Aircraft Design II (FSI-OK2)

Academic year 2020/2021
Supervisor: doc. Ing. Ivo Jebáček, Ph.D.  
Supervising institute: LÚ all courses guaranted by this institute
Teaching language: Czech
Aims of the course unit:
The objective of the course is to make students familiar with aircraft design method with predetermined parameters. Design optimisation regarding the weight and operating costs.
Learning outcomes and competences:
Students will learn a practical aircraft design method, according to defined parameters, optimisation included.
Prerequisites:
The basic knowledge of mathematics, mechanics, structure and strength.
Course contents:
Synthesis of basic aviation subjects leading to the design of aircraft with desired characteristics and fulfilling international airworthiness requirements. Determination of basic dimensions and mass break down of all parts of an aircraft according to the usage of an aircraft.
Teaching methods and criteria:
The course is taught through lectures explaining the basic principles and theory of the discipline. Exercises are focused on practical topics presented in lectures.
Assesment methods and criteria linked to learning outcomes:
Course-unit credit requirements: participation in the course (80% at the minimum), all elaborated tasks must be hand in on time. The exam is of oral form – three questions and if necessary a lecturer asks one additional question.
Controlled participation in lessons:
Lectures and seminars are compulsory, and the attendance (80% at the minimum) is checked and recorded. The absence (in justifiable cases) can be compensated by personal consultation with the lecturer.
Type of course unit:
    Lecture  13 × 2 hrs. optionally                  
    Exercise  13 × 1 hrs. compulsory                  
Course curriculum:
    Lecture 1. General aspects of aircraft configuration
2. Relationship of design parameters. Specification of thickness, sweep angle and loading of a wing.
3. Estimation of mass and drag. Calculation of range, climbing performance and fuel quantity.
4. Optimization methods. Economy criteria. Direct operating cost.
5. Partial optimisation of individual parameters.
6. The general arrangement of aircraft.
7. Preliminary design of a wing and fuselage.
8. Preliminary tailplane design.The undercarriage layout.
9. Suggestion of systems (hydraulics, el., avionics).
10. Analysis of airplane weight and balance. Prediction of aircraft structural weight.
11. Review of stability and manoeuvrability.
12. Evaluation of reliability.
13. Certification methods.
    Exercise 1. Determination of surface loading of the wing.
2. Determination of engine loading.
3. Preliminary estimate of the take-off weight.
4. Calculation of range, max. vertical speed and fuel capacity.
5. Calculation of range, max. vertical speed and fuel capacity.
6. Design of the wing.
7. Estimate of dimensions of horizontal tail surfaces.
8. Estimate of dimensions of vertical tail surfaces.
9. Statistical analysis (of aircraft).
10. Calculation of the neutral point location.
11. Study of existing aircraft systems.
12. Calculation of chosen system reliability.
13. Experimental survey of centrage.
Literature - fundamental:
1. BRUHN, E.: Analysis and design of flight vehicle structures. Jacobs Pub, 1973. ISBN 0961523409.
2. Niu, C. Y.: Airframe structural design, 2nd ed.,Conmilit press LTD., Hong-kong, 1988.
3. Roskam, J.: Airplane design – Part V: Component weight estimation, Roskam aviation and engineering corporation, Ottawa, 1985.
4. Čalkovský A., Pávek J.: Konstrukce a pevnost letadel I., Brno, 1986.
Literature - recommended:
1. PÁVEK, J., KOPŘIVA, Z.: Konstrukce a projektování letadel 1. Vyd.1. Brno, VAAZ, 1979.
2. Stinton, D.: The Anatomy of the Airplane, Loughborough University of Technology, Leicestershire, UK, 1998.
The study programmes with the given course:
Programme Study form Branch Spec. Final classification   Course-unit credits     Obligation     Level     Year     Semester  
M2I-P full-time study M-STL Aircraft Design -- Cr,Ex 3 Compulsory 2 2 W