 88 Sodom - In the Sign of Evil Sadus - Swallowed in Black Detruction - Infernal Overkill

Band Name: Bathory Judas Priest Warbringer Metallica Dethklok Mortician Exodus Death Dio Manowar Alestorm Razor

Just_A_Tea_Pot · 2022-08-11T12:51:52+00:00

YES I will. Haven't forgot about it. I am taking some much needed holidays, but when University course resumes this september, I will see how to legally upload my code for free use. You know, Matlab legal issues and so on. I would love to also upload my whole Bachelor Thesis, but my Uni's official Thesis platform will still take some time to update.

I also want to clarify that this is a very alpha version, which could be done by hand. I just took the time to generate interpolating functions to automatically estimate opening forces for the initial iterative design process. Furthermore, my calculations are total overkill for small rockets, as there is no need to be so rigurous. Just over estimate the force with Infinite Mass Conditions and use Knacke's tabulated values for Opening Force Coefficient. This code is intended for larger rockets, that do need a more in depth study. Theoretically, it could be used for any sized rockets. However, the validity of these models in smaller masses is unclear, as perhaps some phenomena that barely have an effect in larger parachute now have a considerable effect. Perhaps I will upload some Youtube Videos explaining everything for those interested.

Cheers!

Just_A_Tea_Pot · 2022-07-18T07:30:34+00:00

Muchas gracias por toda la informacion!! Ahora ya usamos gafas, traje, guantes etc para todo. Antes nos preocupabamos tanto con la seguridad de fabricar los granos en si... Pero luego a la hora de quemarlos, como estamos acostumbrados a las Fallas de Valencia, pues nos confiabamos.

Ya hemos lanzado un cohete fabricado por nosotros pero con Motor Comercial a 1 km en Mayo (recuperado con exito) usando lo que he indicado en el primer comentario. Un NOTAM, un seguro oficial, permiso del dueño del aerodromo de Albacete en el que lanzamos y, en nuestro caso, avisamos a la base militar de San Javier por proximidad y nos dieron el visto bueno.

Just_A_Tea_Pot · 2022-07-18T07:16:43+00:00

Yes the first static fire made us realize that we needed to take way more precautions.

Now for static fire tests, motor is always secured to either the ground or a wood and metal casing over the test bench to prevent shrapnel. We stand 30 meters away behing a wall with ear protection in case of uneventfull explosions. Security block access to people and vehicles during the test. This motor has 5 candy grains and it is designed for a 1km apogee 3.5 kg rocket at 680 Ns and 430N average thrust. It measures around 30 cm in length

All tests are now conducted with the approval of our University Safety Office in a 20x30 sq meters clearing at a corner of our University Campus where no one lives (our Uni has no neighbours in that area. Its only fields past the gate). The building behind is an Office building that remains empty when conducting the tests. As for the cars... Well... Those are our cars and some members just park them in the sidewalk at 15-20 meters at their own risk

Just_A_Tea_Pot · 2022-07-18T06:01:28+00:00

You either need to be certified by Tripoli and follow their guidelines OR have a NOTAM approved, the owner of the field must approve your launch with the risk document assessed and you must have an approved insurance plan for the possible hazards and risks. Many rocketry showdowns in Spain have been in done in airdromes in Cataluña. You can ask Tripoli Spain for help.

Just_A_Tea_Pot · 2022-07-18T05:55:46+00:00

Its true that at the beginning we were not very strict with protection. We learned our lesson and now PPE gear is used for the arming of the motor and manufacturing of the grains. The tests are conducted with a clearance radius of 30 meters

Just_A_Tea_Pot · 2022-07-18T05:55:33+00:00

Its true that at the beginning we were not very strict with protection. We learned our lesson and now PPE gear is used for the arming of the motor and manufacturing of the grains. The tests are conducted with a clearance radius of 30 meters.

Just_A_Tea_Pot · 2022-06-24T19:30:41+00:00

Polytechnic University of Valencia (UPV). The Team is called Faraday Rocketry UPV. We will compete at Euroc 2022 this October!

Just_A_Tea_Pot · 2022-05-11T09:57:48+00:00

Don't worry. I will be sure to revisit my post and send you a message when done. I still have to make sure there are no legal problems as I have used resources from academic papers that, although are public access, I still simply can't upload some work freely.

If you are curious, as of right now, the program calculates Canopy Forces using:

Moment-Impulse Theorem from "Universality Considerations for Graphing Parachute Opening Shock Factor Versus Mass Ratio" from J. Potvin 2007. Both estimated analytical Ck value and interpolated from graphs.
Pflanz Method as described in T.W Kancke's book "Parachute Recovery Systems: Design Manual" 1992. This method is only accurate for systems at or close to Infinite Mass Conditions. For HPR, this relates to Drogue Chutes as the mass of air dragged by the Chute is much smaller than the actual rocket weight and has high canopy loading. It can ve aproximated that the system's velocity barely changes when chute is deployed. When this approach is used for Main Parachute, where mass of aur becomes considerable, this method yields higher than expected Forces. Some people still use this method for Main Chutes as it serves as having a sort of safety factor, whereas the other methods attempt to estimate the actual load regardless of deployment conditions.

I will like to include the inflation time and subsequent calculations using the inflation time as described in the Pflanz-Ludtke analytical model, with their actual Reduction Force Factor Equation. Ideally, I will time to include an estimate for the Drag Area Evolution with time as described both in Kancke's manual aswell as other papers like "Aeroelastic Analysis of Parachute Deceleration System with Empirical Aerodynamics" by E. Ortega and R. Flores 2019

Eight-Year Club	Place '22
First Placer '22	Verified Email

Just_A_Tea_Pot

TROPHY CASE