RU33748U1 - Spacecraft information display system - Google Patents

Abstract

1. A spacecraft information display system comprising a light and sound alarm subsystem consisting of a signal board, a central light, a sound speaker, a sound alarm and central fire control unit, a sound signal generator unit and a central fire control signal with integrated health monitoring generators and, accordingly, with a failure sensor for sound generators, mute buttons and central lights, with one input group in the signal board it is connected to alarm sensors of emergency events, part of the inputs of the sound alarm and central fire control unit is connected to alarm sensors of emergency events, and one of the inputs of this block is connected to the mute button and the central fire, and the outputs of the same block are connected to inputs a block of generators of sound signals and a central fire control signal, one of the outputs of which is in turn connected to the sound speaker, the second to the astronaut's headset communication system, the third to the central fire input, a control button for light and sound alarms, the outputs of which are connected to the inputs of the signal board and the control unit for sound alarms and central lights, a unit for generating commands for selecting systems of the first group, the outputs of which are connected to inputs, for example, horizontal buses of the command matrix for controlling system units the first group, the unit for generating control commands for the aggregates of the systems of the first group, the outputs of which are connected respectively to the vertical buses of the command matrix of the control matrix ag

Description

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2 2 2 Space Information Display System A spacecraft information display system is designed to control and manually control the systems and processes of a transported manned spacecraft.  The proposed utility model relates to the field of spacecraft manned spacecraft control systems.  The Soyuz-TM spacecraft information display system is known, the block diagram of which is shown in FIG. 1.  / YU. A.  Tyapchenko, Yu. S Karpov, Yu. F.  Alexandrov et al.  Integrated SOI of the Soyuz-TMA spacecraft and the manual control console of the Russian segment of the ISS Alpha // Sat.  Proceedings of the 5th international scientific. -tech.  Symposium “Aviation Technologies of the 21st Century.  Safety is the key to success.  August 17-22, 1999  Volume 2  - TsAGI  Zhukovsky.  - pic 2, p. 584 /.  Where depicted: 1. Subsystem of light and sound alarm - warning alarm 2. Signal board.  3. Sound alarm and central fire control unit.  4. A block of generators of audio signals and a signal for controlling the central fire.  5. Sound speaker.  6. Central fire.  7. Headset communication system of astronauts; 8. Mute and central fire button 9. The first command-signal console with a matrix method of selecting control objects.  10. A block of signaling devices for monitoring the state of aggregates of systems of the first group.  eleven. The unit for generating commands for selecting systems of the first group.  12. Block for generating control commands for units of systems of the first group 7MKH: B64G1 / 12 of work 14. The second command-signal console with a matrix method of selecting control objects.  fifteen. A block of signaling devices for monitoring the state of aggregates of systems of the second group.  16. The unit for generating commands for selecting systems of the second group.  17. The unit for generating commands for controlling aggregates of systems of the second group 18. Command matrix for controlling aggregates of systems of the second group.  19. Button for controlling light and sound alarms.  20. The block of digital indicators of the manual input panel.  21. A device for generating digital information for inputting data into the first and second blocks of manual input of information.  22. The first block of manual input of information 23. The second block of manual input of information 24. Onboard ship systems.  25. TV type video monitor.  26. TV system 27. A unit for converting the analog parameters of systems into a television signal for displaying information on a video monitor in a form convenient for astronauts.  28. Block switching and calibration of analog parameters of on-board systems.  29. Analog sensors on-board systems.  thirty. Alarm sensors of emergency events.  31.  Digital indicator of the stock and fuel consumption of the propulsion system of the ship.  32. Sensor pulse information about the stock and fuel consumption.  33. Voltage indicator of the onboard power supply system.  34. Current indicator in the power supply circuit of the power supply system.  35. Current and voltage sensors of the power supply system.  36. Bodies of operational management and issuance of commands important for the safety of astronauts.  37. Signal sensors of the state of units of on-board systems.    40. Software-temporary device.  41. The electrical circuit input to the information display system of the spacecraft television signal 42. An electrical circuit for outputting a television signal from a spacecraft information display system 43. Electrical circuits for signal input of analog sensors of on-board systems 44. Pulse information input circuit 45. Analog sensor signal input circuit 46. Signal information input circuits 47. Electrical impulse information input circuits 48. The first group of electrical circuits for digital information input into the spacecraft information display system.  49. The first group of electrical circuits for digital information output from a spacecraft information display system.  fifty. The second group of electrical circuits for digital information input into the spacecraft information display system 51. The second group of electrical circuits for digital information output from a spacecraft information display system. This system is characterized by the presence of: a light and sound emergency warning subsystem consisting of a signal board, a central light, a sound speaker, a sound alarm and central fire control unit, a block of sound and signal generators central fire control with built-in generator health monitoring and accordingly with generator failure sensor in the sound signals, the mute button and the central fire, moreover, one group of inputs of the alarm board is connected to the alarm sensors of emergency events, part of the inputs of the control unit for the audio alarm and central fire is connected to the alarm sensors of emergency events, and one of the inputs of this block is connected to the off button sound alarm and central fire, and the outputs of the same unit are connected to the inputs of the block of generators of sound signals and the control signal of the central fire, one of the outputs of which is in turn l is connected to the sound speaker, the second to the astronaut's headset communication system, the third to the central fire input, the light and sound alarm control buttons, the outputs of which are connected to the inputs of the signal board and the sound alarm and central fire control unit, the first command and signal console with matrix selection of control objects, which includes a panel of signaling devices for monitoring the state of the aggregates of the first group of systems, whose inputs are connected via electrical circuits for inputting signal information are connected to signal sensors of the state of the units of these systems, a block of buttons for generating commands for selecting systems of the first group, the outputs of which are connected to inputs, for example, horizontal buses of a command matrix for controlling units of systems of the first group, a block of buttons for generating commands of control for units of systems of the first group, the outputs of which are connected respectively, to the vertical buses of the command matrix for controlling the aggregates of systems of the first group, the second command and signal console with matrix selection of control objects, in which includes a panel of signaling devices for monitoring the state of aggregates of the second group of systems, the inputs of which are connected via electrical signal input circuits to the signal sensors of the state of the units of these systems, a block of buttons for generating commands for selecting systems of the second group, the outputs of which are connected to inputs, for example, horizontal command buses matrix control units of systems of the second group, a block of buttons for generating control commands on units of systems of the second group, the outputs of which are connected respectively vertical buses of the command matrix for controlling the aggregates of systems of the second group, information from the spacecraft information display system is connected to the inputs of the first and second blocks of manual input of information, a block of digital indicators, whose inputs are from the first and second groups of electrical circuits for digital information input into the space information display system the ship is connected to the outputs of the first and, respectively, second blocks of manual input of information, switching unit and calibration analog x parameters, the inputs of which are connected to the analog sensors of the on-board systems using the electrical signal input circuits, the unit for converting analog parameters to a television signal, the inputs of which are connected to the output of the switching and calibration unit of analog signals, and the output of the television information from the information display system through the electric circuit - to a television system, a television-type video monitor, the input of which is through an electrical input circuit into a television spacecraft information display system The signal from the on-board television system is connected to the television system, the voltage and current indicator is the indicator of the main parameters of the on-board power supply system, the inputs of which are connected to the power buses and the current sensor of the power supply system, operational controls and issuing commands important to the safety of the astronauts whose outputs are connected directly to the on-board systems, a space navigation indicator, the input of which is connected to the on-board program-time generator of second marks a device, a digital indicator of the fuel consumption of a propulsion system, the input of which is connected to the fuel consumption sensor using electrical impulse information input circuits, and an external view of the described display system is connected to the control output outputs of the program-time device using electrical impulse information input circuits work in the form of a remote control and is shown attached to the present application of FIG. 2 (the designations are indicated. This system has the following disadvantages: the system has a low level of fault tolerance due to the lack of redundancy of information display facilities, on-board systems controls, information exchange facilities with on-board computer systems, which significantly affects flight safety, the electromechanical navigation indicator does not provide display navigation parameters with a given accuracy when changing the angle of inclination of the orbit and when flying in orbits other than circular, and thereby It cannot serve as a means of determining the location of the ship relative to the ground, light and shadow, and the predicted place of landing of the ship on the ground, the device and the method of displaying information input to and from the onboard computer do not satisfy the ergonomic and flight safety requirements, connecting a video monitoring device to the switch television signals does not provide autonomy of the information display system and thereby reduces the reliability of the display system and its level of control suitability, the hardware for selecting analog parameters and converting them to a television signal is not adapted to flexibly change the way information is presented on the screen of a video monitoring device, the system does not have a connection to a telemetry monitoring system and thus does not provide remote monitoring of the display system and astronauts when monitoring teams, which makes it difficult to identify the causes of emergency situations in flight, the proposed system of displaying information This ship is characterized by the presence of: a light and sound alarm warning subsystem consisting of a signal board, a central fire, a sound speaker, a sound alarm and central fire control unit, an audio signal generator block and a central fire control signal with integrated control of the generators' operability and, accordingly, with a failure sensor sound signal generators, mute buttons and central fire, and one group of signal board inputs is connected to the alarm sensors of emergency events, part of the inputs of the sound alarm control unit and the central fire are connected to the alarm sensors of emergency events, and one of the inputs of this unit is connected to the button to turn off the sound alarm and central fire, and the outputs of the same block are connected to the inputs of the block of sound generators and a central fire control signal, one of the outputs of which is in turn connected to the sound speaker, the second to the astronaut's headset communication system, the third to the central fire input, button and control of light and sound signaling, the outputs of which are connected to the inputs of the signal board and the control unit of the sound signaling and central fire, the unit for generating commands for selecting systems of the first group, the outputs of which are connected to inputs, for example, horizontal buses of the command matrix for controlling units of systems of the first group, unit generating control commands for units of systems of the first group, the outputs of which are connected respectively to the vertical buses of the command matrix for controlling units of systems of the first group s, of the unit for generating commands for selecting systems of the second group, the outputs of which are connected to the inputs, for example, horizontal buses of the command matrix for controlling the aggregates of systems of the second group, respectively, are connected to the vertical buses of the command matrix for controlling the aggregates of the second soil systems, at the electrical cost of inputting signals from analog sensors on-board systems, electrical circuits for inputting signals of impulse and signal information of at least 5 ms duration, the first and second groups of electrical circuits for outputting digital information from a spacecraft information display system, the outputs of which are connected to the inputs of the first and accordingly second blocks of manual input of information, the first and second groups of electrical circuits for digital information input to the spacecraft information display system, whose inputs are connected to the outputs of the first and respectively second blocks of manual information input , switching unit and calibration of analog parameters, the inputs of which are connected to the analog sensors of on-board systems, unit. conversion of analog parameters, the first electrical circuit of the input of the spacecraft information display of the television signal from the on-board television system, the first electrical circuit of the output of the television signal from the spacecraft information display system to the television system, the indicator of the main object parameter, for example, the voltage indicator, the input of which is connected respectively, to the power buses of the on-board power supply system, operational controls and issuing commands, it is important x for the safety of astronauts whose outputs are connected directly to the onboard systems, characterized in that in order to increase the reliability and reduce the number of information display systems and increase the efficiency of astronauts in the system, the first and second control panels are computerized based on modern computing and information technologies, the first and second blocks of input of discrete signals, respectively, into the first and second control panels, the first and second blocks of output of discrete information, respectively essentially from the first and second control panels, the first and second multiplex communication channels, respectively, between the first and second control panels and the descent computer, a second circuit for transmitting television information from a space information display system to a television system, and a second circuit for inputting a television information from the television system to the spacecraft information display system, the first and second blocks for interfacing with the system telemetry control, the inputs of which are connected to the outputs of the first and second discrete information output units, the first and second groups of electrical circuits for transmitting information to the telemetry control system about the operation of the first and second control panels, respectively, which are connected to the outputs of the first and respectively the second pairing units with the telemetry monitoring system, and on the other - to the inputs of the telemetry monitoring system, the first and second pairing units, respectively with the first and second blocks of manual input of information, the inputs of which are connected to the outputs of the first and second blocks of output of discrete information, and the outputs to the first and second groups of electrical circuits for output of digital information, and, in each of the control panels entered: system unit with a set input-output and information exchange devices, a video processor, the television input of which is connected to the first electrical input circuit into the spacecraft information display system of the television signal from the on-board television system, the television output - to the first electrical circuit for outputting a television signal from the spacecraft information display system to the television system, and via a serial data exchange channel connected to the control unit system unit, a set of functional and digital keyboards for managing information on a video monitor including including to control the marker, enter digital data and generate control commands in the on-board system, which is connected to the system unit, the module is mult iplex channel of information exchange between the control unit system unit and the descent computer, which on the one hand is connected to the console system unit, and on the other hand, to the multiplex channel of information exchange between the control unit and the descent computer, sound speaker, the input of which is connected directly to one of the analog outputs of the system unit, the first and second control panels are connected between the oh through the channel for the mutual exchange of information, the moves of the first block The input of discrete signals into control lites is connected to the inputs of the system unit of the first control panel, and the inputs: to electrical circuits for inputting signals from sensors of pulse and signal information of a duration determined by the speed of the control unit system unit, for example, at least 5 ms, to additional outputs of operational control units and issuing commands important to the safety of astronauts, v vrykh connected to the outputs of the first block of manual input of information, alarm sensors of emergency events, generator failure sensor s sound signals, the outputs of the second block of input of discrete signals to the control panels are connected to the inputs of the system unit of the second panel, and the inputs: to the electrical circuits of signal input from sensors of pulse and signal information of a duration determined by the speed of the system block of the control panel, for example, at least 5 ms, additional outputs of operational control and issuing commands important for the safety of astronauts to the second group of electrical circuits for input into the space information display system for digital information, the inputs of which are connected to the outputs of the second block of manual input of information, signal sensors of emergency events, the sensor failure of sound generators, the inputs of the first block of output of discrete information are connected to the discrete outputs of the system unit of the first control panel, and the outputs to the inputs of the first and the second blocks of the formation of commands for selecting systems for control, the first and second blocks of the formation of control commands for system units, the control unit for sound alarms and central it, the first block of interfacing with the first block of manual input of information, aggregates of onboard direct control systems, the first block of interfacing with the telemetry control system, the inputs of the second block of output of discrete information are connected to the discrete outputs of the system unit of the second control panel, and the outputs to the inputs of the first and second units for generating control commands for system units, a second unit for interfacing with a second unit for manually entering information, units for on-board direct control systems, a second unit for interfacing with a telemetry control system, the switching unit and calibration of the analog parameters of the ship systems and the conversion unit of the analog parameters are combined into a single monoblock made in the form of a computer system with digital switching, calibration and information conversion, the inputs of which are connected to the analog sensors of the on-board systems, and the outputs are connected via information exchange channel with system units of the first and second control panels.  The essence of the proposed information display system and manual controls is illustrated by the structural diagram shown in FIG.  3.  The appearance of the console of the spacecraft information display system is shown in FIG. 4 (the notation in FIG. 3 and 4 are identical).  Where depicted: 1. Control panel 1.  2. Control panel 2.  3. Subsystem of light and sound alarm warning.  4. Sound alarm and central fire control unit.  5. Signal board.  6. Block of generators of sound signals and central fire control signal 7. Sound speaker.  8. Central fire.  9. Headset communication system of astronauts.  10. Mute button and central fire.  eleven. Button for controlling light and sound alarms.  12. Block switching, calibration and conversion of analog parameters of on-board systems, 13. Voltage indicator of the onboard power supply system.    fifteen. The first unit for inputting discrete signals to the system unit of the first control panel.  16. The second unit for inputting discrete signals to the system unit of the second integrated control panel.  17. The first discrete information output unit, 18. The second block of discrete information output.  19. The video monitor of the remote control.  20. The system unit of the control panel.  21. Sound speaker remote control.  22. Remote control video processor, 23. Functional and numeric keypad of the control panel.  24. Marker Control Keyboard 25. Module of the multiplex channel of information exchange.  26.  The first unit for interfacing with a telemetry monitoring system 27. The unit for generating commands for selecting systems of the first group.  28. Block for generating control commands for units of the systems of the first group.  29. The unit for generating commands for selecting systems of the second group.  thirty. Block for the formation of control commands for units of systems of the second group.  31. The second unit is interfacing with a telemetry monitoring system.  32. The first block is the pair with the first block of manual input of information.  33.  The second, a block for interfacing with the first block for manual input of information, 34. TV system 35. Analog sensors on-board systems, 36. Power supply system of the facility, 37. Pulse and signal information sensors, 38. Alarm sensors 39. Command matrix for controlling aggregates of systems of the first group.  40. Command matrix for controlling aggregates of systems of the second group, 41. Onboard ship systems, 42. The first block of manual input of information,

46. The first electrical input circuit in the display system of the information spacecraft television signal

47. The first electrical circuit for outputting a television signal from a spacecraft information display system

48. The second electrical circuit input to the display system of the information spacecraft television signal.

49. A second electrical circuit for outputting a television signal from a spacecraft information display system,

50. Signal input circuits for analog sensors on-board systems

51. Electric circuits for inputting pulse and signal information

52. The first group of electrical circuits for digital information output from a spacecraft information display system.

53. The first group of electrical circuits for digital information input into the spacecraft information display system.

54. The second group of electrical circuits for digital information output from the spacecraft information display system

55. The second group of electrical circuits for digital information input into the spacecraft information display system

The main components of the information display system, the structural diagram of which is shown in Fig. 3 and the appearance of the remote control in Fig. 4, are the first 1 and second 2 control panels and a subsystem of light and sound alarms 3. All three components in Fig. 3 grayed out.

The main means of information security for the crew is the light and sound alarm subsystem 3. It consists of: a sound alarm and central fire control unit 4, signal boards 5 with red (emergency), yellow (warning) or green (warning) signaling devices, generator block sound signals and control signal of the central fire 6. To the sound outputs of the block of generators 6 are connected the sound speaker 7 and the headset communication system of the astronauts 9. The output of the low-frequency generator with control signals connected to the central fire 8.

The electrical contacts of the mute button and the central fire 10 are connected to the control unit 4. The electrical contacts of the sound and light alarm control button 11 are connected to the inputs of all signaling devices located in the signal boards 5, to the inputs of the central fire control signal generator, which is located in the control unit 4 , to the input of one of the sound generators, which is also located in the control unit 4.

The inputs of the signaling devices of the signal boards 5 and the control unit 4 are connected to signaling (on-off) sensors of emergency events 38, for example, to sensors of a dangerous gas composition in the spacecraft’s cabin, a fuel remaining sensor, a pressure sensor below the permissible level, etc.

The next important component of the display system is the switching unit, calibrating and converting the analog parameters of the on-board systems 12. The analog signal sensors are resistive pressure sensors, thermistors, temperature sensors, voltage and current generators - sensors for measuring range, speed, angular position of a ship, and measurement systems gas composition, etc. These sensors are combined in block 35 in the diagram of FIG. 3, and in FIG. 1 (analog circuit) to block 29. In an analog system, a switching block is a block of multi-contact push-button switches (see pos. 28 in figure 2), in which resistors are built in to calibrate the measurement channels. In the analog system (see Fig. 1), all sensors are connected to the switch 28 using electrical circuits 43 (Fig. 1). After switching and connecting corrective resistors in the switch, the sensors are connected to the inputs of the conversion unit 27 in figure 1. All conversions are provided by hardware.

In the proposed system, all analog sensors using the same circuits (circuit 50 in FIG. 3) are connected to the inputs of the electronic unit for switching, calibrating and converting analog parameters 12, which is a computer system that is connected to the control panel via a single channel of mutual exchange 1 , and in the second - with a 2. hour remote control, it is baked, as in the analogue system, using a separate voltage indicator 13, the inputs of which are connected to the power supply system power supply buses 36 of the facility. Direct access to control objects has a special place in ensuring flight safety - these are the operational control and issuing commands important for the safety of astronauts 14. These are, as a rule, push-button controls. Many buttons have special hinged covers for protection against accidental pressures. In the analog circuit, the button press was not controlled. In the proposed system, one of the electrical contacts of each of the buttons 14 is connected to the inputs of the input blocks of discrete signals 15 and 16 for subsequent input of information into the control panels 1 and 2. The peculiarity of the technical solution of the proposed system is that it stores all the electrical connection circuits to on-board systems, sensors and blocks, except for the communication of the navigation space indicator (pos. 38 in Fig. 1) with the time-program device (pos. 40 in Fig. 1) and the system’s communication via the channel of temporary pulses for the clock from the same program time ennogo device (poz.40 in Figure 1). The control circuits of the stopwatch of the hours that the analog system had in the proposed system are stored and shown in Fig. 3 in the group of electrical circuits for inputting pulse and signal information 51. The control panels 1 and 2 are identical in designation and composition. In reality, each remote control is an on-board personal computer, which, as a means of display and control, replaces command-and-signal remote controls (pos. 9 and 14 in Fig. 1 and pos. 10, 11, 12 and, respectively, 15, 16, 17 1 and 2), a space navigation indicator (pos. 38 in Figs. 1 and 2), an on-board repeater clock (pos. 39 in Fig. 1), a digital indicator of the stock and fuel consumption (pos. 31 in Fig. 1 and 2), a block of digital indicators of the manual information input panel (pos. 20 in Figs. 1 and 2), a push-button remote control of manual information input (device pos. 21 in Figs. 1 and 2). To enter discrete signals into the consoles 1 and 2, the proposed system introduced blocks 15 and 16, respectively, to the inputs of which are connected electrical circuits for inputting pulse and signal information 51 from signal and pulse information sensors 37, additional electrical contacts of the operative organs 14, and outputs of alarm signal sensors events 38, as well as the outputs of the blocks for manual input of information 42 and 43 (electrical prices 53, 55 in FIG. 3). Analogs of these chains of the circuit 48, 50 in figure 1. From blocks 42 and 43, messages are sent to the system in a binary-decimal positional code; therefore, these circuits are assigned to signal ones; signal signals also include state signals of units that, in an analogous system, were sent to signaling units of state units (item 10 and 15 on figl).

To the pulsed signals are the control signals of the stopwatch, which arrived at the clock (pos. 39 in Fig. 1) along the circuits at pos. 47 in Fig. 1, and the counting pulses that arrived at the circuits in pos. 44 in figure 1 on the indicator of stock and fuel consumption (key 31 in figures 1 and 2).

To interface panels 1 and 2 with blocks of the display system and ship systems, blocks 17 and 18 are introduced.

The control panels 1 and 2 are on-board personal computers. video monitor 19, video processor 22, a limited set of alphanumeric and functional keyboard 23 and marker control keyboard 24. To communicate with the on-board computer 44, a module of a multiplex communication channel 25 is installed in each console. The appearance of the front panel of these remotes (panels 1 and 2) is shown figure 4. In the practice of aircraft of this kind, remotes are called integrated remotes or remotes that are integrated on the basis of modern computer or information technologies.

Blocks 17 and 18 perform the functions of command decoders, which are software and hardware generated by the computer systems of consoles 1 and 2. The main group of connections of blocks 17 and 18 are communications with the command control matrices of the units of the systems of the first group 39 and second 40. The outputs of the matrices 39 and 40 are connected to the inputs of the units of the on-board systems 41. The horizontal matrices 39 and 40 are connected to the outputs of the units for forming the command selection systems of the first group 27 and the second 29, respectively, and the verticals of the matrices 39 and 40 are connected to the outputs of the units for generating control commands the aggregates of the systems of the first group 28 and, accordingly, the second 30. The horizontal and vertical separation is arbitrary, since each of these blocks can perform these functions at the same time, and the function of decrypting commands is performed at a lower level. In the proposed system, block 27 is a functional analogue of a button block for generating commands for selecting systems of the first group (pos. 11 of Fig. 1), block 28 is an analog of block 12 in Fig. 1, block 29 is an analog of block 16 in Fig. 1, block 30 - an analogue of block 17 in figure 1. Matrices 39 and 40 can be structurally identical, but functionally in a system - an analog they are different. The first matrix provides control of one group of systems, the second another. In the proposed system, the matrices are connected to each of the remotes through the appropriate blocks. Thus, in contrast to the analogue, this system provides redundancy of control commands at the console level. The communication with the blocks for manual input of information 42 and 43 was built differently. On the ship, these blocks are reserved. In the display system - an analogue, the data are entered into the indicated blocks using one button switch - a digital information generation device for entering data into the first and second blocks of manual data input (pos. 21 in Fig. 1), but on separate circuits (pos. 49 and 51 in FIG. 1). Therefore, in the proposed system, the device for generating digital information (pos. 21 of FIG. 1) is represented in the form of two (first 32 and second 33) blocks for interfacing with blocks for manual input of information — the first 42 and second 43. The inputs of the blocks 32 and 33 are connected to the outputs of the blocks 17 and 18, respectively, and outputs on circuits 52 and 54, respectively, to the first 42 and, respectively, to the second 43 blocks of manual input of information. The selection of blocks for manual input of information in the system - an analogue is done by a separate command. In the proposed system, the first and second group of electrical circuits for inputting information into the spacecraft information display system (items 53 and 55 in FIG. 3 and items 48 and 50 in FIG. 1) are stored, but the first group 53 is connected to the first discrete input unit information (pos. 15 in FIG. 3), and the second 55 to the second 16. Thus, in the proposed system provides backup information input at the console level. At the same time, the input of information into any of the control panels 1 and 2 is programmatically provided. To ensure this possibility, a connection has been introduced between the control panels 1 and 2 for inter-machine information exchange. In an analogue system, information is displayed on a television-type video monitor (item 25 in FIGS. 1 and 2). The input of this video monitor is connected to a television system (key 26 in FIG. 1) via an electrical input circuit to a television signal information display system (key 41 in FIG.).

In the proposed system, the electric circuit (pos. 41 of FIG. 1) of the analog system is saved (pos. 46 of Fig. 3), which is connected on the one hand, as before, to the television system (pos. 26 in Fig. 1 and pos. 34 in Fig. 3) and on the other, to the video processor 22 of the first control panel 1. Additionally, a second similar circuit (pos. 48 Fig. 3) is introduced, which is connected on one side to the video processor 22 of the second control panel 2 and to the television system 34 on the other. Thus, on the video monitors 19 of the consoles 1 and 2, the television information from the source is displayed. people who are connected to the television system.

Otherwise, a diagram of the information display constructed by means of the display system is constructed. In the analogue system, the output of the unit for converting the analog parameters of the systems into a television signal 27 of FIG. 1 is connected to the television system 26 of FIG. 1 through an electrical circuit for outputting a television signal from the information display system 42 of FIG. 1. In the proposed system, the switching unit, calibration and conversion of the analog parameters of the on-board systems 12 of Fig. H has two channels of inter-machine information exchange. The electrical circuits of the first channel are connected to the system unit 20 of the first control panel (1), and the second to the system unit 20 of the second control panel (2). Thus, information from block 12 is received for processing in the computer systems of the system units 20 of the control panels of panels 1 and 2, bypassing the television system.

In the proposed system, the electrical circuit for outputting television information from the information display system is stored (pos. 42 in Fig. 1 and pos. 47 in Fig. 3), but it is connected to the television output of the video processor 22 of the first control panel 1. A second electrical circuit for outputting the television information from the information display system 49 of FIG. 3, which, on the one hand, is connected to the output of the video processor 22 of the second control panel 2, and on the other, to the input of the television system 34 of FIG.

In the analogue system there were no communications with the telemetry monitoring system, which excluded the possibility of an objective analysis of the crew’s actions. In the proposed system, communications with all elements of the system and input signals are introduced. This allows you to organize the collection of information in the computer systems of the consoles and ensure its transmission to the telemetry monitoring system 45. For this, the first 26 and second 31 units for interfacing with the telemetry monitoring system 45 are introduced into the system.

The system operates as follows.

After supplying power to the system and control panels 1 and 2 (PU), the operating system is started in the system units of the control panels 20 and the applied software and mathematics are loaded, hardware testing is performed, and zero format appears on video monitors 19, on which the main menu of the dialogue system is displayed . The choice of operating modes and control of the units of the on-board systems of the ship 41, the exchange of information with the blocks of manual input of information 42 and 43 and the computer of the returned device 44, the control of the parameters of the on-board systems and the modes of their operation using the switching unit, calibration and conversion of analog parameters of the on-board systems 12, calling the navigation chart, calibration of the measurement channels by electrical signal input circuits of the analog sensors of on-board systems 50, etc., is performed using the marker control keyboard 20 pounds national buttons to enable or disable units.

On the video monitors of 19 consoles 1 and 2, information is provided on the state of the systems, on the reserves of working bodies, on the orientation of the ship in various coordinate systems, on the position relative to the earth, light and shadow, radio communication zones, on the occurrence of important events, etc.

Arrival - the departure of signals from the signal information sensors 37 via electrical circuits 51 and the issuance of control commands is registered by the computing means of the system units 20 of the control panels 1 and 2 and then through the first 17 and second 18 discrete information output blocks and, respectively, the first 26 and second 31 interface blocks are transmitted into the telemetry control system.

The system provides input and presentation of video information on video monitors 19, which is received by the call of operators on electric circuits 46 and 48 from the television system 34.

The system for electric circuits of the output of television information 47 and 49 allows you to transfer information that is presented on the video monitors 19 of the panels 1 and 2 to the television system 34 for subsequent transmission to Earth.

This information is similar to that seen by the astronaut on the video monitors of the display system. At that, video processors 22 provide display of combined information: information from a television system and information generated by the display system itself. Thus, information can be transmitted to the control center in the form in which the astronaut sees it. This is a new quality of the information display system, which increases the reliability of the analysis of decisions made by astronauts.

In case of emergency situations, signals from emergency sensors 38 are received in the system. Based on these signals, the signaling devices in the signal board 5 are turned on and the signal generator corresponding to the given signal and the low-frequency signal generator in block 6 are turned on. Sound signals are sent to the sound speaker 7 and to the input of the headset communication system of the astronauts 9, and the low-frequency signal turns on the central fire in a flashing mode 8. The sound signals and the central fire are turned off navtom touch of a button 10.

At the same time, signals from emergency sensors using the input blocks of discrete signals 15 and 16 enter the system units 20 of the control panels 1 and 2. Based on these signals, signal light information appears on the video monitors. If the audible alarm did not turn on, a failure signal appears at the output of the sound signal generators, which from block 6 goes to the first input block of discrete signals 15 and then to the system block 20 of the first control panel 1. According to this signal, using the means of the system unit 20 of console 1 a sound signal is generated programmatically, which is output to the speaker 21 integrated into the remote control. Thus, the subsystem of light and sound alarms is reserved in this system 3. This is also a new quality of the system.

The system has a separate computing system, a unit for switching, calibrating and converting analog parameters of on-board systems 12, with the help of which conversion and input of analog information from sensors 35 through chains 50 and calibration (calibration) of the measuring channels of the system are made to control panels 1 and 2.

software digital system has significantly improved the technical and operational characteristics of the display system. When switching to this system, there is no longer a need to suspend object tests for a long time to calibrate measurement channels using real sensors. In a digital system, this is done by rebooting the software, which is much less in time, and much better in terms of convenience.

The operational controls 14 are designed to issue special commands, for example, commands to turn the engine off, shoot the hatch, turn on the suit fans, etc. One of the control contacts is connected to the inputs of blocks 15 and 16. Thus, having these connections, in the system blocks 20 Consoles 1 and 2, the crew’s actions are recorded and this information is transmitted through blocks 17, 18 and 26 and 31, respectively, to the telemetry monitoring system 45 for subsequent transmission to the ground.

In the proposed system, the display of one of the main parameters - the voltage of the power supply system of the facility, referred to as the main parameter of the facility, is provided, as in the analogue system, using a separate voltage indicator 13, the inputs of which are connected to the supply busbars of the power supply system 36 of the facility. The significance of this parameter and, accordingly, its attribution to the main parameters of a complex system is that, if there is no supply voltage, then the object, as an activity system, ceases to exist. The display of other main parameters is provided on the video monitors of consoles 1 and 2 in chains 50 and using block 12.

The control circuits of the stopwatch of the hours that the analogue system had were stored in the proposed system and shown in Fig. 3 in the group of electrical circuits for inputting pulse and signal information 51. The initial time value and its correction in the proposed system are provided by the astronauts manually according to the signals of the single time system and it is then supported by the time stamps built into the computer of the remotes 1 and 2. This solution increases the level of autonomy of the display system and allows remote adjustment of the clock, for example, using the on-board system of a single time. This solution significantly enhances the performance of the system.

Similarly, in the proposed system, communications with the sensor of discrete information on the fuel stock and fuel consumption are saved, but in this system, data display and exhibition of initial values are provided by means of panels 1 and 2.

The display of navigation information is provided by means of control panels according to the computer data of the returned device 44, which is connected using modules 25 of multiplexed information exchange channels with system units 20 of control panels 1 and 2. At the same time, this channel is used to transmit information from the machine and enter information into the machine.

On-board systems are controlled using marker 24 control devices and selecting appropriate display formats on video monitors 19. Commands are issued through blocks 17 and 18 and the corresponding command generation blocks 27 and 28 and 29 and 30 — interface blocks of outputs of blocks 17 and 18 with command inputs matrices 39 and 40.

Systems are managed in accordance with the facility’s operating manuals.

A useful model of the information display system and manual controls presented in this application is implemented in the Neptune-ME spacecraft Soyuz-TMA. The astronaut’s console of this system passed all types of ground-based autonomous and complex tests, as well as directly on Soyuz-TMA No. 1 and No. 2 ships. Literature:

Yu.A. Tyapchenko, Yu.S. Karpov, Yu.F. Aleksandrov et al. Integrated SOI of the Soyuz-TMA spacecraft and manual control panel of the ISS Russian Segment Alpha // Sat. Proceedings of the 5th international scientific and technical. Symposium “Aviation Technologies of the 21st Century. Safety is the key to success. August 17-22, 1999 Volume 2. - TsAGI Zhukovsky. - Fig. 2, p. 584 /.

Tyapchenko Yuri Alexandrovich Kornev Alexey Ivanovich Alexandrov Yuri Fedorovich Zakharov Vladimir Lazarevich

The authors:

Claims (3)

1. A spacecraft information display system comprising a light and sound alarm subsystem consisting of a signal board, a central light, a sound speaker, a sound alarm and central fire control unit, a sound signal generator unit and a central fire control signal with integrated health monitoring generators and, accordingly, with a failure sensor for sound generators, mute buttons and central lights, with one input group in the signal board it is connected to alarm sensors of emergency events, part of the inputs of the sound alarm and central fire control unit is connected to alarm sensors of emergency events, and one of the inputs of this block is connected to the mute button and the central fire, and the outputs of the same block are connected to inputs a block of generators of sound signals and a central fire control signal, one of the outputs of which is in turn connected to the sound speaker, the second to the astronaut's headset communication system, the third to the central fire input, a control button for light and sound alarms, the outputs of which are connected to the inputs of the signal board and the control unit for sound alarms and central lights, a unit for generating commands for selecting systems of the first group, the outputs of which are connected to inputs, for example, horizontal buses of the command matrix for controlling system units the first group, the unit for generating control commands for the aggregates of the systems of the first group, the outputs of which are connected respectively to the vertical buses of the command matrix of the control matrix ag by the exegetes of the systems of the first group, the unit for generating commands for selecting the systems of the second group, the outputs of which are connected to the inputs, for example, horizontal buses of the command matrix for controlling the units of systems of the second group, the unit for generating the commands for the units of systems of the second group, whose outputs are connected respectively to the vertical buses of the command matrix control units of systems of the second group, electrical circuits for signal input from analog sensors of on-board systems, electrical circuits for signal input from pulse sensors signal information, the first and second group of electric circuits for digital information output from the spacecraft information display system, the outputs of which are connected to the inputs of the first and second second blocks of manual data input, the first and second groups of electric circuits for digital information input in the spacecraft information display system, inputs which are connected to the outputs of the first and respectively second blocks of manual input of information, the switching unit and calibration of analog parameters, the inputs to of which are connected to the analog sensors of the on-board systems, an analog parameter conversion unit, a first electrical circuit for inputting a television signal from the onboard television system to a spacecraft information display system, a first electrical circuit for outputting a television signal from a spacecraft information display system to a television system, an indicator of the main object parameter for example, a voltage indicator, the input of which is connected respectively to the power buses of the on-board power supply system genes, operational control and issuing commands important for the safety of astronauts, the outputs of which are connected directly to the on-board systems, characterized in that, in order to increase the reliability and reduce the size of the information reflection system and increase the efficiency of the astronauts, the system includes: the first and second control panels computerized on the basis of modern computing and information technologies, the first and second blocks for inputting discrete signals into the first and second panels, respectively control, the first and second blocks of output of discrete information, respectively, from the first and second control panels, the first and second multiplex channels of information exchange, respectively, between the first and second control panels and the computer of the descent vehicle, the second electrical circuit for transmitting television information from the space information display system to a television system, a second electrical circuit for inputting television information from the television system to the info display system the spacecraft’s movements, the first and second blocks interfacing with the telemetric monitoring system, the inputs of which are connected to the outputs of the first and second discrete information output blocks, the first and second groups of electrical circuits for transmitting information to the telemetry monitoring system about the operation of the first and second control panels, respectively which, on the one hand, are connected to the outputs of the first and, respectively, second interface units with the telemetry monitoring system, and on the other, to the inputs of the telemetry system metric control, the first and second blocks of interfacing with the first and second blocks of manual input of information, the inputs of which are connected to the outputs of the first and second blocks of output of discrete information, and the outputs to the first and second groups of electric circuits of output of digital information, and, in each from control panels entered: a system unit with a set of input-output and information exchange devices, a video monitor, the input of which is connected to the output of the system unit, a video processor, a television the path of which is connected to the first electrical circuit of the input to the display system of the spacecraft information of the television signal from the onboard television system, the television output to the first electrical circuit of the output of the television signal from the display system of the information of the spacecraft to the television system, and is connected to the system control unit, a set of functional and digital keyboard for managing information on a video monitor, including for managing I use a marker, enter digital data and form control commands in the on-board system, which is connected to the system unit, the multiplex channel module of the information exchange between the system unit of the control panel and the computer of the descent vehicle, which is connected to the system unit of the panel on the one hand and on the other to the multiplex channel of information exchange between the control panel and the computer of the descent vehicle, the sound speaker, the input of which is connected directly to one of the analogs new outputs of the system unit, the first and second control panels are interconnected via a channel for the mutual exchange of information, the outputs of the first input unit of discrete signals to the control panels are connected to the inputs of the system unit of the first panel, and the inputs to electrical circuits for inputting signals from sensors of pulse and signal information of duration determined by the speed of the system unit of the control panel, for example, at least 5 ms, to the additional outputs of the operational controls and issuing commands important to safety to osmonauts, to the first group of electrical circuits for input into the spacecraft’s information display system of digital information, the inputs of which are connected to the outputs of the first block of manual input of information, alarm sensors of emergency events, the sensor failure of sound generators, the outputs of the second block of input of discrete signals to control panels are connected to the inputs of the system unit of the second console, and the inputs: to the electrical circuits for inputting signals from sensors of pulse and signal information with a duration determined quickly action of the control unit system unit, for example, for at least 5 ms, to additional outputs of operational controls and issuing commands important for the safety of astronauts, to the second group of electrical circuits for inputting digital information into the spacecraft information display system, the inputs of which are connected to the outputs of the second manual unit information input, alarm sensors of emergency events, failure sensor of sound generators, inputs of the first output unit of discrete information are connected to a discrete output the system unit of the first control panel, and the outputs - to the inputs of the first and second blocks for generating commands for selecting systems for control, the first and second blocks for generating control commands for system units, the control unit for audible alarm and central fire, the first block for interfacing with the first block for manual input information, aggregates of onboard direct control systems, the first unit for interfacing with the telemetry monitoring system, the inputs of the second unit for outputting discrete information are connected to the discrete outputs of the system a removable block of the second control panel, and the outputs to the inputs of the first and second blocks for generating commands for selecting systems for control, the first and second blocks for generating control commands for system units, the second block for interfacing with the second block for manual input of information, units for on-board direct control systems, the second unit for interfacing with the telemetry monitoring system, the switching and calibration unit for the analog parameters of the ship systems and the analog parameters conversion unit are combined into a single monoblock made It is a computer system with digital switching, calibration and information conversion, the inputs of which are connected to the analog sensors of the on-board systems, and the outputs are connected via the information exchange channel to the system units of the first and second control panels. 2. The system according to claim 1, characterized in that as a system unit, a system unit with a set of peripheral devices can be used, hardware and software compatible with a system unit on an INTEL x86 platform or another that meets the technical and operational requirements of manned space technology. 3. The system according to claim 1, characterized in that the marker control device can be made in the form of an external marker control unit in the form of a trackball, two-axis control lever and other type with mount in a convenient place for use by an astronaut in an inflatable and not inflated spacesuit.