PART B: Design Problem using Karnaugh Mapping Technique A jet aircraft employs a system for monitoring the rpm, pressure, and temperature values of its engines using sensors that operate as follows: RPM sensor output = 0, only when speed < 4800 rpm P sensor output = 0, when pressure <220 psi T sensor output = 0, only when temperature < 200°F Figure 2.1 shows the logic circuit that controls a cockpit warning light for certain combinations of engine conditions. Assume that a HIGH at output W activates the warning light: (a) Create your truth Table with appropriate input-output combinations (b) Determine what engine conditions will give warning to the pilot. (c) Using K-Map technique to obtain your simplified Boolean equation. (d) Change this circuit to one using all NAND gates and constructs the circuit. Temp Sensor Pressure Sensor RPM Sensor T P R Figure 2.1 W Warning Light

PART B: Design Problem using Karnaugh Mapping Technique A jet aircraft employs a system for monitoring the rpm, pressure, and temperature values of its engines using sensors that operate as follows: RPM sensor output = 0, only when speed < 4800 rpm P sensor output = 0, when pressure <220 psi T sensor output = 0, only when temperature < 200°F Figure 2.1 shows the logic circuit that controls a cockpit warning light for certain combinations of engine conditions. Assume that a HIGH at output W activates the warning light: (a) Create your truth Table with appropriate input-output combinations (b) Determine what engine conditions will give warning to the pilot. (c) Using K-Map technique to obtain your simplified Boolean equation. (d) Change this circuit to one using all NAND gates and constructs the circuit. Temp Sensor Pressure Sensor RPM Sensor T P R Figure 2.1 W Warning Light

Delmar's Standard Textbook Of Electricity

7th Edition

ISBN:9781337900348

Author:Stephen L. Herman

Publisher:Stephen L. Herman

Chapter13: Magnetic Induction

Section: Chapter Questions

Problem 1PA

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A MIG 31 fighter jet has a monitoring system for rpm, pressure and temperature The engine uses several sensors that operate as follows: RPM (R), sensor output = 0 if speed < 10,000 rpm Pressure (P), sensor output = 0 if pressure < 220 psi Temperature (T), sensor output = 0 if temperature < 200 oF The following figure is the logic circuit that controls the warning lights in the cockpit of the aircraft for variations in certain engine conditions. Assume the HIGH condition will make the light turn on. Using the truth table, determine under what condition the engine lights warning will flash 2. Modify the circuit using all NAND gates *Please solve number 2
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