Stringers Aircraft

Stringers Aircraft - In the construction of large aircraft structures, and in some small aircraft as well, the honeycomb sandwich structure employs either aluminum or reinforced plastic materials. Honeycomb panels are usually a lightweight cellular core sandwiched between two thin skins or facing materials such as aluminum, wood, or plastic.

Tension is the stress that resists a force that tends to pull apart. The engine pulls the aircraft forward, but air resistance tries to hold it back. The result is tension, which tries to stretch the aircraft.

Stringers Aircraft

The tensile strength of a material is measured in p.s.i. (pounds per square inch) and is calculated by dividing the load (in pounds) required to pull the material apart by its cross-sectional area (in square inches).

Stringers And Longerons

The wing butt rib is normally the heavily stressed rib section at the inboard end of the wing near the attachment point to the fuselage. Depending on its location and method of attachment, a butt rib may be called a bulkhead rib or a compression rib, if it is designed to receive compression loads that tend to force the wing spars together.

A continuous gusset stiffens cap strips in the plane of the rib. This aids in preventing buckling and helps to obtain better rib/skin glue joints where nail-gluing is used because such a rib can resist the driving force of nails better than the other types.

Continuous gussets are more easily handled than the many small separate gussets otherwise required. As a rule, a wing has two spars. One spar is usually located near the front of the wing, and the other about two thirds of the distance towards the wing's trailing edge.

Regardless of type, the spar is the most important part of the wing. When other structural members of the wing are placed under load, they pass most of the resulting stress on to the wing spars.

Semimonocoque Type

These make up the longitudinal components of the structure. Their primary aim is to transmit the axial loads (tension and compression) that arise from the tendency of the fuselage to bend under loading. The stringers also support the skin, and when combined with the frames, create bays over which the skin is attached.

To smooth out the airflow over the angles formed by the wings and other structural units with the fuselage, shaped and rounded panels or metal skin are attached. This paneling or skin is called fairing. Fairing is sometimes referred to as a fillet.

Some fairing is removable to provide access to aircraft components, while other fairing is riveted to the aircraft structure. The wings of some aircraft are of cantilever design; that is, they are built so that no external bracing is needed.

The skin is part of the wing structure and carries part of the wing stresses. The tail cone serves to close and streamline the aft end of most fuselages. The cone is made up of structural members like those of the fuselage;

Fuselage Loading

however, cones are usually of lighter construction since they receive less stress than the fuselage. Nose wheel aircraft are protected at the fuselage tail section with a tail skid or bumper. By means of wheels and tires (or skis), the landing gear forms a stabilizing contact with the ground during landing and taxiing.

Brakes installed in the wheels enable the aircraft to be slowed or stopped during movement on the ground. Shear is the stress that resists the force tending to cause one layer of a material to slide over an adjacent layer.

Two riveted plates in tension subject the rivets to a shearing force. Usually, the shearing strength of a material is either equal to or less than its tensile or compressive strength. Aircraft parts, especially screws, bolts, and rivets, are often subject to a shearing force.

The semimonocoque fuselage is constructed primarily of the alloys of aluminum and magnesium, although steel and titanium are found in areas of high temperatures. Primary bending loads are taken by the longerons, which usually extend across several points of support.

Wing Tip

The longerons are supplemented by other longitudinal members, called stringers. Stringers are more numerous and lighter in weight than longerons. The vertical structural members are referred to as bulkheads, frames, and formers. The heaviest of these vertical members are located at intervals to carry concentrated loads and at points where fittings are used to attach other units, such as the wings, power plants, and stabilizers.

Ribs are manufactured from wood or metal are used with metal spars. Some typical wooden ribs, usually manufactured from spruce. The most common types of wooden ribs are the plywood web, the lightened plywood web, and the truss types.

Of these three types, the truss type is the most efficient, but it lacks the simplicity of the other types. The fuselage will see a combination of loads from multiple sources during a typical flight. Large bending loads are introduced from the wing and tail sections, as well as a torsional load from the pitching moment of the wing.

The wing is made up of spars, ribs, and lower and upper wing skin covering. With few exceptions, wings of this type are of the stressed skin design (the skin is part of the wing structure and carries part of the wing stresses).

Wing Ribs

The box beam type of wing construction uses two main longitudinal members with connecting bulkheads to furnish additional strength and to give contour to the wing. A corrugated sheet may be placed between the bulkheads and the smooth outer skin so that the wing can better carry tension and compression loads.

In some cases, heavy longitudinal stiffeners are substituted for the corrugated sheets. A combination of corrugated sheets on the upper surface of the wing and stiffeners on the lower surface is sometimes used. The wing-tip cap is secured to the tip with countersunk screws and is secured to the inter spar structure at four points with 1/4 in bolts.

The tip leading edge contains the best anti-icing duct. Wing-heated air is exhausted through a louver on the top surface of the tip. Wing position lights are located at the center of the tip and are not directly visible from the cockpit.

As an indication that the wing tip light is operating, some wingtips are equipped with a lucid rod to transit the light to the leading edge. Toll Free: 877-477-7823 Customer Service: 800-861-3192 Fax: 800-329-3020 The web forms the main depth portion of the spar.

Cap strips are extrusions, formed angles, or milled sections to which the web is attached. These members carry the loads caused by the wing bending and also provide a foundation for attaching the skin. Most metal spars are built up from extruded aluminum alloy sections, with riveted aluminum alloy web sections to provide extra strength.

Starting at: $29.50 The truss type fuselage frame is usually constructed of steel tubing welded together in such a manner that all members of the truss can carry both tension and compression loads. In some aircraft, mainly the light, single-engine models, truss fuselage frames are constructed of aluminum alloy and may be riveted or bolted into one piece, with cross bracing achieved by using solid rods or tubes.

Aerostats are the floating crafts in atmosphere which are made lighter than air either by filling hot air or lighter gases. Their coarse movement can be controlled manually or by remote. These are commonly used for sports, publicity and weather explorations.

For example, Hot air balloons, airships and metrological gas balloons are aerostats. Starting at: $39.00 A nacelle or pod also contains a firewall which separates the engine compartment from the rest of the aircraft. This bulkhead is usually made of stainless steel sheet metal, or as in some aircraft, of titanium.

Starting at: $29.50 Aero dynes are the flying craft. Which are powered by either their self propulsive force or launched into the atmosphere by external force. Aeroplane, helicopters, gliders, rockets or missiles are examples of aerodynes.

Which are commonly used for training, transportation and military purposes. Please note, Aircraft Spruce's personnel are not certified aircraft mechanics and can only provide general support and ideas, which should not be relied upon or implemented in lieu of consulting an A&P or other qualified technician.

Aircraft Spruce assumes no responsibility or liability for any issue or problem which may arise from any repair, modification or other work done from this knowledge base. Any product eligibility information provided here is based on general application guides and we recommend always referring to your specific aircraft parts manual, the parts manufacturer or consulting with a qualified mechanic.

Engine mounts are designed to meet particular conditions of installation, such as the location and the method of attachment of the engine mount and the size, type, and characteristics of the engine it is intended to support.

An engine mount is usually constructed as a single unit which can be detached quickly and easily from the remaining structure. The monospar wing incorporates only one main longitudinal member in its construction. Ribs or bulkheads supply the necessary contour or shape to the aerofoil.

Although the strict monospar wing is not common, this type of design, modified by the addition of false spars or light shear webs along the trailing edge as support for the control surfaces, is sometimes used.

To overcome the strength/weight problem of monocoque construction, a modification called semimonocoque construction was developed. In addition to formers, frame assemblies, and bulkheads, the semimonocoque construction has the skin reinforced by longitudinal members. The reinforced shell has the skin reinforced by a complete framework of structural members.

In a semi-monocoque structure, both the outer skin and the internal substructure are load bearing, and both contribute to the overall stiffness of the structure. This design methodology was born out of the use of aluminum, rather than steel or wood, as the primary structural material used to manufacture airframe structures.

Aluminum has many advantages over steel. The density of an aluminum alloy is approximately one-third that of steel which allows for thicker structural sections to be built without any weight penalty. Thicker skins are advantageous as these are less likely to buckle under load, resulting in a more efficient structure.

The fuselage is the main structure or body of the aircraft. It provides space for cargo, controls, accessories, passengers, and other equipment. In single engine aircraft, it also houses the power plant. In multi-engine aircraft the engines may either be in the fuselage, attached to the fuselage, or suspended from the wing structure.

They vary mainly in size and arrangement of the different compartments. The directional control of a fixed-wing aircraft takes place around the lateral, longitudinal, and vertical axes by means of flight control surfaces. These control devices are hinged or movable surfaces through which the altitude of an aircraft is controlled during takeoff, flight, and landing.

They are usually divided into two major groups, the primary or main, and the auxiliary control surfaces. These stringers are not very strong at all. If you are using for aircraft with Light Fabric. It might hold up.

But for Med. or Heavy Fabric. These stringer tend to want to bend over to one side or the other. Just not stable, and stay straight. These do not have a welded seam. This would help a little.

But I am sure they are still a little on the light side of construction, for fabric use. The actual spar configuration may have either a plate or truss type web. The plate web consists of a solid plate with vertical stiffeners which increase the strength of the web.

Some spar plate webs are constructed differently. Some have no stiffeners; others contain flanged holes for reducing weight.

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