RU2414669C1 - Method of recording and processing digital information when checking missiles - Google Patents

Abstract

FIELD: information technology.

SUBSTANCE: method is meant for multichannel recording and processing information when checking missiles on checkout equipment, as well as when carrying out interfacing with ship, ground and aircraft carriers. The recording apparatus is connected to a data exchange bus and voltage is applied across at least one inspected missile. Information from the data exchange bus is recorded and recorded data are stored in the storage module of the recording device. Further, the recorded data are converted to physical quantities and binary, octal and hexadecimal codes. The results are stored in the storage module of the recording apparatus. The results are transmitted to the information display module and a conclusion is made on intactness of the missile as a whole. Operation of the recording apparatus does not have an effect on data exchange between the missile and checkout equipment or between the missile and the carrier equipment.

EFFECT: use of the disclosed method enables the engineer to assess the quality of functioning of the missile as a whole and analyse data exchange in accordance with the protocol for communication with the carrier and the inner protocol for information interaction with missile subsystems.

9 cl, 3 dwg

Description

The invention relates to the field of information-measuring equipment and is intended for operational control of the information interaction of a complex product, such as a rocket, with the equipment of carriers (sea, aviation or ground) or with the equipment of test complexes.

The prior art method of automated ground control of an aircraft rocket (patent RU, F41G 7/00, No. 2231733), in which voltage is applied to an automated test complex and a controlled rocket, a stimulus delivery program is launched, a rocket response to these stimuli is measured, and missile performance test assessment. The disadvantages of this method are the low reliability and the long verification time.

The prior art also knows a method for testing a rocket at a technical position (US Patent No. 5721680, MKI F42B 15/01), in which the rocket is monitored on an operational basis and an operational conclusion is made about the health of the rocket as a whole, and in the event of a malfunction of the rocket as a whole, they are found defective rocket component. The disadvantage of this method is the insufficient depth of control of the state of the rocket and its components.

The objective of the invention is to eliminate the above disadvantages and create a universal method of recording and processing digital information when checking missiles, allowing for deep and operational control of the progress and results of a comprehensive check of missile systems. This method allows to reduce the time of rocket testing, as well as to analyze the information exchange for compliance with the communication protocol with the carrier and the internal protocol of information interaction of the product subsystems.

The problem is solved due to the fact that the registration and processing of digital information during the rocket verification is carried out as follows: connect the registration device to the information exchange bus, apply voltage to at least one monitored missile, register information from the information exchange bus, place the registered data in the module storage device registration, convert the recorded data into physical quantities and binary, octal and hexadecimal codes, place the result you are in the storage device registration module, transmit the results on the display unit, give opinion on the health of the rocket as a whole.

In the first particular case, the objective of the invention is solved due to the fact that they additionally issue a conclusion on the serviceability of the components of the rocket.

In the second particular case, the objective of the invention is solved due to the fact that before registering and processing digital information, the registration device is self-tested by connecting the “Self-control” plug to the input-output connector of the registration device.

In the third particular case, the objective of the invention is solved due to the fact that additionally secondary processing of the data is carried out.

In the fourth particular case, the objective of the invention is solved due to the fact that the rocket is placed in a transport and launch container.

In the fifth particular case, the objective of the invention is solved due to the fact that the information exchange is carried out between the rocket and the test equipment.

In the sixth particular case, the objective of the invention is solved due to the fact that the information exchange is carried out between the missile and the ship's automated control system.

In the seventh particular case, the objective of the invention is solved due to the fact that the information exchange is carried out between the rocket and the equipment for preparing and launching the carrier.

In the eighth particular case, the problem of the invention is solved due to the fact that they transmit the registered data and the results to specialists for further analysis.

The introduction of additional health checks of rocket components, self-testing of a recording device, and secondary data processing increase the depth of rocket control.

The invention is illustrated by drawings, on which:

figure 1 is a structural diagram of a registration device;

figure 2 - diagram of one of the options for connecting the registration device to the bus information exchange according to GOST 18977-79 when checking the rocket using the test equipment at a technical position;

figure 3 - diagram of one of the options for connecting the registration device to the bus information exchange according to GOST 18977-79 when checking the rocket in the transport and launch container on the ship.

In figure 1, 2, 3 are indicated:

1 - input-output connector;

2 - input-output module;

3 - source data preparation module;

4 - module for recording channel data;

5 - channel data storage module;

6 - module for primary processing of channel data;

7 - module secondary processing of channel data;

8 - test editor module;

9 - hardware timer module;

10 - file manager module;

11 - matching device;

12 - information display module;

13 - connector for an external recording device;

14 - rocket;

15 - test equipment;

16 - a rocket in a transport and launch container;

17 - ship automated control system;

18 - plug "Self-control."

The proposed method consists in connecting a registration device to the information exchange bus in accordance with GOST 18977-79, supplying voltage to at least one controlled missile, signals from the information exchange bus in accordance with GOST 18977-79 through the matching device 11 to the input-output connector 1, from the input-output connector 1, the signals are fed to the input-output module 2 and to the source data preparation module 3, the signals from the input-output module 2 are fed to the channel 4 data recording module. Also, the input of the channel 4 data recording module is post the signals from the hardware timer module 9, which synchronizes the operation of the I / O module 2 due to the formation of a hardware interrupt at a given frequency, during the processing of which the I / O device 2 is interrogated and digital information is recorded, are dropped.

In the data recording module of channel 4, information is recorded using the registration program. Channel 4 data recording module can consist of three parts: inertial system data recording module, homing head registration module and radio altimeter data recording module. The signals from the channel 4 data recording module enter the channel 5 data storage module, from the channel 5 data storage module enter the channel 6 primary data processing module, in which the received data is converted into physical quantities, as well as into binary, octal and hexadecimal codes. The received data also goes to the channel 5 data storage module.

The processing results are text files that are written next to the source file. Data from the channel 5 data storage module enters the text editor module 8, which generates information for displaying the registered data obtained after processing on the information display module 10.

When implementing the method before registering, it is possible to conduct a self-test of the registration device. To do this, connect the "Self-control" plug to the I / O connector of device 1, turn on the device, switch to the "Self-control" mode of the main menu and display the result of the check.

When implementing the method, additional secondary data processing is possible, while the information from the channel 5 data storage module enters the channel 7 secondary data processing module, in which the received data from physical quantities are converted into values convenient for subsequent analysis. The obtained results also go to the channel 5 data storage module.

When implementing the method, it is possible to test the rocket located in the transport and launch container.

When implementing the method, it is possible to test the rocket at a technical position with the help of test equipment, while the data exchange bus in accordance with GOST 18977-79 connects the missile and test equipment. Channel 4 data recording module can consist of the following parts: inertial system data recording module, homing head registration module, radio altimeter data recording module, and also data recording module of control and testing equipment. The recorded data allows us to assess the health of the rocket and its components, as well as to give an opinion on the compliance of the data of the control and testing equipment with the protocol of information interaction.

When implementing the method, it is possible to test a rocket located on a ship in a transport and launch container, while an information exchange bus according to GOST 18977-79 connects the rocket and the ship's automated control system (KASU). Channel 4 data recording module may consist of the following parts: inertial system data recording module, homing head registration module, radio altimeter data recording module, and also KASU data recording module. The recorded data allows us to evaluate the health of the rocket, as well as give an opinion on the health of the rocket and KASU.

When implementing the method, it is possible to test a rocket located on an aircraft carrier, for example, on an airplane, while an information exchange bus according to GOST 18977-79 connects the rocket and the equipment for preparing and launching the aircraft carrier. The channel 4 data recording module may consist of the following parts: inertial system data recording module, homing head registration module, radio altimeter data recording module, and also the data recording module of the aircraft preparation and launch equipment.

When implementing the method, it is possible to record data from the connector for an external recording device 13 of the recording device, while data from the data storage module of channel 5 is transferred to the file manager module 10, which further records information on external data storage devices (disk or flash memory) through a connector for an external recording device 13. Then this data can be transferred to specialists to find out the cause of the malfunction.

When testing a rocket at a technical position, you have access only to the information that can be obtained from the external connectors of the rocket. The parameter and command codes transmitted by the digital control system to the product are sequentially fed to the input-output connector of each channel, and the operation of the onboard control complex in the normal mode is checked and the interaction of the onboard missile control complex with the verification system is checked. The results of the verification are presented on the information display module.

The registration device used in the implementation of this method may include a mobile computer of the type "Fieldworks" or "Kontron" in the climatic version. The PC429-3-44 (88) board in accordance with GOST 18977-79 from ELKUS company can be used as an input-output module, and the ISP DAS board DIO-64 board can be used as a hardware timer module.

The proposed method of recording and processing digital information is intended for multichannel registration and processing of information when checking missiles at a technical position or at a test station; for this, the recording device is connected to the data exchange bus in accordance with GOST 18977-79, while the operation of the registration device does not affect on the process of exchanging information during missile inspections. This method allows to reduce the time of missile verification, as well as to analyze the information exchange for compliance with the communication protocol with the carrier and the internal protocol of the information interaction of the product subsystems, and check the interaction of the rocket and the test equipment, or missiles and various types of carriers (sea, aviation or land ) Testing a rocket using ground-based carriers is similar to checking with marine carriers, only instead of KASU an automated control system is used.

The existing elemental base allows you to implement the proposed method, which characterizes the invention as industrially applicable.

Claims (9)

1. A method of recording and processing digital information when testing a rocket, in which the registration device is connected to the data exchange bus, voltage is supplied to at least one controlled missile, information is recorded from the information exchange bus, the registered data is stored in the storage module of the registration device, and the registered data is converted data in physical quantities and binary, octal and hexadecimal codes, place the results in the storage module of the registration device, transmit the result ultaty on the information display module, issue a conclusion about the health of the rocket as a whole. 2. The method according to claim 1, in which additionally issue a conclusion on the health of the components of the rocket. 3. The method according to claim 1, wherein before registering and processing the digital information, the registration device is self-tested by connecting the “Self-control” plug to the input-output connector of the registration device. 4. The method according to claim 1, in which additionally carry out the secondary processing of data. 5. The method according to claim 1. in which the rocket is placed in a transport and launch container. 6. The method according to claim 1, wherein the information exchange is carried out between the rocket and the test equipment. 7. The method according to claim 1, wherein the information exchange is carried out between the rocket and the shipboard automated control system. 8. The method according to claim 1, wherein the information exchange is carried out between the rocket and the equipment for preparing and launching the carrier. 9. The method according to claim 1, wherein the transfer of registered data and the results obtained to specialists for further analysis.

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