| 摘要 |
FIELD: transport. ^ SUBSTANCE: aircraft incorporates a supply inverter, a computer, a controller, a cooling system frequency converter, an IR radiators power supply, a control panel and power modules arranged along the vertical and horizontal relative the geometric center of aircraft IR radiation with a geometry representing a line or a polygon. The produced modulated IR-radiation flow cuts off the maximum vertical and horizontal values of the aircraft IR-radiation indicatrix. Every module incorporates an onboard servo amplifier and a casing with vents arranged either on board or moving relative to the aircraft. The aforesaid casing accommodates fans connected to the cooling system frequency converter, a servo motor connected by its supply input to the servo amplifier and coupled with the latter via the feedback and control circuits, a platform articulated to the said servo motor. The casing houses also the following optically connected in series components, i.e. the IR radiator connected to the appropriate power supply, the preset IR-spectrum filter, IR-radiation transducer to control the modulated IR-radiation flow, IR-radiation focusing system and IR-radiation reflector arranged on the said platform and participating in forming the IR-radiation indicatrix. The power supply inverter input is connected to the onboard power supply, while its outputs are connected to the supply inputs of the cooling system frequency converter, controller, servo amplifiers and IR-radiators power supply. The controller can be connected to the aircraft object control system and interconnected with the control panel and servo amplifiers. The controller control input is connected to the computer output, its signal inputs are connected to the module IR-radiation transducer outputs and outputs are connected to control inputs of the cooling system frequency converter and IR-radiators power supply. ^ EFFECT: expanded application and higher efficiency. ^ 18 cl, 4 dwg |
