F-22 Raptor fighter project

Contents

Introduction

1 Terms of Reference

1.1 Statistical material

1.2 Technical and economic requirements

1.3 Tactical and technical requirements

2 Technical Proposal

2.1 Aerodynamic diagram, relative geometric parameters

2.1.1 Wing parameters

2.1.2 Wing mechanization parameters

2.1.4 Fuselage parameters

2.1.5 LG parameters

2.2 Type of power plant and its placement

2.3 Relative fuel weight

2.4 Wing specific load

2.4.1 Specific load based on provision of set landing conditions

2.4.2 Specific load due to provision of cruise flight mode

2.4.3 Specific load based on manoeuvrability

2.4.4 Design value of specific wing load

2.5 Aircraft propulsion

2.5.1 Aircraft thrust strength according to the condition of assigned speed lifting

2.5.2 Aircraft thrust capability based on maximum speed

2.5.3 Aircraft thrust strength based on the condition of assigned G-load

2.5.4 Design value of aircraft propulsion

2.6 Relative weight of power plant

2.7 Relative weight of the structure

3 Sketch Design

3.1 Take-off weight of the aircraft of the first approach

3.2 Geometric parameters of the first approximation

3.2.1 Wing parameters

3.2.2 Plumage parameters

3.2.3 Fuselage parameters

3.2.4 LG parameters

3.3 Parameters of power plant and engines

3.4 Take-off mass of the second approach

3.4.1 Relative weight of wing

3.4.2 Relative plumage mass

3.4.3 Relative weight of fuselage

3.4.4 Relative weight of LG

3.4.5 Relative weight of fuel

3.4.6 Relative weight of equipment and control

3.4.7 Take-off weight of the aircraft

3.5 Final geometric parameters, weight summary and mass recoil of the aircraft

3.6Structural and power diagram of the aircraft

3.6.1 Structural power diagram of the wing

3.6.2 Structural power scheme of the empennage

3.6.3Structurally power diagram of the fuselage

3.7 Aircraft layout and alignment

3.8 Technical description of the aircraft

Conclusion

Introduction

This course project is the final qualification work in the discipline "Aircraft Design." In the process of its implementation, the student should gain skills in designing the aircraft and consolidate the theoretical knowledge obtained earlier.

The course project considered the design process of the F22 Raptor type fighter, consisting of three stages:

development of the technical assignment;

development of a technical proposal;

Perform sketched design.

The following software products were used in this course project:

AutoCAD - for drawing and drawing;

MicrosoftWord - to issue an explanatory note;

MicrosoftExcel - to perform calculations.

Technical Proposal

2.1 Aerodynamic diagram, relative geometric parameters

Aircraft of normal aerodynamic scheme. Wing is located relative to fuselage as per scheme of high-plane.

Structural and power diagram of the aircraft

3.6.1 Structural power diagram of the wing

Wing is made according to scheme of caissons with two spars. At the same time the main part of load from bending moment is carried by panels, and the remaining part is taken up by flanges of spars. The torsion load is taken up by panels and walls of spars.

The wing structure includes spars, panels (skin and stringers) and ribs (power and normal).

Wing structure is made of aluminium materials.

Wing consists of center-wing and two cantilevers .

The wing consoles are connected to the centroplane along the side rib along the entire caisson circuit.

3.6.2 Structural power scheme of the empennage

The plumage is made according to the caisson scheme with two spars.

The structure of the plumage includes spars, panels (skin and stringers) and ribs (power and normal).

The structure of the plumage is made of aluminum materials.

Plumage is installed on fixed axis. The plumage deviates from this axis.

3.6.3Structurally power diagram of the fuselage

The fuselage structure includes panels (skin and stringers) and frames (power and normal).

Fuselage consists of nose part (includes cockpit), middle part (includes air intakes) and rear part (includes engine nacelles).

Technical description of the aircraft

The design of the aircraft is based on the principle of ensuring increased survival due to the implementation of the First look - first kill principle (the first discovered - the first struck). For this, Stealth technologies are widely used. An important design solution characteristic of 5th generation fighters that reduces the visibility of the aircraft is the placement of standard weapons in internal compartments. The F22 also has external suspensions, but the installation of ammunition on them worsens stealth. The purpose of this design solution was to increase the versatility of the aircraft.. In the airframe design, the proportion of polymer composite materials (PCM) is at least 40% (according to other sources - 60%), of which at least 30% is thermoplastic [the source is not indicated 3368 days] carbon plastics, radio absorbing materials (RPM) are widely used. In particular, the RPM structurally forms the edges of the wing of the aircraft. Most of the design is made of bismaleimides-based PCM, a class of heat-resistant polymers that are operable at temperatures up to 230 degrees Celsius. The second most important polymer composites are represented by thermoplastic carbon plastics, in particular Avimid KIII material from Dupont, the advantages of which, in addition to strength, repairability and heat resistance, include the best characteristics of permissible damage.

The contours of the slots formed at the points of connection of the cockpit canopy with the fuselage, the doors of the LG compartments and weapons are sawtooth in shape, which also provides effective dispersion of electromagnetic energy and prevents its direct reflection in the direction of the transceiving antenna of the enemy radar. The wing is diamond-shaped, the vertical stabilizer is V-shaped.

The design of the aircraft was carried out taking into account the requirements of combat survivability. According to a number of data, the survivability of the airframe design has been solved in relation to the high-explosive fragmentation incendiary (OFZ) shell, which forms the basis of the ammunition load of Russian 30mm aircraft guns.

Conclusion

In course work, an F22 type fighter was designed. For this, a terms of reference was developed. Taking into account the requirements of the task, a variant of the aircraft is proposed. According to the proposed version of the aircraft, a preliminary design is made.

Based on the results of the course project, a general view drawing was built.

In the course design process, the aircraft design skills were acquired, as well as knowledge of the studied disciplines.

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