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| {{About|devices used on ships|gyroscope used in aircraft|heading indicator}}
| | Got nothing to write about myself I think.<br>Yes! Im a part of wmflabs.org.<br>I really wish I'm useful in one way .<br><br>Review my web page: [https://independent.academia.edu/ClaudetteMorrell/Posts/3742005/You-may-feel-you-had-enough-of-listening-to-your-Rottweiler-barking-in-your-home-and-finding-ways-to clickers for dog training] |
| [[File:Kreiselkompass Schnitt Anschütz.jpg|thumb|Cutaway of an Anschütz gyrocompass]]
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| [[File:Algonquin gyro compass2.jpg|thumb|A gyrocompass repeater]]
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| A '''gyrocompass''' is a type of non-magnetic [[compass]] which is based on a fast-spinning disc and rotation of the [[Earth]] (or another planetary body if used elsewhere in the universe) to automatically find geographical [[Direction (geometry)|direction]]. Although one important component of a gyrocompass is a [[gyroscope]], these are not the same devices; a gyrocompass is built to use the effect of [[gyroscopic precession]], which is a distinctive aspect of the general [[gyroscopic effect]].<ref name=an>{{cite book|title=[http://books.google.com/books?id=VJ3WCpegQxwC The Anschutz Gyro-Compass and Gyroscope Engineering]|pages=7–24}}</ref><ref name=l>{{cite journal|title=The gyroscope pilots ships & planes |journal=Life|date=Mar 15, 1943 |pages=80–83|url=http://books.google.com/books?id=YlEEAAAAMBAJ&pg=PA82}}</ref> Gyrocompasses are widely used for [[navigation]] on [[ship]]s, because they have two significant advantages over [[magnetic compass]]es:<ref name=l/>
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| * they find [[true north]] as determined by [[Earth's rotation]], which is different from, and navigationally more useful than, [[Magnetic_North_Pole#Magnetic_north_and_magnetic_declination|''magnetic'' north]], and
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| * they are unaffected by [[ferromagnetic]] materials, such as ship's [[steel]] [[hull (watercraft)|hull]], which change the [[magnetic field]]
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| == Operation ==
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| A [[gyroscope]], not to be confused with gyrocompass, is a spinning wheel mounted on [[gimbal]] so that the wheel's axis is free to orient itself in any way.<ref name=l/> When it is spun up to speed with its axis pointing in some direction, due to the law of conservation of [[angular momentum]], such a wheel will normally maintain its original orientation to a fixed point in [[outer space]] (not to a fixed point on Earth). Since our planet rotates, it appears to a stationary observer on Earth that a gyroscope's axis is completing a full rotation once every 24 hours.<ref group=note>Although the effect is not visible in a specific case when the gyroscope's axis is precisely parallel to the Earth's rotational axis.</ref> Such a rotating gyroscope is used for navigation in some cases, for example on aircraft, where it is known as [[heading indicator]], but cannot ordinarily be used for long-term marine navigation. The crucial additional ingredient needed to turn such gyroscope into a gyrocompass, so it would automatically position to true north,<ref name=an/><ref name=l/> is some mechanism that results in an [[torque|application of torque]] whenever the compass's axis is not pointing north.
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| One method uses [[friction]] to apply the needed torque:<ref name="maritime.org">[http://www.maritime.org/fleetsub/elect/chap17.htm Gyrocompass, Auxiliary Gyrocompass, and Dead Reckoning Analyzing Indicator and Tracer Systems], San Francisco Maritime National Park Association.</ref> the gyroscope in a gyrocompass is not completely free to reorient itself; if for instance a device connected to the axis is immersed in a viscous fluid, then that fluid will resist reorientation of the axis. This friction force caused by the fluid results in a [[torque]] acting on the axis, causing the axis to turn in a direction orthogonal to the torque (that is, to [[precess]]) along a [[line of longitude]]. Once the axis points toward the celestial pole, it will appear to be stationary and won't experience any more frictional forces. This is because true north is the only direction for which the gyroscope can remain on the surface of the earth and not be required to change. This axis orientation is considered to be a point of minimum [[potential energy]].
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| Another, more practical, method is to use weights to force the axis of the compass to remain horizontal (perpendicular to the direction of the center of the Earth), but otherwise allow it to rotate freely within the horizontal plane.<ref name=an/><ref name=l/> In this case, gravity will apply a torque forcing the compass's axis toward true north. Because the weights will confine the compass's axis to be horizontal with respect to the Earth's surface, the axis can never align with the Earth's axis (except on the Equator) and must realign itself as the Earth rotates. But with respect to the Earth's surface, the compass will appear to be stationary and pointing along the Earth's surface toward the true North Pole.
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| Since the gyrocompass's north-seeking function depends on the rotation around the axis of the Earth that causes [[Gyroscopic_precession#Torque-induced|torque-induced gyroscopic precession]], it will not orient itself correctly to true north if it is moved very fast in an east to west direction, thus negating the Earth's rotation. However, aircraft commonly use [[Heading indicator|heading indicators or directional gyros]], which are not gyrocompasses and do not position themselves to north via precession, but are periodically aligned manually to true north.<ref>NASA [http://asrs.arc.nasa.gov/publications/callback/cb_304.htm NASA Callback: Heading for Trouble], NASA Callback Safety Bulletin website, December 2005, No. 305. Retrieved August 29, 2010.</ref><ref>Bowditch, Nathaniel. [http://books.google.com/books?id=M54M8qjxLQMC&pg=PA93 American Practical Navigator], Paradise Cay Publications, 2002, pp.93-94, ISBN 978-0-939837-54-0.</ref>
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| == Mathematical model of a gyrocompass ==
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| We will consider here a gyrocompass, as a gyroscope which is free to rotate about one of its symmetry axis, and the whole rotating gyroscope is also free to rotate on the horizontal plane, about the local vertical, the zenith. Therefore there are two independent local rotations. In addition to these rotations we will also consider the rotation of the Earth about its North-South (NS) axis, and we will model the planet as a perfect sphere. We will neglect friction and the rotation of the Earth about the Sun.
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| In this case a non-rotating observer located at the center of the Earth can be approximated as being an inertial frame. We can set cartesian coordinates <math>\textstyle (X_{1},Y_{1},Z_{1})</math> for such an observer (that we will name as 1-O), and the baricenter of the gyroscope will be located at a distance <math>R</math> from the center of the Earth.
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| === First time-dependent rotation ===
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| Let us consider another (non-inertial) observer (the 2-O) located at the center of the Earth but rotating about the NS-axis by <math>\textstyle\Omega</math>, then we set coordinates attached to the observer as
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| :<math>
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| \left(\begin{array}{c}
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| X_{2}\\
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| Y_{2}\\
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| Z_{2}
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| \end{array}\right)=\left(\begin{array}{ccc}
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| \cos\Omega t & \sin\Omega t & 0\\
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| -\sin\Omega t & \cos\Omega t & 0\\
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| 0 & 0 & 1
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| \end{array}\right)\left(\begin{array}{c}
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| X_{1}\\
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| Y_{1}\\
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| Z_{1}
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| \end{array}\right),
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| </math>
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| so that the unit <math>\hat{X}_{1}</math> versor <math>(X_{1}=1,Y_{1}=0,Z_{1}=0)^{T}</math> is mapped to the point <math>(X_{2}=\cos\Omega t,Y_{2}=-\sin\Omega t,Z_{2}=0)^{T}</math>. For the 2-O the Earth is not moving so as the baricenter of the gyroscope. The rotation of 2-O, according to 1-O, is performed with angular velocity <math>\vec{\Omega}=(0,0,\Omega)^{T}</math>. We will suppose that the <math>X_{2}</math> axis denotes points with zero longitude.
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| === Second and third fixed rotations ===
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| We will now rotate about the <math>\textstyle Z_{2}</math> axis, so that the <math>\textstyle X_{3}</math>-axis will have the longitude of the baricenter. In this case we have
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| :<math>\left(\begin{array}{c}
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| X_{3}\\
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| Y_{3}\\
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| Z_{3}
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| \end{array}\right)=\left(\begin{array}{ccc}
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| \cos\Phi & \sin\Phi & 0\\
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| -\sin\Phi & \cos\Phi & 0\\ | |
| 0 & 0 & 1
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| \end{array}\right)\left(\begin{array}{c}
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| X_{2}\\
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| Y_{2}\\
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| Z_{2}
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| \end{array}\right).</math>
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| With the next rotation (about the axis <math>\textstyle Y_{3}</math> of an angle <math>\textstyle \delta</math>, the co-latitude) we will bring the <math>\textstyle Z_{3}</math> axis along the local zenith (<math>\textstyle Z_{4}</math>-axis) of the baricenter. This can be achieved by the following orthogonal matrix (with unit determinant)
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| :<math>\left(\begin{array}{c}
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| X_{4}\\
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| Y_{4}\\
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| Z_{4}
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| \end{array}\right)=\left(\begin{array}{ccc}
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| \cos\delta & 0 & -\sin\delta\\
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| 0 & 1 & 0\\
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| \sin\delta & 0 & \cos\delta
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| \end{array}\right)\left(\begin{array}{c}
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| X_{3}\\
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| Y_{3}\\
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| Z_{3}
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| \end{array}\right),</math>
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| so that the <math>\textstyle\hat{Z}_{3}</math> versor <math>\textstyle (X_{3}=0,Y_{3}=0,Z_{3}=1)^{T}</math> is mapped to the point <math>\textstyle (X_{4}=-\sin\delta,Y_{4}=0,Z_{4}=\cos\delta)^{T}</math>.
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| === Constant translation ===
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| We now choose another coordinate basis whose origin is located at the baricenter of the gyroscope. This can be performed by the following translation along the zenith axis
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| :<math>\left(\begin{array}{c}
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| X_{5}\\
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| Y_{5}\\
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| Z_{5}
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| \end{array}\right)=\left(\begin{array}{c}
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| X_{4}\\
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| Y_{4}\\
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| Z_{4}
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| \end{array}\right)-\left(\begin{array}{c}
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| 0\\
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| 0\\
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| R
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| \end{array}\right)\,,</math>
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| so that the origin of the new system, <math>(X_{5}=0,Y_{5}=0,Z_{5}=0)^{T}</math> is located at the point <math>(X_{4}=0,Y_{4}=0,Z_{4}=R)^{T}</math>, and <math>R</math> is the radius of the Earth. Now the <math>X_{5}</math>-axis points towards the south direction.
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| === Forth time-dependent rotation ===
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| Now we rotate about the zenith <math>Z_{5}</math>-axis so that the new coordinate system is attached to the structure of the gyroscope, so that for an observer at rest in this coordinate system, the gyrocompass is only rotating about its own axis of symmetry. In this case we find
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| :<math>\left(\begin{array}{c}
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| X_{6}\\
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| Y_{6}\\
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| Z_{6}
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| \end{array}\right)=\left(\begin{array}{ccc}
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| \cos\alpha & \sin\alpha & 0\\
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| -\sin\alpha & \cos\alpha & 0\\
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| 0 & 0 & 1
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| \end{array}\right)\left(\begin{array}{c}
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| X_{5}\\
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| Y_{5}\\
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| Z_{5}
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| \end{array}\right).</math>
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| The axis of symmetry of the gyrocompass is now along the <math>X_{6}</math>-axis.
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| === Last time-dependent rotation ===
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| The last rotation is a rotation on the axis of symmetry of the gyroscope as in
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| :<math>\left(\begin{array}{c}
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| X_{7}\\
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| Y_{7}\\
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| Z_{7}
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| \end{array}\right)=\left(\begin{array}{ccc}
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| 1 & 0 & 0\\
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| 0 & \cos\psi & \sin\psi\\
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| 0 & -\sin\psi & \cos\psi
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| \end{array}\right)\left(\begin{array}{c}
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| X_{6}\\
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| Y_{6}\\
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| Z_{6}
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| \end{array}\right).</math>
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| === Dynamics of the system ===
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| Since the gyroscope is not moving the height of its baricenter (and the origin of the coordinate system is located at this same point), its gravitational potential energy is constant. Therefore its Lagrangian <math>\mathcal{L}</math> corresponds to its kinetic energy <math>K</math> only. We have
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| :<math>\mathcal{L}=K=\frac{1}{2}\,\vec{\omega}^{T}I\vec\omega\,,</math>
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| where the tensor of inertia is given by
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| :<math>I=\left(\begin{array}{ccc}
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| I_{1}&0&0\\
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| 0 & I_{2}&0\\
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| 0 &0 & I_{2}
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| \end{array}\right)\,,</math>
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| and
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| :<math>\begin{align}
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| \vec{\omega}&=\left(\begin{array}{ccc}
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| 1 & 0 & 0\\
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| 0 & \cos\psi & \sin\psi\\
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| 0 & -\sin\psi & \cos\psi
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| \end{array}\right)\left(\begin{array}{c}
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| \dot{\psi}\\
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| 0\\
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| 0
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| \end{array}\right)+\left(\begin{array}{ccc}
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| 1 & 0 & 0\\
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| 0 & \cos\psi & \sin\psi\\
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| 0 & -\sin\psi & \cos\psi
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| \end{array}\right)\left(\begin{array}{ccc}
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| \cos\alpha & \sin\alpha & 0\\
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| -\sin\alpha & \cos\alpha & 0\\
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| 0 & 0 & 1
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| \end{array}\right)\left(\begin{array}{c}
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| 0\\
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| 0\\
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| \dot{\alpha}
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| \end{array}\right)\\
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| &{}+\left(\begin{array}{ccc}
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| 1 & 0 & 0\\
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| 0 & \cos\psi & \sin\psi\\
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| 0 & -\sin\psi & \cos\psi
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| \end{array}\right)\left(\begin{array}{ccc}
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| \cos\alpha & \sin\alpha & 0\\
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| -\sin\alpha & \cos\alpha & 0\\
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| 0 & 0 & 1
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| \end{array}\right)\left(\begin{array}{ccc}
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| \cos\delta & 0 & -\sin\delta\\
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| 0 & 1 & 0\\
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| \sin\delta & 0 & \cos\delta
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| \end{array}\right)\left(\begin{array}{ccc}
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| \cos\Phi & \sin\Phi & 0\\
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| -\sin\Phi & \cos\Phi & 0\\
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| 0 & 0 & 1
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| \end{array}\right)\\
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| &{}\times\left(\begin{array}{ccc}
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| \cos\Omega t & \sin\Omega t & 0\\
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| -\sin\Omega t & \cos\Omega t & 0\\
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| 0 & 0 & 1
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| \end{array}\right)\left(\begin{array}{c}
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| 0\\
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| 0\\
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| \Omega
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| \end{array}\right)\\
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| &= \left(\begin{array}{c}
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| \dot{\psi}\\
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| 0\\
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| 0\\
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| \end{array}\right)+\left(\begin{array}{c}
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| 0\\
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| \dot{\alpha}\sin\psi\\
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| \dot{\alpha}\cos\psi
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| \end{array}\right)+\left(\begin{array}{c}
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| -\Omega\sin\delta\cos\alpha\\
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| \Omega(\sin\delta\sin\alpha\cos\psi+\cos\delta\sin\psi)\\
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| \Omega(-\sin\delta\sin\alpha\sin\psi+\cos\delta\cos\psi)
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| \end{array}\right).\end{align}</math>
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| Therefore we find
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| :<math>\begin{align}
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| \mathcal{L}&=\frac{1}{2}\,[I_{1}\omega_{1}^{2}+I_{2}(\omega_{2}^{2}+\omega_{3}^{2})]\\
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| &= \frac{1}{2}\, I_{1}(\dot{\psi}-\Omega\sin\delta\cos\alpha)^{2}
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| {}+\frac{1}{2}\, I_{2}\{[\dot{\alpha}\sin\psi+\Omega(\sin\delta\sin\alpha\cos\psi+\cos\delta\sin\psi)]^{2}
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| {}+[\dot{\alpha}\cos\psi+\Omega(-\sin\delta\sin\alpha\sin\psi+\cos\delta\cos\psi)]^{2}\}\\
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| &= \frac{1}{2}\, I_{1}(\dot{\psi}-\Omega\sin\delta\cos\alpha)^{2}+\frac{1}{2}\, I_{2}\{\dot{\alpha}^{2}+\Omega^{2}(\cos^{2}\delta+\sin^{2}\alpha\sin^{2}\delta)
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| {}+2\dot{\alpha}\Omega\cos\delta\}.
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| \end{align}</math>
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| The Lagrangian can be rewritten as
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| :<math>\mathcal{L}=\mathcal{L}_{1}+\frac{1}{2}\, I_{2}\Omega^{2}\cos^{2}\delta+\frac{d}{dt}(I_{2}\alpha\Omega\cos\delta)\,,</math>
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| where
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| :<math>\mathcal{L}_{1}=\frac{1}{2}\, I_{1}(\dot{\psi}-\Omega\sin\delta\cos\alpha)^{2}+\frac{1}{2}\, I_{2}\,(\dot{\alpha}^{2}+\Omega^{2}\sin^{2}\alpha\sin^{2}\delta)\,,</math>
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| is the part of the Lagrangian responsible for the dynamics of the system. Then, since <math>\partial \mathcal{L}_1/\partial\psi=0</math>, we find
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| :<math>L_{x}\equiv\frac{\partial \mathcal{L}_{1}}{\partial\dot{\psi}}=I_{1}(\dot{\psi}-\Omega\sin\delta\cos\alpha)=\mathrm{constant}.</math>
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| Since the angular momentum <math>\vec L</math> of the gyrocompass is given by <math>\vec L=I\vec\omega</math>, we see that the constant <math>L_x</math>, is the component of the angular momentum about the axis of symmetry. Furthermore, we find the equation of motion for the variable <math>\alpha</math> as
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| :<math>\frac{d}{dt}\!\left(\frac{\partial \mathcal{L}_{1}}{\partial\dot{\alpha}}\right)=\frac{\partial \mathcal{L}_{1}}{\partial\alpha}\,,</math>
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| or
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| :<math>\begin{align}
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| I_{2}\ddot{\alpha} &=I_{1}\Omega(\dot{\psi}-\Omega\sin\delta\cos\alpha)\sin\delta\sin\alpha+\frac{1}{2}\, I_{2}\,\Omega^{2}\sin^{2}\delta\sin2\alpha\\
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| &=L_{x}\Omega\sin\delta\sin\alpha+\frac{1}{2}\, I_{2}\,\Omega^{2}\sin^{2}\delta\sin2\alpha\,.\end{align}</math>
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| ==== Particular case: the poles ====
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| At the poles we find <math>\sin\delta=0</math>, and the equations of motion become
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| :<math>\begin{align}
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| L_{x} &=I_{1}\dot{\psi}=\mathrm{constant}\\
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| I_{2}\ddot{\alpha}&=0\,.\end{align}</math>
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| This simple solution implies that the gyroscope is uniformly rotating with constant angular velocity in both the vertical and symmetrical axis.
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| ==== The general and physically relevant case ====
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| Let us suppose, now that <math>\sin\delta\neq0</math>, and that <math>\alpha\approx0</math>, that is the axis of the gyroscope is approximately along the North-South line, and let us find the parameter space (if it exists), for which the system admits stable small oscillations about this same line. If this situation occurs, the gyroscope will be always approximately aligned along the North-South line, giving direction. In this case we find
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| :<math>\begin{align}
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| L_{x}&\approx I_{1}(\dot{\psi}-\Omega\sin\delta)\,,\\
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| I_{2}\ddot{\alpha}&\approx (L_{x}\Omega\sin\delta+I_{2}\,\Omega^{2}\sin^{2}\delta)\,\alpha\,.\end{align}</math>
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| Let us consider the case that
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| :<math>
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| L_{x}<0\,,</math>
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| and, further, we allow for fast gyro-rotations, that is
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| :<math>|\dot{\psi}|\gg\Omega\,.</math>
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| Therefore, for fast spinning rotations, <math>L_x<0</math> implies <math>\dot\psi<0</math>. In this case, the equations of motion further simplify to
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| :<math>\begin{align}
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| L_{x}&\approx -I_{1}|\dot{\psi}|\approx\mathrm{constant}\,,\\
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| I_{2}\ddot{\alpha}&\approx -I_{1}|\dot{\psi}|\Omega\sin\delta\,\alpha\,.\end{align}</math>
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| Therefore we find small oscillations about the North-South line, as <math>\alpha\approx A\sin(\tilde\omega t+B)</math>, where the angular velocity of this harmonic motion of the axis of symmetry of the gyrocompass about the North-South line is given by
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| :<math>\tilde\omega=\sqrt{\frac{I_{1}\sin\delta}{I_{2}}}\,\sqrt{|\dot{\psi}|\Omega}\,,</math>
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| which corresponds to a period for the oscillations given by
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| :<math>T=\frac{2\pi}{\sqrt{|\dot{\psi}|\Omega}}\,\sqrt{\frac{I_{2}}{I_{1}\sin\delta}}\,.</math>
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| Therefore <math>\tilde\omega</math> is proportional to the geometric mean of the Earth and spinning angular velocities. In order to have small oscillations we have required <math>\dot{\psi}<0</math>, so that the North is located along the right-hand-rule direction of the spinning axis, that is along the negative direction of the <math>X_7</math>-axis, the axis of symmetry. As a side result, on measuring <math>T</math> (and knowing <math>\dot{\psi}</math>), one can deduce the local colatitude <math>\delta</math>.
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| == History ==
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| The first, not yet practical,<ref name=hee>{{cite book|pages=34–37|url=http://books.google.com/books?id=DN-9m2jSo8YC&pg=PA37|title=How experiments end|isbn=9780226279152|author1=Galison|first1=Peter|year=1987}}</ref> form of gyrocompass was patented in 1885 by Marinus Gerardus van den Bos.<ref name=hee/> Usable gyrocompass was invented in 1906 in Germany by [[Hermann Anschütz-Kaempfe]], and after successful tests in 1908 became widely used in German Imperial Navy.<ref name=an/><ref name=hee/><ref>http://downloads.german-pavilion.com/downloads/pdf/exhibitor_24199.pdf Standard 22
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| Anschütz Gyro Compass <nowiki>[sic]</nowiki> System: Gyro Compass <nowiki>[sic]</nowiki> Technology <nowiki>[sic]</nowiki> for over than <nowiki>[sic]</nowiki> 100 years</ref>
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| The gyrocompass was an important invention for nautical navigation because it allowed accurate determination of a vessel’s location at all times regardless of the vessel’s motion, the weather and the amount of steel used in the construction of the ship.<ref name="maritime.org"/> In the United States, [[Elmer Ambrose Sperry]] produced a workable gyrocompass system (1908: patent #1,242,065), and founded the [[Sperry Corporation|Sperry Gyroscope Company]]. The unit was adopted by the U.S. Navy (1911<ref name=l/>), and played a major role in World War I. The Navy also began using Sperry's "Metal Mike": the first gyroscope-guided autopilot steering system. In the following decades, these and other Sperry devices were adopted by steamships such as the [[RMS Queen Mary]], airplanes, and the warships of World War II. After his death in 1930, the Navy named the [[USS Sperry]] after him.
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| Meanwhile, in 1913, C. Plath (a Hamburg, Germany-based manufacturer of navigational equipment including sextants and magnetic compasses) developed the first gyrocompass to be installed on a commercial vessel. C. Plath sold many gyrocompasses to the Weems’ School for Navigation in Annapolis, MD, and soon the founders of each organization formed an alliance and became Weems & Plath.<ref>[http://www.weems-plath.com/weems-and-plath-story.php The Invention of Precision Navigational Instruments for Air and Sea Navigation], Weems & Plath.</ref>
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| [[File:1889 Gymnote Gyroscope.jpg|thumb|The 1889 Dumoulin-Krebs gyroscope]]
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| Before the success of gyrocompass, several attempts had been made in Europe to use gyroscope instead. By 1880, [[William Thomson]] (lord Kelvin) tried to propose a gyrostat (tope) to the British Navy. In 1889, [[Arthur Krebs]] adapted an electric motor to the Dumoulin-Froment marine gyroscope, for the French Navy. Giving the ''Gymnote'' submarine the ability to keep a straight line under water during several hours, it allowed her to [http://rbmn.free.fr/Gymnote_Blocus_1890.jpg force a naval block] in 1890.
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| == Errors ==
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| A gyrocompass is subject to certain errors. These include streaming error, where rapid changes in course, speed and [[latitude]] cause [[Magnetic deviation|deviation]] before the gyro can adjust itself.<ref>[http://www.navis.gr/navaids/gyro.htm Gyrocompass: Steaming Error], Navis. Accessed 15 December 2008.</ref> On most modern ships the [[GPS]] or other navigational aids feed data to the gyrocompass allowing a small computer to apply a correction. Alternatively a design based on an orthogonal triad of [[fibre optic gyroscope]] or [[ring laser gyroscope]]s will eliminate these errors, as they depend upon no mechanical parts, instead using the principles of [[optical path length|optical path difference]] to determine rate of rotation.<ref name="House">Seamanship Techniques:Shipboard and Marine Operations, D. J. House, Butterworth-Heinemann, 2004, p. 341</ref>
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| == Patents ==
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| * {{US patent|1279471}} : "Gyroscopic compass" by [[Elmer Ambrose Sperry|E. A. Sperry]], filed June, 1911; issued September, 1918
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| == See also ==
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| * [[Acronyms and abbreviations in avionics]]
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| * [[Heading indicator]], also known as direction indicator, a lightweight gyroscope (not a gyrocompass) used on aircraft
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| * [[Fluxgate compass]]
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| * [[Fibre optic gyrocompass]]
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| * [[Inertial navigation system]], a more complex system that also incorporates accelerometers
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| * [[Schuler tuning]]
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| == Notes ==
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| {{Reflist|group=note}}
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| == References ==
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| {{Reflist}}
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| == Bibliography ==
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| * {{Cite journal | title = Albert Einstein's expert opinions on the Sperry vs. Anschütz gyrocompass patent dispute | last = Trainer | first = Matthew | url = http://202.114.89.60/resource/pdf/1317.pdf | doi = 10.1016/j.wpi.2008.05.003 | year = 2008 | journal = World Patent Information | volume = 30 | pages = 320 | issue = 4}}
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| == External links ==
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| * [http://fi.edu/case_files/sperry_2524/ Elmer A. Sperry case file] at the [[Franklin Institute]] contains records concerning his 1914 Franklin Award for the gyroscopic compass
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| * [http://imperialclub.com/Yr/1945/45Impossible/Cover.htm "A Job Thought Impossible"], the story of Chrysler Corporation's mass-production of previously hand-made gyrocompasses for World War II naval requirements.
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| * [http://www.globmaritime.com/martech/marine-navigation/compasses/2840-errors-of-the-gyrocompass Errors of the Gyrocompass]
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| * [http://www.globmaritime.com/martech/marine-navigation/compasses/9918-using-the-gyrocompass Using the Gyrocompass]
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| * [http://www.sonardyne.com/products/inertial-navigation/lodestar-ahrs.html Ring Laser Gyrocompass manufactured by Sonardyne]
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| [[Category:1908 introductions]]
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| [[Category:Navigational equipment]]
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| [[Category:Avionics]]
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| [[Category:Aircraft instruments]]
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| [[Category:German inventions]]
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