Aircraft Design ULM and VDS at-aerospaceservice

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Aircraft Design is a discipline of Aeronautical Engineering distinct from other analytical disciplines such as Aerodynamics, Aeronautical Structures, Controls, and Propulsion. An Aircraft Designer must, therefore, be well trained in these and many other specializations. The true concept of "Design" is to create the geometric description of something that has to be built. However, the real work of a "Designer" is primarily mental; he must spend many hours of the day on a drawing board or on a PC terminal; a good Designer Designer must interfere with all other specialists, so as to minimize the revisions of his own "Design", such as those relating to  
design of the landing gear, fuel tank position with respect to the center of gravity of the aircraft, with the structural members that are simple and lightweight, good aerodynamic arrangements, a functional and clean installation of the propulsion also from the point of view of future maintenance and other details. Obviously, what we have said is about designing a "Designer" within a large company that builds large aircraft or military aircraft, while it is hoped that in the case of small aircraft such as ultra-light (ULM ) or VDS all ratings related to other specializations such as aerodynamics etc. can be made by the same designer who deals with the layout of the project. So, in case the Designer is at the service of a large company, all "Design" analysis must be carried out by the same Designer during the design and calculation of the aircraft performance with the assistance of experts in aerodynamics, weights,
  propulsion, stability and other technical specialties. However, an aircraft design process generally includes three major operations: analysis, synthesis, and evaluation of the results obtained. Analysis is the process that characterizes the performance or behavior of the future aircraft to be designed (for example, the mission performance of a military Fighter in terms of maximum climb rate, maximum instantaneous and sustained turn rate, track length during takeoff and landing, maximum g-load factor etc. are very different from those required for a commercial vehicle, an acrobatic aircraft in which for example, the "static margin" should be optimal otherwise it becomes too "stable" and therefore "rigid" for competition maneuvers and more suitable for example to a general aviation aircraft to be used for simple cruise trips for the weekend pilots).  
The Evaluation process is used to compute performance to compare them with the intended ones in order to determine and/or highlight the shortcomings of the project itself. The Synthesis process, in this case, serves to put together all the known features Of the project into new and useful combinations, becoming the vehicle of "Design" itself and having the Evaluation process as its own compass; thus all projects that do not meet (partially and/or totally) the requirements required in terms of performance etc are reiterated with new values in terms of features and parameters that are determined precisely during the synthesis process. The redesigned project This way (in an iterative way) is reorganized until it meets all the required requirements. Our Technical Engineering Office is available for the necessary technical assistance in the above-mentioned steps also for those who deal with self-built and/or modified aircraft (Homebuilders).
 
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