Various descriptions of gyrocompasses that I can find (such as the Wikipedia article) claim that the compass will seek to align itself with the earth's rotational axis.

I think I can understand how that works if we place the compass on the ground, at rest with respect to the surface. Then the entire compass housing changes direction in space at a steady 15 degrees per hour, and it makes sense that one can use gyroscopic torques to sense the axis of that rotation and align a readout with it.

However, gyrocompasses are not usually employed at rest on the ground -- they're used on ships and aircraft. That's a moving, rolling, pitching, platform. Ships roll on the waves. Aircraft roll to maneuver, and pitch up and down to modulate lift -- all much more violently than the rate of the earth's rotation. How does a gyrocompass manage to pick out the slow overlaid rotation of the earth out from all that noise, accurately enough to be of any use for navigation?

In a (relatively slow-moving) ship I suppose you can put the compass close to the center of the rolling motion and use an outer set of weighted gimbals to keep one axis pointing straight down. But that won't work in an aircraft which moves so fast that the lateral accelerations while turning displace the direction of "down" (as measured by an onboard plumb line or accelerometer) by tens of degrees -- which again seems to drown out any hope of detecting the rotation of the earth.

The aircraft's orientation in space isn't even tied to the earth's rotation on average; you can fly it to the other side of the planet in about one planetary revolution's time.

Is there some additional effect at work here? Newtonian gravity and mechanics don't appear to offer anything the the moving compass could hang on to.

  • $\begingroup$ It won't attempt to align itself with the Earth's rotational axis: it will seek to keep itself pointing in the same direction, whatever that direction is, due to conservation of angular momentum. If it is suitably isolated (by gimbals) then it will just keep pointing in the same direction. $\endgroup$
    – user107153
    Aug 12, 2017 at 11:04
  • $\begingroup$ @tfb: No, that is what the Wikipedia article describes as a "directional gyro", which is explicitly different from a gyrocompass. $\endgroup$ Aug 12, 2017 at 11:05
  • $\begingroup$ Doh, yes. Sorry. $\endgroup$
    – user107153
    Aug 12, 2017 at 11:07
  • $\begingroup$ You might get better answers on engineering.stackexchange. $\endgroup$
    – user154997
    Aug 12, 2017 at 13:04

2 Answers 2


Here's what I get from the sources that David (+1) pointed to:


One of David's references describes a true gyrocompass for use aboard ships. It deals with short-period "noise" from rolling and pitching by averaging them out. It uses (essentially) two nested sets of gimbals with different damping constants to filter the motion of the compass mount to remove the high-frequency components from rolling and pitching (which start at several mHz), leaving the 11.6 μHz component from the earth's rotation.

Since the frequency difference between noise and signal is about three orders of magnitude it really shouldn't have surprised me that it is simple to filter out.

Apart from that: It doesn't!

The ship's gyrocompass cannot automatically compensate for changes in the ship's absolute orientation caused by sailing to a different place on the earth's surface. It needs to be explicitly told the latitude and its time derivative so it can correct for the influence of Coriolis forces on the apparent direction of gravity.

(Actually, the gyrocompass in the reference just gets told the speed of the ship, presumed to travel in the direction the compass itself shows, but that's enough to derive the N/S velocity component).

In more modern systems these inputs can probably come automatically from a GPS unit.

Aircraft gyrocompasses?

The other of David's reference is a 1960 instructional film on aircraft instruments. What it describes are not gyrocompasses, but mere directional gyros. They're used (from a high-level point of view) as short term directional standards for filtering out short-period noise from an on-board magnetic compass.

A gyrocompass designed for ships would probably not work in an airplane. In contrast to a ship, a plane routinely undergoes significant horizontal accelerations that won't average out when integrated relative to the airframe -- e.g. in a racetrack holding pattern.

On the other hand, modern solid state or fiber-optic directional gyros are apparently precise enough that they won't drift significantly before the plane needs to land for refueling anyway. Once the plane is known to be stationary on the ground, the true north direction can be calibrated using the gyrocompass principle. (Wikipedia also mentions that some inertial navigation systems can bootstrap themselves in flight based on GPS position fixes).


I had the same question and found the following 2 resources very useful:

  1. https://www.youtube.com/watch?v=JnKloSdUJLo.

This video talks about:

a) how a free mounted gyro can be used for attitude indication (roll, pitch) by using it's rigidity in space property.

b) It also discusses how the second property of a gyro (precession) can be used for rate of turn (yaw) indication.

c) Finally (and more related to your question) it discusses 2 gyrocompass systems:

The C-1 system uses a free mounted gyro but has important limitations, including having no drift compensation and so has to be periodically adjusted using a magnetic compass as reference.

The second system (MA-1) overcomes this problem by providing an electronic system that continuously tracks the error between the compass and the gyro, adjusting it's heading accordingly. Also, the short term small oscillations of the magnetic needle are effectively filtered out due to the gyro rigidity in space which tends to align to the average of these oscillations.

  1. http://ed-thelen.org/SperryManual-05.pdf

This is the manual of the Sperry Gyrocompass (mentioned in the Wikipedia article). It goes into great detail on the gyro properties and how the North seeking function is achieved, with wonderful illustrations.

  • $\begingroup$ It's not clear that what you have here answers the question. The essential elements of the answer should be here, not at the links. Links that provide further detail, definitely great. $\endgroup$
    – Brick
    Sep 12, 2018 at 19:28
  • $\begingroup$ In the first case the gyro is free mounted so it maintains it's orientation (since no torque can be imposed on it). The Earth's rotation will cause a long term drift in the gyro which needs to be continuously corrected using a magnetic compass as reference. So in reply to the question, the Earth's rotation is the only change than can be detected because the gyro is free mounted and hence does not respond to any change in the aircraft's attitude. In the Sperry gyro there is no magnetic compass. A torque is induced by the 'mercury ballistic' which causes the North-seeking function (precession). $\endgroup$
    – David
    Sep 12, 2018 at 22:30

Your Answer

By clicking “Post Your Answer”, you agree to our terms of service, privacy policy and cookie policy

Not the answer you're looking for? Browse other questions tagged or ask your own question.