Weight and balance computer apparatus for aircraft

• US 4,110,605 A
• Filed: 02/25/1977
• Issued: 08/29/1978
• Est. Priority Date: 02/25/1977
• Status: Expired due to Term

• Current Assignee: Honeywell Incorporated (Honeywell International Inc.)
• Original Assignee: Sperry Rand Corporation (Unisys Corporation)
• Inventors: Miller, Harry
• Primary Examiner(s): Kunin, Stephen G.
• Application Number:
  US05/772,186
• Time in Patent Office: 550 Days
• Field of Search: 73/65, 73/178 R, 73/178 T, 235/150.2, 235/150.22, 235/150.21, 235/92 WT, 235/151.33, 235/197, 244/181-183, 340/27
• US Class Current: 701/124
• CPC Class Codes: G01G 19/07 for weighing aircraft
• CPC Class Codes: G01M 1/127 during the flight

Abstract

Aircraft weight and balance computer apparatus processes sensor outputs to generate an electrical signal that is proportional to aircraft gross weight at the time take-off thrust is initially applied to the aircraft on the runway and continually updates the weight signal when airborne to account for burn off of fuel or other weight loss and also provides a measure of the location of the aircraft center of gravity position. This is achieved by computing the aerodynamic forces on the aircraft in its longitudinal plane and the thrust generated by the engines and relating these computations to the corresponding acceleration components measured by a pair of linear accelerometers that are mounted orthogonally in this longitudinal plane.

Claims

1. Apparatus for providing a measure of the gross weight of an aircraft having engines for providing propelling thrust therefor comprising

a. means responsive to an operating characteristic of the engines for providing a measure of the thrust thereof,

b. means responsive to aerodynamic forces acting on said aircraft and said measure of thrust for providing a measure of a function of the angle of attack of said aircraft, and

c. means responsive to said angle of attack function measure for providing an output measure of the gross weight of said aircraft.

2. The apparatus as set forth in claim 1 wherein said engines are turbo-jet engines and said operating characteristic thereof is the engine pressure ratio.

3. The apparatus as set forth in claim 1 wherein said engines are turbo fan engines and said operating characteristic is the engine fan speed.

4. The apparatus as set forth in claim 1 wherein the thrust of said engines at a predetermined operating characteristic thereof vary as a predetermined function of the aircraft Mach number speed and altitude and wherein said thrust measure providing means comprises

a. means providing a signal proportional to said engine operating characteristic,

b. means providing signals respectively proportional to the aircraft Mach number speed and altitude, and

c. means responsive to said last mentioned signals for modifying said engine operating characteristic signal in accordance with said predetermined function to provie said measure of engine thrust.

5. The apparatus as set forth in claim 4 wherein said engine operating characteristic is its engine pressure ratio.

6. The apparatus as set forth in claim 4 wherein the means for varying said engine operating characteristic comprises computer means responsive to said engine pressure ratio signal and said Mach number and altitude signals for computing the value of a polynominal with Mach number and having variable coefficients which are a function of said engine operating characteristic, multiplied by a function of altitude.

7. The apparatus as set forth in claim 1 further comprising

a. means responsive to said aircraft gross weight measure and said thrust measure for providing a measure of the thrust-to-weight ratio of said aircraft, and

b. means supplying said thrust-to-weight measure to said function of angle of attack measure providing means.

8. The apparatus as set forth in claim 7 wherein said function of angle of attack measure varies as a predetermined function of normal and longitudinal accelerations of said aircraft relative to earth gravity and its thrust-to-weight ratio at a predetermined condition of aircraft control surfaces affecting the lift and drag thereof and its Mach number speed, said function of angle of attack measure providing means comprising

a. means providing a signal proportional to acceleration of said aircraft along its normal axis,

b. means providing a signal proportional to acceleration of said aircraft along its longitudinal axis,

c. means providing a signal proportional to the thrust-to-weight ratio of said craft,

d. means responsive to said acceleration signals and said thrust-to-weight ratio signal for providing a resultant signal proportional to said predetermined function thereof, and

e. means responsive to the position of said aircraft control surfaces and its Mach number speed for determining the value of said measure of said function of angle of attack for said control surfaces'"'"' position and Mach number speed.

9. The apparatus as set forth in claim 8 wherein the means for determining said measure of said function of angle of attack comprises computer means responsive to said acceleration, thrust-to-weight ratio, Mach number speed and said resultant signals for computing the value of K as a function J in accordance with the following equations:

##EQU35## wherein J = said resultant signal

a_x and a_z are the longitudinal and normal accelerations of the aircraft respectively

(T/W) = thrust-to-weight ratio of the aircraft

g = earth gravity acceleration,

wherein said control surface positions are

δ

_FL = aircraft flap-slat position and

i_H = horizontal stabilizer position

and wherein said function of angle of attack is of the form

space="preserve" listing-type="equation">K = C.sub.L cos α

+ C.sub.D sin α

wherein

K = measure of said angle of attack function

α

= angle of attack of the aircraft, and

C_l and C_D = coefficients of lift and drag, respectively of the aircraft.

10. The apparatus as set forth in claim 1 wherein said aircraft gross weight measure is a predetermined function of said function of angle of attack, aircraft normal acceleration and dynamic air pressure and wherein said gross weight measure providing means comprises

a. means responsive to said function of angle of attack measure for providing a signal in accordance therewith,

b. means for providing a signal proportional to normal acceleration of said aircraft,

c. means for providing a signal proportional to the dynamic pressure of said aircraft, and

d. means responsive to said angle of attack function signal, said normal acceleration signal and said dynamic pressure signal for providing a signal proportional to the gross weight of said aircraft.

11. The apparatus as set forth in claim 10 wherein said last mentioned means comprises computer means responsive to said signals for providing a signal proportional to weight as a function of said signals in accordance with the equation

12. The apparatus as set forth in claim 10 wherein said gross weight signal includes undesired high frequency components included in said angle of attack function signal, further including

a. means responsive to said gross weight signal for providing an output signal including only long term variations thereof

b. means responsive to said long term weight signal and said gross weight signal including said high frequency components for providing a weight error signal, and

c. means supplying said weight error signal to said weight measure providing means for reducing the effects of said high frequency components of said angle of attack measure in said aircraft gross weight signal.

13. The apparatus as set forth in claim 1 further including means providing an output measure of the take-off weight of said aircraft comprising

a. means for providing a measure of the longitudinal acceleration of said aircraft,

b. means responsive to said measure of the thrust of said aircraft and said longitudinal acceleration measure for providing a resultant measure of the take-off weight of the aircraft,

c. switch means for substituting said resultant take-off weight measure for said angle of attack function measure to said weight measure providing means, and

d. means responsive to a predetermined value of said engine operating characteristic for operating said switch means.

14. The apparatus as set forth in claim 13 wherein said aircraft is equipped with brakes on the landing gear wheels, said apparatus further including

a. means responsive to release of said brakes for providing a corresponding signal, and

b. logic means responsive to said predetermined value of said engine operating characteristic and said brake signal for operating said switch means.

15. The apparatus as set forth in claim 12 further including means providing an output measure of the take-off weight of the aircraft comprising

a. means for providing a measure of the longitudinal acceleration of the aircraft,

b. means responsive to said measure of thrust of said aircraft and said longitudinal acceleration measure for providing a resultant measure of the take-off weight of the aircraft.

c. first switch means for substituting said resultant take-off weight measure for said angle of attack function measure to said weight measure providing means,

d. second switch means for rendering said long term weight variation signal and said weight error signal ineffective and substituting thereofor the instantaneous value of said take-off weight signal, and

e. means responsive to a predetermined value of said engine operating characteristic for operating both first and second switch means.

16. The apparatus as set forth in claim 13 further including

a. timing means responsive to operation of said switch means for rendering said substitution of said take-off weight measure effective for only a short time period, on the order of one to five seconds, and for thereafter effectively clamping said take-off weight measure at the value then obtaining.

17. The apparatus as set forth in claim 16 further including:

a. Further switch means responsive to an airborne condition of said aircraft for reinstating said angle of attack function measure to said weight measure providing means.

18. The apparatus as set forth in claim 13 wherein said means for providing said resultant measure of take-off weight comprises computer means responsive to said measure of thrust and longitudinal acceleration for providing a measure proportional to take-off weight as a function of said signals in accordance with the equation ##EQU36## where W_TO = aircraft take-off weight

a_x = longitudinal acceleration of the aircraft

g = gravity acceleration

μ

_RL = rolling friction of the aircraft

19. Apparatus for providing a measure of the take-off weight of an aircraft comprising

a. means for providing a measure of an operating characteristic of the aircraft engines for providing a measure of the take-off thrust thereof,

b. means for providing a measure of the longitudinal acceleration of the aircraft,

c. means for providing a measure of the rolling friction of the aircraft,

d. means responsive to said measures for providing an output measure of the take-off weight of said aircraft as a predetermined function of said signals,

e. switch means for rendering said means responsive to said measures effective, and

f. means responsive to a predetermined value of said engine operating characteristic for operating said switch means.

20. The apparatus as set forth in claim 19 wherein said predetermined function is of the form ##EQU37## wherein W_TO = aircraft take-off weight

a_x = longitudinal acceleration of the aircraft

g = gravity acceleration

μ

_RL = rolling friction of the aircraft

21. The apparatus as set forth in claim 19 further including,

a. timing means responsive to the operation of said switch means for rendering said take-off weight measure providing means effective for only a short period of time, on the order of one to five seconds, and

b. means responsive to said timing means for effectively clamping said take-off weight measure at the value then obtaining.

22. Apparatus for providing a measure of the gross weight of an engine powered aircraft comprising

a. means responsive to an operating characteristic of each of the aircraft engines at the Mach number speed and static pressure environment of the aircraft for providing a signal corresponding to the thrust produced on the aircraft by each of the engines and means for summing all of said thrust signals for providing a resultant signal corresponding to the total thrust produced by all of the engines,

b. means responsive to accelerations of the aircraft along mutually perpendicualr axes corresponding to the vertical and longitudinal axes of the aircraft and for providing signals corresponding thereto,

c. means responsive to the Mach number speed of the aircraft and the static pressure environment of the aircraft for providing signals corresponding thereto,

d. means responsive to the positions of aerodynamic surfaces of the aircraft affecting the lift and drag characteristics thereof, and

e. computer means responsive to all of said signals for providing an output signal corresponding to the solution of the pair of equations ##EQU38## wherein W = the gross weight of the aircraft

T = the total thrust of the engines

a_x = longitudinal acceleration of the aircraft

a_z = normal acceleration of the aircraft

M = the Mach number speed of the aircraft

P_s = the static air pressure at the aircraft

α

= the angle of attack of the aircraft

C_l = the coefficient of lift of the aircraft

C_d = the coefficient of drag of the aircraft

S = the wing area of the aircraft

g = the gravity acceleration of the earth,

said output signal corresponding to the simultaneous solution of said equations for said gross weight term W.

23. Apparatus for providing a measure of the position of the center of gravity of an aircraft having a main sustaining wing, wing flags, horizontal stabilizer and elevator, relative to the mean aerodynamic chord of said wing comprising

a. means for providing a signal proportional to the effective position of the horizontal stabilizer in producing a pitching movement on said aircraft,

b. means for providing a signal proportional to a function of the horizontal and normal accelerations of the aircraft and the thrust-to-weight ratio of said aircraft, and

c. means responsive to said signals for providing a signal proportional to the position of the center of gravity of the aircraft about which said pitching moment is effective.

24. The apparatus as set forth in claim 23 wherein the means for providing said horizontal stabilizer effective position signal includes

a. means for providing a signal proportional to the position of said elevator,

b. means for providing a signal proportional to the actual position of said horizontal stabilizer,

c. means responsive to the Mach number speed of the aircraft for modifying said horizontal stabilizer position signal in accordance therewith,

d. means for combining said elevator position signal and said modified horizontal stabilizer position signal for providing said horizontal stabilizer effective position signal.

25. The apparatus as set forth in claim 24 further including

a. filter means having a relatively long time constant responsive to said center of gravity position signal for providing a signal proportional to average center of gravity position of said aircraft.

26. The apparatus as set forth in claim 25 further including

a. means responsive to the difference between said center of gravity position signal and said average center of gravity position signal for providing a center of gravity error signal proportional to the essentially short term components of said center of gravity position signal, and

b. means for feeding back said center of gravity error signal to said elevator signal and modified horizontal stabilizer signal combining means for compensating for the short term affects of said elevator on said horizontal stabilizer effective position signal.

27. The apparatus as set forth in claim 23 further including

a. means responsive to the Mach number speed of said aircraft above a predetermined value thereof for further modifying said effective stabilizer position signal in accordance therewith, and

b. means responsive to the position of said wing flaps below said predetermined value of Mach number speed for modifying said effective stabilizer position signal in accordance with said flap position signal.

28. The apparatus as set forth in claim 23 when said horizontal and normal acceleration and thrust-to-weight ratio function signal providing means comprises

a. means providing signals proportional respectively to the horizontal and normal accelerations of said aircraft,

b. means for providing a signal proportional to the thrust over weight ratio of said aircraft, and

c. computer means responsive to said signals for providing a signal J proportional to the function thereof defined by the equation ##EQU39##