4 results about "Pressure altitude" patented technology

The invention provides an ADS-B (Automatic Dependent Surveillance-Broadcast) height updating method based on compatibility of air pressure and geometric height, which belongs to the technical field of air traffic surveillance and specifically comprises the following steps: judging the track information of a local aircraft and the effectiveness of geometric height and air pressure height in the track information of a target aircraft; calculating the relative barometric altitude by using the calculated value of the barometric altitude of the target aircraft at the moment T1 and the barometric altitude calculated value of the local aircraft at the moment t; obtaining a predicted value of the track data of the target aircraft at the T1 moment; performing correlation judgment on the observed value and the predicted value of the track information of the target aircraft at the T1 moment to obtain a final output track; and outputting the relative height of the target aircraft and the local aircraft according to the final output flight path middle height data, the local aircraft height data and the effectiveness of the local aircraft pressure height. Through the processing scheme provided by the invention, the reliability of ADS-B track monitoring is improved.

The application discloses a kind of barometric altitude dynamic correction method based on airborne data.First, the sliding window parameters are screened using recursive feature elimination method, and then the sliding window is initialized and updated;Clean the sliding window data, first determine whether the sliding window data is null, then correct;For the data fusion multiple methods to detect outliers and correct after completing null judgment and correction;Construct the LSTM model and optimize the sliding window size, select the window size of the best performance indicator, use the LSTM model to correct the barometric altitude dynamically.This method has the characteristics of high precision, strong real-time, etc., improves the deficiency that the existing method can only correct the barometric altitude at a specific location, realizes the dynamic correction of barometric altitude in the whole approach process, improves the obstacle safety under low temperature conditions, at the same time, has the ability to correct the barometric altitude under high temperature conditions, and can be widely used in flight operation using barometric vertical navigation program.

The application discloses a method for correcting aircraft height based on atmospheric data, and relates to the technical field of measurement. A specific embodiment of the application comprises the following steps: S1: obtaining a current pitot pressure altitude Hp of an aircraft and a pitot pressure altitude Hpn of the first previous n times, wherein n is a first preset value; obtaining a current inertial pressure altitude HINS of the aircraft and a pitot pressure altitude HINSm of the first previous m times, wherein m is a second preset value; S2: performing Fourier filtering on the current pitot pressure altitude Hp and the pitot pressure altitude Hpn of the first previous n times to form a current pitot Fourier pressure altitude Hpfft and a pitot Fourier pressure altitude Hpnfft of the first previous n times; S3: determining a difference value ΔHpfft of the current pitot Fourier pressure altitude Hpfft and the pitot Fourier pressure altitude Hpnfft of the first previous n times; determining a difference value ΔHINS of the current inertial pressure altitude HINS and the pitot pressure altitude HINSm of the first previous m times; and S4: determining a corrected altitude Hc according to the following formula: Hc = Hpfft + α1*ΔHINS - α2*ΔHpfft.

The invention discloses a flight atmospheric parameter resolving method based on state uniqueness, belongs to the technical field of space flight and aviation, is suitable for resolving flight atmospheric parameters of a flying wing aerodynamic layout aircraft, and solves a local Mach number according to pressure values of five embedded atmospheric data sensors. All possible attack angle and sideslip angle combined states and attack angle pressure coefficients, sideslip angle pressure coefficients, static pressure, total pressure and Mach numbers corresponding to all the combined states are obtained through the local Mach numbers, and the static pressure, the total pressure and the Mach numbers in all the attack angle and sideslip angle states are compared; the combined states in the threshold range are the attack angle, the sideslip angle, the static pressure, the total pressure and the Mach number in the real flight state. According to the method, high-reliability atmospheric data parameters can be provided for various flying wing aerodynamic layout aircrafts, the method is not limited by aerodynamic shapes and air pressure heights of the aircrafts, a unique solution can be determined from multiple combinations, the correctness of parameter solution is ensured, the problem of non-convergence does not exist, and the method has universality.