Course detail

Aircraft Design

FSI-OK2-AAcad. year: 2025/2026

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

Mode of study

Not applicable.

Guarantor

doc. Ing. Ivo Jebáček, Ph.D.

Department

Institute of Aerospace Engineering (LÚ)

Entry knowledge

The basic knowledge of mathematics, mechanics, structure and strength.

Rules for evaluation and completion of the course

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.
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.

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.
Students will learn a practical aircraft design method, according to defined parameters, optimisation included.

Study aids

Not applicable.

Prerequisites and corequisites

Not applicable.

Basic literature

Niu M.C.Y.: Airframe Structural Design, , 0
Roskam J.: Airplane Design, , 0
Stinton D.:The Anatomy of the Airplane
Šulženko M.N.: Konstrukce letadel, , 0

Recommended reading

Čalkovský A.: Konstrukce a pevnost letadel, , 0
Roskam J.: Airplane Design, , 0
Stinton D.:The Anatomy of the Airplane

Classification of course in study plans

  • Programme N-AST-A Master's 2 year of study, winter semester, compulsory

Type of course unit

 

Lecture

26 hod., optionally

Teacher / Lecturer

doc. Ing. Ivo Jebáček, Ph.D.

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 hod., compulsory

Teacher / Lecturer

doc. Ing. Ivo Jebáček, Ph.D.

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.