RU2635022C1 - Maneuvering method for high-speed unmanned aerial vehicle in possible coverage area of anti-missile and air defense means - Google Patents

Abstract

FIELD: aviation.

SUBSTANCE: invention relates to a manoeuvring method for a high-speed unmanned aerial vehicle (HSUAV) in possible coverage area of anti-missile and air defence means. To implement the method, the trajectory of mandatory HSUAV manoeuvring, consisting of a sequence of individual manoeuvres with a certain duration, is selected stochastically in certain spatial boundaries of the plane of the individual manoeuvre vectors, calculated in a certain way, while the parameters of the acceleration vector of the next manoeuvre are limited by the design features of HSUAV.

EFFECT: poor predictability and low vulnerability of the trajectories of a high-speed unmanned aerial vehicle in the area of their possible damage.

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Description

The invention relates to the field of assigning trajectories of high-speed unmanned aerial vehicles (UAVs).

The well-known "Adaptive Route Control Aircraft" (LA) (patent RU No. 2568161) to reduce the likelihood of aircraft damage in a priori known areas of possible damage by anti-aircraft missile defense systems (AED) due to their bypass.

The disadvantage of this method is that bypassing the air defense zones increases, as a rule, the time and range due to several necessary bypass maneuvers. In addition, the location of the air defense zones can change, including during the flight of the aircraft (especially in relation to mobile air defense systems).

Known methods for reducing the effectiveness of air defense systems by using maneuvers of aircraft to disrupt the guidance mode and increase miss missile defense guided missiles (SAM). So, one of such methods is the method of using the horizontal maneuver of unmanned aerial vehicles (UAVs) with the aim of disrupting the stability of homing and increasing the miss of a guided weapon (USP) (missiles) on an aircraft for given conditions for the approach of these objects (“A way of evading an aircraft from guided weapons ". Application for invention No. 2002124531/11 dated 09.16.2002. B64C 13/18, F44B 15/01, G05D 1/08, G05D 1/10).

The disadvantage of this method is that its implementation on the application is difficult due to the need for rapid detection of the launch of missiles, identifying its type, as well as the target, which is being fired at the moment, and calculating the evasion parameters. In addition, the requirements for maneuvering missiles from missiles in these conditions for acceleration and its duration can not always be met by aircraft, especially manned aircraft.

Also known is the "Method of reducing the likelihood of an aircraft being damaged by air defense systems" (Application for invention No. 95101418/02 of 01/25/1995. F41H 13/00) by implementing a special maneuver that excludes the possibility of extrapolating the parameters of the aircraft trajectory. The proposed maneuver is a trajectory combining a set of eights mutually moving in nodes of eight, while the aircraft flies along spiral turns in a plane perpendicular to the direction of flight. The transition from one eight to another is carried out randomly.

The disadvantage of this method is the limitation of the direction of the spiral turns by a plane perpendicular to the direction of flight, which practically does not reduce the accuracy of extrapolation of the flight path. Another drawback is the lack of requirements for the quality parameters of the turns, which, if the turn radius is too large, can make it possible to ensure the accuracy of the aircraft’s trajectory extrapolation for the aircraft trajectory, which is sufficient to aim the appropriate means of destruction on the aircraft, and if the turn radius is too small, such a maneuver may not interfere with the means indirect defeat.

There is also a comprehensive way to reduce the vulnerability of UAVs. He, like the method according to patent RU No. 2568161, suggests reducing the likelihood of UAV damage by bypassing the a priori known zones of destruction of anti-aircraft missile defense systems and (or) anti-missile defense (hereinafter - missile defense). Inside missile defense zones, if it is not possible to plan their bypass completely, maneuvering is proposed in the form of one of several standard maneuvers, including in accordance with application No. 95101418/02, which, presumably, should not allow the target designation of a missile defense ( PR) on UAV or USP PR exit on homing mode on UAV.

The disadvantages of this method are, firstly, the disadvantages associated with bypassing the missile defense zones, namely the increase in time and flight range due to bypass maneuvers, the unpredictability of the coordinates of the missile defense zones in relation to their mobile systems. Secondly, these are the shortcomings associated with maneuvering the aircraft in the anti-aircraft defense zone, namely the lack of quality requirements for maneuvering parameters (start and end maneuvering times, the number of individual maneuvers and requirements for maneuvers for overloads and duration), which generally does not allow (qualitatively) determine the possibility of reducing the vulnerability of the UAV due to such actions. The parameters of possible maneuvers are not related to the parameters of the missile defense and air defense systems for targeting the target.

To ensure reliable overcoming of the PRO-Air Defense zones, it is necessary to connect the temporary UAV maneuvering parameters with the temporary capabilities of the PRO-Air Defense and USP systems radar to aim at a maneuvering target.

The technical result of the proposed method is the assignment of difficult-to-predict and low-vulnerability UAV trajectories in the area of their possible defeat by missile defense systems.

This goal is achieved by the fact that when specifying a separate maneuver of the UAV, the proposed new parameter of the individual maneuver is observed, namely, the critical maneuver time (CME), T _CME , which is understood as the maximum permissible time between individual maneuvers, in compliance with which the missile defense and air defense system does not able to produce (prepare, calculate) target designation (CC) on the UAV with sufficient accuracy to defeat the UAV. KVM should be, respectively, less than the minimum target designation time for UAVs from radar systems of missile defense and air defense and homing system USP.

The KVM value should be determined on the basis of the best at the time of application of the UAV characteristics of the PRO-air defense system and USP for target designation on the UAV:

KVM <min {T _TsU.RLS , T _TsU.USP }, KVM → max,

where T _ЦУ.РЛС , Т _ЦУ.УСП - minimum target designation time for UAVs from radar systems of PRO-air defense and homing system USP.

This goal is also achieved by the fact that when defining the UAV trajectories, a new approach to constructing trajectories is observed - the KVM approach (critical maneuvering time), the essence of which is as follows:

1. The exact location of the radar system of the PRO-air defense system for defining the UAV trajectories is not important, the region of their possible location relative to the target is important in order to set the mandatory maneuvering zones (ZOM) for the UAV.

2. The time between individual maneuvers should be no more than a KVM, and the number of maneuvers is determined by the length of the ZOM and the speed of the UAV.

3. The plane of the acceleration vector of the next maneuver should be stochastic (within certain spatial boundaries), and the magnitude of the vector is limited by the design features of the UAV.

With the KVM approach, there is no need to expend energy on circumventing the missile defense zones, enough quasistochastic changes in the trajectory, making it impossible to target the aircraft.

The method is illustrated using figure 1, which shows a section of a separate maneuver of the KVM trajectory of the UAV in the maneuvering area.

The claimed method is implemented as follows.

When defining the UAV trajectories in the maneuvering area, the exact location of the radar of the PRO-air defense system is not important, the area of their location is taken into account, in which the ZOM of the UAV is set. The frequency of maneuvering in the ZOM is determined by the length of the ZOM and the parameters of an individual maneuver - the velocity and acceleration vectors of the UAV, as well as the KVM. The time interval between individual maneuvers is not more than KVM. At the start point of a separate maneuver, H _{OM, a} plane of the acceleration vector of the next maneuver is stochastically selected (in certain spatial boundaries, which are determined by the required time to achieve the target and the reserve of the characteristic speed of the UAV). The parameters of this vector are limited by the design capabilities of the aircraft. For KVM separate maneuver UAV passes the distance D _OM .

Thus, when using the claimed method of maneuvering, the unpredictability and low vulnerability of the UAV trajectories in the zone of their possible defeat are achieved.

Claims (1)

A method for maneuvering a high-speed unmanned aerial vehicle in the zone of the possible action of anti-ballistic and anti-aircraft defense means, which consists in setting a mandatory maneuvering trajectory in this zone, including a sequence of individual maneuvers, the duration of each of which should not exceed the critical maneuver time equal to the maximum allowable maneuver time in which targeting to a high-speed unmanned aerial vehicle from radar stations is impossible of antiaircraft missile and (or) air defense systems and homing systems of controlled weapons of these systems, while the vectors of individual maneuvers are selected stochastically in spatial boundaries, which are determined by the required time to achieve the target and the characteristic speed stock of a high-speed unmanned aerial vehicle, and the parameters of the next maneuver is limited by the design features of a high-speed unmanned aerial vehicle.

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