Control Surface of airplane

Control Surface of airplane

              Control surface of Aircraft is an aerodynamic device mean by which pilot stabilize aircraft and controls the direction and altitude of an aircraft on flight. Control surface is a movable surface which is lighter in construction has light  spar rod at the front edges to provide strength and rigidity, the spar connect the ribs and covered by the thin skinned sheet. The tabs are attached to the trailing edge of the control surface additional device will be attached based of purpose the control surface is used for transmission of tab loads to the surface.

Sheet Materials used in Control Surface

1. Metal structure                   -        Covered with metal skin
2. Composite Structure          -        Covered with fabric
3. Wooden Structure              -        Covered with Plywood or fabric

Drilling

The hole on the surface made using drain holes to prevent water  trapped inside the structure , which causes the control surface to be thrown out of balance

Jointing

Process involved in jointing the components includes fasteners like adhesive and bonding agents.

Flight Control Surface are sub branched into

• Primary Control Surface
• Secondary Control Surface

Primary Control Surfaceis designed to provide adequate response to controlling device giving a natural feel.

At low speed control will be smooth and sluggish

At high speed control will become increasingly firm

Responding to speed

At low speed the aircraft respond slow to control applied

At high speed the aircraft respond more rapid (faster) to control applied

Primary Control Surface includes:

Ailerons - (ROLL) Control motion along longitudinal axis.

Elevator - (PITCH) Control rotational motion along lateral axis.

Rudder  - (YAW) Control motion along Vertical axis.

Secondary Control Surface are use to improve the aircraft performance characteristics and to release the excessive control loads applied.

Secondary Control Surface includes:

Wing flaps - Used to increase the Lift and Drag increase while Take off.

Slats- Located on the leading edge of the wings. Creates enough lift at high Angle of attack.

Slots- Span wise gap present at each wing allowing air to flow between the wings, which creates lift thus reduces stall.

Trimtabs - Connect trailing edge to large Control Surface, Used to Stabilize the aircraft.

Balancetabs - Control loads on the control surface is significantly reduced, makes aircraft easy to fly.

Anti-Balancetabs - Maintain the stability in the desire position.

Servo tabs- Small Hinged device to assist the movement of the control surface.

The Combination of this Control Surface of Aircraft helps the pilot in controlling and stressing the aircraft during flight .

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Aircraft Wing Structure

Aircraft Wing Structure

          The Wing, in aeronautics are airfoils attached to each side of the fuselage Wings is the primary lifting surface of the aircraft that support the aircraft in flight, The load acting on the aircraft structure are carried the wing structure. So the design of the wing depends on many facts like lift to weight ratio, rate of climb, size, weight and which aircraft it is used, thought its shape may be widely varied its function remains the same.

Basic features of Wing Constructions

The primary structural parts of the wing are spars, ribs, and stringers.

Sparsare also called as wing beams is a main member of the wing structure, it extends from the fuselage to the tip of the wing, all the forces and loads acting on wing are carried and balances by the spars. When the engine or landing gear are mounted on the wing , Spare incorporate structure attached to the components, as spars are designed to have greater bending stress.

Ribsare also called as plain ribs, it’s a chord wise member of the wing structure used to give wing structure it shape, It extends from the leading edge to the trailing edge of the wing It transmits air load from skin to the spars also stabilize the spare against twisting

Stringers are assist to hold shape of wing the span wise called stringers are used. They are attached to the skin usually found fare closed spaced on the upper wing surface, it is used on compression and stiffening of the compression skin to overcome the induced bending loads. But when the wing need of more stiffening where skin is reinforced by panels instead of individual stringers.

Based in this concept, Wing lift the aircraft on air and keeps flying.

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Types of Aircraft Fuselage Structure

Types of Aircraft Fuselage

            The basics of the Aircraft Fuselage was explained in the before posts (https://sabaeroline.blogspot.com/2020/07/aircraft-fuselage-structure.html), Fuselage types would clearly explain in the present post.

    

    In general, fuselage is classified into three major types base on the method by which stress are transmitted to the structure.

There are three most common types of fuselage are:

Truss or Frame Type Fuselage

A truss is a light gauge steel tube assemblage of members forming a frame triangular shape which giver geometric structure to the fuselage. The Primary members of Truss are the four logerons, the longerons are longitudinal member of the fuselage. Lateral bracing are placed at intervals between the longerons. The lateral surface are called as Bulkheads, Space between two bulkheads are called as bays. Lateral and Longitudinal member are made strong stell wires which are design to withstand compression during load applied.

Truss Fuselage are sub-branched into

• Pratt Truss
• Warren Truss

Monocoqne Structure

The word Monocoqne is French word which means “single shell”. In this type the fuselage skin carries all structural stress. The design involves constructing a tube or core which involves no internal structural members which looks like a empty Shell. These types of fuselage are formed by riveting preformed two half together. This Structure carry load effective when the diameter is small. Increasing of the structure diameter depends on the internal cavity.

Semi Monocoqne Structure

It is combination of Truss and Monocoqne type structure together. In Present days Aircraft become large Monocoqne structure not to strong enough. Weight to strength ration is ineffective. Longerons are run length across the monocoqne structure jointing the frame together. Now the Longerons and frame is attached the thin alloy skin shell by rivets and abrasive bonding.

Semi Monocoqne Structure type of fuselage is commonly used both military and commercial aircraft in Modern Days.

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AirCraft Fuselage Structure

Fuselage of Aircraft

    Fuselage is a body of an aircraft to which the wings, tail and Landing Gear units are attached. Spaces from the cockpit cabin, Passenger cabin, Cargo, Controls unit are located inside the fuselage. Design and size of the fuselage varies according to the function to the aircraft. The word fuselage comes from a French word “fusele” means “splindle-shape” Fuselage is a long and vertical spindle hollow tube. The hollow shape design provides maximum strength with minimum weight.

Fuselage are designed to satisfy two major criteria:

• Protect the passengers in the event of crash.

• Efficient in fitting together the wing, tail, landing gear and other control surface in perfect place accomplished with interior space for passenger comfort with minimum frontal area to contour drag for maximum performance.

Fuse large must have a point of attachment for each part such as wings, tail, Landing Gear and Engines to arrange and installed. So that at time of emergency this part can be inspected, removed, repaired and replaced again easily. The fuselage must be very strong at the point of attachment as more loads would be acting on the fuselage and fitted parts during flying and landing.

Outer Design Criteria of Fuselage

Fuselage is the outer shell of the aircraft, the cabin inside are fully pressurized and the pressure inside the aircraft is greater than the pressure outside due to which the fuselage is exposed to different stress, It must be designed with strong durable material. If were any pressure loss occurs. Oxygen levels will drop it can create a dangerous environment to the crew and the passenger inside.

During the time of rotation of the aircraft more torque will be produce fuselage should be designed to withstand this torque force which leads to collapse of the entire structure, as more load will be acting on the outer surface of Fuse large.

Fuselage design base on Aircraft Usage

In fighter jet have a slender and streamline fuselage  to contour drag for maximum performance  and cockpit will only cabin space present large enough only for the controls and pilot. Cockpit is place on the top of the fuselage for ground visualization and the engines and fuel are place at the rear of the fuselage.

In airlines Civil aircraft use to have a wide, long fuselage carry the many number of passenger as well as cargo. The cockpit will have large space and separate desk for passenger cabin and cargo, Cargo space will be located below the passenger cabin and fuel is stored at the wing.

In single engine aircraft the engine is mounted in nose of the fuselage. Cockpit will be place at the top to provide ground visibility.

Fuselage skeleton and skin

Fuselage shielded by a thin sheet of material stiffened by large number of longitudinal stringers running together with transverse frames place between, they carry bending moment, shear force and torsional load which causes axial stresses in the stringers and skin. As shear stress acts on the skin because of the resistance stringers the shear force gets ignored.

(Shear Force: Force acting perpendicular to its longitudinal axis)

Distance between adjacent stringer is usually small due which shear flow in the connecting panel is small.

Material Used

Most airplane uses an Aluminium Fuselage, As Aluminium is strong, corrosive resist to rust and light weight. This characters makes aluminium effect used material for making aircraft component which includes fuselage.

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