Method for monitoring of parameters of guided missile equipment and automatic check-out system or its realization

FIELD: defense equipment, in particular, complex means of monitoring of guided missile parameters, for example, missiles teleoriented in a beam.

SUBSTANCE: the method consists in simultaneous synchronous supply of simulating control signals to the command formation unit and comparison of the current values of the control commands from the outputs of the guided missile equipment and command formation unit respectively in heading and pitch. If the values of the control commands at the output of the command formation unit equal to the preset ones, and differ from the respective values at the output of the guided missile equipment by the value not exceeding the tolerance value, a decision on the equipment serviceability is taken. Introduction into the automatic check-out system of series-connected command formation unit and comparison unit has enhanced the accuracy of monitoring of the parameters.

EFFECT: enhanced accuracy of monitoring of the parameters due to the exclusion of the influence of the accuracy of decoding of the relay signal and accuracy of formation of simulating control signals.

3 cl, 3 dwg, 1 ex

 

The invention relates to defense systems and, in particular, to integrated funds control parameters guided missiles, for example tereorieribum in the beam.

Currently, due to high performance and a high degree of confidence in the results obtained control automated control systems replace conventional test equipment manual control.

The known method of control parameters of the guided missile, the rotating roll, and an automated control system for its implementation [RF Patent №2243494 from 27.12.04 g, IPC7F 42 B 15/00]. The method of control parameters guided missiles, rotating the roll, including the task of simulating commands, comparing the current values of the control commands on the steering actuator with preset simulating values, evaluation by comparing the results of compliance of the monitored parameter to a specified value, at the same time with the task of simulating the teams form to produce a signal of rotation of the missile angle of roll and serve it on a roll sensor missiles, thus changing the frequency of the simulating signal of rotation of the missile roll is directly proportional to mimic the speed of the missile, as imitating commands use the command message, which modulate, is converted into electromagnetic radiation and taut to the input of the receiving tract missiles, moreover, the command value is set as a function that simulates changing the position of the missile relative to the aiming point.

Known automated control system parameters guided missiles, rotating roll, consisting of series-connected receiver, instrument separation channels and decoding Converter command roll sensor and a steering actuator, contains the control unit and the simulator command message, it is equipped with a signal simulator rotation of the rocket, and the roll sensor is made in the form N opto-couples the led - photodiode, where N=1, ..., n, the first terminals of the LEDs and photodiodes is connected to the housing, and the second leads through respective resistors connected to the power source, while the latter conclusions N photodiodes are connected respectively with N the inputs of the control unit, (N+1)-th input of which is connected to the input of the steering actuator, and (N+2)-th input to the first output of the simulator command message, the second output of which is connected to the input of the receiver. This part of the control unit includes an indicator.

Thus, in the known technical solution (patent RF №2243494) decode the current value of the control commands, i.e. the relay signal to the control winding of steering rockets, which is then compared with a preset simulates the command value.

<> The disadvantage of this method of control parameters of the guided missile, the rotating angle of roll, and automated monitoring system for its implementation is the presence of measurement errors due to the accuracy of simulating the formation of control signals and decoding precision of the relay signal.

The present invention is to improve the accuracy of the control parameters by eliminating the influence of the accuracy of simulating the formation of control signals and the accuracy of the decoding relay signal.

The problem is solved due to the fact that in the method parameters control equipment guided missiles, which serves simulating the control signals for the equipment guided missiles, while simultaneously serves simulating the control signals to the processing unit commands and compare the current values of the control commands with output equipment guided missile and block the formation of teams respectively at the rate and pitch, when the command value of the control output processing unit commands equal to specified, and the difference from the corresponding values at the output of the equipment guided missile at an amount not exceeding tolerance, decide on efficiency equipment.

Automated control system parameters and the equipment guided missiles containing the indicator and has consistently enabled simulator control signals and equipment guided missile; it introduced connected in series forming unit commands and block comparison, the yield of equipment guided missile is connected to the second input of the comparison, the output of the simulator control signals connected to the signal input processing unit commands, and the output of the Comparer is connected to the input of the indicator.

Additionally, the automated system parameters control equipment guided missile second output equipment guided missile is connected to a clock input of the processing unit commands.

The claimed method is implemented as follows. Simulating the control signals, i.e. the command messages (signals), simulating pointing missiles at the target on the course and pitch, as well as, for example, signals that mimic the rotation of the missile angle of roll (in case of rotation of the missile roll), served on the equipment guided missile. Simultaneously simultaneously serves the same simulating the control signals to the processing unit commands. Compare the current (changed) value of control commands with output equipment guided missile and block the formation of teams according to their size, respectively, at the rate and pitch, while the values of the control command to the output unit of the formation is of commands, equal to a given, and the difference from the corresponding values at the output of the equipment guided missile by an amount not exceeding the tolerance, the decision about the health of the equipment. The tolerance may, for example, be set different for different types of tests.

Therefore, the command message at the rate and pitch, for example, signals with VIM, proceed simultaneously and synchronously as for the equipment guided missile and block the formation of teams, where they form the management team, which without decoding, for example in the form of a relay pulse-width modulated (PWM) signal, compares, when this error WIM have the same magnitude and the same effect on the form of (duty cycle) of the relay signal, thus they do not affect the accuracy of measurement, as mutually offset.

The invention is illustrated by drawings (figures 1, 2 and 3). Figure 1 shows the structural electrical diagram of the automated system parameters control equipment guided missiles, where 1 - simulator control signals (ICS), 2 - equipment guided missile (AURAS), 3 - forming unit control commands (BC), 4 - block comparison (BS), 5 - indicator (S).

Figure 2 shows as an example the implementation of structural circuit diagram of the block comparison 4, where 6 - logicist the I scheme "exclusive OR" (IP), 7 Converter ″duration - code″ (PR), 8A and 8b, the first and second pulse shapers respectively (PHI1 and PHI2), 9a and 9b, the first and second ″RS″triggers respectively (T1 and T2), 10 - pulse counter (C), 11 - logic "OR" (BOS), 12 - oscillator (AG).

Figure 3 shows diagrams of the signals, where ″and″ - signal on the first input unit of comparison 4, i.e. at the first input logic "exclusive OR" 6, "b" signal on the second input unit of comparison 4, i.e. at the second input logic "exclusive OR" 6, ″″ - output logic "exclusive OR" 6, ″d″ - signal at the output of the first pulse shaper 8A, ″d″ - signal at the output of the second pulse shaper 8b, ″e″ - signal (analog) output pulse counter 10, "W" signals at the output of the second ″RS″-trigger 9b.

In the automated system parameters control equipment guided missile consistently enabled simulator control signals 1, equipment guided missile 2 and unit 4 comparison. Signal input processing unit commands 3 is connected with the output of the simulator control signal 1, and the output processing unit commands 3 is connected to the first input unit of comparison 4, the output of which is connected to the input of the indicator 5. Additionally, the clock input of the processing unit 3 teams can is be connected to a clock output equipment guided missile 2 (depicted in figure 1 by the dotted line).

Simulator control signals 1 can be performed, for example, as signal simulator command message and signal the rotation of the rocket in the prototype (together). Equipment guided missile 2 may consist of cascaded receiver, instrument separation channels and decoding Converter command with the tilt sensor and the steering actuator and to be performed, as in the prototype. The forming unit control commands 3 can be performed similarly as equipment guided missile 2, thus to reduce errors caused by asynchronous operation of the equipment guided missile 2 and the processing unit 3 teams, their work can be fully synchronized, which share a common clock stable frequency oscillator pulses located in the equipment guided missile 2, which can be used, for example, in the apparatus of the separation channels and decoding, as well as in the formation PWM relay signal. Indicator 5, for example - led.

An example of execution of a block of 4 comparison is shown in figure 2. Logic "exclusive OR" 6, the first 9a and 9b of the second ″RS″triggers pulse counter 10, the logic circuitry "And" ordinary digital circuits, such as a series of 564. First 8A 8b and the second pulse shapers, such as standby multivibrators, the oscillator 12 generator is stabilizirovannykh frequency pulses.

Declared automated system parameters control equipment guided missile works as follows. In the initial state, for example, through a differentiating network to the switching on of the power source is formed by a single pulse, which on input "R" sets the zero logic level at the output of the second ″RS″-trigger 9b (plot ″W″ figure 3).

When forming the simulator control signal 1, for example signals of the rotation of the rocket on the corner of the roll and feed them to the inputs of equipment guided missile 2 and the processing unit 3 teams, they are one and the same time a signal is generated to beginning work equipment guided missile 2 and block the formation of teams 3 through the fixing torque [RF Patent №2242698 IPC 4 F 41 G 7/24, F 41 B 15/00].

When filing with the simulator control signals 1 signal command message to the inputs of equipment guided missile 2 and the processing unit 3 teams on their outputs are generated relay PWM signals (commands), similarly as in the prototype [RF Patent №2243494], which are shown respectively in plots ″and″ and ″b″ 3. These signals are sent to first and second inputs of the logic exclusive-OR 6 which are formed differential pulses (plot "in figure 3). Duration differential pulses equal to the difference d is of telestai input signals, and their value is directly proportional to the magnitude of the error in the period T.

Differential pulse output logic "exclusive-OR 6 is fed to the input of inverter ″duration - code″ 7, i.e. on the first and second pulse shapers 8A and 8b, respectively. The first pulse shaper 8A forms from leading edge pulse (plot ″d″ figure 3), which goes to the "R" input of the pulse counter 10 and sets its output (all bits zero logical level (plot "e" in figure 3, which shows an analog signal). At the same time the pulse from the output of the first pulse shaper 8A enters the "S" input of the first ″RS″-trigger 9a and sets at its output a single logical level, which is supplied to the first input of the logic "And" 11 and permit the passage of pulses from the output of the oscillator 12 at the counting input "C" of the pulse counter 10.

The pulse counter 10 begins by the number of pulses received at its input. A second pulse shaper 8b forms from the trailing edge of the input pulse (plot "in figure 3) impulse (plot ″d″ figure 3), which goes to the "R" input of the first RS-flip-flop 9a and sets at its output a zero logic level, which prohibits the passage of pulses from the output of the oscillator 12 at the counting input "From" account is the IR pulses 10. The pulse counter 10 stops the account and keeps its state until the arrival of the next pulse, shown in the plot ″d″ figure 3, then the whole process repeats again.

Previously installed on the "R" input on the output of the second RS-flip-flop 9b zero logic level. When the output of the pulse counter 10, for example at its second discharge unit logical level (even briefly), he will arrive at the "S" input of the second ″RS″-trigger 9b and install at its output a single logical level (plot "W" in figure 3), which will arrive on the indicator 5 and adds it to the end of the process control settings that will match with the marriage.

Since the emergence of the output of the second discharge pulse counter 10 single logical level corresponds to the duration of the four periods of repetition of the pulses at the input of the pulse counter 10, the value will be the value of tolerance. To avoid errors due to the initial phase of the signal output from the oscillator 12, instead you can apply a pulse signal with a clock output equipment guided missile 2.

As follows from the above, for the normal functioning of the claimed technical solution is required to confirm compliance with the control commands given to subject the unit formed the Finance teams 3 periodic inspection, for example once a year. These one-time check can be performed, for example, conventional means of control at a very considerable cost of time or inspections as part of the control loop rocket flight on physical and mathematical models in the evaluation of the characteristics (parameters) block the formation of teams 3 and so on

Thus, the claimed group of inventions increases the accuracy of the control parameters of the guided missile.

1. Method of monitoring the health of equipment guided missiles, which serves simulating the control signals for the equipment guided missiles, characterized in that at the same time synchronously serves simulating the control signals to the processing unit commands and compare the current values of the control commands with output equipment guided missile and block the formation of teams respectively at the rate and pitch, when the command value of the control output processing unit commands given equal, and the difference from the corresponding values at the output of the equipment guided missile by an amount not exceeding the tolerance, establish the operability of the equipment.

2. Automated control system of parameters of equipment guided missiles containing the indicator and connected in series with the equipment guided missile simulator signals from the management, characterized in that the input connected in series forming unit commands and block comparison, the yield of equipment guided missile is connected to the second input of the comparison, the output of the simulator control signals connected to the signal input processing unit commands, and the output of the Comparer is connected to the input of the indicator.

3. The automated system according to claim 2, characterized in that the second output of the equipment guided missile is connected to a clock input of the processing unit commands.



 

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The invention relates to defense systems and, in particular, to integrated control means guided missiles

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