by the anode connection of plates with each other. This makes packaging of elements
easier and allows using gas attenuation in the sensing element.
Gravimeter is made with two channels, each of which contains one capacitive
element in CG1 and CG2. They are identical and are fabricated in the form of two
metallic movable and immovable plates separated by a dielectric, and two identical
inertial masses m
1
and m
2
, attached to two moving plates CG1 and CG2. The outputs
of capacitive elements CG1 and CG2 of both channels are connected to the input of the
adder. The latter is connected to the input of the amplifier with additionally introduced
protective ring whose output is connected through the digital module with the onboard
computer (OC) input that computes the output signal of gravitational anomaly Δg. The
connection of the adder, amplifier, digital module and OC in series is carried out using
shielded coaxial cables to provide improved accuracy for measuring the anomalies in
the acceleration of gravity.
The output electrical signals of capacitive elements of both channels enter the
adder's input. The resulting useful analog signal will be proportional to the doubled
signal of the acceleration of gravity and will enter the input of the amplifier with
additionally introduced protective ring. Next, the amplified signal arrives at the input
of the digital module where it will be converted into digital code and sent to the input
of OC for subsequent calculation of gravitational anomaly Δg.
CONCLUSION
The expediency of using aviation gravimetric systems for gravimetric
measurements and receiving information about the Earth's gravitational field is proved.
An analysis of existing gravimeters of aviation gravimetric systems is done, identified
their strengths and weaknesses. Modern perspective developments in the area of
designing a new type of aviation gravimeters with higher accuracy and speed of the
known are considered. For a given specific force sensor uncertainty, the minimum
system uncertainty results when the sensor is physically stabilized along the z axis
(vertical axis) of an in strumented local geographic coordinate frame. Errors in the z
axis alignment of such a frame result in 1…20 mGal error for each arc minute of
misalignment due to projection of horizontal Coriolis forces along the measurement
axis.
BIBLIOGRAPHICAL REFERENCES
1.
Bezvesilna O.M., Aviation gravimetric systems and gravimeters, Zhytomyr:
ZSTU, 2007, 604 p. [in Ukrainian].
2.
Bezvesilna O.M., Tkachuk A.H. (2013) Piezoelectric gravimeter of aviation
gravimetric system, Zhytomyr: ZSTU, 240 p. [in Ukrainian].
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