3 results about "Pulsar" patented technology

The invention discloses a method and system for suppressing non-pulse noise to accurately measure pulse arrival time, and the method comprises the steps: S1, generating pulsar simulation parameters which comprise a rotation period P, a flow density S1250 and a pulse arrival phase delay standard deviation sigma delta p; s2, constructing a pulsar standard contour Q (x), and generating based on a pulse contour type Ptype, a sub-pulse number and a sub-pulse contour shape; s3, simulating multi-epoch observation data, injecting noise, adding phase delay delta p, and generating an average contour q (x); s4, judging a pulse region: positioning a candidate pulse region through baseline identification, and screening a final pulse region according to a contour type; s5, calculating a phase difference delta x between the standard contour and the average contour by using a phase gradient method; and S6, comparing a difference value between the phase difference delta x and the analog phase delay delta p, and verifying whether higher timing accuracy is obtained by removing the noise in the non-pulse region or not. The pulsar timing precision is remarkably improved by reducing noise interference in a non-pulse area, and the pulsar timing method is suitable for a high-precision scientific target.

A kind of relative navigation reference deviation calibration method of star and pulsar information fusion is disclosed, which comprises the following steps: configuring a star angular distance measuring sensor and an X-ray detector on a spacecraft; observing stars by the star angular distance measuring sensor to extract navigation information contained in two kinds of relativistic effects, i.e., star aberration caused by the movement of the spacecraft and light deflection caused by celestial gravitational field; observing pulsars by the X-ray detector to obtain pulse arrival time difference observations; combining spacecraft and earth orbit dynamics model to predict the state; processing star angular distance and pulse arrival time difference observations by an extended Kalman filter to correct the state prediction value, and obtaining the estimation of the spacecraft position and velocity, the geocenter position and velocity, and the sensor system error parameters, so as to realize the calibration of two kinds of reference deviations, i.e., earth ephemeris error and sensor system error. The present application provides a new way to improve the performance of relativistic navigation system.

This invention discloses a method and system for determining the current time using radio observations of multiple pulsars, comprising the following steps: S1. Correcting the deviation between the local clock time and the absolute time to within a set threshold; S2. Selecting N radio pulsars, where N is greater than or equal to 4, and continuously observing the selected radio pulsars using a radio telescope to obtain observation data; S3. Processing the observation data to generate the observed pulse profile; calculating the pulsar pulse phase φ. i S4. Calculate the standard pulse profile P k With the observed pulse profile P' k The relative phase deviation δφ between i Calculate the relative phase deviation δφ with error S5. i With phase φ i deviation Δφ i S6. The deviation δT between the telescope's local clock time and absolute time is calculated, thereby determining the absolute time. This invention eliminates the need to synchronize the local clock with the absolute time of a certain time standard. It can obtain absolute time with an accuracy on the order of tens of microseconds by analyzing observed pulsars, and significantly reduces calculation time.