By V. Shmyrov, et al.,
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Additional info for Airplane Power Plants Systems Designing (synopsis)
The amplitude of the forced oscillations does not depend on entry conditions and time. I. е. the forced oscillations are not damped. 6. At a resonance ( ω = p ) the amplitude of the forced oscillations q remains finite AF = . e. up to the resonance, and makes: AF = qp 2 2 2 . 2κ p − κ 7. In the forced oscillations with drag, a shift of phase of oscillations 2 κω ϕF = arctan 2 , in comparison with the phase of shaking force, alp − ω2 π ways takes place. The maximal value of the phase shift ϕ F = , is 2 reached at the resonance.
2 > p 2 − 2 κ 2 ; μ < 1 ; y DYN < y ST . On the basis of this diagram it is possible to make the following conclusions: 1. The coincidence of frequencies of forced and natural oscillations (the second zone) is inadmissible. 2. The case, that the frequency of forced oscillation is smaller than the frequency of natural one (the first zone), is allowable, but is undesirable. Thus there is a capability to hit in a resonance with higher harmonics of the shaking force. (It occurs in turboprop engine mounts).
4. Schemes of Fuel System The following ways are applied to supply the fuel use from tank: gravity feed, forced out feed and pump feed. At gravity feeding (Fig. 4, a) fuel goes into the engine due to potential energy of the difference of levels between the fuel tank (which should be higher) and the engine. This scheme is the easiest and simplest. However at changes of aircraft attitude, this fuel feeding stops. It is applied on aircraft (especially on super light aircraft) with low-powered piston engines, because the required pump inlet pressure of such engines is rather small.
Airplane Power Plants Systems Designing (synopsis) by V. Shmyrov, et al.,