An aircraft must possess sufficient stability to maintain a uniform flightpath and to recover naturally from various disturbing forces such as gusts, turbulence, or control inputs. At the same time, to achieve optimum performance and safe handling qualities, the aircraft must respond properly and predictably to pilot control inputs. Control refers to the pilot’s action of moving the flight controls to generate aerodynamic forces that cause the aircraft to follow a desired flightpath. When an aircraft is described as controllable, it responds smoothly, promptly, and proportionally to control movements.
Different control surfaces are used to control the aircraft about each of the three principal axes—longitudinal, lateral, and vertical. Movement of these control surfaces alters the airflow over the aircraft surfaces, producing changes in lift, drag, and moments. These changes modify the balance of forces acting on the aircraft, allowing it to maneuver from straight-and-level flight to any desired attitude or flight condition.
Three fundamental terms appear in any discussion of aircraft stability and control: stability, maneuverability, and controllability.
- Stability is the inherent characteristic of an aircraft that causes it to return to straight-and-level flight after a disturbance, without continuous pilot input.
- Maneuverability is the ability of the aircraft to be guided along a desired flightpath and to withstand the aerodynamic and structural stresses imposed during maneuvers.
- Controllability refers to the effectiveness and responsiveness of the aircraft to pilot control inputs throughout the flight envelope.
Static Stability
An aircraft is said to be in a state of equilibrium when the sum of all forces and moments acting on it is zero. In this condition, the aircraft experiences no linear or angular acceleration and continues in a steady state of flight. When a gust of wind or a control deflection disturbs this equilibrium, an imbalance of forces or moments occurs, resulting in acceleration.
The three types of static stability are defined by the aircraft’s initial tendency following a disturbance:
- Positive static stability exists when the aircraft tends to return toward its original equilibrium position.
- Negative static stability, also called static instability, exists when the aircraft continues to move away from equilibrium in the direction of the disturbance.
- Neutral static stability exists when the aircraft remains in its new displaced position without a tendency to return or diverge.
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| Three types of stability |
Dynamic Stability
While static stability describes the initial tendency following a disturbance, dynamic stability concerns the aircraft’s motion over time after that disturbance. The manner in which oscillations develop, decay, or increase determines the dynamic stability characteristics.
An aircraft demonstrates positive dynamic stability if the amplitude of oscillation decreases with time and the aircraft gradually returns to equilibrium. If the amplitude remains constant, the aircraft has neutral dynamic stability. If the oscillations increase in magnitude, the aircraft exhibits dynamic instability.
Aircraft must be designed with appropriate degrees of both static and dynamic stability. An aircraft with static instability combined with rapidly increasing dynamic instability would be extremely difficult, if not impossible, to control manually. For most conventional aircraft, positive dynamic stability is essential to prevent sustained or divergent oscillations that could compromise safety and passenger comfort.
Longitudinal Stability
Longitudinal stability refers to stability about the aircraft’s lateral axis and involves pitching motion. An aircraft with good longitudinal stability tends to maintain a constant angle of attack (AOA) relative to the airflow. This means it does not naturally pitch nose-up toward a stall or nose-down into a dive following a disturbance.
The horizontal stabilizer is the primary component responsible for longitudinal stability. Its effectiveness depends on aircraft speed, angle of attack, center-of-gravity location, and stabilizer configuration. By producing a balancing pitching moment, the horizontal stabilizer helps restore the aircraft to its trimmed flight condition.
Directional Stability
Stability about the vertical axis is known as directional stability and involves yawing motion. A directionally stable aircraft tends to maintain its heading during straight-and-level flight, even when the pilot releases the rudder pedals.
If an aircraft naturally recovers from a skid or yaw disturbance, it is said to have good directional stability. The vertical stabilizer is the primary surface responsible for this stability. Directional stability can be enhanced through design features such as a large vertical tail, dorsal fins, a long moment arm, and sweptback wings, all of which help align the aircraft with the relative wind.
Lateral Stability
Lateral stability refers to stability about the aircraft’s longitudinal (fore-and-aft) axis and involves rolling motion. An aircraft with positive lateral stability tends to return to a wings-level attitude after being displaced by turbulence or control input.
Design features contributing to lateral stability include dihedral angle, wing sweep, keel effect, and high-wing configurations. These features help create restoring rolling moments when the aircraft is disturbed from level flight.
Dutch Roll
Dutch roll is a coupled lateral-directional oscillation consisting of an out-of-phase combination of yaw and roll. It is most commonly associated with swept-wing aircraft and can result in uncomfortable oscillatory motion if not adequately controlled.
To improve Dutch roll damping, many aircraft are equipped with a yaw damper, which automatically applies rudder inputs to counteract yaw oscillations. This system significantly enhances lateral-directional stability and improves overall handling qualities, particularly during cruise flight.