An Aircraft Control Systems - Assignment Example

Control Systems There are auxiliary hydraulic and electrical power sources for an aircraft systems. One of these improves is the compound hydraulic generator or motor, which is mechanically coupled to the electrical generator/motor. This device is called a Compound hydraulic/electro Motor Generator Pump (CMGP). CMGP system allows hydraulic power to be supplied from any electric power source or an electric power from a hydraulic source of power. Another improvement entails a combination of a ducted air turbine drive (ram) with the CMCP, which defines means of providing continuous hydraulic and electric power to an aircraft in case all aircraft engines that are driven by power sources totally fail. For the modern CAT aircraft, power systems are important because they are the sources of forces for an aircraft control. Most of the modern CAT aircraft favor mechanical backup to purely powered controls for dispense. These aircrafts also have hydraulic powered surface actuators, electronically controlled, electrically controlled and electrically powered actuators. A combination of both is also highly favored. For powered controls, sufficient power is required to be available always in order to maintain the aircraft control in the event of a foreseeable failure. Power required to control an aircraft must be available continuously so that in the event that all the aircraft engines including the auxiliary power units fail. In an airspeed indicator, its static ports were located on an exterior part of an aircraft at a certain location that is chosen to help in detecting the prevailing atmospheric pressure with minimum disturbance from the aircraft’s presence. The open end on a pitot tube is mounted on the aircraft wing facing the flow of water or air. The air speed indicator measures the existing differences between a sensor in the air stream and the static senor not in air stream. When an aircraft is in a standing mode, the pressure in each of the tubes is always equal. The air speed indicator reads zero. In a flight the rush of air leads to differential pressure between the pitot tube and the static tube. This difference in pressure causes the pointer at an air indicator speed to move. Any increase in the forward speed causes the pressure at the pitot tube to raise. This in turn causes the air pressure to push against a diaphragm, which moves the mechanical pointer connected on the indicator. This indicator is calibrated in such a way as that it compensates for winds flowing in the air current. For most airspeed indicators, were calibrated to be used in sea level standard atmosphere. Whenever the temperature or pressure combination results in a density altitude which goes higher that the sea level, a lower airspeed is indicated on an airspeed. On the contrary, in cases where the density altitude falls below a sea level, airspeed indicator shows a faster airspeed. Read More