ABSTRACT The significance of title of the project is to calculate the static and the dynamic characteristics of Helicopter rotor wings have been analyzed with ANSYS software package. During the analysis of rotor blades, the influence of aerodynamic force and centrifugal forces are applied with the comparison of weight for two different materials (Aluminium and composite material). In static analysis, analyze angular velocity and gravity of earth. During dynamic analysis, to calculate the natural frequency and modal shape of rotor blade is modulating those frequencies and avoiding resonance during rotational speed, then the vibration level of helicopter may reduce. The procedural step includes various aspects such as selecting the material based
The Elevons are present in an aircraft control surfaces that which will combine the functions of a elevator and a aileron. These elevons are frequently utilized on the tailless aircraft such as flying with wings. The elevon that is not part of the main wing, but instead is a separate tail surface, is a stabilator (but stabilators are also used for pitch control only, with no roll function, as on the Piper Cherokee series of aircraft). The word "elevon" is a portmanteau of elevator and aileron. Elevons are installed on each side of the aircraft at the trailing edge of the wing.
Introduction Helicopters are also known as rotary wing aircraft. Their rotating wing is known as the main rotor. It is a type of rotorcraft. In this thrust and lift are supplied by rotors. The helicopter is capable of direct vertical take-off and landing and it can also hover in a fixed position.
It is a primary source of shock attenuation at landing. It controls the rate of compression extension and prevents damage to the vehicle by controlling load application rates and peak values. Thus utmost care must be taken while designing a main landing gear. It should be able to take 90% of the weight of the aircraft while standing. The Landing gear is the principal support for the airplane when parked, taxing, taking off or landing.
ADVANTAGES Unmanned aerial vehicles (UAV), as a flexible aerial photography platform, have been widely used in many applications, such as agriculture, water conservation, mapping, 3D reconstruction, and disaster relief. The ability to obtain high-resolution images makes large-scale mapping possible. RC Plane has several advantages, such as low altitude, low speed (for a low-altitude aerial photography system, high speed will result in a blurred image), low cost, flexible and simple operation, and high-resolution
 A major part of aeronautical engineering is aerodynamics, the science of passage through the air. With the increasing activity in spaceflight, nowadays aeronautics and astronautics are often combined as aerospace engineering. The science of aerodynamics deals with the motion of air and the way that it interacts with objects in motion, such as an aircraft. The study of aerodynamics falls broadly into three areas: Incompressible flow occurs where the air simply moves to avoid objects, typically at subsonic speeds below that of sound (Mach 1). Compressible flow occurs where shock waves appear at points where the air becomes compressed, typically at speeds above Mach
The Gray Eagle provides convoy protection, IED detection and defeat, and close air support, which assist in moving troops and equipment. The Intelligence Warfighting Function supports force generation, situational awareness of the Area of Operation (AO), and targeting. This asset has ISR and FMV capabilities, allowing GFC’s better overviews of the battle space. The major limitation to this aircraft is weather
1.1 Introduction: The Aerospatiale Alouette III is a multi-purpose light helicopter having a single engine and was developed by Sud Aviation and manufactured by Aerospatiale of France in 1959. It is the successor to the Alouette II, it is larger and has more seating capability. 1.2 Dimensions Minimum Length (blade: folded): 10.03 m 32.90 ft Width (blades folded): 2.60 m 8.53 ft Height: 3.00 m 9.84 ft Main rotor disc diameter: 11.02 m 36.15 ft Tail rotor disc diameter: 1.91 m 6.27 ft Main rotor disc area:
Mechanical or physically worked flight control frameworks are the most essential system for controlling a flying machine. They were utilized as a part of right on time airplane and are presently utilized as a part of little air ship where the air motion facilitating powers are not exorbitant. A manual flight control framework utilizes a gathering of mechanical parts, for example, pushrods, pressure links, pulleys, stabilizers, and here and there fastens to transmit the strengths connected to the cockpit controls specifically to the control surfaces. In light flying machine the control surfaces are moved by the force of the pilot's muscles. Each one control surface is joined straightforwardly to the control section or rudder pedals with an arrangement
When the brakes are applied, the piston housed in the brake presses the rotors against the stators and the kinetic energy of the wheels is converted into heat. The temperature of the brake linings, discs and other peripheral systems can reach from 500° C to 2000° C. Therefore, designing a robust braking is imminent to ensure safety of the plane. In this paper, a design methodology for designing brakes of Boeing 737 has been discussed, historical and current material selection trends for the brakes and using the accumulated data, a numerical example is solved taking in account the data of a Boeing 737 aircraft. The brake disc (produced by Parker Cleveland) is modeled in SolidWorks 17 and structural and thermal analysis of the brake