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Stability is the ability of the aircraft to counteract disturbances to its flight path. According to David P. Davies, there are six types of aircraft stability: speed stability, stick free static longitudinal stability, static lateral stability, directional stability, oscillatory stability, and spiral stability. [5]: 164
Three cases for static stability: following a pitch disturbance, aircraft can be unstable, neutral, or stable. If an aircraft is longitudinally statically stable, a small increase in angle of attack will create a nose-down pitching moment on the aircraft, so that the angle of attack decreases.
Static stability is the ability of a robot to remain upright when at rest, or under acceleration and deceleration Static stability may also refer to: In aircraft or missiles: Static margin — a concept used to characterize the static stability and controllability of aircraft and missiles.
Stability derivatives, and also control derivatives, are measures of how particular forces and moments on an aircraft change as other parameters related to stability change (parameters such as airspeed, altitude, angle of attack, etc.). For a defined "trim" flight condition, changes and oscillations occur in these parameters.
In aviation, an aircraft is said to have relaxed stability if it has low or negative stability. [1] [2] An aircraft with negative stability will have a tendency to change its pitch and bank angles spontaneously. An aircraft with negative stability cannot be trimmed to maintain a certain attitude, and will, when disturbed in pitch or roll ...
Although usually stable in a normal aircraft, the motion may be so slightly damped that the effect is very unpleasant and undesirable. In swept-back wing aircraft, the Dutch roll is solved by installing a yaw damper, in effect a special-purpose automatic pilot that damps out any yawing oscillation by applying rudder corrections. Some swept-wing ...
Aircraft are prone to aeroelastic effects because they need to be lightweight while enduring large aerodynamic loads. Aircraft are designed to avoid the following aeroelastic problems: divergence where the aerodynamic forces increase the twist of a wing which further increases forces;
When an aircraft encounters a horizontal gust of wind, yaw stability causes the aircraft to turn into the wind, rather than turn in the same direction. [26] Fuselage geometry, engine nacelles and rotating propellers all influence lateral static stability and affect the required size of the stabilizer. [27] Not all aircraft have a vertical ...