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The longitudinal stability of an aircraft, also called pitch stability, [2] refers to the aircraft's stability in its plane of symmetry [2] about the lateral axis (the axis along the wingspan). [1] It is an important aspect of the handling qualities of the aircraft, and one of the main factors determining the ease with which the pilot is able ...
A sample CG-moment envelope chart, showing that a loaded plane weighing 2,367 lb (1,074 kg) with a moment of 105,200 lb⋅in (11886 N⋅m) is within the "normal category" envelope. Center of gravity (CG) is calculated as follows: Determine weights and arms for all mass within the aircraft. Multiply weights by arms for all mass to calculate moments.
The period is usually on the order of 3–15 seconds, but it can vary from a few seconds for light aircraft to a minute or more for airliners. Damping is increased by large directional stability and small dihedral and decreased by small directional stability and large dihedral.
Diagram showing the three main cases for aircraft pitch dynamic stability. Here all three cases are for a statically stable aircraft. Following a pitch disturbance, three cases are shown: Aircraft is dynamically unstable (although statically stable); Aircraft is dynamically damped (and statically stable);
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
Diagram showing the three main cases for aircraft pitch static stability, following a pitch disturbance: Aircraft is statically stable (corrects attitude); Aircraft is statically neutral (does not correct attitude); Aircraft is statically unstable (exacerbates attitude disturbance).
To provide longitudinal stability, the wings must differ in aerodynamic characteristics: typically the angle of incidence and/or the aerofoils chosen differ between the two wings. The wings on each side may meet at their tips to form a joined wing (see above). [7] Three surface: [23] both conventional tail and canard auxiliary surfaces.
The missile is characterised by only three stability derivatives, and hence provides a useful introduction to the more complex aeroplane dynamics. This diagram shows lift as perpendicular to the longitudinal body axis. In most technical usage, lift is perpendicular to the oncoming flow. That is, perpendicular to the longitudinal stability axis.