Method and apparatus for an aircraft inner loop elevator control system

Claim 2

In an aircraft flight control system wherein inner loop damping signals are combined with outer loop command signals to produce an elevator control signal, improved inner loop damping signal apparatus comprising: means for providing a signal h representative of aircraft vertical acceleration; means for amplifying said h signal by a predetermined gain factor K h ; means for providing a signal θ representative of aircraft pitch; means for amplifying said θ signal by a predetermined gain factor K.sub.θ ; low pass filter means for attenuating said h signal above a predetermined frequency ω; high pass filter means for attenuating said θ signal below said frequency ω; means for providing a signal θ representative of aircraft pitch rate; means for amplifying said θ signal by a predetermined gain factor K.sub.θ ; and summer means for summing said low pass filtered h signal, said high pass filtered θ signal, said amplified θ signals and the outer loop command signal to thereby produce the control signal.

Claim 3

In an aircraft flight control system wherein inner loop damping signals are combined with outer loop command signals to produce an elevator control signal, improved inner loop damping signal apparatus comprising: means for providing an aircraft vertical acceleration signal h; means for providing an aircraft pitch rate signal θ; means for amplifying said h and θ signals by predetermined gain factors; first low pass filter means for attenuating said vertical acceleration signal h above a predetermined frequency ω; high pass filter means for attenuating said pitch rate signal θ below said predetermined frequency ω; second low pass filter means for attenuating said pitch rate signal θ above said predetermined frequency ω; and summer means for summing said low pass filtered h and said high pass and low pass filtered θ signals to produce an inner loop damping signal.

Claim 4

In an aircraft flight control system wherein inner loop damping signals are combined with outer loop command signals to produce an elevator control signal, improved inner loop damping signal apparatus comprising: means for providing an aircraft vertical acceleration signal h; means for providing an aircraft pitch rate signal θ; means for amplifying said h and θ signals by predetermined gain factors; first low pass filter means for attenuating said vertical acceleration signal h above a predetermined frequency ω; high pass filter means for attenuating said pitch rate signal θ below said predetermined frequency ω; second low pass filter means for attenuating said pitch rate signal θ above said predetermined frequency ω; and summer means for summing said low pass filtered h and said high pass and low pass filtered θ signals to produce an inner loop damping signal.

Claim 5

In an aircarft flight control system wherein an inner loop command signal is combined with an outer loop damping signal to produce an elevator control signal, an improved method of producing said inner loop damping signal comprising the steps of: (a) providing an aircraft vertical acceleration signal h; (b) providing an aircraft pitch rate signal θ; (c) amplifying said h and θ signals by predetermined gain factors; (d) attenuating said vertical acceleration signal h above a predetermined frequency ω; (e) attenuating said pitch rate signal θ below said predetermined frequency ω; (f) attenuating said pitch rate signal above said predetermined frequency ω; and (g) summing said attenuated h and θ signals from steps (d), (e) and (f) to produce the inner loop signal.

Claim 6

In an aircarft flight control system wherein an inner loop command signal is combined with an outer loop damping signal to produce an elevator control signal, an improved method of producing said inner loop damping signal comprising the steps of: (a) providing an aircraft vertical acceleration signal h; (b) providing an aircraft pitch rate signal θ; (c) amplifying said h and θ signals by predetermined gain factors; (d) attenuating said vertical acceleration signal h above a predetermined frequency ω; (e) attenuating said pitch rate signal θ below said predetermined frequency ω; (f) attenuating said pitch rate signal above said predetermined frequency ω; and (g) summing said attenuated h and θ signals from steps (d), (e) and (f) to produce the inner loop signal.

Claim 7

In an aircraft flight control system, apparatus for producing an elevator control signal, the apparatus comprising: means for providing signals θ and θ representative of aircraft pitch and pitch rate, respectively; means for providing signals h, h and h representative of aircraft altitude, altitude rate and vertical acceleration, respectively; first high pass filtering means for attenuating said θ signal below a predetermined frequency; first amplifying means for amplifying each of said θ, h, h and h signals by individual predetermined gain factors; first summing means for summing said amplified h, h and h signals and the amplified and high pass filtered θ signal; second high pass filter means for attenuating said θ signal below a predetermined frequency; second amplifying means for amplifying each of said θ, θ, h and h signals by individual predetermined gain factors; second high pass filter means for attenuating said amplified θ below a predetermined frequency; second summing means for summing said amplified θ, h and h signals and the amplified and high pass filtered θ signal; and complementary filter means for outputting said first summing means signal at frequencies below a predetermined frequency and outputting said second summing means signal at frequencies above said predetermined frequency, whereby the output of said complementary filter means is said produced elevator control signal.

Claim 8

In an aircraft flight control system, apparatus for producing an elevator control signal, the apparatus comprising: means for providing signals θ and θ representative of aircraft pitch and pitch rate, respectively; means for providing signals h, h and h representative of aircraft altitude, altitude rate and vertical acceleration, respectively; first high pass filtering means for attenuating said θ signal below a predetermined frequency; first amplifying means for amplifying each of said θ, h, h and h signals by individual predetermined gain factors; first summing means for summing said amplified h, h and h signals and the amplified and high pass filtered θ signal; second high pass filter means for attenuating said θ signal below a predetermined frequency; second amplifying means for amplifying each of said θ, θ, h and h signals by individual predetermined gain factors; second high pass filter means for attenuating said amplified θ below a predetermined frequency; second summing means for summing said amplified θ, h and h signals and the amplified and high pass filtered θ signal; and complementary filter means for outputting said first summing means signal at frequencies below a predetermined frequency and outputting said second summing means signal at frequencies above said predetermined frequency, whereby the output of said complementary filter means is said produced elevator control signal.

Claim 9

In an aircraft flight control system wherein inner loop damping signals are combined with outer loop command signals to produce an elevator control signal, apparatus for producing an improved inner loop damping signal, the apparatus comprising: means for providing signals h and h representative of aircraft altitude and vertical acceleration, respectively; means for providing a signal θ representative of aircraft pitch rate; high pass filter means for attenuating said θ below a predetermined frequency ω 0 ; first circuit means for amplifying said h signal by a predetermined gain factor and predeterminedly attenuating said amplified h signal above a predetermined frequency ω; second circuit means for amplifying the output of said high pass filter by a predetermined gain factor and predeterminedly attenuating the resultant signal above said frequency ω; third circuit means for amplifying the output of said high pass filter by a predetermined gain factor and predeterminedly attenuating the resultant signal below said frequency ω; fourth circuit means for amplifying said h signal by a predetermined gain factor and attenuating said amplified h signal below said frequency ω; combiner means for combining the outputs from said first, second, third and fourth circuit means to thereby provide said inner loop damping signal.

Claim 10

In an aircraft flight control system wherein inner loop damping signals are combined with outer loop command signals to produce an elevator control signal, apparatus for producing an improved inner loop damping signal, the apparatus comprising: means for providing signals h and h representative of aircraft altitude and vertical acceleration, respectively; means for providing a signal θ representative of aircraft pitch rate; high pass filter means for attenuating said θ below a predetermined frequency ω 0 ; first circuit means for amplifying said h signal by a predetermined gain factor and predeterminedly attenuating said amplified h signal above a predetermined frequency ω; second circuit means for amplifying the output of said high pass filter by a predetermined gain factor and predeterminedly attenuating the resultant signal above said frequency ω; third circuit means for amplifying the output of said high pass filter by a predetermined gain factor and predeterminedly attenuating the resultant signal below said frequency ω; fourth circuit means for amplifying said h signal by a predetermined gain factor and attenuating said amplified h signal below said frequency ω; combiner means for combining the outputs from said first, second, third and fourth circuit means to thereby provide said inner loop damping signal.

Claim 11

In an aircraft flight control system, apparatus for producing an elevator control signal, the apparatus comprising: means for providing signals θ and θ representative of aircraft pitch and pitch rate, respectively; means for providing signal h, h and h representative of aircraft altitude, altitude rate and vertical acceleration, respectively; first high pass filtering means for attenuating said θ signal below a predetermined frequency; first amplifying means for amplifying each of said θ, h, h and h signals by individual predetermined gain factors; first summing means for summing said amplified h, h and h signals and the high pass filtered and amplified θ signal; second amplifying means for amplifying each of said θ, θ, h and h signals by individual predetermined gain factors; second summing means for summing said amplified θ and θ signals; washout filter means for high pass filtering the output of said second summer means; third summing means for summing said amplified h and h signals and the output of said washout filter means; and complementary filter means for outputting said first summing means signal at frequencies below a predetermined frequency and outputting said third summing means signal at frequencies above said predetermined frequency, whereby the output of said complementary filter means is said produced elevator control signal.

Claim 12

In an aircraft flight control system, apparatus for producing an elevator control signal, the apparatus comprising: means for providing signals θ and θ representative of aircraft pitch and pitch rate, respectively; means for providing signal h, h and h representative of aircraft altitude, altitude rate and vertical acceleration, respectively; first high pass filtering means for attenuating said θ signal below a predetermined frequency; first amplifying means for amplifying each of said θ, h, h and h signals by individual predetermined gain factors; first summing means for summing said amplified h, h and h signals and the high pass filtered and amplified θ signal; second amplifying means for amplifying each of said θ, θ, h and h signals by individual predetermined gain factors; second summing means for summing said amplified θ and θ signals; washout filter means for high pass filtering the output of said second summer means; third summing means for summing said amplified h and h signals and the output of said washout filter means; and complementary filter means for outputting said first summing means signal at frequencies below a predetermined frequency and outputting said third summing means signal at frequencies above said predetermined frequency, whereby the output of said complementary filter means is said produced elevator control signal.

Claim 13

In an aircraft flight control system wherein inner loop damping signals are combined with outer loop command signals to produce an elevator control signal, apparatus for producing an improved inner loop damping signal, the apparatus comprising: means for providing signals h and h representative of aircraft altitude, altitude rate and vertical acceleration, respectively; means for providing a signal θ representative of aircraft pitch rate; first circuit means for amplifying said θ signal by a first predetermined gain factor and attenuating the resultant signal below a predetermined frequency ω 1 ; second circuit means for amplifying said θ signal by a second predetermined gain factor and attenuating the resultant signal below a predetermined frequency ω 2 ; third circuit means for attenuating the output signal of the first circuit means above a predetermined frequency ω; fourth circuit means for attenuating the output signal from the second circuit means above the predetermined frequency ω; fifth circuit means for amplifying said h signal by a third predetermined gain factor and attenuating the resultant signal above the frequency ω; sixth circuit means for amplifying said h signal by a fourth predetermined gain factor and; combiner means for combining the signals produced by the second third, fourth, fifth, and sixth circuit means to thereby produce said inner loop damping signal.

Claim 14

In an aircraft flight control system wherein inner loop damping signals are combined with outer loop command signals to produce an elevator control signal, apparatus for producing an improved inner loop damping signal, the apparatus comprising: means for providing signals h and h representative of aircraft altitude, altitude rate and vertical acceleration, respectively; means for providing a signal θ representative of aircraft pitch rate; first circuit means for amplifying said θ signal by a first predetermined gain factor and attenuating the resultant signal below a predetermined frequency ω 1 ; second circuit means for amplifying said θ signal by a second predetermined gain factor and attenuating the resultant signal below a predetermined frequency ω 2 ; third circuit means for attenuating the output signal of the first circuit means above a predetermined frequency ω; fourth circuit means for attenuating the output signal from the second circuit means above the predetermined frequency ω; fifth circuit means for amplifying said h signal by a third predetermined gain factor and attenuating the resultant signal above the frequency ω; sixth circuit means for amplifying said h signal by a fourth predetermined gain factor and; combiner means for combining the signals produced by the second third, fourth, fifth, and sixth circuit means to thereby produce said inner loop damping signal.