RU2801840C1 - Device for preparing for rocket launch - Google Patents

Abstract

FIELD: rocketry.

SUBSTANCE: device for preparing for a rocket launch, comprising a switching module, a secondary power supply source for the switching module, a common power bus for pyroelements, a temperature control module, a memory module, a secondary power supply source for the memory module and a temperature module, while the switching module of the device additionally performs the functions of monitoring the integrity and initial state of the rocket components, receiving pyroelement control commands generated by a bipolar code of a certain type, executing the received commands after checking their compliance with the logical-temporal cyclogram of the rocket operation and removing the blocking of the executive bus by the rocket pyroelements by the external control system, and then by the device itself.

EFFECT: increasing the safety of rocket handling due to the introduction of digital control of its pyroelements and rocket means providing control and use of pyroelements.

1 cl, 1 dwg

Description

The invention relates to rocket technology and can be used to ensure safe interaction with the rocket during its periodic maintenance, pre-launch preparation and launch.

Due to the presence of pyroelements, combustible fuel, as well as damaging substances in the composition of the rocket, it belongs to the class of technical means of increased potential danger.

A device is known for implementing a method for simulating the interaction of a rocket with carrier equipment (RU, patent No. 2 414 746, IPC G06G 7/48, publ. digital data output according to GOST 18977-79, one-time command input-output module, information display module, information exchange parameter setting module, digital exchange error setting module. This device allows you to conduct a reliable simulation of the interaction of the rocket with the equipment of the carrier, which has one of two possible information exchange interfaces (GOST 18977-79 or GOST R 52070-2003), providing a large amount of checks and a large depth of control due to the control of the logical-temporal cyclogram, as well as through the use of modern software and modern element base.

Also known is a device for checking the launch and zeroing circuits of blocks of unguided aircraft missiles, containing a measuring unit, a block of start circuits, a zeroing unit and a check indication unit (RU, patent No. 2 716 375, IPC F41F 3/065, publ. No. 8). The device allows to reduce the time of testing the launch circuits of unguided aircraft missiles with full control of the weapon control system and improve the manufacturability of the cold zeroing process.

The disadvantage of both devices is that they are essentially technological equipment designed to diagnose control channels and information exchange with missiles, belong to the category of information-measuring systems and are not directly involved in missile control. Since these devices provide for performing only autonomous checks of the missile control circuits or working out the logical-temporal cyclogram of interaction with the missile simulator, the way to increase the level of safety when handling a missile, implemented with their help, is indirect.

In addition, the closing of the starting circuits in these devices is carried out by switching the supply voltage, which does not provide complete protection against the occurrence of interference and false commands.

As a prototype, the “Device for controlling and detonating squibs” (RU, patent No. 2 493 603, IPC G08B 17/06, publ. squibs, remote switches, first and second switching units with key elements, current-limiting resistors and control relays. The device allows you to control the state and undermine the squibs one by one and sequentially. At the same time, the increase in safety when working with pyrotechnics is achieved due to the galvanic isolation of the monitoring and control circuits, as well as the two-stage switching of the squibs power bus.

The disadvantages of the prototype device include the following factors.

1) Commands to undermine the squibs are formed by switching the power bus current to the control relays and do not depend on the shape and characteristics of the control signal.

2) The device does not provide diagnostics of the rocket equipment, which is necessary before the detonation of the squib, which is part of the launch operations.

3) The device does not include technical means of recording information on the progress of preparatory and launch operations, which does not allow to control the process of performing the logical-temporal cyclogram of the rocket operation.

The objective of the proposed device is to improve the safety of handling a rocket through the introduction of digital control of its pyroelements and rocket means that provide control and use of pyroelements. The technical result is achieved:

- performing preliminary diagnostics of the health of both the pyroelements themselves and the rocket devices that ensure their use;

- formation of pyroelement power supply buses according to code commands from an external control system with the complication of the control signal shape;

- monitoring the compliance of incoming commands with the logical-temporal cyclogram of the rocket operation;

- implementation of a system for documenting received and executed commands.

The essence of the device is illustrated by a block diagram shown in Fig. 1. The device includes:

1. Switching module (MK);

2. Memory module (MP);

3. Temperature control module (MT);

4. Secondary power supply source of the switching module (IVEP MK);

5. Secondary power supply for the memory module and temperature module (IVEP MP and MT).

The switching module is designed for:

- receiving code information from the control system (CS) via the main exchange channel (MCC), its conversion and the formation of relay commands to the missile's executive equipment;

- issuing commands for generating control signals, receiving relay signals and converting them into an information code for transmission via MCO to the control system;

- switching of terminal resistors to the MKO line when performing launch operations with a rocket to avoid short circuits;

- formation or removal of blocking in the circuits for issuing all commands according to the code information on the MCO and the relay signal from the control system.

The MC provides control of the serviceability of relay command generators, control signal generators and relay signal receivers, as well as voltage control on the command issuing bus.

The exchange over the interface based on GOST R 52070-2003 is carried out by the MK over two buses of the redundant channel. A 5559IN73T integrated circuit is used as a transceiver device, which converts the signal from the TIL6 V transformer into a signal with a level of 3.3 V and back into a signal with a level from 18 to 27 V. The TIL6 V transformers are connected directly to the MKO SU input line through protective resistors with a nominal value of 56 .2 ohm, providing current limiting.

The relay command generators in the MC are implemented in such a way that two logical signals are used to control one key. When the key is turned on, the logical signals are two meanders with a frequency of about 100 kHz, operating in antiphase. When turned off, both logic signals take the same constant level. Each of the two logical signals is fed to the buffer element (Schmidt trigger) 5514BTs2T1-14. The outputs of the buffer elements 5514BTs2T1-14 are connected to the terminals of the transformer BTI6-112 V, each to one of the ends of the winding. Transformers carry out voltage matching to control the gate of field-effect transistors 2P7235AS and galvanic isolation of the digital part of the module from the output stage of the switch. At the output of BTI6-112 V transformers, rectifier diodes 2D814A1 and current-limiting resistors with a nominal value of 390 Ohm are connected in the gate control circuit of 2P7235AS field-effect transistors. Shunt resistors are connected between the gate and the source, which are necessary to discharge the gate capacitance of the 2P7235AS transistors when they are turned off. A resistor is included in the source circuit of the 2P7235AS field effect transistor, which limits the maximum output current. Such a scheme eliminates the possibility of false issuance of a relay command when the microcontroller freezes.

The formation of MK control signals is carried out using a buffer element (Schmidt trigger) 5514BTs2T1-14, from which a control voltage is supplied to the 249KP15BR microcircuit, switching a voltage of 27 V to the output contact of the control signal. A resistor with a nominal value of 390 Ohm limits the current in the input circuit 249KP15BR, another resistor limits the current in the output circuit of the control signal shaper.

Reception of control signals is made according to a similar scheme. A distinctive feature is the use of a 2S515A1 zener diode, which acts as a threshold element that limits the flow of current in the input circuit until a voltage of at least 15 V appears on it.

When a relay signal appears in the polling circuit (over 20 V), the 249KP15BR microcircuit switches the microcircuit polling bus to a low logic level (GND_OCH). In the absence of voltage in the input circuit or the presence of a voltage of less than 15 V, the 249KP15BR microcircuit at the output disconnects the microcircuit polling bus from a low logic level, while the microcircuit polling bus is connected to the power supply through a current-limiting resistor, which is perceived by the controller as a high logic level.

The switching of terminal resistors to the MCO line is performed by the command of the bus controller. In this case, other MCO subscribers are disconnected from the device output side, and terminal resistors with a nominal value of 75 Ohm are switched to ensure stable communication between the device and the bus controller. The terminal resistors are switched through the REA15 relay, which is controlled by the 1986 VEZT microcontroller using the 249KP15BR optocoupler.

The presence of the 1986 VEZT microcontroller in the MC, which processes incoming commands, makes it possible to implement in the working program of the proposed device algorithmic control of the sequence of issuing control commands according to the gating principle. This approach makes it possible to exclude the execution of individual commands issued in isolation from the time diagram of the normal operating mode of the rocket in order to activate its pyroelements.

A two-stage blocking in the command issuing circuits is necessary to prevent unauthorized issuance of relay commands by the MC.

The blocking is released by sequential issuance of the relay command of the control system and the command generated directly by the device. In the absence of voltage from the control system in the polling circuit, the 249KP14BR microassembly, which has normally closed contacts at the output, bypasses the transistor control circuit (gate-source), blocking the transistor from opening even in the presence of input voltage. If there is a signal from the control system at the input of the external blocking unit, the 249KP14BR microassembly opens the contacts, and the transistor control circuit begins to be controlled similarly to the key of the relay command generator. Inside the device, blocking is organized similarly to the formation of relay commands, except for the use of a high-current field-effect transistor 2P7152A.

The memory module is designed for:

- storage of digital information necessary for the operation of the device in non-volatile memory, as well as storage of data for documenting operations performed with the rocket;

- data transfer from non-volatile memory to the control system via MCO;

- receiving, storing and transmitting data about the rocket in the format of an electronic form.

After the beginning and until the end of the operation of the device in the main mode, the MP receives data from the MCO, being a line monitor, and writes them to memory. Reading the recorded information is carried out via the same interface as the reception. If it is necessary to transfer the recorded data, the MP becomes a terminal device and transmits them via the MCO.

1636РР6У memory chips are used for data storage, 5514BTs1T3-245 chips are used for memory addressing, and a 5514BTs1T2-138 decoder chip is used to expand the memory address space. The MP construction architecture allows, if necessary, a hardware increase in the amount of permanent memory used by the device.

The temperature control module ensures the control of temperature values during storage of the missile, their recording in non-volatile memory and transmission to the control system via MCO.

The MT is built on a 1986 BE4U microcontroller; a 5400TP125-010 digital integrated temperature sensor is used as a temperature sensor, connected to the microcontroller via a 1-Wire interface.

The frequency of monitoring temperature parameters is determined by the operating program of the 1986 BE4U microcontroller. To bind the control points of the measured temperature parameters to time, a real-time clock is used, implemented in the MT by the hardware of the 1986 BE4U microcontroller. Temporary storage of the measured control points of the temperature parameters is carried out in the 1636PP6U memory chip connected via the SPI interface to the 1986 BE4U microcontroller.

The MT is powered independently from an external chemical current source and does not affect the normal operation of the device.

The transfer of temperature data to the MP is carried out via a galvanically isolated UART interface.

Secondary power supplies MK, MP and MT are designed to provide DC voltage MK, MP and MT 3.3 V / 1.21A and 5 V / ODA, depending on the connected load. IVEP modules are powered from the primary DC network with a voltage of 27 V. IVEP modules are galvanically isolated from the primary power supply. The outputs of the module are galvanically separated from each other. The nominal voltage of 3.3 V organizes the power supply of the MP, MT and the main part of the MK. The rated voltage of 5 V organizes the power supply of the test part of the MK.

The operation of the device is organized as follows.

In the initial state, IVEP MP and MT devices are connected to an autonomous chemical power source. With the established frequency, the MT of the device performs measurements of the missile storage temperature with registration of the measurement results on the MP. This information is used to assess the state of the pyroelements, allowing them to predict their failure in a timely manner and replace them.

During loading and subsequent storage of the rocket in the launcher, the operation of the device is carried out in cooperation with the external control system. During periodic scheduled maintenance, the CS supplies power to the IVEP MK device. The MC of the device performs self-diagnostics and informs the MCO control system about its readiness for operation. According to the commands received from the control system via the MCO, the MC of the device checks the initial state of the dangerous components of the rocket, including the pyroelements. Upon receipt of each next command, the MC analyzes its compliance with the course of execution of the time cyclogram of the rocket preparation. A command that does not correspond to the given cyclogram is not accepted for execution. The results of the checks are issued according to the MCO in the control system and are involved in determining the serviceability of the missile as a whole.

When performing pre-launch operations, the operation of the device is generally similar to operation during routine control. After the diagnostics is completed and the control system is determined to be in good condition, the transition to the launch cycle operations is performed. The control system removes the first stage of protection from the pyroelement power bus. On command from the control system, issued via the MCO, the MC of the device removes the second stage of protection from the pyroelement power bus. Starting from this moment, it becomes possible to perform irreversible operations associated with the undermining of pyroelements. On commands from the control system issued by the MKO, the MC of the device undermines the pyroelements of the fixing devices that hold the rocket elements in their original state, transferring them to the starting state. The rocket launch is also carried out on command from the CS. Upon receiving a command to launch a rocket, the MC of the device switches the terminal resistors to the MCO line to prevent its short circuit and undermines the pyroelements of the rocket launch system. The start cycle commands are also monitored by the MCU for compliance with the required timing diagram.

Regardless of the operating mode of the device, all commands received from the control system and operations performed by the MC for their execution are documented in the device's MP in the format of an electronic missile log. This information allows you to perform analysis and identify deviations in the operation of the device or CS.

Within the specified modes of operation, the claimed device provides:

- information (code) interaction with the control system via a redundant exchange channel based on the main serial interface of the system of electronic modules;

- formation and issuance of relay signals to control the initial state of the rocket;

- reception of relay signals of the "dry" contact type and the formation of the corresponding code receipts for transmission to the control system;

- formation of circuit blocking of the pyroelement activation bus;

- formation of high-current relay commands for switching "positive" and "minus" potentials of the pyroelement activation buses upon receipt of the corresponding code commands from the control system;

- control of circuits for issuing relay commands;

- periodic temperature control and storage of temperature values in a non-volatile memory, with reference to time for the analysis of temperature differences during storage;

- self-testing as part of the missile during routine control.

The safety of performing periodic maintenance operations, pre-launch preparation and rocket launch is ensured by the following technical solutions of the proposed device.

1) The use of a digital control channel, which requires the formation of pyroelement control commands in the form of a bipolar code of a strictly defined format. This technical solution practically eliminates the issuance of false commands, the occurrence of which is possible when controlling pyroelements with potential commands with the issuance of direct current with a certain voltage level through the control circuits. The occurrence of abnormal issuance of potential commands in the latter case is possible, for example, due to a malfunction of the control equipment or the action of the electromotive force of self-induction.

2) The use of the pyroelement executive bus with its two-stage blocking, which guarantees the absence of voltage in the pyroelement control circuits until the moment of irreversible launch operations with the rocket. In this case, the removal of blocking is possible only upon receipt of the sanction of the control system and the simultaneous formation of a sign of readiness of the device itself to perform the starting cycle.

3) Control of the sequence of issued control commands, excluding the possibility of using pyroelectric elements when issuing a separate command in isolation from the timing diagram of the mode being carried out. Taking into account the fact that actuation of pyroelements refers to irreversible operations and is carried out at the final stage of pre-launch preparation, the possibility of triggering pyroelements due to the formation of false commands or the deliberate issuance of individual regular commands is excluded.

4) Implementation in the device of an automatic documentation system that allows you to set the date, time and some circumstances under which the issuance or attempted issuance of commands to actuate the pyroelements was carried out. This information is material for researching the reasons for the issuance of abnormal commands, with the identification of a corresponding malfunction or the identification of officials who attempted the unauthorized use of rocket pyroelements.

Claimed as an invention "Device for ensuring the safe launch of a rocket" has a novelty and industrial applicability.

Claims (1)

A device for preparing for a rocket launch, containing a switching module, a secondary power supply source for the switching module, a common power bus for pyroelements, characterized in that the device additionally includes a temperature control module that performs the functions of controlling the storage conditions of the rocket, a memory module used in conjunction with the switching module for registering the commands received and executed by the device and the temperature control module for registering the results of temperature measurement, the secondary power supply source for the memory module and the temperature module, while the switching module of the device additionally performs the functions of monitoring the health and initial state of the rocket components, receiving pyroelement control commands generated by a bipolar code of a certain type, execution of the received commands after checking their compliance with the logical-temporal cyclogram of the rocket operation and removing the blocking of the executive bus by the pyroelements of the rocket by the external control system, and then by the device itself.

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