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In aviation, relaxed stability is the tendency of an aircraft to change its attitude and angle of bank of its own accord. An aircraft with relaxed stability will oscillate in simple harmonic motion around a particular attitude at an increasing amplitude.
This can be contrasted with the behaviour of an aircraft with positive stability, which, when trimmed to fly at a certain attitude, will continue to do so in the absence of control input, and if perturbed will oscillate in simple harmonic motion on a decreasing scale around and eventually return to the trimmed attitude. A positively stable aircraft will also resist any bank movement. A Cessna 152 is an example of a stable aircraft. Similarly, an aircraft with neutral stability will not return to its trimmed setting without control input, but will oscillate in a stable simple harmonic motion around the trimmed setting continuously, neither increasing nor decreasing oscillation amplitude, and be susceptible to bank influences.
Early attempts at heavier-than-air flight were marked by a differing concept of stability than is used today. Most aeronautical investigators regarded flight as if it were not so different from surface locomotion, except the surface was elevated. They thought of changing direction in terms of a ship's rudder, so the flying machine would remain essentially level in the air, as did an automobile or a ship at the surface. The idea of deliberately leaning, or rolling, to one side seemed either undesirable or did not enter their thinking.
Some of these early investigators, including Langley, Chanute, and later Santos-Dumont and the Voisin brothers, sought the ideal of inherent stability in a very strong sense, believing a flying machine should be built to automatically roll to a horizontal (lateral) position after any disturbance. They achieved this with the help of Hargrave cellular wings (wings with a box kite structure, including the vertical panels) and strongly dihedral wings. In most cases they did not include any means for a pilot to control the aircraft roll — they could only control elevator and rudder. The unpredicted effect of this was that it was very hard to turn the aircraft without rolling. They were also strongly affected by side gusts and side winds upon landing.
The Wright brothers designed their 1903 first powered Flyer with anhedral (drooping) wings, which are inherently unstable. They showed that a pilot can maintain control of lateral roll and it was a good way for a flying machine to turn—to "bank" or "lean" into the turn just like a bird or just like a person riding a bicycle. Equally important, this method would enable recovery when the wind tilted the machine to one side. Although used in 1903, it would not become widely known in Europe until August 1908, when Wilbur Wright demonstrated to European aviators the importance of the coordinated use of elevator, rudder and roll control for making effective turns.
Vertical wing position
The vertical positioning of the wing changes the roll stability of an aircraft.
- An aircraft with a "high" wing position (i.e., set on top of the fuselage) has a higher roll stability. For example, the Cessna 152.
- An aircraft with a "low" wing (i.e., underneath the fuselage) has less roll stability. The Piper Pawnee uses a "low" wing.
This behavior is often explained through comparison to a pendulum, that is, the fuselage hangs below the wings like a pendulum and its weight keeps the aircraft oriented correctly, but this explanation is incorrect (see Pendulum rocket fallacy). Instead, this effect is due to the aircraft's response to sideslip. An aircraft which is rolled to one side will tend to start to sideslip towards the low side of the airplane. A high wing tends to cause the aircraft to roll away from the sideslip, which tends to level the aircraft. A low wing tends instead to roll into the sideslip, increasing the roll angle and therefore increasing the sideslip further.
Modern military aircraft, particularly low observable ("stealth") designs, often exhibit instability as a result of their shape. The Lockheed F-117 Nighthawk, for instance, employs a highly non-traditional fuselage and wing shape in order to reduce its radar cross section and enable it to penetrate air defences with relative impunity. However, the flat facets of the design reduce its stability to the point where a digital fly-by-wire system was required to allow safe operation.
Relaxed stability designs are not limited to fighter jets. The McDonnell Douglas MD-11 has a relaxed stability design which was implemented to save fuel. To ensure stability for safe flight, an LSAS (Longitudinal Stability Augmentation System) was introduced to compensate for the MD-11's rather short horizontal stabilizer and ensure that the aircraft would remain stable. However, there have been incidents in which the MD-11's relaxed stability caused an "inflight upset."
The latest generation of fighter aircraft often employ design elements which reduce stability to increase maneuverability.[clarification needed] The BAE Harrier GR7/GR9 employs a significant and obvious anhedral angle to its wings, this reduces the inherent lateral stability of the wings mounted high on the fuselage.
A less stable aircraft requires smaller control deflections to initiate maneuvering; consequently drag and control surface imposed stresses will be reduced and aircraft responsiveness will be enhanced. Since these characteristics will typically make control by the pilot difficult or impossible, an artificial stability will typically be imposed using computers, servos, and sensors as parts of a fly by wire control system.
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