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July 1958.
4. Stammers, C. W., ‘The flutter of a helicopter rotor blade in forward flight’, Aeronaut. Q.,
February 1970.
5. Carta, F. O., ‘An analysis of the stall flutter instability of helicopter rotor blades’, J. Amer.
Helicopter Soc., October 1967.
6. Ham, N. D. and Young, M. I., ‘Torsional oscillations of rotor blades due to stall’, J. Aircraft,
May to June 1966.
7. Ham, N. D. ‘Helicopter blade flutter’, AGARD Rep. 607, January 1973.
8. Coleman, Robert P., and Stempin, Carl W., ‘A preliminary theoretical study of aerodynamic
instability of a two-bladed helicopter rotor’, NACA Res. Memo. L6H 23, 1946.
9. Balmford, D. E. H., Hansford, R. E. and King, S. P. ‘Helicopter dynamics’. Westland Helicopters
Ltd. Report, March 1985.
10. Ormiston, Robert A. and Hodges, Dewey H., ‘Linear flap–lag dynamics of hingeless rotor
blades in hover’, J. Amer. Helicopter Soc., April 1972.
11. Coleman, R. P. and Feingold, A. M., ‘Theory of self-excited mechanical oscillations of helicopter
rotors with hinged blades’, NACA Rep. 1351, 1958.
12. Price, H. L., ‘Simplified helicopter ground resonance stability boundaries’, Aircraft Engineering,
October and November 1962.
13. Mil, M. L., et al., Helicopters – calculation and design, vol. II, ‘Vibrations and dynamic
stability’, NASA Tech. Transl. NASA TT F–519, 1968.
14. Done, G. T. S., ‘A simplified approach to helicopter ground resonance’, Aeronaut. J., May 1974.
15. Bramwell, A. R. S., ‘An introduction to helicopter air resonance’, Aeronautical Research
Council R & M. 3777, 1975.
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rotors’ J. Amer. Helicopter Soc., April 1971.
17. Baldock, J. C. A., ‘Some calculations for air resonance of a helicopter with non-articulated
rotor blades’, Aeronautical Research Council R & M 3743, 1974.
18. Ormiston, R. A., ‘Aeromechanical stability of soft in-plane hingeless rotor helicopters,’ Paper
25, 3rd European Rotorcraft Forum, Aix-en-Provence, September 1977.
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Annual Forum of American Helicopter Society, St Louis, MO, May 1983.
Appendices
A.1 Euler’s equations
A.1.1 Angular momentum and the equations of angular motion
We define the relative angular momentum, h, of a system of particles comprising a
body by
h = Σr × (mvr) (A.1.1)
where r is the position vector of a particle of mass m and vrel is the velocity of the
particle relative to the origin, which may be that of a moving frame. The summation
is taken over all the particles of the system. Then
dh/dt = Σ(dr/dt) × (mvrel) + Σr × (mdvrel/dt) (A.1.2)
Now, if v is the absolute velocity of the particle and v0 the velocity of the origin
of the moving frame,
vrel = dr/dt = v – v0
and dvrel/dt = dv/dt – dv0/dt
Since
(dr/dt) × vrel = (dr/dt) × (dr/dt)
the first term of eqn A.1.2 is zero; therefore,
dh/dt = Σ r × (mdv/dt) – Σr × (mdv0/dt)
But mdv/dt = F, where F is the resultant external force acting on the particle.
Hence
Σr × (mdv/dt) = Σr × F = T
where T is the moment of the external forces about the origin.
Also, since dv0/dt is constant over the system of particles,
Appendices 361
Σr × (mdv0/dt) = Mrg × a0
since Σmr is the mass moment of the system relative to the origin, M being the total
system mass, rg the position vector of the centre of gravity of the system, and a0 the
acceleration of the origin of the moving frame. Thus, finally,
dh/dt = T – Mrg × a0 (A.1.3)
We can obtain an alternative formula by defining the absolute angular momentum
by
H = Σr × (mv) (A.1.4)
where, as above, v is the absolute velocity of the particle. By an argument similar to
that above we obtain the equation
dH/dt = T – v0 × Mvg (A.1.5)
where vg is the velocity of the centre of gravity of the system of particles.
We now expand the general vector eqns A.1.3 and A.1.5 in terms of components
measured in the chosen frame of reference.
From the defining equations A.1.1 and A.1.2 we find that
H = h + Σr × mv0 = h + Mrg × v0
For subsequent applications we shall choose axes which are fixed in the body, as
it is clearly convenient that the inertial properties of the body should remain constant
with time. We can then write for the particle velocity vr
 
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