Document Type and Number:
Japanese Patent JPS5034318
Kind Code:
B1
Abstract:
1,192,183. Monitoring apparatus, SPERRY RAND CORP. Aug. 2, 1967 [Aug. 9, 1966], No. 35413/67. Heading G1U. A system for monitoring the output of three devices providing three normally identical output signals and three in-line monitoring signals during normal operation has two display channels only, to which the output signals from two of the devices are applied, together with two comparators wherein output signals from the first and second channels are separately compared with the third output signal. Gates respond to the comparator outputs and the in-line monitoring signals to detect and indicate malfunctions. The apparatus is used to monitor the attitude data presented to the pilot and co-pilot of an aircraft from remote vertical gyroscopes, in a system incorporating a third gyroscope for monitoring the other two and also acting as a spare. The first and second gyros 1 and 2 are connected to the attitude indicators 4 and 5 via separate channels, each including a control transformer, amplifier and servo. The output from the third gyro is fed to two control transformers 19, 20 which are controlled respectively by the servos in the first and second channels. If the channels are functioning properly, the control transformers 19, 20 provide null outputs which are detected by sensors 23 and 30 to provide pulse outputs. The output e.g. from 23 is passed to AND gate 26, and if the gyro 1 is providing an in-line monitor signal, the gate provides an output to prevent the warning flag 27 appearing. The flag would warn that the first channel is not functioning correctly. The second channel is monitored similarly. If however no output is obtained from both sensors 23 or 30, it is probable that the standby gyro is at fault. In this circumstance the NAND circuit 25 delivers a pulse to suppress operation of the flags 27 and 33 through the gates 26 and 32 and operate a warning indicator 35, showing that the standby gyro system is faulty. The standby gyro also provides an in-line monitor signal when faulty, which also operates the warning 35. To test the monitoring channels themselves, switches 10, 16 are used to apply bias voltages which should produce predetermined indications in the indicators 4 and 5. Switches 6, 12, 21, 22 are provided to switch out a faulty gyro and bring in the standby if required.
Application Number:
JP4602567A
Publication Date:
November 07, 1975
Filing Date:
July 17, 1967
Export Citation:
International Classes:
B64C13/00; B64D45/00; G01C19/44; G01C25/00; G08C19/38; (IPC1-7): G01C19/00