Armor plating has been used primarily in static and surface-based (land and water) equipment. Aircraft usage has been restricted due to weight restrictions. This paper takes a look at the basic theory and parameters to derive those applicable to light weight armor for aircraft. The creation of new surfaces by internal fracture removes much of the impact energy during the transient stages. Hence, the continuum formula for composites requires modification to account for transients in moduli and area variations, as also for texture variations in various layers. Equations describing variation of various material parameters are examined to give insights into ways of strengthening the composite structure.

There is scant literature on the use of armor in civil and fighter aircraft. Armor plating has been mainly applied on land-based vehicles, tanks, armored carriers and on ships. Modern aircraft rely on speed and various evasive ploys to deflect incoming missiles and projectiles. However, protection against air-to-air fire and flak has to be envisaged even for nominal protection. The possibility of encountering missiles with increased penetrability and hard materials like tungsten, molybdenum and Depleted Uranium (DU) cannot be discounted.

Protective shields have been used on spacecraft and satellites put into orbit for research and commercial use. These valuable craft have incorporated various shields to protect them from impact with high-speed space debris and meteorites. Usually, impact is with micrometeorites and dust particles; however, larger objects can be anticipated. Newer armaments and armor use high strength materials and design technologies to anticipate damage and avoid damage. Hence, it is necessary to appreciate the materials now being used by advanced nations and technologies.

Mechanical Engineering Journal, Armor plate, Composites, Fracture, Elastic modulus, Depleted Uranium (DU), Kinetic energy penetrators, Ballistic Limit Equations (BLE).