Determining liquid fill fraction on a spacecraft

• US 5,383,359 A
• Filed: 12/02/1992
• Issued: 01/24/1995
• Est. Priority Date: 12/02/1992
• Status: Expired due to Fees

• Current Assignee: Hughes Electronics Corporation (Rtx Corporation)
• Original Assignee: Hughes Aircraft Company (Rtx Corporation)
• Inventors: Or, Arthur C., Challoner, A. Dorian
• Primary Examiner(s): GUTIERREZ, DIEGO F
• Application Number:
  US07/984,146
• Time in Patent Office: 783 Days
• Field of Search: 73/290 R, 73/291, 364/509, 364/564, 340/870.16, 340/618
• US Class Current: 73/290.00R
• CPC Class Codes: B64G 1/402 Propellant tanks; Feeding propellants
• CPC Class Codes: G01F 23/00 Indicating or measuring liquid level or level of fluent solid material, e.g. indicating in terms of volume or indicating by means of an alarm
• CPC Class Codes: G01F 23/22 by measuring physical variables, other than linear dimensions, pressure or weight, dependent on the level to be measured, e.g. by difference of heat transfer of steam or water involving the use of floats G01F23/30
• CPC Class Codes: G01F 23/2966 making use of acoustical resonance or standing waves

Abstract

A method and apparatus of determining the fill fraction of a liquid in a spacecraft in weightless space is disclosed. A small motion is introduced about the center of mass of the spacecraft undergoing steady spin and/or thrust, and resulting spacecraft oscillations are sensed. The measured frequency, amplitude and phase of the spacecraft oscillations are compared with counterpart values predicted for possible liquid quantities by a nonempirically computed model of spacecraft dynamics.

Claims

1. An apparatus for determining the volume of a liquid contained within at least two rigid tanks disposed within a spacecraft, the tanks revolving about an axis about which they are rigidly and axisymmetrically disposed, the apparatus comprising:

predicting means for nonempirically predicting, for a number of possible quantities of liquid in the tanks, frequency, amplitude and phase oscillatory constituents of the spacecraft resulting from a small acceleration about its equilibrium position;

actuating means for applying force or torque to the spacecraft to produce the relatively small acceleration;

measuring means for measuring frequency, amplitude and phase oscillatory constituents resulting from the relatively small acceleration of the spacecraft; and

comparing means for comparing the predicted frequency, amplitude and phase oscillatory constituents with those measured, a match thereby identifying the quantity of liquid in said tanks.

2. The apparatus as defined by claim 1, further including sun sensing means disposed on the spacecraft for sensing the presence of sunlight and generating a spin frequency reference signal representative of the rate of revolution of said tanks.

3. The apparatus as defined by claim 2, wherein said tanks are revolving about the axis at an angular velocity within a range of 45 to 65 revolutions per minute.

4. The apparatus as defined by claim 2, wherein the predicting means includes a computer that nonempirically computes, according to a computed model of spacecraft dynamics and for said number of possible quantities of liquid in said tanks, said predicted frequency, amplitude and phase oscillatory constituents generated by the relatively small acceleration about the equilibrium position of the spacecraft.

5. The apparatus as defined by claim 4, wherein said actuating means includes means disposed on the spacecraft for releasing, under the influence of tank pressure and in a direction parallel to the axis, a controlled amount of liquid stored in said tanks.

6. The apparatus as defined by claim 5, wherein the measuring means includes an accelerometer disposed on the spacecraft for measuring said measured frequency, amplitude and phase oscillatory constituents resulting from the acceleration of said tanks and generating an oscillation signal representative thereof.

7. The apparatus as defined by claim 6, wherein the accelerometer has a resolution limit less than 1 micro-g, a sensitivity in the range of 3 to 10 volts per g, and a bandwidth of 0 to 60 Hertz.

8. The apparatus as defined by claim 6, further including analyzing means for analyzing the oscillation signal to determine the measured frequency, amplitude and phase oscillatory constituents represented by the oscillation signal.

9. The apparatus as defined by claim 8, wherein the analyzing means includes a dynamic signal analyzer.

10. The apparatus as defined by claim 9, wherein the dynamic signal analyzer has a dynamic range from 60 to 100 decibels;

estimates the linear spectrum of acquired data over a 2.5 Hertz bandwidth with a resolution of 800 lines; and

has an accuracy of estimated frequency determination of ±

0.1 percent with typical slosh damping in the range of 0.5 percent of critical.

11. The apparatus as defined by claim 8, wherein said computer includes said comparing means for comparing the measured frequency, amplitude and phase oscillatory constituents represented by the oscillation signal with those predicted and generating a signal representative of the quantity of liquid associated with the predicted frequency, amplitude and phase oscillatory constituents that match those measured.

12. The apparatus as defined by claim 11, further comprising:

a spacecraft telemetry system for receiving the oscillation signal and the spin frequency reference signal and generating in response thereto a composite telemetry downlink signal; and

a ground station telemetry system for receiving the composite telemetry downlink signal and generating in response thereto a composite downconverted signal.

13. The apparatus as defined by claim 12, further including a sharp, low-pass filter for filtering the composite downconverted signal from the ground station telemetry system and communicating it to the dynamic signal analyzer.

14. The apparatus as defined by claim 13, wherein the sharp, low-pass filter has a cutoff frequency of 2.5 Hertz.

15. A method for determining the volume of a liquid contained within at least one pair of rigid tanks disposed within a spacecraft, the tanks revolving about an axis about which they are rigidly and axisymmetrically disposed, the method comprising the steps of;

predicting nonempirically, for a number of possible quantities of liquid in the tanks, frequency, amplitude and phase oscillatory constituents of the spacecraft to a small acceleration about its equilibrium position;

applying a force to the spacecraft to produce the relatively small acceleration thereof;

measuring frequency, amplitude and phase oscillatory constituents resulting from the relatively small acceleration of the spacecraft; and

comparing the predicted frequency, amplitude and phase oscillatory constituents with those measured, a match thereby identifying the quantity of liquid in the tanks.

16. The method as defined by claim 15, further including the step of generating an oscillation signal representative of the measured frequency, amplitude and phase oscillatory constituents.

17. The method as defined by claim 16, further including the step of analyzing the oscillation signal to determine the measured frequency, amplitude and phase oscillatory constituents represented by the oscillation signal.

18. The method as defined by claim 17, further including the step of generating a fill fraction signal representative of the quantity of liquid associated with the predicted frequency, amplitude and phase oscillatory constituents that match those measured.