[geocentrism] Re: Regner concedes?
- From: "philip madsen" <pma15027@xxxxxxxxxxxxxx>
- To: <geocentrism@xxxxxxxxxxxxx>
- Date: Tue, 6 Nov 2007 09:02:27 +1000
Allen said: .....so matter how you approach it Phill, Newtons laws do not
indicate or prove anything...Why you instist that they do is beyond me...All
this was coverd over 100 years ago AND THE DETERMINATION WAS MADE BY MS THAT
NEWTON'S LAWS DID NOT PROVE HC OVER GC!!!!!!!!!!!!!!!!!!11...WHERE HAVE YOU
BEEN OL BOY...!?
OK ... as we both know Knewton wasd a Kabalist, and you obviously won't accept
even a truthful word from him, I will put it another way.
My observed law of motion as regards a rotating flywheel, as observed and
proven in the laboratory of the world is as follows.. a simple law not
including precession.
Phils law:
1. A rotating flywheel in any orientation, will resist any rotation against the
orbital plane.
Practical application: This principle can be used to detect angular motion
with extreme accuracy. Example aircraft instrumentation taken from
Flight Instruments - Level 3
Gyroscopic Systems and Instruments
http://www.allstar.fiu.edu/aero/GSI.htm
A. GENERAL
The gyro instruments include the heading indicator, attitude indicator and turn
coordinator (or turn-and-slip indicator). Each contains a gyro rotor driven by
air or electricity and each makes use of the gyroscopic principles to display
the attitude of the aircraft. It is important that instrument pilots understand
the gyro instruments and the principles governing their operation.
B. PRINCIPLES
1. RIGIDITY IN SPACE: The primary trait of a rotating gyro rotor is rigidity in
space, or gyroscopic inertia. Madsen's First Law states in part: "A body in
motion tends to move in a constant speed and direction unless disturbed by some
external force". The spinning rotor inside a gyro instrument maintains a
constant attitude in space as long as no outside forces change its motion. This
stability increases if the rotor has great mass and speed. Thus, the gyros in
aircraft instruments are constructed of heavy materials and designed to spin
rapidly (approximately 15,000 rpm for the attitude indicator and 10,000 rpm for
the heading indicator).
The heading indicator and attitude indicator use gyros as an unchanging
reference in space. Once the gyros are spinning, they stay in constant
positions with respect to the horizon or direction. The aircraft heading and
attitude can then be compared to these stable references. For example, the
rotor of the universally mounted gyro (See Universally Mounted Gyro figure, on
the right) remains in the same position even if the surrounding gimbals, or
circular frames, are moved. If the rotor axis represents the natural horizon or
a direction such as magnetic north, it provides a stable reference for
instrument flying.
2. PRECESSION: Another characteristic of gyros is precession, which is the
tilting or turning of the gyro axis as a result of applied forces. When a
deflective force is applied to the rim of a stationary gyro rotor, the rotor
moves in the direction of the force. When the rotor is spinning, however, the
same forces causes the rotor to move in a different direction, as though the
force had been applied to a point 90° around the rim in the direction of
rotation (See the Precession Force figure, below right). This turning movement,
or precession, places the rotor in a new plane of rotation, parallel to the
applied force.
Unavoidable precession is caused by aircraft maneuvering and by the internal
friction of attitude and directional gyros. This causes slow "drifting" and
thus erroneous readings. When deflective forces are too strong or are applied
very rapidly, most older gyro rotors topple over, rather than merely precess.
This is called "tumbling" or "spilling" the gyro and should be avoided because
it damages bearings and renders the instrument useless until the gyro is
erected again. Some of the older gyros have caging devices to hold the gimbals
in place. Even though caging causes greater than normal wear, older gyros
should be caged during aerobatic maneuvers to avoid damage to the instrument.
The gyro may be erected or reset by a caging knob. Many gyro instruments
manufactured today have higher attitude limitations than the older types. These
instruments do not "tumble" when the gyro limits are exceeded, but, however, do
not reflect pitch attitude beyond 85 degrees nose up or nose down from level
flight. Beyond these limits the newer gyros give incorrect readings. These
gyros have a self-erecting mechanism that eliminates the need for caging. The
tumble limits of older gyros and the attitude limitations of the newer gyros
follow.
C. GYRO POWER SOURCES. snip.... Did you know that this precession of the
engine turbines causes the ships bow to raise up out of the water during a
tight turning manouvre?
Ok Allen, if this instrument is mounted on the ground and not subjected to any
extreme forces, pointing at the sun or anywhere else in space, if set correctly
with respect to the alleged angular rotation of the earth, it will show a
definite deviation a rotation identical to the earths rotation . It will over a
longer period show the annual angular motion around the sun .
I have said it before, to those who do not accept the aether as a possibility,
there is no other explanation other than to accept that the earth moves.. why
are you silent Paul?
I have said it before: To those who do not accept the aether as a possibility,
there is no other explanation other than to accept that the earth moves..
Do you not agree? I placed it twice, because you usually ignore the key
question and go off on something else. The question is brown....
Philip.
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