RU2818964C2 - Method of determining trajectory of manoeuvring aerospace object - Google Patents

Abstract

FIELD: physics.

SUBSTANCE: invention relates to radar, in particular to methods of determining parameters of the position of a target with radar tracking systems. At the same time determination of trajectory of aerospace defence is carried out under conditions of external noise and taking into account measurement error. Disclosed method consists in the fact that a set of real hypotheses on possible trajectories of the monitored aerospace defence, which cannot lead to its destruction due to mechanical overloads, are put forward. Density of real hypotheses, that is minimum distance between adjacent hypothetical trajectories, should be comparable with radius of valid damage of aerospace defence. For each hypothesis, values of standard deviations are calculated. At the same time measurement by radar tracking systems of the section of the aerospace defence route is carried out at a length comparable to the period of the first harmonic of the trajectory of the manoeuvring object along any of the coordinate axes. Criterion of minimum standard deviation is used to determine the true hypothesis, on the basis of which the position of the tracked object is determined at an arbitrary future moment in time.

EFFECT: providing the possibility of determining the true trajectory of a manoeuvring aerospace object among a plurality of possible ones based on analysis of measurement results of a section of its route and, thus, implementation of long-term prediction of its position in space.

1 cl, 5 dwg

Description

ANNOTATION

Method for determining the trajectory of a maneuvering aerospace object (ASO). The inventive method allows, based on an analysis of the measurement results of a section of the route of a maneuvering aerospace defense, to determine its true trajectory among many possible ones and thus carry out a long-term forecast of its position in space. In this case, the determination of the aerospace defense trajectory is carried out under conditions of external interference and taking into account the measurement error. The invention relates to radar, in particular to methods for determining target position parameters by radar tracking systems.

DESCRIPTION

Field of technology

The invention relates to radar and can be used to determine the trajectory of a maneuvering air defense system. Achieved technical result: increasing the reliability, accuracy and sustainability of air defense support.

Prerequisites for creating an invention

Prerequisites for the creation of the invention, on the one hand: an unprecedented increase in the number and types of aerospace defense (rockets, aircraft, unmanned aerial vehicles, low-orbit satellites); vigorous increase in air defense speeds; the development of electronic warfare (EW) methods and, as a consequence, the presence of electromagnetic interference in aerospace, on the other hand: a significant increase in the productivity of microelectronic processors.

Similar methods of tracking the East Kazakhstan region

From the existing level of technology, a method for tracking the air defense route is known, given in patent RU 2624467 C2 “Method for determining the height of a two-coordinate radar target.” This invention relates to radar, in particular to methods for determining the position parameters of a target during rectilinear uniform movement in the vicinity of a radar station (radar), and can be used to obtain additional data on the movement of objects in space, including height, when using two-dimensional radars, providing a circular or sector view of the space. The technical result is an expansion of the functionality of existing two-dimensional radars. This result is achieved due to the fact that a target trajectory data post-processing block, consisting of a calculator, a subtractor and a comparator, is introduced into the two-coordinate radar between the secondary information processing block and the information display block; filtered measurements are received at the input of the target trajectory data post-processing block from the secondary information processing block target position, from which three consecutive measurements are selected, processed in the computer, one reliable value of the expected target height for a straight trajectory is selected and stored in the subtractor, then, in the case of the first iteration, they proceed to processing the next measurements of the target position in the computer, and when the second iteration is carried out and subsequent iterations, the deviation of the newly obtained estimated height from the previously calculated one is determined in the subtractor, the deviation is recorded in the comparator, the correctness of the hypothesis of straightness and uniformity is assessed, the calculated value of the height is taken, which is transferred to the information display block and then proceeds to processing the next measurements received in the block post-processing of target trajectory data.

The disadvantages of this technical solution are: restrictions on the type of VKO trajectory (uniform linear motion) and lack of consideration of external interference.

Also known is the “Method of tracking the trajectory of a target emitting or illuminated by an external radio-electronic device”, protected by patent RU 2667898 C1 (01.2006).

The inventions relate to the field of radar IPC G01S 13/66 and can be used in radar stations (radars). The achieved technical result is a reduction in the time of using the active mode of a radar equipped with direction finders, with them independently tracking the trajectory of a target emitting or illuminated by an external radio-electronic device and eliminating false targets. This result is achieved due to the fact that the method of tracking a target's trajectory is based on its direction finding by emissions or reflections using several (n>2) direction finders spaced apart in space and on calculating the range to the target. At the same time, when surveying the space using an active radar station (radar) in active mode, based on bearing data transmitted to the radar from several direction finders that independently track target bearings, bearing intersection points corresponding to false targets are eliminated, based on the transmitted data on bearings of real targets, they form graphs of changes in bearing from the location points of the direction finders, by extrapolation they determine the values of the bearings for different points in time, on their basis they calculate the range to the target, track in passive mode along the bearings and range of the trajectory, occasionally clarifying its position in the active mode, except In addition, the position of the trajectory is clarified when the parameters of the target radiation change or when there is a break in the radiation.

The disadvantage of this technical solution is the lack of consideration of external interference.

Invention prototype

The prototype of the invention can be considered patent RU 2716495 “Method and system for multi-purpose tracking in two-position radar systems” (12/27/2018). The invention relates to radar (IPC G01S 13/72) and can be used in the development of promising multi-position radar systems and their modernization. The achieved technical result is increasing the reliability and accuracy of identifying air objects in tracking mode. The essence of the method is that for each incoming measurement from all air objects from any information position, indirect measurements are formed at the leading (first) position, on the basis of which, for each tracked trajectory, the fulfillment of certain conditions for the received coordinates of the air object is checked (hits in the identification gate ) For the trajectory for which these conditions are met, the forecast is corrected, while the forecast itself (extrapolation) is carried out according to the appropriate rules.

The disadvantage of this technical solution is the lack of consideration of external interference.

The essence of the invention

The essence of the proposed method for determining the trajectory of a maneuvering aerospace object (ASO) is as follows.

A priori a set of real hypotheses is put forward W{F _i (x,y,z,t),F ₂ (x,y,z,t),…F _i (x,y,z,t),…F _n (x, y,z,t),} about the possible trajectories of the monitored air defense system. The density of real hypotheses - the minimum distance between neighboring hypothetical trajectories - should be comparable to the radius of a reliable lesion of the EKO. Here the real hypothesis is understood in the sense that the evolution of a maneuvering aerospace defense cannot lead to its destruction due to mechanical overloads.

In the process of tracking a spacecraft using a stationary or mobile radar system, a segment of its trajectory F _m (x,y,z,t) is measured with additive noise H _m (x,y,z,t) and measurement error Q _m (x,y, z,t) and using an analog-to-digital converter, a sample of medium size is created - from 70 to 100 values

For each hypothesis, a sample of differences between the trajectory points and the corresponding hypothesis points is calculated:

For each hypothesis for a sample of differences, based on known formulas, the values of standard deviations σ ₁ (W ₁ ), σ ₂ (W ₂ ),…σ _i (W _i ),…σ _n (W _n ) are calculated along the coordinate axes (x, y , z).

In this case, the measurement of a section of the air defense route by radar tracking systems is carried out at a length comparable to the period of the first harmonic of the maneuvering object’s trajectory along any of the coordinate axes; no additional restrictions are imposed on the power of additive external interference and the dispersion of measurement errors, and the accuracy of the method is constantly monitored by tracking one or more known trajectories of space objects.

The true hypothesis F _true (x,y,z,t) is determined by the criterion: min{σ ₁ (W ₁ ), σ ₂ (W ₂ ),…σ _i (W _i ),…σ _n (W _n )} for each of the coordinate axes (x,y,z).

The position of the tracked object at an arbitrary future time T is calculated using the formula

F _true [x(T,)y(T),z(T)].

Below, as an example, are the results of determining the projection of the air defense trajectory onto the X axis for five maneuvering hypotheses: Sinx; Sin0.75x; Sin1.25x; Sin(x+π/4); Sin(x-π/4). Computer modeling was carried out using the electronic spreadsheet processor Microsoft Excel.

It can be seen from the table that the standard deviations of the differences are minimal if and only if the hypothesis corresponds to the GKO trajectory.

Graphs constructed from samples of differences between measured and hypothetical values are shown in Figures 1-5.

Claims (7)

A method for determining the trajectory of a maneuvering aerospace object (ASO), providing for the following operations: put forward a priori a finite set of real hypotheses about the entire possible trajectory of the aerospace defense, described by a harmonic sinusoidal function along any of the coordinate axes, and real hypotheses about the possible trajectories of the aerospace defense are put forward taking into account the fact that the evolution of the maneuvering aerospace defense cannot lead to its destruction due to mechanical overloads, and the density of real hypotheses, which is the minimum distance between adjacent hypothetical trajectories, is comparable to the radius of reliable damage to the EKO; a short section of the aerospace defense trajectory is measured by radar tracking systems at 70-100 points at equidistant points in time, while the measurement of a section of the aerospace defense route by radar tracking systems is carried out at a length comparable to the period of the first harmonic of the trajectory of the maneuvering vessel along any of the coordinate axes; calculate the differences between the measurement results and each of the hypotheses at the corresponding points in time; calculate the values of standard deviations along the coordinate axes in samples of differences between the measurement results and each of the hypotheses at the corresponding points in time; determine the true hypothesis F _true (x,y,z,t) by the criterion of the minimum standard deviation for each of the coordinate axes; determine the trajectory of a maneuvering aerospace defense at an arbitrary future time T using the formula F _true [x(T),y(T),z(T)].