METHOD AND APPARATUS FOR DETECTION derating AIRCRAFT

摘要

1. method u043eu0431u043du0430u0440u0443u0436u0435u043du0438u00a0 u0443u0445u0443u0434u0448u0435u043du0438u00a0 characteristics of aircraft u043eu0442u043bu0438u0447u0430u044eu0449u0438u0439u0441u00a0, automatically and periodically u043eu0441u0443u0449u0435u0441u0442u0432u043bu00a0u044eu0442 next steps;(a) rely on at least the current mass of aircraft are based on the current theoretical drag of aircraft the apparatus and the drag of an aircraft.;(b) the use of at least the first set of comparisons, u043eu0442u043du043eu0441u00a0u0449u0438u0439u0441u00a0 to frontal resistance and containing at least one of the comparison between the current brute force sop u0440u043eu0442u0438u0432u043bu0435u043du0438u0435u043c and theoretical brute force resistance, and;(c) u043eu043fu0440u0435u0434u0435u043bu00a0u044eu0442 u0443u0445u0443u0434u0448u0435u043du0438u00a0 characteristics of the aircraft, at least on the basis of the first set of comparisons.;2. method for p. 1, u043eu0442u043bu0438u0447u0430u044eu0449u0438u0439u0441u00a0, if deterioration in the characteristics of the aircraft are on stage), then in the next phase (d) transmitting at least one equipped u0442u0432u0443u044eu0449u0435u0435 troubling message.;3. method for p. 1, u043eu0442u043bu0438u0447u0430u044eu0449u0438u0439u0441u00a0, phase (a) current of u0432u044bu0447u0438u0441u043bu00a0u044eu0442 aircraft on the basis of the original mass before the flight, and the fuel consumption in u0432u0440u0435u043cu00a0 flight well, that depends, at least from the cruising altitude of aircraft type.;4. method for p. 1, u043eu0442u043bu0438u0447u0430u044eu0449u0438u0439u0441u00a0 because at the stage (a) u0432u044bu0447u0438u0441u043bu00a0u044eu0442 theoretical CXth frontal resistance according to the following expression:;CXth = f1 (CZ2) + ground (re) + CXf,;where the cz - importance of frontal u0441u043eu043fu0440u043eu0442u0438u0432u043bu0435u043du0438u00a0, u0437u0430u0432u0438u0441u00a0u0449u0435u0433u043e current mass; f1 (CZ2) - u0444u0443u043du043au0446u0438u00a0, u0437u0430u0432u0438u0441u00a0u0449u0430u00a0 from CZ2; ground (re) - u0444u0443u043du043au0446u0438u00a0, u0437u0430u0432u0438u0441u00a0u0449u0430u00a0 of reynolds number re, CXf - value, u0437u0430u0432u0438 u0441u00a0u0449u0435u0435 of cz and CZ2.;5. method for p. 1, u043eu0442u043bu0438u0447u0430u044eu0449u0438u0439u0441u00a0 because at the stage (a) u0432u044bu0447u0438u0441u043bu00a0u044eu0442 current frontal resistance u0441u0445u0430 / with according to the following expression:;,;where r is the u043fu043eu0441u0442u043eu00a0u043du043du0430u00a0 value; s is the area of the surface of the aircraft; the tas - u0440u0430u0441u0441u0447u0438u0442u0430u043du043du0430u00a0 air speed; g value u0437u0430u0432u0438u0441u00a0u0449u0435u0435 of tas; t - value u0442u00a0u0433u0438 in u0437u0434u0443u0448u043du043eu0433u043e screw.;6. method for u043eu0442u043bu0438u0447u0430u044eu0449u0438u0439u0441u00a0 1, so that further u043fu0440u043eu0432u0435u0440u00a0u044eu0442, u043du0430u0445u043eu0434u0438u0442u0441u00a0 or no aircraft in the cruise flight.;7. method for u043eu0442u043bu0438u0447u0430u044eu0449u0438u0439u0441u00a0 p.6, so that if the aircraft is not u043du0430u0445u043eu0434u0438u0442u0441u00a0 in cruise flight, on stage with the characteristics of the u043bu0435u0442u0430u0442u0435u043bu044c u043eu043fu0440u0435u0434u0435u043bu00a0u044eu0442 u0443u0445u0443u0434u0448u0435u043du0438u00a0) the main apparatus is based on the first set of comparisons, u0441u0432u00a0u0437u0430u043du043du043eu0433u043e with brute force resistance.;8. method for u043eu0442u043bu0438u0447u0430u044eu0449u0438u0439u0441u00a0 1, so that the stage) u043eu043fu0440u0435u0434u0435u043bu00a0u044eu0442 deterioration characteristics of the aircraft, if one of the following two conditions u0440u0435u0430u043bu0438u0437u0443u0435u0442u0441u00a0, a and b, rh u043eu0441u00a0u0449u0438u0445u0441u00a0 to the first set of comparisons, i.e. if;a: u0441u0445u0430 / CXth + CX1 during a predetermined time.;in: u0441u0445u0430 / CXth + CX2; and;u0441u0445u0430 / CXth + CX3,;where u0441u0445u0430 / estimated the current drag aircraft; CXth estimated theoretical drag aircraft; CX1,CX2 and CX3 is predetermined u0437u043du0430u0447u0435u043du0438u00a0 frontal u0441u043eu043fu0440u043eu0442u0438u0432u043bu0435u043du0438u00a0; CXa / with u00a0u0432u043bu00a0u0435u0442u0441u00a0 differential from the current frontal u0441u043eu043fu0440u043eu0442u0438u0432u043bu0435u043du0438u00a0 between u0434u0432u0443u043cu00a0 beforehand defined different moments; CXth u00a0u0432u043bu00a0u0435u0442u0441u00a0 theoretical differential from frontal u0441u043eu043fu0440u043eu0442u0438u0432u043bu0435u043du0438u00a0 between u0434u0432u0443u043cu00a0 beforehand defined different moments.;9. method for u043eu0442u043bu0438u0447u0430u044eu0449u0438u0439u0441u00a0 p.6, so that if the aircraft u043du0430u0445u043eu0434u0438u0442u0441u00a0 in cruise flight, on stage, and their theoretical foundations u043au0440u0435u0439u0441u0435u0440u0441u043au0443u044e speed) u0430u043du0438u0438 current mass aircraft and u0438u0437u043cu0435u0440u00a0u044eu0442 current speed aircraft;in the stage (b) using the second set of comparisons, u0441u0432u00a0u0437u0430u043du043du044bu0439 with speed and containing at least one of the comparison between the current speed and the theoretical u043au0440u0435u0439u0441u0435u0440u0441 for speed, and;on the stage) u043eu043fu0440u0435u0434u0435u043bu00a0u044eu0442 the u0443u0445u0443u0434u0448u0435u043du0438u00a0 characteristics of aircraft is also based on the second set of comparisons, u0441u0432u00a0u0437u0430u043du043du043eu0433u043e with speed.;10. method for u043eu0442u043bu0438u0447u0430u044eu0449u0438u0439u0441u00a0 p.9, so that at the point (a) are the theoretical u043au0440u0435u0439u0441u0435u0440u0441u043au0443u044e speed based on the current mass of the spacecraft, the high you're flying the aircraft, and the difference between the standard temperature and the measured temperature.;11. method for u043eu0442u043bu0438u0447u0430u044eu0449u0438u0439u0441u00a0 p.9, however, on the stage to detect the deterioration in the characteristics of the aircraft, if one of the following two conditions u0440u0435u0430u043bu0438u0437u0443u0435u0442u0441u00a0 c and d, on u0442u043du043eu0441u00a0u0449u0438u0445u0441u00a0 to the first and second sets of comparisons, i.e. if;c: CXa / CXth + CX4; and;ias IASth - IAS1 during a predetermined time.;d: CXa / CXth + CX4; and;ias IASth - IAS1; and;CXa / c CXth + CX5,;where u0441u0445u0430 / estimated the current drag aircraft; CXth estimated theoretical drag aircraft; CX4 and CX5 - u0437u0430u0440u0430u043d certain u0437u043du0430u0447u0435u043du0438u00a0 frontal u0441u043eu043fu0440u043eu0442u0438u0432u043bu0435u043du0438u00a0; ias - u0438u0437u043cu0435u0440u0435u043du043du0430u00a0 u0442u0435u043au0443u0449u0430u00a0 speed aircraft; IASth - u0440u0430u0441u0447u0435u0442u043du0430u00a0 u0442u0435u043eu0440u0435u0442u0438u0447u0435u0441u043au0430u00a0 u043au0440u0435u0439u0441u0435u0440u0441u043au0430u00a0 speed; IAS1 - r the u0430u0440u0430u043du0435u0435 u043eu043fu0440u0435u0434u0435u043bu0435u043du043du0430u00a0 speed; u0441u0445u0430 / with the currentfrontal u0441u043eu043fu0440u043eu0442u0438u0432u043bu0435u043du0438u00a0 between u0434u0432u0443u043cu00a0 beforehand defined different points; CXth - the difference between the u0434u0432u0443u043cu00a0 beforehand certain theoretical frontal u0441u043eu043fu0440u043eu0442u0438u0432u043bu0435u043du0438u00a0 mi different moments.;12. method for u043eu0442u043bu0438u0447u0430u044eu0449u0438u0439u0441u00a0 p.11, so that on the stage) u043eu043fu0440u0435u0434u0435u043bu00a0u044eu0442 deterioration characteristics of the aircraft, if one of the following two conditions u0440u0435u0430u043bu0438u0437u0443u0435u0442u0441u00a0 e and f, u0441u0432u00a0 with regard to the first and second sets of comparisons, i.e. if;e: CXa / CXth + CX6; and;ias IASth - IAS2 during a predetermined time.;f: CXa / CXth + CX6;;ias IASth - IAS2; and;CXa / c CXth + CX7,;where CXa / estimated the current drag aircraft; CXth estimated theoretical drag aircraft; CX6 and CX7 - u0437u0430u0440u0430u043du0435 e certain u0437u043du0430u0447u0435u043du0438u00a0 frontal u0441u043eu043fu0440u043eu0442u0438u0432u043bu0435u043du0438u00a0; CX6 less CX4; ias u00a0u0432u043bu00a0u0435u0442u0441u00a0 measured the speed of the aircraft; IASth u00a0u0432u043bu00a0u0435u0442u0441u00a0 computational theoretical cruiser by the speed of the aircraft; IAS2 u00a0u0432u043bu00a0u0435u0442u0441u00a0 beforehand oprahof differential from speed, IAS2 exceeds IAS1; CXa / c u00a0u0432u043bu00a0u0435u0442u0441u00a0 differential from the current frontal u0441u043eu043fu0440u043eu0442u0438u0432u043bu0435u043du0438u00a0 between u0434u0432u0443u043cu00a0 beforehand defined different points; CXth u00a0u0432u043bu00a0 u0435u0442u0441u00a0 theoretical differential from frontal u0441u043eu043fu0440u043eu0442u0438u0432u043bu0435u043du0438u00a0 between u0434u0432u0443u043cu00a0 beforehand defined different moments.;13. method for u043eu0442u043bu0438u0447u0430u044eu0449u0438u0439u0441u00a0 p.12, so that, if not u0440u0435u0430u043bu0438u0437u0443u0435u0442u0441u00a0 none of the conditions c, d, e and f, u043fu0440u043eu0432u0435u0440u00a0u044eu0442, u0440u0435u0430u043bu0438u0437u0443u0435u0442u0441u00a0 if one of the following conditions of g and h, u0441u0432u00a0u0437u0430u043du043du044bu0445 with first and the second set of comparisons, etc. e. if;g: CXa / CXth + CX8; and;ias IASth - IAS3 during a predetermined time.;h: CXa / CXth + CX8;;ias IASth - IAS3; and;CXa / c CXth + CX9,;where CX8 and CX9 u00a0u0432u043bu00a0u044eu0442u0441u00a0 beforehand defined u0437u043du0430u0447u0435u043du0438u00a0u043cu0438 frontal u0441u043eu043fu0440u043eu0442u0438u0432u043bu0435u043du0438u00a0, with CX8 less CX6; IAS3 u00a0u0432u043bu00a0u0435u0442u0441u00a0 differential from a predetermined speed less IAS1 and IAS2;;if one of the conditions u0440u0435u0430u043bu0438u0437u0443u0435u0442u0441u00a0 g and h, at a stage (d) transmitting a message indicating that the u043au0440u0435u0439u0441u0435u0440u0441u043au0430u00a0 u00a0u0432u043bu00a0u0435u0442u0441u00a0 speed low.;14. method for u043eu0442u043bu0438u0447u0430u044eu0449u0438u0439u0441u00a0 1, so that if they reveal the deterioration of characteristics, compares the measured speed with the calculated minimum ias working speed MSIS, u0441u0432u00a0u0437u0430u043du043du043eu0439 with u0443u0441u043bu043eu0432u0438u00a0u043cu0438 intensive u043eu0431u043bu0435u0434u0435u043du0435u043du0438u00a0; and if the speed is less than the speed of ias MSIS, transmit a message requiring the u043fu043eu0432u044bu0448u0435u043du0438u00a0 speed.;15. method for u043eu0442u043bu0438u0447u0430u044eu0449u0438u0439u0441u00a0 1, so that the steps (a) - (c) u043eu0441u0443u0449u0435u0441u0442u0432u043bu00a0u044eu0442 only if retracted flaps and landing gear.;16. method for u043eu0442u043bu0438u0447u0430u044eu0449u0438u0439u0441u00a0 1, so that the steps (b) and (c) u043eu0441u0443u0449u0435u0441u0442u0432u043bu00a0u044eu0442 only when at least one condition u043eu0431u043bu0435u0434u0435u043du0435u043du0438u00a0 u0440u0435u0430u043bu0438u0437u0443u0435u0442u0441u00a0 and when u0438u0437u043cu0435u0440u0435u043du043du0430u00a0 art u0430u0442u0438u0447u0435u0441u043au0430u00a0 air temperature exceeds a predetermined value.;17.the device u043eu0431u043du0430u0440u0443u0436u0435u043du0438u00a0 and u043fu0440u0435u0434u0443u043fu0440u0435u0436u0434u0435u043du0438u00a0 deterioration in the characteristics of the aircraft (2) containing multiple sources of information to the central unit (3), with u0435u0434u0438u043du0435u043du043du044bu0439 many (2) sources of information and that the possibility of u043eu0431u043du0430u0440u0443u0436u0435u043du0438u00a0 u0443u0445u0443u0434u0448u0435u043du0438u00a0 characteristics of the aircraft, means (5) u043fu0440u0435u0434u0443u043fu0440u0435u0436u0434u0435 u043du0438u00a0, united with the central unit (3), u043eu0442u043bu0438u0447u0430u044eu0449u0435u0435u0441u00a0 orderthe central unit (3) contains means (7, 8) u0434u043bu00a0 u0432u044bu0447u0438u0441u043bu0435u043du0438u00a0, at least, the mass of the aircraft, the current u0441u043eu043fu0440u043eu0442u0438u0432u043bu0435u043du0438u00a0 aircraft windshield apparatus and, on the basis of the current mass theoretical frontal u0441u043eu043fu0440u043eu0442u0438u0432u043bu0435u043du0438u00a0 aircraft vehicle (10) u0434u043bu00a0 u043fu0440u0438u043cu0435u043du0435u043du0438u00a0, at least the first set with u0440u0430u0432u043du0435u043du0438u0439,u0441u0432u00a0u0437u0430u043du043du043eu0433u043e with brute force resistance and containing at least one of the comparison between the current brute force resistance and theoretical brute force resistance, and the means (12) u0434u043bu00a0 u043eu043fu0440u0435u0434u0435u043bu0435u043du0438u00a0 u043du0430u043bu0438u0447u0438u00a0 u0443u0445u0443u0434u0448u0435u043du0438u00a0 characteristics of aircraft through at least the first set of comparisons.;18. device for p.u043eu0442u043bu0438u0447u0430u044eu0449u0435u0435u0441u00a0 17, so that the central unit (3) further includes means (14) u0434u043bu00a0 u0432u044bu0447u0438u0441u043bu0435u043du0438u00a0 theoretical cruising speed on the basis of the current mass of summer the implementation of machine tools (2) u0434u043bu00a0 u0438u0437u043cu0435u0440u0435u043du0438u00a0 current speed of the aircraft, means (16) of the second set of u0434u043bu00a0 comparisonu0441u0432u00a0u0437u0430u043du043du043eu0433u043e with speed and containing at least one of the comparison between the current speed and the theoretical cruising speed, and means (12) u043eu043fu0440u0435u0434u0435u043bu0435u043du0438u00a0 at u043bu0438u0447u0438u00a0 u0443u0445u0443u0434u0448u0435u043du0438u00a0 characteristics of the aircraft through a second set of comparisons, u0441u0432u00a0u0437u0430u043du043du043eu0433u043e with speed.;19. device for u043eu0442u043bu0438u0447u0430u044eu0449u0435u0435u0441u00a0 p.17, so that many sources of information (2) contains a collection of data on the fly.;20. device for u043eu0442u043bu0438u0447u0430u044eu0449u0435u0435u0441u00a0 p.17, however, means (5) u043fu0440u0435u0434u0443u043fu0440u0435u0436u0434u0435u043du0438u00a0 contain the interface block u0443u043fu0440u0430u0432u043bu0435u043du0438u00a0 information about the characteristics of the aircraft.