Thank you very much for your comments! The design of the upper shell was one of the specifications given in the project. On the one hand, our focus was on maturing processes that are currently still under development, and on the other hand on demonstrating these processes on a large scale and in a highly automated manner. It`s true that the use of CFR-TP`s offer new possibilities for advanced airframe concepts which should be considered within the design phase.

Thank you for your question and your interest in our research! The scientific goals of DLR in this project are not related to defence or the colonization of space. The fairing in the video is being developed for the small satellite launcher VLM and for sounding rocket experiments based on VS50 configuration.

@@dlrinstituteofstructuresan6594 It's very interesting to study!

vay amk

made by hand?!

Purposefully overlooking the performance difference between the first planes and modern aircraft is a real 🤡moment. This may not be a giant innovative step like developing all-metal monocoques or jet engines, but it's definitely another incremental step forward.

Just a notice - big conceptual diff here it's all thermo-plastic - making the base wall and welding parts together. vs. thermo/chem sets. and riveting. No autoclave baking required either.

@@flyfree1935 Thanks for comment.... yes no autoclave or even bagging parts under vacuum.

Thank you very much! The demonstrator certainly has further potential for optimization in some areas. The stacking sequence of the skin laminate was in fact specified in the project and was merely adapted to the boundary conditions of a production-orientated design. Our focus was on maturing processes undergoing technological development and demonstrating them on a large scale. This made it possible to identify technological opportunities, limits and development potential in many areas.

Thank you for your comment! There are many different design concepts for manufacturing an aircraft structure. Which of these concepts ultimately finds its way into application naturally depends on various factors. A mix of materials can certainly be expedient here. We use the term "Best Eco-Mix", which intends to evaluate the build concept from production through operation to recycling. (Manufacturing and assembly processes would also be required for the use of hemp fibers and recycled wood... this is where we feel at home)

Im gesamten MFFD-barrel wurden verschiedenste Bauweisenkonzepte, Fertigungs- und Fügeverfahren abgebildet. So war es die bspw. im Projekt definiert in der Oberschale Z-Stringer und Integrale C-Spanten zu verwenden, während in der Unterschale Ω-Stringer und differentielle Spanten zum Einsatz kamen. Dies ermöglicht es einerseits die entsprechenden Fertigungs- und Fügeverfahren weiter zu entwickeln, andererseits die technologische Reife der der Prozesse und dessen Herausforderungen besser verstehen zu können.

Rather little engineered, because fiber orientation can be applied with topology optimization or other softwares as in the north sails 3d sails That would be "over engineered" or the only reason to use machines

Медную сетку забыли как Статик снимать и не ремонта пригодна заплату ни поставиш

Thank you very much for your comments! The design of the upper shell was one of the specifications given in the project. It is certainly possible to make the upper shell even lighter by optimizing the topology. In this project, however, the focus was not on optimizing the upper shell structure but rather on maturing various manufacturing and joining technologies which, among other things, should make it possible to meet the rate capability requirements in aircraft production.

Material: Toray CF/LM-PAEK For the In-Situ Tape Lay-up process we are using a Laser as heating source. You can find more Information on our website: www.dlr.de/en/latest/news/2023/03/mffd-thermoplastics-instead-of-aluminium-in-aircraft-construction And in this article: www.compositesworld.com/articles/manufacturing-the-mffd-thermoplastic-composite-fuselage

@@dlrinstituteofstructuresan6594 Thank you and keep up the great work 👍🏻

Hello Kamil, you understood the basic principle of the process correctly. Layers of carbon fiber composite tapes are processed in an additive method. Instead to duct tape there is no adhesive. The bond between the layers is achieved by laser melting the thermoplastic material of the tape and the surface layer. Cooling under pressure generates a solid component. Work relating the quality of the process can be found here: journals.sagepub.com/doi/epub/10.1177/00219983241240585 For the first flying fuselage application the process still has to be certified.

This work is mainly focused on improvement of the required core technologies, and patents of other entities may apply. However, DLR has a strong focus and supports technology transfer to industry.

Thank you for your interest in our research! You can read about the first results here: elib.dlr.de/196708/

Yes, that's right. Thank you for your interest!

That is amazing ! Which type of thermoplastic resin was used for manufacturing that part ? İs there Any source can we look at that process ?

Hi, thank you for your interest! Yes, actually it is carbon fibre. But the matrix, the material surrounding the fibres, is thermoplastic material, not thermoset as for the most other applications. The thermoplastic properties leads to a number of advantages, like you can weld parts together after manufacturing.

I think its for the vs 50 project. So yes

Yes exactly. Typically, two semi-finished laminate products are welded together with our ultrasonic welding device. These can be structures made of fabric or UD, or similar composites. In any case, thermoplastic matrix is required.

carbon fibre ... pretty fire retardant in the first place ...

Thank you for your interest in our project! This hydrogen fuel tank is a rocket tank. The lifetime is therefore only a few minutes. A battery solution is physically not solvable.

Thank you for your interest in our project! We are currently not working with Basalt fibers. Reasons for that are the comparatively low tensile modulus and the high variance in mechanical properties. Nevertheless Basalt fibers might be interesting in the future due to their natural occurrence.

​@@dlrinstituteofstructuresan6594 I believe in hydrogen much greater than batteries except in toy cars and laptops. Your videos are helpful to keep people interested. Basalt might make a good replacement for E-glass fiberglass but probably not S-glass, although it might make a useful outerlayer against the carbon fiber. I wouldn't say never on possible discovery of a better basalt fiber in the same was E-glass was improved. Because carbon fiber is conductive I wonder it's conductivity could be used in as a heat source for H2 in a metal hydride storage system? Also there might be improvements to the composite resin which would be beneficial, I'm thinking graphene mixed in, would recommend the company HydroGraph Clean Power Inc. as a possible source to experiment with graphene composites.

@@chisaomusician7752 Thank you for your thoughtful input, it is highly appreciated and we will look into that!

It is a servo motor from model making (KST). This has worked flawlessly so far, but we do not recommend it for series use.

Thank you for your interest in our research project! The video does not actually show a process that produces flying parts but the results of a research project in which a real (manual) process was automated to a very high degree on the DLR research facilities. Therefore, as mentioned in the description, the state shown is only a demonstration at the end of the project where one single sample of the RPB was built. Don’t hesitate to contact us if there are any questions.

@@dlrinstituteofstructuresan6594 Alright, much appreciated for clarification