Course detail

Aircraft Design I

FSI-OK1Acad. year: 2014/2015

The course is concerned with the following topics: Design of aircraft with unmovable carrying surface, including the strength of carrying structure considering airworthiness requirements. Stability, controllability and high-lift devices including. Design and structure of carrying surfaces, means of stability and controllability.

Language of instruction

Czech

Number of ECTS credits

4

Mode of study

Not applicable.

Guarantor

doc. Ing. Jaroslav Juračka, Ph.D.

Department

Institute of Aerospace Engineering (LÚ)

Learning outcomes of the course unit

Students acquire theoretical knowledge concerning the design of aircraft with regard to international regulations.

Prerequisites

Basic knowledge of aerodynamics of an aircraft. Basic knowledge of strength and elastic theory. Basic knowledge of aircraft materials.

Co-requisites

Not applicable.

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), presentation of diploma project and interview about the project topic. The exam consists of the oral part only.

Course curriculum

Not applicable.

Work placements

Not applicable.

Aims

The goal is to set the general principles of students’ diploma project and their application to specific diploma project tasks.

Specification of controlled education, way of implementation and compensation for absences

Exercises are compulsory, and the attendance (80 % at the minimum) is controlled and recorded. The absence (in justifiable cases) can be compensated by personal consultation with the lecturer

Recommended optional programme components

Not applicable.

Prerequisites and corequisites

Not applicable.

Basic literature

Čalkovský A., Pávek J.: Konstrukce a pevnost letadel I., Brno, 1986. (CS)
Niu, C. Y.: Airframe structural design, 2nd ed.,Conmilit press LTD., Hong-kong, 1988. (EN)
Roskam, J.: Airplane design – Part V: Component weight estimation, Roskam aviation and engineering corporation, Ottawa, 1985. (EN)

Recommended reading

PÁVEK, J., KOPŘIVA, Z.: Konstrukce a projektování letadel 1. Vyd.1. Brno, VAAZ, 1979. (CS)
SLAVÍK, S.: Stavba letadel. Praha: Vydavatelství ČVUT, 1997. (CS)
Mertl, V.: Konstrukce a projektování letadel, Vysoké učení technické v Brně, Fakulta strojního inženýrství, Brno, 2000. (CS)

Classification of course in study plans

  • Programme N2301-2 Master's

    branch M-STL , 1 year of study, summer semester, compulsory

Type of course unit

 

Lecture

26 hod., optionally

Teacher / Lecturer

doc. Ing. Miloslav Petrásek, CSc.

Syllabus

1.Introduction. Specific requirements put on aircraft structure.
2.Wings, general arrangement of a wing and their advantages and disadvantages.
3.Geometry of wings. Airfoils, planforms, wing sweep, wing twist.
4.Design of master geometry model of a wing for requirements for development and manufacturing.
5.Aerostatic data for calculation of a wing loads. Load distribution on a wing.
6.Aerodynamic loads, shearing force, bending moment and torque loading on a wing.
7.Inertia loads, flight load factor.
8.Types of a wing design - spar wing, semi-monocoque, monocoque.
9.Longitudinal structure system. Spars design, booms, shear webs. Stringers.
10.Cross structure system. Ribs, force ribs. Rules for metalsheet elements design.
11.Skin, cutouts, covers. Rules for aircraft structures riveting.
12.Wing-fuselage joints for a one-piece wing and a divided wing. Rules for design of fittings.
13.Comparison of loadings on a straight and a swept wing.

Exercise

13 hod., compulsory

Teacher / Lecturer

doc. Ing. Jaroslav Juračka, Ph.D.

Syllabus

1.Determination of velocities and gust envelope.
2.Lift distribution along a wing span for symmetrical load cases. GLAUERT software application.
3.Lift distribution along a wing span for aileron and flap load cases.
4.Investigation of share forces, bending and torque moment along a wing span.
5.Creating of a geometrical etalon of a wing and determination of cross section characteristics of the wing in the desired cross sections.
6.Investigation of inertia loading at aileron load case.
7.Excursion to aircraft manufacture.
8.Investigation of flange cross sections in selected profiles. Design of flange.
9.Loading imposed on the wing with strut.
10.Calculation of hinges for two spar wing.
11.Calculation of loading and load capacity of rivet joints.
12.Software calculation of wing load cases (Introduction to software application).
13.Loading of swept monospar wing.