Course - military transport strategic aircraft

Contents

INTRODUCTION

1 Analysis of design situation and development of tactical and technical requirements of the designed aircraft

1.1 Compilation of statistics

1.2 Development of tactical and technical requirements

1.2.1 Functional requirements

1.2.2 General Technical Requirements

1.2.3 Basic technical requirements for the designed aircraft

2 Selection of aircraft diagram

2.1 Selection of wing diagram

2.2 Fuselage diagram selection

2.3 Relative position of wing and fuselage

2.4 Aircraft balancing diagram

2.5 Diagram of aircraft controls location

2.6 Selection of plumage scheme

2.7 LG diagram selection

2.8 Power plant selection

2.9 Selection of wing mechanization type

2.10 Wing Specific Load Selection

2.11 Determination of maximum aerodynamic quality

3 Determination of required aircraft propulsion

3.1 Cruise mode flight

3.2 Provision of the specified run length

3.3 Take-off with one failed engine

4 Determination of aircraft take-off weight

4.1 Determination of target load and crew weight

4.2 Determination of probable value of take-off weight of the aircraft

4.3 Determination of relative masses

4.3.1 Determination of relative weight of the structure

4.3.2 Determination of relative weight of power plant

4.3.3 Determination of relative weight of fuel system

4.3.4 Determination of relative weight of equipment

4.3.5 Determination of take-off mass of the first approach

5 Determination of aircraft main parameters

5.1 Determination of wing parameters

5.2 Fuselage sizing

5.3 Determination of plumage parameters

5.4 Determination of LG parameters

5.5 Determination of fuel mass

5.6 Determination of parameters and selection of engines

6 Compilation of aircraft mass summary

7 Development of the aircraft general view and technical description drawing

7.1 General Information

7.2 Airframe Design

7.3 Power Plant

7.4 Aircraft control

7.5 Aircraft equipment and systems

LIST OF SOURCES USED

APPENDIX A

Introduction

Aircraft belong to the class of aircraft using the aerodynamic principle of flight. They use the energy of stored fuel to create driving, lifting and control forces using air. Currently, this type of aircraft with great potential for further development, since the mastered field of flight speeds and altitudes, in which it is possible to implement the aerodynamic principle of flight, is very small, and the needs of society for such aircraft are constantly increasing.

In any aircraft, you can distinguish a number of functional subsystems that determine in the aggregate its useful properties. This is a subsystem for creating a lift force, a subsystem that provides stability and controllability of the aircraft on a given trajectory, a subsystem for providing a driving force, subsystems for providing an objective function, life support, control and navigation in various flight conditions .

The design task is to develop the diagram, structure and design of the future aircraft and its components, which should ensure, under certain restrictions, the most effective fulfillment of the goals set. The solution to this problem is implemented in this course work.

Conclusion

The designed military transport strategic aircraft with a target load weight of 120 tons, an estimated flight range of 6,500 km at this target load weight and a maximum flight range of 8,000 km at a reduced target load meets the criteria for safety and reliability of international air transportation. The aircraft has good economic efficiency and tactical and technical characteristics. Rational design and geometric parameters are developed for the aircraft. The aircraft can be used for mass production, since this class of aircraft is currently in demand.

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