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Verified method of ice elimination on the leading edges of wings
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Highly reliable control system
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Possibility to modify technical parameters based on the aircraft type
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Intuitive control of panel
For Safety of Passengers and Crew
For Safety of Passengers and Crew
The system eliminates ice and indicates possible failures
The icing can occur with aircraft not only in winter months, but also below the temperature of 3 °C. Even a low icing accretion can affect the wing profile and impair flight characteristics; therefore, the system for airframe de-icing is one of the important systems in terms of flight safety.
The system for the pneumatic de-icing control of the airframe is designed for the elimination of the icing occurring during the flight in icing conditions and at the same time for the indication of de-icing system failures. The control system is characterised by high reliability and enables technical parameter modifications depending upon the aircraft type. The panel control is intuitive.
System Description
System Description
Principle of aircraft de-icing
Several physical principles are used for aircraft de-icing, the most common methods are the heating of an aircraft part or mechanical elimination of icing on the appropriate part of the airframe. Powerful electrical sources, three-phase converters 115VAC/28V DC, are used for the electrical de-icing of cockpit windshields or for the de-icing of leading edges of propeller blades. The wings and the tail units of the airframe are de-iced pneumatically, normally by section. The whole de-icing process is often controlled automatically based on the icing layer thickness which is measured by the sensors located in individual aircraft sections.
System for L410 Aircraft
System for L410 Aircraft
The system for the pneumatic de-icing of the L410 airframe is designed for the elimination of icing accumulated during flight in icing conditions. In automatic mode the rubber boots attached to the leading edges of the wings are inflated by hot air from the engine compressor via air valves. The ice, released by cracking, is removed from the aircraft by airflow. The action of valves is controlled from the electronics bank, automatically or manually, by means of the illuminated buttons located on the system panel. The information on reaching the required pressure in the boots is ensured by pressure switches integrated in individual air channels by indication on the buttons A, B and C of the panel.
The control box, in connection with the electronic timer, simple electromagnetic air valve, doubled electromagnetic valve and the pressure transmitter, serves for the control of all functions and the measurement of pressure of the pneumatic airframe de-icing unit. The control box allows switching of the de-icing system, selecting the type of operation and cycle length, measuring the pressure in the system and checking the bulb status. It is possible to preselect 60-second or 80-second cycle of de-icing by controller.
System for L410NG Aircraft
System for L410NG Aircraft
System modification
The system for the control of pneumatic de-icing of the airframe of the new aircraft L410NG was solved by a modification of the above-mentioned system. The control unit of airframe’s pneumatic de-icing which includes the timer and allows controlling the pneumatic de-icing system of the airframe and also the indication of de-icing system failures. The control unit includes the indication circuits that check when the required pressure is reached in the de-icing sections and correct deflation of compressed air in individual sections.
The control unit serves for controlling and monitoring the activity of pneumatic de-icing system of the airframe. It controls the electromagnetic valves and processes the signals from the pressure switches. It allows the automatic or manual control of de-icing system. The system can be operated in two de-icing speeds in the automatic mode – i.e. with a 60-second or 180-second cycle. In the manual mode, the system is controlled by push buttons. The electronic signalisation evaluates the signals from the pressure switches and monitors whether the required pressure was reached in individual sections A, B and C. In the event a failure occurs in a certain section, the electronics ensure its indication by illuminating the light-emitting diode. The light-emitting diode is permanently illuminated until the instrument is switched off. The failure indication works for each section separately, both in automatic and manual modes.
