Ascent and descent slope tracker system

Claim 3

The method of navigating an aircraft as set forth in claim 1 wherein the altitude of waypoint factor is subtracted from the aircraft altitude factor thereby relating the aircraft to a theoretical descent slope.

Claim 4

The method of navigating an aircraft as set forth in claim 1 wherein the altitude of the aircraft factor is subtracted from the altitude of waypoint factor thereby relating the aircraft to a theoretical ascent slope.

Claim 5

The method of navigating an aircraft as set forth in claim 1 wherein the aircraft is also subjected to a rate of change of distance factor by producing a distance offset factor therefrom and reducing the distance to waypoint factor thereby.

Claim 6

The method of navigating an aircraft as set forth in claim 1 wherein the aircraft is also subjected to a rate of change of distance factor, by producing a distance offset factor therefrom and reducing the distance to waypoint factor thereby, and by resolving intensity of the ratio between the actual and predicted slope factors with the magnitude thereof.

Claim 7

The method of navigating an aircraft as set forth in claim 1 wherein the independently produced predicted slope factor is a synthetic value.

Claim 8

The method of navigating an aircraft as set forth in claim 1 wherein the independently produced predicted slope factor is acquired as an instantaneous sample of said actual slope factor.

Claim 9

The method of navigating an aircraft as set forth in claim 1 wherein the aircraft is also subjected to a rate of change of distance factor, by producing a distance offset factor therefrom and reducing the distance to waypoint factor thereby, and by resolving intensity of the ratio between the actual and predicted slope factors with the magnitude thereof, and wherein the independently produced predicted slope factor is synthetic value.

Claim 10

The method of navigating an aircraft as set forth in claim 1 wherein the aircraft is also subjected to a rate of change of distance factor, by producing a distance offset factor therefrom and reducing the distance to waypoint factor thereby, and resolving intensity of the ratio between the actual and predicted slope factors with the magnitude thereof, and wherein the independently produced predicted slope factor is acquired as an instantaneous sample of the said actual slope factor.

Claim 11

An airborne slope tracker system for the navigation of aircraft along a slope to a predetermined waypoint, and includIng; an altitude displacement means producing an altitude factor signal, a distance displacement means producing a remaining distance factor signal, means relating the altitude factor signal and the distance factor signal and producing therefrom an actual slope factor signal, a slope determining generator means producing a predicted slope signal, and a comparator means responsive to the ratio between the said actual slope factor signal and the said predicted slope signal and producing therefrom a navigation signal.

Claim 12

An airborne slope tracker system for the navigation of aircraft along a slope to a predetermined waypoint, and includIng; an altitude displacement means producing an altitude factor signal, a distance displacement means producing a remaining distance factor signal, means relating the altitude factor signal and the distance factor signal and producing therefrom an actual slope factor signal, a slope determining generator means producing a predicted slope signal, and a comparator means responsive to the ratio between the said actual slope factor signal and the said predicted slope signal and producing therefrom a navigation signal.

Claim 13

The slope tracker system for navigating aircraft as set forth in claim 10, wherein the said remaining distance factor signal is modified by a deceleration factor generating means producing a distance offset signal, there being means subtracting the said distance offset signal from the remaining distance factor signal and producing a modified remaining distance factor signal.

Claim 14

The slope tracker system for navigating aircraft as set forth in claim 10, wherein the said remaining distance factor signal is modified by a deceleration factor generating means producing a distance offset signal with means limiting the same to Zero, there being means subtracting the said distance offset signal from the remaining distance factor signal and producing a modified remaining distance factor signal.

Claim 15

The slope tracker system for navigating aircraft as set forth in claim 10, wherein the altitude displacement means includes means subtracting altitude of the waypoint from altitude of the aircraft to produce an altitude factor descent signal.

Claim 16

The slope tracker system for navigating aircraft as set forth in claim 10, wherein the altitude displacement means includes means subtracting altitude of the aircraft from altitude of the waypoint to produce an altitude factor ascent signal.

Claim 17

The slope tracker system for navigating aircraft as set forth in claim 10, wherein the altitude displacement means is a dual channel means with one channel that subtracts altitude of the waypoint from altitude of the aircraft to produce an altitude factor descent signal, and a second channel that subtracts altitude of the aircraft from altitude of the waypoint to produce an altitude factor ascent signal, there being selector means directing the output signal of one of said channels to said means relating the altitude factor signal and the distance factor signal.

Claim 18

The slope tracker system for navigating aircraft as set forth in claim 10, wherein the altitude displacement means includes means subtracting altitude of waypoint from altitude of the aircraft to produce an altitude factor descent signal, there being means dividing the altitude factor descent signal by an increment factor signal related to altitude of the aircraft.

Claim 19

The slope tracker system for navigating aircraft as set forth in claim 10, wherein the altitude displacement means includes means subtracting altitude of the aircraft from altitude of the waypoint to produce an altitude factor ascent signal, there being means dividing the altitude factor ascent signal by an increment factor signal related to altitude of the aircraft.

Claim 20

The slope tracker system for navigating aircraft as set forth in claim 10, wherein the altitude displacement means is a dual channel means with one channel that subtracts altitude of the waypoint from altitude of the aircraft to produce an altitude factor descent signal, and a second channel that subtracts altitude of the aircraft from altitude of the waypoint to produce an altitude factor ascent signal, there being means associated with each of said channels dividing the altitude factor signal thereof by an increment factor signal related to altitude of the aircraft, there being selector means directing the output signal of one of said channels to said means relating the said altitude factor signal and the distance factor signal.

Claim 21

The slope tracker system for navigating aircraft as set forth in claim 10, wherein the said remaining distance factor signal is modified By a deceleration factor generating means producing a modified distance offset signal varied by means responsive to aircraft altitude and speed, and wherein resolution means responsive to said modified distance offset signal adjusts the magnitude of the navitation signal inversely in proportion to the magnitude of said distance offset signal.

Claim 22

An airborne slope tracker system for the navigation of aircraft along a slope to a predetermined waypoint, and including; an altitude displacement means producing an altitude offset signal, a Distance Measurement Equipment means producing a remaining distance to waypoint output signal, a deceleration factor generator means producing a distance offset signal, a subtractor means to calculate the difference between the Distance Measurement Equipment means output signal and said distance offset signal and producing a signal, a divider means utilizing the subtractor means output signal as a numerator and utilizing the altitude displacement means output signal as a denominator and producing an actual slope signal, a slope determining generator means producing a predicted slope signal, and comparator means responsive to the ratio between the said actual slope signal and the said predicted slope signal and producing therefrom a navigation signal.

Claim 23

An airborne slope tracker system for the navigation of aircraft along a slope to a predetermined waypoint, and including; an altitude displacement means producing an altitude offset signal, a Distance Measurement Equipment means producing a remaining distance to waypoint output signal, a deceleration factor generator means producing a distance offset signal, a subtractor means to calculate the difference between the Distance Measurement Equipment means output signal and said distance offset signal and producing a signal, a divider means utilizing the subtractor means output signal as a numerator and utilizing the altitude displacement means output signal as a denominator and producing an actual slope signal, a slope determining generator means producing a predicted slope signal, and comparator means responsive to the ratio between the said actual slope signal and the said predicted slope signal and producing therefrom a navigation signal.

Claim 24

The slope tracker system for navigating aircraft as set forth in claim 20 and wherein limit means restricts the deceleration factor means output signal to Zero.

Claim 25

The slope tracker system for navigating aircraft as set forth in claim 20, wherein a rate of change means produces a ground speed output signal GS, means producing a predetermined minimum speed signal Fs, and operating means relating the Fs signal from the GS signal each according to its effect and producing said distance offset signal.

Claim 26

The slope tracker system for navigating aircraft as set forth in claim 20, wherein a rate of change means produces a ground speed output signal GS, mean producing a predetermined minimum speed signal Fs, and operating means relating the Fs signal from the GS signal each according to its effect and producing said distance offset signal, there being means restricting the said distance offset signal to Zero.

Claim 27

The slope tracker system for navigating aircraft as set forth in claim 20, wherein an altitude detecting means produces an altitude output signal A, and wherein the deceleration factor generator means includes a variable resistance having the speed change characteristics of the aircraft related to altitude, said variable resistance being varied in response to the said altitude output signal A.

Claim 28

The slope tracker system for navigating aircraft as set forth in claim 20, wherein an altitude detecting means produces an altitude output signal A, and wherein the deceleration factor generator means includes a variable resistance having the predetermined minimum speed characteristics of the aircraft related to altitude, said variable resistance being varied in response to said altitude output signal A.

Claim 29

The slope tracker system for navigating aircraft as set forth in claim 20, wherein a rate of change means produces a ground speed output signal Gs, and wherein the deceleration factor generator means includes a variable resistance having the deceleration characteristics of the aircraft related to ground speed, said variable resistance being varied in response to said ground speed output signal GS.

Claim 30

The slope tracker system for navigating aircraft as set forth in claim 20, wherein an altitude detecting means produces an altitude output signal A, and wherein the deceleration factor generator means includes a variable resistance having the cruise speed characteristics of the aircraft related to altitude, said variable resistance being varied in response to the said altitude output signal A.

Claim 31

The slope tracker system for navigating aircraft as set forth in claim 20, wherein an altitude detecting means produces an altitude output signal A, and wherein the deceleration factor generator means includes a variable resistance having the cruise speed characteristics of the aircraft related to altitude and a variable resistance having the predetermined minimum speed characteristics of the aircraft related to altitude, said variable resistance being varied in response to the said altitude output signal A.

Claim 32

The slope tracker system for navigating aircraft as set forth in claim 20, wherein an altitude detecting means produces an altitude output signal A, wherein a rate of change means produces a ground speed output signal GS, and wherein the deceleration factor generator means includes a variable resistance having the cruise speed characteristics of the aircraft related to altitude, a variable resistance having the predetermined minimum speed characteristics of aircraft related to altitude and a variable resistance having the deceleration characteristics of the aircraft related to ground speed, variable resistance related to altitude being varied in response to the said altitude output signal A and the variable resistance related to ground speed being varied in response to the said ground speed output signal GS.

Claim 33

An airborne slope tracker system for the navigation of aircraft along a slope to a predetermined waypoint, and including; an altitude detecting means producing an altitude output signal A, an altitude of the waypoint means producing a waypoint altitude output signal Aw, a Distance Measurement Equipment means producing a remaining distance to waypoint signal, a deceleration factor generator means producing a distance offset signal, a subtractor means responsive to the difference between the Distance Measurement Equipment means output signal and said distance offset signal and producing an output signal, an altitude displacement means differentiating between the altitude signal A and waypoint altitude signal Aw producing an altitude offset signal, a divider means utilizing the subtractor means output signal as a numerator and utilizing the altitude displacement means output signal as a denominator and producing an actual slope signal, a slope determining generator means producing a predicted slope signal, and comparator means responsive to the ratio between the said actual slope signal and the said predicted slope signal and producing therefrom a navigation signal.

Claim 34

An airborne slope tracker system for the navigation of aircraft along a slope to a predetermined waypoint, and including; an altitude detecting means producing an altitude output signal A, an altitude of the waypoint means producing a waypoint altitude output signal Aw, a Distance Measurement Equipment means producing a remaining distance to waypoint signal, a deceleration factor generator means producing a distance offset signal, a subtractor means responsive to the difference between the Distance Measurement Equipment means output signal and said distance offset signal and producing an output signal, an altitude displacement means differentiating between the altitude signal A and waypoint altitude signal Aw producing an altitude offset signal, a divider means utilizing the subtractor means output signal as a numerator and utilizing the altitude displacement means output signal as a denominator and producing an actual slope signal, a slope determining generator means producing a predicted slope signal, and comparator means responsive to the ratio between the said actual slope signal and the said predicted slope signal and producing therefrom a navigation signal.

Claim 35

The slope tracker system for navigating aircraft as set forth in claim 30, wherein the altitude displacement means subtracts the altitude of the waypoint signal Aw from the altitude signal A to produce a descent altitude offset signal.

Claim 36

The slope tracker system for navigating aircraft as set forth in claim 30, wherein the altitude displacement means subtracts the altitude signal A from the altitude of the waypoint signal Aw to produce an ascent altitude offset signal.

Claim 37

The slope tracker system for navigating aircraft as set forth in claim 30, wherein the altitude displacement means is a dual channel means with one channel that subtracts the altitude of the waypoint signal Aw from the altitude signal A to produce a descent altitude offset signal, and with a second channel that subtracts the altitude signal A from the altitude of the waypoint signal Aw to produce an ascent altitude offset signal, there being selector means directing the output signal of one of said channels to the said divider means.

Claim 38

The slope tracker system for navigating aircraft as set forth in claim 30, wherein the altitude displacement means subtracts the altitude of the waypoint signal from the altitude signal A to produce a descent altitude offset signal, and wherein limit means restricts the deceleration factor means output signal to Zero.

Claim 39

The slope tracker system for navigating aircraft as seT forth in claim 30, wherein the altitude displacement means subtracts the altitude signal A from the altitude of the waypoint signal Aw to produce an ascent altitude offset signal, and wherein limit means restricts the deceleration factor means output signal to Zero.

Claim 40

The slope tracker system for navigating aircraft as set forth in claim 30, wherein the altitude displacement means is a dual channel means with one channel that subtracts the altitude of the waypoint signal Aw from the altitude signal A to produce a descent altitude offset signal, and with a second channel that subtracts the altitude signal A from the altitude of the waypoint signal Aw to produce an ascent altitude offset signal, there being selector means directing the output signal of one of said channels to the said divider means, and wherein limit means restricts the deceleration factor means output signal to Zero.

Claim 41

The slope tracker system for navigating aircraft as set forth in claim 30, wherein the deceleration factor generator means includes a variable resistance having the speed characteristics of the aircraft related to altitude, said variable resistance being varied in response to the said altitude output signal A, and wherein the altitude displacement means subtracts the altitude of the waypoint signal Aw from the altitude output signal A to produce a descent altitude offset signal.

Claim 42

The slope tracker system for navigating aircraft as set forth in claim 30, wherein the deceleration factor generator means includes a variable resistance having the speed characteristics of the aircraft related to altitude, and wherein the altitude displacement means subtracts the altitude signal A from the altitude of the waypoint signal Aw to produce an ascent altitude offset signal.

Claim 43

The slope tracker system for navigating aircraft as set forth in claim 30, wherein the deceleration factor generator means includes a variable resistance having the speed characteristics of the aircraft related to altitude, and wherein the altitude displacement means is a dual channel means with one channel that subtracts the altitude of the waypoint signal Aw from the altitude and with a second channel that subtracts the altitude signal A from the altitude of the waypoint signal Aw to produce an ascent altitude offset signal, there being selector means directing the output signal of one of said channels to the said divider means.

Claim 44

The slope tracker system for navigating aircraft as set forth in claim 30, wherein the said remaining distance factor signal is modified by a deceleration factor generating means producing a modified distance offset signal varied by means responsive to aircraft altitude and speed, and wherein resolution means responsive to said modified distance offset signal adjusts the magnitude of the navigation signal inversely in proportion to the magnitude of said distance offset signal.