Pendulous induction compass transmitter including means external to the transmitter to compensate for heading errors in turns due to the vertical component of the Earth's magnetic field and due to two cycle error

• US 4,112,754 A
• Filed: 12/20/1976
• Issued: 09/12/1978
• Est. Priority Date: 12/20/1976
• Status: Expired due to Term

• Current Assignee: Ametek Aerospace Products, Inc. (Ametek Incorporated)
• Original Assignee: John Suminsby
• Inventors: Suminsby, John
• Primary Examiner(s): Kunin, Stephen G.
• Application Number:
  US05/752,278
• Time in Patent Office: 631 Days
• Field of Search: 33/326, 33/356, 33/357, 33/361, 73/178 R, 235/150.25, 235/150.26, 235/186, 244/175, 244/179, 318/629, 318/633, 318/647, 318/654, 318/661, 340/197, 340/347 SY, 324/43 R, 324/47
• US Class Current: 73/178.00R
• CPC Class Codes: G01C 17/30 Earth-inductor compasses

Abstract

The invention relates to an apparatus for compensating the output signals from a pendulous induction compass transmitter to eliminate heading errors during turns due to the vertical component of the Earth'"'"'s magnetic field as well as those due to the horizontal component of the Earth'"'"'s magnetic field perpendicular to the axis of tilt, i.e., two cycle error. By compensating for the effect of Earth'"'"'s vertical field component, instabilities and anomalies such as "Northerly Turning Error" are eliminated or minimized. Compensation for vertical field error is achieved by generating a signal proportional to the product of the Earth'"'"'s magnetic field M, the sine of the magnetic dip angle D at the given latitude and longitude and the sine of the aircraft bank or roll angle φ. This signal is combined (by summation) with the demodulated signal from the sin ψ channel (i.e., the signal from the windings of the compass transmitter which senses the field along the athwartships axis) to cancel vertical error. Similarly, a signal proportional to the cosine of the aircraft bank or roll angle φ is generated and combined with the corrected DC signal from the compass transmitter to cancel two cycle error. Since the magnitude of the bank angle φ or its trigonometric functions, i.e., sin φ and cos φ, can readily be obtained from the aircraft vertical gyroscope and the dip angle D is known for any latitude and longitude, these two compensating signals can easily be generated and applied to the output signal processing channels from the compass transmitter to cancel the effects of vertical field error and two cycle error during a turn.

Claims

1. In a pendulous induction compass transmitter compensated for errors due to the Earth'"'"'s vertical field during turns, the combination comprising:

a. magnetic sensing means for producing modulated signals proportional to the strength of the Earth'"'"'s field along the fore/aft and athwartships axes of an aircraft;

b. means to demodulate the modulated signal representative of the sensed fore/aft field to produce a varying, DC, demodulated signal proportional to the sensed Earth'"'"'s field along the fore/aft axis of the aircraft and thus to the cosine of the magnetic heading angle ψ and

of the aircraft;

c. means to demodulate the modulated signal representative of the sensed athwartships field to produce a varying, DC, demodulated signal proportional to the sensed Earth'"'"'s field along the athwartships axis of the aircraft and thus to the sine of the magnetic heading angle ψ

of the aircraft;

d. means to compensate the demodulated signals for errors due to the Earth'"'"'s vertical field during turns, including;

1. means to generate a DC correction signal proportional to the product of the Earth'"'"'s magnetic field M, the sine of the magnetic dip angle D and the sine of the bank angle φ

,

2. means to add said DC correcting signal algebraically to said demodulated DC signal proportional to the Earth'"'"'s field and thus to the sine of the magnetic heading angle ψ

to cancel the signal component due to the Earth'"'"'s vertical field sensed along the athwartships axis during turns.

2. The pendulous induction compass transmitter according to claim 1 wherein said magnetic sensing means produces three phase output signals representative of the sensed field along the respective axes and includes means for converting the three phase output signals from said magnetic sensing means to a pair of signals representative of the product of the Earth'"'"'s magnetic field and the sine and cosine of the magnetic heading angle ψ

respectively.

3. The pendulous induction compass transmitter according to claim 2 wherein said means for converting includes a Scott-Tee transformer having a three phase input to which the three phase signals from the magnetic sensing means are coupled and a two phase output coupled to the said demodulating means.

4. The pendulous induction compass transmitter according to claim 1 including further means to compensate for two cycle error comprising

a. first and second closed loop, null balanced modulating means each having an input and an output and the compensated demodulated DC signals coupled thereto, each of said modulating means including a negative feedback path from its output to its input,

b. demodulating means in each of said negative feedback paths,

c. means to reduce the negative feedback in one of said paths by a factor proportional to the cosine of the bank angle φ

whereby the output signal of the modulator associated with the said one negative feedback path is increased correspondingly to cancel two cycle error during turns.

5. The pendulous induction compass transmitter according to claim 4 wherein said means to reduce the negative feedback in said one path includes;

1. multiplying means in said path and,

2. means to apply the output signal from the associated modulating means and a signal proportional to the cosine of the bank angle φ

during a turn to said multiplier to reduce the feedback by the cosine of bank angle φ

.