Course detail
Aircraft Design II
FSI-OK2-A Acad. year: 2019/2020 Winter semester
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.
Language of instruction
English
Number of ECTS credits
3
Supervisor
Department
Learning outcomes of the course unit
Students will learn a practical aircraft design method, according to defined parameters, optimisation included.
Prerequisites
The basic knowledge of mathematics, mechanics, structure and strength.
Planned learning activities and teaching methods
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.
Aims
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.
Specification of controlled education, way of implementation and compensation for absences
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.
The study programmes with the given course
Programme M2I-A: Mechanical Engineering, Master's
branch M-STL: Aircraft Design, compulsory
Type of course unit
Lecture
26 hours, optionally
Teacher / Lecturer
Syllabus
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
13 hours, compulsory
Teacher / Lecturer
Syllabus
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.