Airborne short-range air-to-air missile guidance system software/hardware complex technical layout and methodological support

Аuthors

Zakharov I. V.^1*, Trubnikov A. A.^2**, Reshetnikov D. A.^2***

1. ,
2. Moscow Aviation Institute (National Research University), 4, Volokolamskoe shosse, Moscow, А-80, GSP-3, 125993, Russia

*e-mail: il-ya-zakharov@yandex.ru
**e-mail: a-trubnikov@inbox.ru
***e-mail: grapler@yandex.ru

Abstract

Based on the present-day maintenance conditions of modern missiles the paper reveals essential factors, which determine their reliability and readiness support at the required level. This, in its turn, allows establish that up to 70% of failures during instrumental control relate to guidance system, and more than half of them falls at the missile control system. The above mentioned problem manifested itself most acutely with short-range air-to-air airborne missiles. This implies the effective solution of missile control problem by employing guidance system functional control method and its realization based on hardware/software complex.

The paper suggests an original solution for short-range air-to-air airborne missile guidance-system loop technical condition, enhancing its functional control methodological efficiency, confirmed by methodological and hardware support synthesis.

Functional control scientific and methodological basics are determined by theory of similarity modeling and automatic control theory harmonic balance methods. The functional control effectiveness achieved with this method is determined by basic concepts inherent to the complete mathematical model structure, using the original inciting signal, generated by standard harmonic oscillations installation. These basic concepts include generation of such initial impact, which allow enhance missile guidance system controlled signals observability in system normal operation mode in space of parameters control.

The direct guidance system direct control time is one of the important parameters, related to its activation. This time is comparable to missile operation while intended application. It ensures the short-range air-to-air airborne missile specified life substantial saving.

Effectiveness of the methodological approach used by authors is supported by developing the guidance system software and hardware functional control complex that prevents introduction of changes to the guidance system hardware and sensors regular system. Thus, the possibility of practical implementation of the methodology, suggested by the authors, into field aerospace forces of the Russian Federation is guaranteed.

Keywords:

hardware and software system, functional control method, harmonic oscillations installation, guidance system, missile control system, linear acceleration sensors, angular acceleration sensors

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