Functional control software/hardware complex master side model

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

With implementation of existing methodological support of regular automated verification systems (AVS) the state and performance of a short-range missile of air-to-air class (AAM SRM) control system sensors are unobservable. Thus, while regular AVS typical control algorithms realization technical state of control system sensors, such as linear accelerometers (LA), or angular accelerometers (AA) can be estimated through indirect parameters, without their basic parameters determination (transfer factor, etc.). This could significantly reduce methodological fidelity of guidance system control.

To solve the above said problem the authors offer implementation of functional control (FC) method. This method can be realized based on software/hardware complex (SHC).

The paper suggests scientific basics of functional control. They are stipulated by implementation of harmonic balance of automated control theory. The FC structure, organized by duplication method, was used to realize AAM SRM guidance system FC control sensors.

To minimize the control structure dimensionality at the inputs a single primary impact  on the missile guidance system is applied using harmonic oscillation workbench (HOW). To close FC links one should be aware of HOW functioning as a master side of SHC.

HOW is the main preset part of SHC, generating a single primary stimulating effect  on the missile during FC of its guidance system sensors. To close FC system it is necessary to set correct stimulating action on an FC object. It is necessary herewith to eliminate FC resonant mode, and ensure FC main sensors functioning in linear range, i. e. exclude: guidance system signals overload limiting for LAs; missile body spin velocity limiting for AA detection unit, as well as angular target tracking rate and locating angle limiting for target-seeking head (TSH).

To ensure harmonic oscillation “comfort mode” for the missile guidance system, selection and adjustment of HOSs design values is carried out. For this purpose, the developed SHC FC master side model is used. In addition, the developed model is used for characterization of secondary stimulating effects on HOW, LA and AA detection units and determination of the signals of their reactions.

The process of HOW operation can be represented by a certain model in Laplace operator form. This model includes oscillating and measuring loops. The oscillating circuit dynamic model represents an oscillating link with time constant and damping factor, as well as nonlinearity of saturation type with known parameters, stipulated by HOW design specifics.

Measuring loop includes axial power transmission (PT) and inertia-free angular sensor. PT is free of reduction elements, and its gain K_PT = 1.

The conducted experiments on a certain HOW embodiment confirmed the adequacy and performance capacity the developed models of SHC FC master side, as well as correctness of the HOW design values, allowing eliminate AAM SRM guidance system's signals limiting and their termination to stop.

Keywords:

functional control method, software/hardware complex, harmonic oscillation workbench, guidance system, target-seeking head, missile control system, linear accelerometer, angular accelerometer

References

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