RU2115163C1 - Flight information acquisition, recording, and statistical processing device - Google Patents

Abstract

FIELD: computing, data processing, and measurement technology; systems for real-time acquisition, recording, and statistical processing of parametric and voice flight information. SUBSTANCE: device has storage unit, analyzing unit, control unit, timer, multiplexor, speech synthesizer, switch, data stream distribution unit, voice information input unit, transmitters and receivers of aircraft and ground radio stations, encoder, decoder, and OR gate. EFFECT: enlarged functional capabilities with regard to flying safety, and improved operating efficiency. 20 dwg , 2 tbl

Description

 The invention relates to computing and information-measuring equipment and can be used in systems for collecting, recording and statistical processing of parametric and speech flight information in real time in the interests of flight safety and improve operational efficiency.

 A device [1] is known for collecting and analyzing data on the operation of an information-computing system, which contains a control unit for writing to memory, a store-type memory unit, a unit for generating control signals, a data analysis unit, and provides for the registration of qualitative changes in the parameters of the process under study, their immediate output the operator, adaptation to the capabilities of the operator to perceive the displayed amount of information for a given time.

 The closest to the invention in technical essence is the known on-board device [2], containing analog value converters, one-time command converters, distribution panel, UP-2 analysis unit, MLP-main memory unit, PU-13 control unit, ITV timer and distribution RU-1 device.

 These devices have several disadvantages. Firstly, documented information is not prepared for a generalized assessment of the current state of the aircraft as a whole as an object of control directly in flight; secondly, there are no devices for the operational processing of documented information in the interests of flight safety and operational efficiency; thirdly, the possibility of conducting inter-flight analysis during the flight is completely excluded. The device [2] involves the use of specialized ground-based equipment of the type "Luch-71", "Luch-74", Mayak-85MS [3]. The practical use of flight information in air in [2] is not assumed. Only on the ground after landing, flight information is read from a magnetic storage device and processed using special algorithms. Thus, regardless of the technical condition of the aircraft, the entire fleet of the aircraft is forced to stand idle until the end of the verification cycle and the formation of a conclusion on the possibility of release on a second flight. With the massive use of aviation, this bottleneck significantly increases the time taken to prepare the aircraft for re-departure and determines the critical path in preparing the aircraft. Aircraft on which, according to objective monitoring data (for example [3] of Mayak-85MS equipment), equipment failures that have occurred in the air are detected, they are forced to stand idle without restoring in the queue to obtain an opinion on their condition.

 A common drawback of these devices [2] and [1] is the low efficiency of using flight information in the interests of flight safety, providing assistance to crews in distress, reducing the time for preparing the aircraft for a second flight, and operational efficiency.

The proposed device allows you to:
for serviceable aircraft, reduce the preparation time to the time required to refuel the aircraft with fuel and equip it with weapons or special equipment, cargo, and special equipment;
for aircraft that have failed in the air, according to operational analysis, it seems possible to shorten their recovery time due to the time margin for preliminary diagnosis of the technical condition in air in a real situation and time. In practice, to make a decision on the release of a perfectly operational aircraft in the prototype [2], it is necessary to read and analyze the information recorded during the flight in the memory block (MLP-based) for the absence of commands, the issuance of which is unacceptable in flight, and the absence of excess restrictions on the glider, engine, aircraft systems, weapons and equipment. The task is complicated by the fact that the list of these restrictions is a function of flight speed, altitude, overload, spatial position of the aircraft (core, pitch, angle of attack, ...), the amount of remaining fuel, suspension of weapons, the state of wing mechanization, brake flaps, landing gear, etc. For each type of l / a, this set is different and it is determined by the instruction to the pilot.

 These disadvantages of the prototype are eliminated by the following distinctive features of the proposed device.

Firstly, the state space of a spacecraft is represented as a discrete set of subspaces of states of systems, subsystems and devices in real connections and time in a space of situations, which in turn are discretely described in the form of flight stages. This allows you to more deeply and in detail see the "Specificity" of the occurring failure, its development and tendency. This fact is quite obvious. The same failure of the same device has a different effect on the task, depending on the totality of the signs that determine the quality of its performance, taking into account all existing restrictions on the aircraft and its external and internal systems in real time, including flight safety, application means of destruction, overcoming air defense means, ..., spatial position of the aircraft (altitude, speed, roll, pitch, angle of attack, overload, ...), condition of the engine, glider, aircraft systems, equipment, sales mode of operation under the actual state of all systems providing this mode. The deeper the situation is described, the less ambiguity it is possible to evaluate it and with greater efficiency to dispose of available forces and means, and in critical situations it is optimal to realize a shortage of time;
Secondly, the system not only states a fact, for example, a failure situation, but also gives instructions on actions in it with a description depth defined in paragraph 1. In situations of specific instructions for pilots as “Special Cases in Flight”, the system gives its generalized assessment at the level of making a decision and gives it to the crew. Thus, an algorithm for evaluating a failure situation in the interests of flight safety in the air is laid. That is, on the one hand, an algorithm is used - a classifier of the state of aircraft systems, which, in accordance with the priority laid down, distinguishes special cases in flight from the general flow of failures. On the other hand, because the very nature of the "Special Occasion..." and its course depends on a whole complex of factors that are dynamically related to each other and in time, then the crew instruction monitors the status and development of the “Special case in flight ...” in real time. At the same time, information about failures that threaten flight safety is broadcast through the radio station to inform the flight management group about the situation on board the aircraft and assist him in the form of tips on operating with fittings in the cockpit or commands on appropriate actions in the interests of crew safety or rescue ;
Thirdly, if there are errors in the actions of the crew to work with fittings in the cockpit, the system implements a hint. Thus, the algorithm for evaluating the actions of the crew is laid in the interests of achieving the potential effectiveness of the aircraft in operating conditions.

 Fourthly, according to information received from the aircraft using powerful computing tools on the ground, it seems possible to conduct a more in-depth analysis of the failure situation, comparing the current failure situation with a bank of emergency statistics on board the aircraft information to prevent the development of the failure situation. Another objective of the ground loop for the operational support of decisions made in emergency situations is to increase the operational efficiency of the aircraft and its equipment.

соответственно - "Обжатие есть", "Обжатие нет". Команда "Обжатие есть" соответствует замкнутому положению выключателя основной стойки шасси. При отрыве самолета стойка основного шасси разгружается, амортизатор выходит, концевой выключатель размыкается - формируется команда "Обжатия нет".In a variant of technical implementation, this is as follows. The three main stages of any flight, "Takeoff", "Flight", "Landing" are divided into sub-stages. The depth of the sub-stages is selected for reasons of ambiguity in deciding on the situation and the actions of the crew in it. An example of a description of the take-off stage and its characteristic features in relation to a hypothetical aircraft is given in table. one,
Where
S _about

accordingly - “Compression is”, “There is no compression”. The "Compression is" command corresponds to the closed position of the switch of the main landing gear. When the aircraft breaks off, the main landing gear is unloaded, the shock absorber exits, the limit switch opens - the "No compression" command is formed.

- приборная скорость самолета V₀;

- приборная скорость самолета V₁;

- приборная скорость самолета V₂;

- приборная скорость самолета V₃;
S_шу - шасси убраны;
S_nx - продольная перегрузка равна или более взлетной;
V, * - соответственно логические операции ИЛИ, И.Wherein
S _{d max} - engine operating mode "Maximum";
S _stars - flaps released (take-off position);
S _zu - flaps removed;
S _kmin - the sweep of the wing is minimal;

- instrumental speed of the aircraft V ₀ ;

- instrument speed of the aircraft V ₁ ;

- instrument speed of the aircraft V ₂ ;

- Instrument speed of the aircraft V ₃ ;
S _shu - chassis removed;
S _nx — longitudinal overload equal to or more than take-off;
V, * - respectively, logical operations OR, I.

 Situation 1. The crew may stop taking off and leave the plane without damage.

 Situation 2. You can’t eject. The cessation of take-off with a regular BC and full refueling is dangerous.

 Situation 3. Ejection is possible. The cessation of takeoff is due to aircraft breakdowns.

 Situation 4. Ejection is possible. You can’t stop taking off - it is dangerous for the life of the crew.

 Situation 5. Take-off. Chassis removed. Bailouts are possible.

 Situation 6. Take-off. Chassis and flaps retracted. Height is about 100 m. The transition of the take-off stage to the flight stage is performed according to the first command of the flight stage.

 An example of the description of Failure of alternating current and alternating current generators in the attribute space of the states of a / c OK is given in Table 2.

From the example given in table. Figure 2 shows that the same set of failures, even the simplest, in the attribute space of the states of the aircraft and its systems requires an exceptional amount of knowledge from the crew. The more complicated the situation (the wider the indicative space of failures and aircraft conditions), the more knowledge and practical skills the crew should possess. Given the limited capabilities of the crew, in the proposed system, the task of analyzing the situation is assigned to it, leaving the decision-making functions for the crew;
Fourth, to further increase the depth of the description of the failure, in addition to that described in table. 1 and 2, the device generates a generalized failure situation code (CEP) taking into account the current system of restrictions on the aircraft and its systems in real time. Aircraft (l / a) of today have thousands of restrictions on speed, altitude, ..., overload depending on the amount of fueling, cargo, ..., quantity, range and suspension points of the weapon, configuration of landing devices, operating modes power plant, etc. A complete list of restrictions for each l / a is purely specific. As an example of a complete list of these restrictions on an aircraft of type 9-12, 9-13, 9-51 and its systems are presented in [4]. Taking into account the said restrictions, the essence of the algorithm for the formation of the CEP is reduced to the fact that the sign of failure is additionally superimposed on the sign of failure determined by the stage (Tables 1 and 2) regardless of the reasons for their occurrence. Moreover, violations of certain restrictions simply lead to equipment failure and do not significantly affect flight safety. For example, takeoff with the headlights released and further flight without cleaning them incapacitates them and violates the aerodynamic qualities of the aircraft. Failure to comply with other restrictions creates real prerequisites for accidents and disasters. For example, flying with the landing gear and landing gear at speeds above the permissible mechanical (high-speed air pressure) destroys them and creates a real threat of disaster, making it impossible to land the aircraft. Similarly, speeding or permissible overload for loads on external suspensions, especially weapons. In these cases, a real safety risk is posed [4]. The general formation algorithm is similar to that described in Table. 1 and 2 with the addition of a member that takes into account the restrictions for a given failure situation, expression (1.1);
Fifth, taking into account the failure history. Against the general background of a failure situation, accounting for history is an essential distinguishing feature, which allows you to detail the failure situation with almost any depth of history. In the proposed device, in addition to the aforementioned, one more term is introduced into the algorithm for generating a generalized failure situation, taking into account the background of the failure situation on board the flight in this flight. In general, the algorithm is determined by the expression
S ^ooc = S ^aci • S $\genfrac{}{}{0ex}{}{\text{aci}}{\text{ogre}}$ • S $\genfrac{}{}{0ex}{}{\text{aci}}{\text{prdi\_o\_b}}$ , (1.1)
Where
S ^ooc - algorithm for generating a generalized failure situation code,
S ^aci - algorithm for generating a failure code (tab. 1 and 2);
S $\genfrac{}{}{0ex}{}{\text{aci}}{\text{ogre}}$ - an algorithm for creating restrictions;
S $\genfrac{}{}{0ex}{}{\text{aci}}{\text{prdi\_o\_b}}$ - an algorithm for the formation of a failure history on board an aircraft in a given flight.

 To explain the use of the prehistory feature space in the interests of solving flight safety problems, we take the “Oil” command, which exists in almost all engine control systems. The issuance of the “Oil” command is associated with oil starvation of the engine, and the duration of its issuance significantly affects flight safety, therefore, it is essential not only to state the fact of issuing this command, but also to monitor the duration of its issuance for the entire flight, regardless of the time it was issued and its frequency.

It is also important to compare the time of issuing a command with the admission standards for it and, as a result, the formation of a generalized situation for the “Oil” command. As a result of the secondary processing of information, the system forms a sign of the processing results to the internal circuit - the crew of the warning signal "Caution oil" and broadcast, "Dangerous oil" when the total issuance of the oil command exceeds the established norms. This is the essence of the history formation algorithm for the Oil team;
Sixth, the proposed system has an additional advantage over the prototype and when conducting deep ground research using information from an emergency storage device, a voice information memory unit and ground processing devices, which consists in the fact that the proposed system records all the information issued to the crew through a digital synthesizer speech (CSR), and the code of a generalized failure situation in flight to the ground is triggered, thus expanding the initial amount of information for analysis and adoption of p sheniya. In this case, the main difference from the prototype is that this information "comes" from the board in real time and is documented on the ground.

 Seventh, an essential distinguishing feature of the proposed device from the ones described above is the possibility of continuous assessment of the current level of flight safety due to continuous contact with the aircraft side in a failure situation and the use of a statistics bank for this type of aircraft for the entire period of its operation. In the limit, it seems possible for each situation in the data bank to store a complete sufficient set of recommendations on the appropriate actions for all categories of the flight management group and crew with a depth of description that ensures guaranteed prevention of the development of a special case in flight.

 At the same time, the accumulated operating experience will be continuously replenished, providing an ever-increasing depth and reliability of the description of special cases in flight. On the other hand, the reliable value of the initial features of the description of the situation allows us to approximate the course of development of the situation and act ahead of time, preventing the transition of a special case in flight into an unsolvable situation. The above approach (the availability of a continuous technical communication channel between the aircraft and the ground through the CEP and a data bank on the ground for operational use by the CEP) opens up almost unlimited possibilities for generating a forecast for the development of a failure situation. The proposed device provides for the formation of a forecast of a special case in flight at each step of the exchange of information on the CEP between the side of the aircraft and the ground. Taking into account the continuity of information exchange on-board CEP - Earth-Forecast, as a whole, each subsequent step expands the characteristic space of the CEP description and narrows the characteristic space of uncertainty in the development of the failure situation. In the limit, the Forecast reliably determines the CEP and, as a result, unambiguously describes the actions of the crew to prevent the development of a failure situation.

где
S $\genfrac{}{}{0ex}{}{\text{aci}}{\text{прог\_о\_з(i+1)}}$ - составляющая, учитывающая прогноз развития ситуации по данным статистики на базе КООС при i+1 шаге апроксимации статистики.This significant distinguishing feature from the prototype [2] provides an increase in the current level of flight safety. Given this member (S $\genfrac{}{}{0ex}{}{\text{aci}}{\text{prog\_o\_z}}$ ) the general algorithm for the formation of the CEP has the form

Where
S $\genfrac{}{}{0ex}{}{\text{aci}}{\text{prog\_o\_z (i + 1)}}$ - a component that takes into account the forecast of the development of the situation according to statistics on the basis of the CEP at the i + 1 step of approximating statistics.

 Eighth, given the fact that today flights are carried out according to strictly established routes, zones and levels and the vast majority of flight mission exercises are specified in terms of speeds, altitudes, overloads, operation parameters of the power plant and aircraft systems, it seems possible to formalize the entire space of restrictions, beyond which the exit is not permissible either for safety reasons or operational efficiency. The use of a formalized description of the system of restrictions in conjunction with a static (weighted) characteristic of the significance of going beyond the limits of the restrictions makes it possible to monitor not only the current level of flight safety but also the effectiveness of the practical use of the aircraft. Thus, the problem of increasing the efficiency of operation of the aircraft.

 The purpose of the invention is the expansion of functionality in the interests of safety and operational efficiency.

 The goal is achieved by the fact that in the known device [2] for collecting and recording flight information containing an analysis unit, a memory unit, a control unit and a timer, a multiplexer, a speech synthesizer, a switch, an information flow distribution unit, a voice information input unit, a second memory unit are additionally included , transmitter of the first channel of the on-board radio station, receiver of the first channel of the on-board radio station, transmitter of the second channel of the on-board radio station, receiver of the second channel of the on-board radio station, first decoder, first encoder, l a logical OR element, a transmitter of a first channel of a terrestrial radio station, a receiver of a first channel of a terrestrial radio station, a transmitter of a second channel of a terrestrial radio station, a receiver of a second channel of a terrestrial radio station, a second decoder, a second encoder. The first group of information inputs of the device is the first group of information inputs of the multiplexer, the second group of information inputs of which is the first output of the timer connected to the information input of the switch, the control input of which is connected to the first output of the control unit, the start input of which is connected to the second output of the timer, the second the output of the control unit is connected to the control input of the multiplexer, the output of which is connected to the information input of the first memory unit, the first I control the input input of which is connected to the third output of the control unit, the fourth output of which is connected to the first control input of the information flow distribution unit, the first and second information inputs of which are connected to the outputs of the same memory unit of the same name, the third output of which is connected to the input of the speech synthesizer, the readiness output of which is connected with the second control input of the first memory block, the corresponding bit of the third output of the first memory block is connected to the on-board input of the transmitter of the first channel radio station, the output of which is connected to the first input of the OR gate, the second input of which is connected to the information output of the speech synthesizer, connected to the first information input of the second memory unit and the information input of the transmitter of the first channel of the on-board radio station, the output of the receiver of the second channel of the on-board radio station through the first decoder is connected to the second control input of the information flow distribution unit, the output of which is connected to the information input of the first encoder, the input is sync of which is connected to the fifth output of the control unit, the output of the first encoder is connected to the input of the transmitter of the second channel of the on-board radio station, the output of the switch is connected to the control input of the second memory unit, the second information input of which is connected to the output of the voice information input unit, the output of the receiver of the first channel of the terrestrial radio station is connected with the first information input of the analysis unit, the first output of the analysis unit is connected to the input of the transmitter of the first channel of the terrestrial radio station, the output of the second receiver Nala terrestrial stations through a second decoder connected to the second data input of the analysis unit, the second output of which through a second encoder coupled to the transmitter input of the second channel terrestrial station.

 In FIG. 1 shows a structural diagram of the proposed device; in FIG. 2 is a structural diagram of a multiplexer 1; in FIG. 3 is a structural diagram of a control unit 2; in FIG. 4 is a structural diagram of a first memory block 3; in FIG. 5 is a block diagram of a block 4 timer; in FIG. 6 is a structural diagram of a block 6 input speech information; in FIG. 7 is a structural diagram of a switch 7; in FIG. 8 is a structural diagram of a second memory unit 8; in FIG. 9 is a block diagram of a block 9 for distributing information flows; in FIG. 10 is a block diagram of an analysis unit 10; in FIG. 11 is a structural diagram of a historical accounting unit 37; in FIG. 12 is a structural diagram of a block 44 operational ERPZU; in FIG. 13-17 - the general algorithm of the analysis unit; in FIG. 18 is a parry algorithm "Failure to control the socks of the wing in Automatic mode"; in FIG. 19 - an algorithm for parrying the situation "Speed over 700 km / h with the chassis released"; in FIG. 20 is a parry algorithm for the situation "The number M is more than 0.9 at an altitude of less than 3000 m with the suspension option N2".

 The device comprises a multiplexer 1, a control unit 2, memory blocks 3, 8, a timer 4, a speech synthesizer 5, a voice information input unit 6, a switch 7, an information flow distribution unit 9, an analysis unit 10, a transmitter 11 of a first channel of an on-board radio station, a receiver 12 the first channel of the radio station, the receiver 13 of the second channel of the radio station, the transmitter 14 of the second channel of the radio station, the receiver 15 of the first channel of the radio station, the transmitter 16 of the first channel of the radio station, the receiver 17 of the second channel of the ground radio diostantsii, the transmitter 18 of the second channel terrestrial radio stations, a first decoder 19, the first encoder 20, the second decoder 21, the second encoder 22, the element 23 OR.

 Multiplexer 1 (Fig. 2) contains 16 groups of multiplexers with 9 multiplexers in each group — multiplexers 24.1, ..., 24.144 for polling sensors, a decoder 25 for selecting multiplexers.

 The control unit 2 (Fig. 3) comprises a first divider counter 26, a second divider counter 27, a single-vibrator 28 of the control unit, a control unit generator 29, and a frequency divider 30 of the control unit.

 The first memory unit 3 (Fig. 4) comprises a decoder 31.0 for selecting decoders, decoders 31.1, ..., 31.16 for selecting an input information register, a flight stage code generating unit (BFCEP) 33, a failure situation code generating unit (BFCOS) 34, block 35 restrictions (BO), block 36 generating the code of a generalized failure situation (BFKOOS), block 37 accounting history (BUP), multiplexers 38.1, ..., 38. To operational analysis, registers 39.1, ... 39.J operational analysis, registers 40.1, ... 40.K fixing the code of the generalized failure situation (CEP), element 41 AND operational analysis, element 42 IL Operational analysis, the button 43 "Reset CEP" operating unit 44 reprogrammiruemogo memory (ERPZU).

 Block 4 timer (Fig. 5) contains the button 45 "Settings of seconds", 46 "Settings of minutes", 47 "Settings of hours", 48 "Settings of days", 49 "Settings of months", 50 "Entry of time", diodes 51 "Settings minutes ", 52" Clock settings ", 53" Day settings ", 54" Month settings ", typesetters 55 units of years, 56 tens of years, 57 hundreds of years, 58 thousand years, a master pulse generator 59 pulses, counter 60 units of seconds, counter 61 tens of seconds, decoder 62 seconds, indicator 63 seconds, decoder 64 tens of seconds, indicator 65 tens of seconds, counter 66 minutes and hours, registers 67 units of minutes and 68 dozens of minutes, decoders 69 units of minutes and 70 dozens of minutes, indicators 71 units of minutes and 72 dozens of minutes, registers 73 units of hours and 74 dozens of hours, decoders 75 units of hours and 76 dozens of hours, indicators 77 units of hours and 78 dozens of hours, counter 79 days and months, registers 80 units of days and 81 dozens of days, decoders 82 units of days and 83 dozens of days, indicators 84 units of days and 85 dozens of days, registers 86 units of months and 87 dozens of months, decoders 88 units of months and 89 dozens of months , indicators of 90 units of months and 91 dozens of months , the first element And 92 year transfers, a single vibrator 93 year transfers, counters 94 units of years, 95 tens of years, 96 hundreds of years, 97 thousand years, decoders 98 units of years, 99 tens of years, 100 hundreds of years, 101 thousand years, indicators 102 units years, 103 decades, 104 hundred years, 105 thousand years.

 The voice information input unit 6 (Fig. 6) contains microphones 106.1, ... 106.N, pre-amplifiers 107.1, ..., 107.N, filters 108.1, ... 108.N.

 Block 7 switch (Fig. 7) contains registers 109 thousand and hundreds of years, 110 tens and units of years, 111 tens and units of months, 112 tens and units of days, 113 tens and units of hours, 114 tens and units of minutes, 115 tens and units seconds.

 The second memory block 8 (Fig. 8) contains blocks 116.1, ..., 116.N an amplifier for recording analog signals, blocks 117.1, ..., 117.3 pairing digital information (BSCI) with the input of an analog tape recorder 118, the first resistor 119 BSCI, the first capacitor 120 BSCI, the second resistor 121 BSCI, the second capacitor 122 BSCI.

 Block 9 distribution of information flows - BRIP (block multiplexing). BRIP (Fig. 9) contains registers 123.1, ..., 123. N + 1 CEP, the first element 124 is NOT BRIP, the second element is 125 NOT BRIP, the first one-shot 126 BRIP, elements 127.1, ..., 127. N + 1 AND BRIP, element 128 OR BRIP, BRIP buffer register 129, BRIP output register 130, latch register 131 of request, second BRIP single-vibrator 132, request decoder 133, BRIP write cycle counter 134, third BRIP single-vibrator 135.

 The analysis unit 10 (FIG. 10) comprises a statistical processing unit 136 for determining the cross-correlation function, a priority generation unit 137, a data bank 138, a visual information display unit 139, a speech recognition unit 140, a speech synthesizer 141.

 Block 37 accounting history (BUP), (Fig. 11) contains the circuit 142.1, ..., 142. N comparison BUP, counters 143.1, ... 143.N BUP, single-shot 144 initial setup BUP, capacitor 145 BUP, resistor 146 BUP, element 147 OR BUP, block 148 setting comparison codes BUP.

 Block 44 operational reprogrammable read-only memory (BERPZU) (Fig. 12) contains a block 149 RPM, counters 150.1, ... 150. N EEPROM addresses, read-only memory (EEPROM) 151, EEPROM read-write memory, EEPROM read-ROM 152, EEPROM erase ROM 153, the first EPROM ROM element 154, the EEPROM initial installation one-shot 155, the first EEPROM capacitor 156, the first EPRZ recorder 156, the EPRC resistor 157 EPROS , one-shot 159 reading the EEPROM, one-shot 160 erasing the EPROM, second element 161 OR EPROM, flip-flop 162 EEPROM, element 163 AND EPROM, generator 164 clock pulses EEPROM, counter 165 programs EEPROM, element 166 NOT EEPROM, the second resistor, one-shot 168 ERPZU , the second capacitor 169 ERPZU, the third element OR 170 ERPZU.

 The device operates as follows.

 All information about the spatial position of the aircraft is primary — roll, pitch, speed, height, angle of attack, overload in horizontal and vertical planes, glide angle — state of control (steering) surfaces, wing mechanization, landing devices, systems, devices, .. ., information about the pilot’s index, about the aircraft’s flight number, ..., the position of the controls in the cockpit as a whole, about the technical condition of all systems endowed with integrated control systems (VSK), comes in one of four possible mnogo forms on the corresponding groups of inputs of the multiplexer 1.

 Block 1 multiplexer (Fig. 2) provides a serial survey of the sensors of the initial information. All information from the groups of inputs of parametric information, as well as the current time from timer 4, is supplied to the inputs of the multiplexers 24.1, ..., 24.144 for polling sensors. The multiplexers are controlled by signals from the control unit 2 directly and through the decoder 25 of the choice of multiplexers. Directly select one input of each multiplexer 24.1, ..., 24.144 polling sensors, signals A0, ..., A3. And with the help of the decoder 25 selection of multiplexers, one of the 16 columns is selected. The decoder is controlled by high-order signals A4,. .., A7. A sequential search of the control signals A0, ... A7 by the control unit 2 provides an interrogation of all sensors. The polling frequency of the sensors is determined by the control unit 2 and is 1 Hz. As multiplexers 24.1,. .., 24.144 polling sensors used the well-known IC 133 KP1, [5, p. 78]. As a decoder 25, the choice of multiplexers is the well-known IC 133 ID3, [5]. The signals from the output of block 1 of the multiplexer are fed to the first block 3 of the memory.

 The control unit 2 (Fig. 3) is designed to generate control signals. The signal from block 4 of the timer with a frequency of 1024 Hz is used as a reference. The control signals 1, 2, 4, 8, 16, 32, 64, 128, 256 Hz are formed from this signal by the first divider counter 26 and the second divider counter 27. Frequency signals 1, 2, 4, 8, 16, 32, 64, 128 Hz are used to iterate over addresses A0,. . . , A7 for block 1 of the multiplexer (A0, ..., A3 are the lowest addresses, respectively, 128, 64, 32, 16 Hz; A4, ..., A7 are the highest addresses, respectively, 8, 4, 2, 1 Hz) and for the first block 3 memory. A frequency signal of 64 Hz, as a clock pulse (TI), is supplied to block 7 of the switch. A frequency signal of 1 Hz, is fed to a single-shot 28 of the control unit and starts it with a leading edge. The single-shot generates a pulse of a given duration, which is supplied to the switch 7 as a pulse of the beginning of the frame (INC). The master oscillator 29 generates rectangular pulses with a frequency of 4800 Hz, which are supplied to the information flow distribution unit 9 and to the frequency divider 30 of the control unit 2, from the output of which pulses with a repetition frequency of 1200 Hz are supplied to the first on-board encoder 20. To the information flow distribution unit 9 pulses with a frequency of 1 Hz also come from the output of the second counter 27 of the control unit. As the first counter 26 of the divider, the second counter 27 of the divider and frequency divider 30, the well-known IC 564 IE10, [6] is used, as the one-shot 28 of the control unit, the well-known IC 155 AG1, [5] is used. As the master oscillator 29, the well-known “controlled oscillator” circuit [7] is used.

 The first block 3 of the memory (Fig. 9). To record information coming from block 1 of the multiplexer to the input of block 3, control signals from control block 2 are used. An 8-bit bus is used as an example. In this case, the lower addresses A0,. .., A3 arrive at all sixteen decoders 33.1,. . . , 33.16 select the register of input information in parallel, and the senior addresses A4,. . ., A7 arrive at the decoder 31.0 of the choice of decoders. Thus, the control signals A0, ..., A7 uniquely determine the register for each category of incoming information from unit 1 of the multiplexer. Information from unit 1 of the multiplexer on the aircraft side number, pilot index, current time, flight information (speed, course, altitude, overload, roll, pitch, ...), information on the state of aircraft systems (automatic control system for aircraft - self-propelled guns, hydraulic systems - main, booster, air, oxygen recharge, weapons control system, fuel, ...), power plant, ... aircraft equipment, state of the cockpit controls, landing devices, etc. arrives at the inputs of the registers 32.1, ..., 32.256 of the input information and is fixed in the corresponding register. The information in the registers is updated with a frequency of 1 Hz and is provided by the control unit 2. As the decoder 31.0 of the choice of decoders and decoders 31.1, ..., 31.16 of the choice of the register of input information is used known IC type 133 ID3, [5]. As registers 32.1, ..., 32.256 of input information, known ICs of type 564 IR9, [6] are used. To obtain the required number of bits, three schemes are used for each register. The information necessary for generating a code situation from the outputs of the registers 32.1, ..., 32.256 is fed to the input of the flight stage code generation unit 33 (BFCEP), to the failure situation code generation unit 34 (BFCOOS), to the restriction block (BO) 35, and to block 9 distribution of information flows.

 Block 33 BFKEP (Fig. 4) is a read-only memory (ROM). In this case, the input information is supplied to the address inputs of the ROM, and the code corresponding to the flight stage is removed from the data outputs. Thus, when changing any input effect (address), a different data cell is selected and, accordingly, the output code is changed or remains the same, depending on the firmware card of this ROM. An example of the formation of the code of the flight stage is described above (see the description to Tables 1 and 2). The code of the flight phase from the output of block 33 goes to the input of the block 36 for generating the generalized failure situation code (BFKOOS), to the block 35 of restrictions, to the first input of the OR element 42, to the second input of the historical account unit (BUP) and to the input of the operational reprogrammable block 44 read-only memory device (EEPROM). As the ROM of block 33 BFKEP, the well-known ICs of type 573 RF4 are used [5]. To implement the required amount of address space, these microcircuits are connected in cascade.

 Block 34 formation of the code of the failure situation (BFKOS) (Fig. 4) is a read-only memory (ROM). In this case, the input information, which is the failure code of the corresponding system, unit or device, is fed to the address inputs of the ROM, and it removes the code corresponding to the failure situation from the data outputs.

 Thus, when changing any input effect (address), a different data cell is selected and, accordingly, the output code is changed or remains the same, depending on the firmware card of this ROM. An example of the failure code generation is described above (see the description to Tables 1 and 2). As ROM block 34 BFKOS used well-known IC type 573 RF4 [5]. To implement the required amount of address space, these microcircuits are connected in cascade.

 Block 35 restrictions (BO) (Fig. 4) is a read-only memory (ROM). In this case, the input information of the registers 32.1, ..., 32.256 of the input information, which is the codes of the systems that are subject to application restrictions depending on the phase of the flight (for example, weapon systems, fuel system, landing gear, wing mechanization, ...), and also the code of the flight stage from the output of block 33 of the BFECP is supplied to the address inputs of the ROM, and from the outputs of the data of block 35 (BO) the generalized code of the system is removed, which has restrictions on the application taking into account the phase of the flight. Thus, when changing any input effect (address), a different data cell is selected and, accordingly, the output code is changed or remains the same, depending on the firmware card of this ROM. As the ROM of block 35 BO, the well-known ICs of type 573 RF4 are used [5]. To implement the required amount of address space, these microcircuits are connected in cascade.

 Block 36 of the formation of the code of the generalized failure situation (BFKOOS) (Fig. 4) is a ROM, while the input information from the unit 33 BFKEP, block 34 BFKOS, block 35 BO and block 37 accounting history (BUP) is supplied to the address inputs of the ROM, and from the BFKOOS data outputs, a generalized failure situation code is taken into account, taking into account the flight stage, system failures, the restrictions placed on them, and the history of the generalized failure situation.

 Thus, when changing any input action (address), a different data cell is selected and, accordingly, the output code is changed or kept the same, depending on the firmware card of this ROM. The code of the generalized failure situation is generated in accordance with the expression (1.2) and is flashed into the BFKOOS ROM at the stage of manufacturing the system.

 Thus, at the end of the flight, a code of the generalized failure situation will be generated corresponding to the moment of the flight end, and if there were no failures for the entire flight, then at the output of the BFKOOS block 36 there is a code of the aircraft working condition. As the ROM of block 36 of the BFKOOS, the well-known ICs of type 573 RF4 are used [5]. To implement the required amount of address space, these microcircuits are connected in cascade.

 The history accounting unit (BUP) 37 and the operational reprogrammable ROM unit (BEPROM) are shown in FIG. 11 and 12, respectively, and are described below.

 Multiplexers 38.1, ..., 38. To the first memory block 3 (Fig. 4), the code of the generalized failure situation (COOS) passes to the speech synthesizer 5 through the registers 41.1, ..., 40. To fix the CEP. Registers 39.1, ... 39.J of operational analysis fix the CEP for recording in block 44 of the EEPROM. Depending on the presence of a control signal supplied from the output of the OR element 42, the COOS is provided either from the EEPROM block 44 or from the BFKOOS block 36. So, when a logic level signal is supplied to the control inputs of multiplexers 38.1, ... 38.K, the code is passed from block 44 of the EEPROM, and when a logical zero is supplied, the code is passed from block 36 of the BFKOOS. The logical unit at the output of the element 42 OR is formed when the button 43 is pressed Reset the code of the general failure situation ("Reset CEP"), or when the "Landing L" command is generated. The Landing L command is formed when the aircraft runs along the runway after landing during compression of the main landing gear (see explanations to Table 1). The code of the generalized failure situation from the output of the multiplexers 38.1, ..., 38.K is supplied to the inputs of the registers 40.1, ..., 40. To the fixing of the code of the generalized failure situation (CEP), the recording inputs of which receive a control signal from the output of the logic element 41 And, which provides information recording in registers 40.1, ..., 40. To fix the CEP with a frequency of 1 Hz in the absence of a busy signal from the speech synthesizer 5. Clock pulses with a frequency of 1 Hz are supplied to the first input of the And element 41, and the busy signal from the speech synthesizer 5 is supplied to the second input of this element. If the busy signal is active, i.e. has a logic zero level, then the passage of clock pulses through the logic element 41 AND and, accordingly, writing to the registers 40.1, ..., 40. To the next code is prohibited, until the signal is busy from the speech synthesizer 5 to the passive state (logical unit level ) The structure of the generalized failure situation code includes a sign of turning on the transmitter 11 of the first channel of the on-board radio station for transmission - the signal "transmission", which is sent to turn on the transmitter 11 and ensures that the radio station is in transmission mode. Thus, in both cases, when you press the button 43 "Reset COOS", and when the command "Landing L" is reset, the code of the generalized failure situation is provided through the transmitter 11 of the first channel of the on-board radio station to the receiver 15 of the first channel of the ground-based radio station. This achieves efficiency in obtaining a conclusion on the technical condition of the aircraft that made the landing (command "Landing L"), or upon request from the flight management group at any stage of the flight (pressing the pilot 517 button "Reset CEP").

 Registers 39.1, ..., 39.J (Fig. 4) are used to fix the code of the generalized situation (COO) to be recorded in block 44 EEPROM. Fixation is provided by the signal "Recording ERPZU", coming from block 36 BFKOOS. To registers 39.1 ,. .., 39.J receives a code of a generalized failure situation with a time reference. From the output of registers 39.1, ..., 39.J, the information enters the EPROM unit 44 for recording and storage.

 As multiplexers 38.1, ... 38.K, the well-known IC of type 533 KP11 is used [5, p.242]. As registers 39.1, ..., 39.J of operational analysis and 40.1, ..., 40. The well-known IC type 564 ИР9 is used to fix the CEP [6, p. 71]. As a logical element 41 I use the well-known IC type 533 LI1 [5, p.245]. As a logical element, 42 OR - 533 LL1 [5, p. 246].

The timer 4 (Fig. 5) contains devices for dialing and setting the initial time information. Using the buttons 45 "Set seconds", 46 "Set minutes", 47 "Set hours", 48 "Set days", 49 "Set months", the current time is set to the month inclusively. These buttons provide switching of the setting signals from the master oscillator 59 through diodes 51 "Set the minutes", 52 "Set the hours", 53 "Set the days", 54 "Set the months" on the respective counters 66 and 79. Using a dial device 55 units of years , a dialing device 56 decades, a dialing device 57 hundreds of years, a dialing device 58 millennia, the current year values are set, which, when you press the 50 "Save Time" button 50, are entered in the corresponding counters 94, ..., 97. When the button 45 "Set seconds" is pressed, the master pulse generator 59, a counter of 60 units of seconds (counter with a counting module 10) and a counter of 61 tens of seconds (counter with a counting module 6) are reset to zero, which ensures the accuracy of setting the seconds for accurate time signals. The display of information about units of seconds and tens of seconds occurs, respectively, through a decoder of 62 units of seconds, a decoder of 64 tens of seconds to an indicator of 63 units of seconds and an indicator of 65 tens of seconds. After zeroing, the counters of 60 units of seconds and 61 tens of seconds start a continuous count of second pulses with the display of 63 units of seconds and 65 tens of seconds of the current value of the time count. As the master pulse generator 59, a known device is used [8, p. 64, fig. 1, the inclusion circuit chip DD1]. As the counter 60 with the counting module 10 and the counter 61 with the counting module 6, the well-known IC 564IE15 is used, programmed accordingly to the counting module 6 and 10 [5, p. 0 - 158]. We set the minutes, for which we press the button 46 "Set minutes". In this case, the pulses "T1" from the output of the master oscillator 59 pulses through the pressed button 46 "Set minutes" are fed to the counter 66 minutes and hours, which provides the installation of units of minutes and tens of minutes and this information through the registers 67 units of minutes, 68 tens of minutes, decoders 69 units of minutes, 70 dozens of minutes are displayed on indicators of 71 units of minutes and 72 dozens of minutes. To set the clock and dozens of hours, the button 47 "Set hours" is pressed. In this case, pulses T2 from the output of the master pulse generator 59 pulses through the pressed button 47 "Set hours" are supplied to the same counter 66 minutes and hours, which this time provides the setting of hours and tens of hours. This information through registers 73 units of hours, 74 dozens of hours, decoders 75 units of hours, 76 dozens of hours are displayed on indicators of 77 units of hours and 78 dozens of hours. Setting days. When you press the button 48 "Set days" pulses T1 from the output of the master oscillator 59 pulses through the pressed button 48 "Set days" are sent to the counter 79 days and months, which provides the installation of units of days and tens of days and this information through registers 80 units of days, 81 dozens of days, decoders 82 units of days, 83 dozens of days are displayed on indicators of 84 units of days and 85 dozens of days. To set the months, press the button 49 "Set months". In this case, pulses T2 from the output of the master pulse generator 59 pulses through the push-button 49 "Set months" are supplied to the same counter 79 days and months, which this time ensures the installation of months and tens of months. This information through the registers of 86 units of the months 87 dozens of months, decoders 88 units of the months 89 dozens of months are displayed on the indicators of 90 units of the months and 91 dozens of months. The operation of the counter for 79 days and months is described [9, p. 74 and 75]. To form the momentum transfer of the year, a circuit is assembled consisting of the first element 92 AND of the transfer of the year and a single-vibrator 93 of the transfer of the year. When the month 12 (December) is changed to the first month (January), the output of the first logical element 208 "And" transfer year appears slice of the pulse of the twelfth month (the pulse at the output of the 1st logical element 92 And transfer year appears when switching from the 11th month on the 12th and exists throughout the entire twelfth month), according to which the one-shot 93 of the transfer of the year is triggered. The momentum of a one-shot 93 of the year transfer is fed to a counter of 94 units of years, providing an increase in content by one. To set the units of years, tens of years, hundreds of years and millennia, typesetters 55 units of years, 56 dozens of years, 57 hundreds of years, 58 thousand years and the button 50 "Entry time" are used. Recording and displaying information of units of years, tens, hundreds and thousands of years is identical. For example, consider the entry of information in units of years. On a typesetter 55 units of years, we type the current value of the year (similar to tens of years, hundreds of years, a thousand years) and press the button 50 "Entering time". Information from all typesetters 55 units of years, 56 - of decades, 57 - of hundreds of years, 58 - of thousands of years is simultaneously transferred to the corresponding counters of 94 units of years, 95 decades, 96 hundreds of years, 97 thousand years. Information from the counters through decoders 98 units of years, 99 decades, 100 hundreds of years, 101 thousand years goes to the corresponding indicators 102 units of years, 103 decades, 104 hundreds of years, 105 thousand years. Information from the outputs of the counters 60 units of seconds, 61 dozens of seconds, registers 67 units of minutes, 68 dozens of minutes, 73 units of hours, 74 dozens of hours, 80 units of days, 81 dozens of days, 86 units of months, 87 dozens of months, counters 94 units of years, 95 decades, 96 hundreds of years, 97 thousand years goes to multiplexer 1 and switch 7. As decoders, 62 units of seconds, 64 tens of seconds, 69 units of minutes, 70 tens of minutes, 75 units of hours, 76 tens of hours, 82 units of days, 83 dozens of days, 88 units of months, 89 dozens of months, 98 units of years, 99 dozens of years, 100 hundred is 101 thousands of years used a known chip 514ID1 [5, p.118]. As indicators, 63 units of seconds, 65 tens of seconds, 71 units of minutes, 72 tens of minutes, 77 units of hours, 78 tens of hours, 84 units of days, 85 tens of days, 90 units of months, 91 tens of months, 102 units of years, 103 decades , 104 hundred years, 105 thousand years, the well-known ALS324A microcircuit is used [9, p. 96]. As registers, 67 units of minutes, 68 dozens of minutes, 73 units of hours, 74 dozens of hours, 80 units of days, 81 dozens of days, 86 units of months, 87 dozens of months, the well-known microcircuit 564 IR9 is used [6, p. 71]. As counters of 94 units of years, 95 decades, 96 hundreds of years, 97 thousand years, the well-known microcircuit 564 IE14 is used [6, p. 104]. As the one-shot 93 of the year transfer, hereinafter, in other blocks, the well-known 564AG1 microcircuit is used [6, p. 294]. Diodes 51 minutes setting, 52 hours setting, 53 days setting, 54 months setting are used to decouple the pulse chains T ₁ and T ₂ during the time setting (by pressing any button 46, ..., 49). Clocking pulses of frequency 1024 Hz from the output of the master oscillator 59 pulses are fed to the control unit 2.

The information output unit 5 (Fig. 1) is a known device - a digital speech synthesizer (DSP). At the input of block 5 of the DAC receives COOS from the first block 3 of the memory. This signal goes directly to the first input of the temporary storage register, where it is stored until it is read by the central processor of the DSS, identified by it and reproduced in speech form. From the output of the DSS, a speech signal is received:
the outputs of the device for connecting the head phones of the crew through the element 23 OR;
to the transmitter modulator 11 of the first channel of the on-board radio station for broadcasting and subsequent reception by the receiver 15 of the first channel of the ground-based radio station. The second purpose of this signal is to inform the crews of aircraft in the air about a special incident in flight and to assist the crew in distress;
to the input of the second memory unit 8 for recording in an analog tape recorder with reference to the current time.

 From the moment the speech signal is synthesized until the end of the current word form, the signal “Busy” is generated at the output of the DSP block 5. This signal is fed to the input of the first memory block 3 and is used to maintain unchanged COOs for the duration of its scoring. To this end, this signal is supplied to the control inputs of the registers 40.1, ..., 40.K through element 41 AND of the first memory block 3. Each CEP has its own speech accompaniment, which is formed at the stage of preparing the dictionary and training the system. Thus, all information issued to the crew and the CSR is documented in real time. As block 5 DAC used the known device [10].

 Block 6 input speech information (Fig. 6). At the input of the unit, microphones 106.1, ..., 106.N are installed, where N is the number of crew members. The processing of voice information of each crew member is identical. From the output of the microphones, the information goes to the preliminary amplifiers 107.1, ..., 107.N, which are used as preliminary amplifiers of the RI-65 equipment [11, p. 40 and 41, Fig. 27, the circuit is assembled on transistor T1]. The voltages from the outputs of the pre-amplifiers 107.1, ..., 107.N are supplied to the corresponding filters 108.1, ..., 108. N, (all filters are identical) which are used as low-pass filters of the type IZh2.067.151 [12]. Appendix 10, element U6. The voltage from the outputs of the low-pass filters 108.1, ..., 108.N is supplied to the second memory unit 8.

 Switch 7 (Fig. 7). The unit receives information about the current time from timer 4 in parallel to all registers 109 thousand and hundreds of years, 110 tens and units of years, 111 tens and units of months, 112 tens and units of days, 113 tens and units of hours, 114 tens and units of minutes , 115 tens and units of seconds, which is entered into the registers by the signal recording. As control signals for writing and reading (serial output), signals are used that come from the control unit 2 of the frequency of 1 Hz (pulse of the beginning of the frame) and frequency of 64 Hz (such pulses), respectively. As registers 109, ..., 115, the well-known IC 564 IR6 is used [6]. The signals from the output of block 7 of the switch are fed to the second block 8 of the memory in the form of three sequences: - Pulses of the beginning of the frame (INC), the following with a frequency of 1 Hz; - clock pulses (TI) following with a frequency of 64 Hz; information impulses (AI) - code information containing all information about the current time. All three sequences are recorded on three tracks of the analog tape recorder 118 (each for the entire track). Thus, time information is updated in each frame with a frequency of 1 Hz. Discrete time description 1 s.

 The second memory unit 8 (Fig. 8) is designed to coordinate the levels of signals received from the DSP unit 5, the voice information input unit 6 and the switch unit 7 to levels that ensure the normal operation of unit 118 (analog tape recorder) and their recording. In this case, the processing of analog signals is performed in blocks 116.1, ..., 116.N of the recording amplifiers of analog signals, which use the well-known circuit of the recording amplifier of the RI-65 equipment [11, p.40, 41, Fig. 27, the circuit is assembled on transistors T2, ... , T7]. From the switch 7 receives digital information - pulses of the beginning of the cycle (INC), clock pulses (TI) and information pulses (AI), which contain information about the current (at the time of recording) time. To implement the recording of digital information on an analog tape recorder, the well-known blocks 117.1, ..., 117.3 of pairing digital information with the input of an analog tape recorder are used. The well-known scheme is depicted in the framework of block 117.1 [13, p. 33]. As block 118 of the voice information memory, a well-known multitrack analog tape recorder of the P-500 type is used [14].

 Block 9 distribution of information flows (BRIP) (Fig. 9) distributes information flows in accordance with the request received from the Earth. Upon request from Earth from the first decoder 19, a request code is received, which is registered in the register-latch 131 of the request. Writing to the register is made according to the signal generated by the 2nd single-shot 132 BRIP. The request code is decrypted on the request decoder 133 and, depending on the request code, allows the passage of clock pulses with a frequency of 4800 Hz through the logic elements 127.1, ..., 127.N + 1 And to the registers 123.1, ..., 123.N + 1, respectively. The recording of COOS and COOS + Additional SP (additional information flow) is carried out through the 1st and 2nd logical elements 124 and 125 NOT with a frequency of 1 Hz, coming from the control unit 2. The use of two elements does NOT provide a signal delay to eliminate uncertainty at the edges, i.e. they function as a digital delay line. Thus, the reading of information is provided, either only CEP or CEP + Add. IP for aircraft, engine, aircraft systems, ..., crew, depending on the request code from Earth. The first one-shot 126 provides the prohibition of the passage of clock pulses with a frequency of 4800 Hz through the logic element 127.1 And in the presence of a request code for issuing Additional IP. The information read from one of the registers 123.1, ..., 123.N is sent through the logical element 128 OR to the input of register 129 of the buffer, where it is written in a serial code with a clock frequency of 4800 Hz. Then, the recorded information is fed to the input of the output register 130 in parallel code. The entry in the output register 130 is made with a frequency of 1 Hz from the third single-vibrator 135. Thus, the information flow is assigned according to the destination depending on the request code from the Earth.

 As registers 123.1, ..., 123.N + 1 129, 130, 131, the well-known IC 564IR6 is used [6]. As logical elements 124 and 125, the well-known IC 564LN2 is NOT used [6]. As the first single vibrator 126, the second single vibrator 132 and the third single vibrator 135, the well-known IC 133AG1 is used [5]. As a logical element 127.1, ..., 127.N + 1 And the well-known IC 133 LI1 is used [5]. As a logical element of 128 OR, the well-known IC 133LD3 is used [5]. As the request decoder 133, the well-known IC 564 ID1 is used [6]. As the counter 134 of the recording cycle, the well-known IC 564IE15 is used [6].

 Analysis block 10 is designed for static processing of incoming information, prioritization of situations, speech recognition, speech synthesis and display of graphic and alphanumeric information in the interest of improving flight safety and operating efficiency of aircraft.

From the receiver 15 of the first channel of the terrestrial radio station, a speech signal is supplied to the speech recognition unit 140, where each voice message is uniquely associated with a digital code. The resulting code, as well as COOS (COOS + Ext. IP) received from the second decoder 21, are received at the inputs of block 136 of statistical processing. One of the possible options for statistical processing of incoming information is presented in FIG. 13 (sheets 1 to 5). The algorithm begins by executing standard initialization routines, setting interrupts, programming ports, a timer, etc. After completing the initial settings, information is received from the second decoder 21 and the speech recognition unit 140. According to the CEP, a state is formed displaying the controls of aircraft systems and indicator devices in the cockpit. The next step in the algorithm is the analysis of ensuring the current level of flight safety (TUBP). If TUBP is not provided, then a deeper analysis of the CEP is performed:
The nearest statistics on a database (DB) are determined;
ranking statistics on the database;
Priority hypotheses for the development of a failure situation are determined.

 Next, an analysis is made whether the situation is standard and whether a request for an additional information flow (Additional IP) from the aircraft is needed. If Add. IP is needed, then a request is generated for the corresponding Ext. Type N IP and this request through the second encoder 22 and transmitter 18 of the second channel of the ground-based radio station arrives on board the aircraft via the second Earth-to-Board communication channel. To increase the depth of analysis and the reliability of decisions made at the next stage according to the obtained Extras. IP, the analysis of the total information flow as part of - the information flow requested and received from the 138 data bank (IPBD) and CEP, + Add. SP from the aircraft. Based on the results of the analysis, the situation on board the aircraft is determined, possible options for its development are selected and, according to the selected hypothesis, an additional request is made. SP N + 1 from the aircraft. If the situation on board is not defined unambiguously, then several options for the possible development of the situation in accordance with their priority and recommendations for preventing failures are provided to the visual information display unit 139. After that, the information processing cycle is repeated. If the situation on board is uniquely defined, then the only solution to prevent the development and eliminate the consequences of the failure situation is prepared and displayed on the visual information display unit 139. The specified algorithm works continuously and ensures that the current level of flight safety is not lower than the specified one.

If the required level of flight safety is provided, then the algorithm for evaluating and ensuring the current level of operational efficiency is activated, while at the first stage of the algorithm, the composition, configuration and operating modes of the airborne complex (LHC) are determined. It analyzes whether the current level of operational efficiency corresponds to the required configuration with the selected configuration. If not, then a decision is being prepared to adjust the composition, configuration and operation of the LHC. At the next stage, the number of the failure group is determined, and in case of a failure _of type N ₁ , the corresponding routine of analysis of a group of failure _of type N ₁ is called. After conducting an in-depth analysis, the visual information block 139 is issued with possible actions to increase the efficiency of the LHC operation in graphical form and the recommendations are issued to increase the efficiency of the LHC in alphanumeric. The algorithm works continuously and at each subsequent stage increases the depth and reliability of decisions.

 Thus, the proposed algorithm maintains the current level of operational efficiency not lower than the specified. Both algorithms together provide the maintenance of current levels of flight safety and operational efficiency at specified levels. The exclusive advantage of the proposed device is the performance of these functions in almost real time.

As examples of a deeper analysis of failure situations, particular algorithms for processing three failure situations are shown (Figs. 14-16). FIG. 14. The algorithm for parrying the failure of the control of the toes of the wing in the "Automatic" mode. The event is monitored during the flight with a Mach number of less than 0.75. Event formation conditions:
the presence of one of the three teams "Flight", "Takeoff", "Landing";
lack of a one-time team "Wing socks released";
angle of attack of the wing more than 12.5 ^o ;
Mach speed less than 0.75.

 In this situation, the conclusion of the event (Fig. 14) means (see. The main algorithm of Fig. 13, the left shoulder, the stage "Issue to the flight management group (HF) to block 139 a prepared decision to eliminate the consequences of the failure situation in graphical and alphanumeric form "). In particular, in this situation, a section of the cockpit armature is presented on the visual information displaying unit 139, the control of which ensures the development of a failure situation and the message "Switch to manual control of the wing socks, set the position of the wing socks in accordance with the flight phase" (at the "Take-off" stages) "," Landing "- released; at the" Flight "stage - removed).

FIG. 15. The algorithm for parrying the situation "Speed over 700 km / h with the chassis released." This situation is recorded under the following conditions:
the presence of one of the three teams "Flight", "Takeoff", "Landing";
the presence of a one-time command "Chassis released";
time more than 5 s;
instrument flight speed of more than 700 km / h.

 In this situation, the conclusion of the event (Fig. 15) is understood (see. The main algorithm of Fig. 13, the left shoulder, stage "Issue to the flight management group (HF) to block 139 of the prepared decision to eliminate the consequences of the failure situation in graphical and alphanumeric form "In particular, in this situation, a section of the cabin fittings is presented on the visual information displaying unit 139, the control of which provides the prevention of the development of a failure situation and the message" Reduce speed (V <700 km / h) "," remove the chassis "is displayed.

FIG. 16. The algorithm for parrying the situation "Number M is more than 0.9 at an altitude of less than 3000 m with the suspension option N2". This situation is recorded under the following conditions:
the presence of one of the three teams "Flight", "Takeoff", "Landing";
the presence of a single command "N (height) less than 3000 m;
suspension option 2;
Mach flight speed over 0.9.

 In this situation, the conclusion of the event (Fig. 16) means (see. The main algorithm of Fig. 13, the left shoulder, the stage "Issue to the flight management group (HF) to block 139 a prepared decision to eliminate the consequences of the failure situation in graphical and alphanumeric form ". In particular, in this situation, a section of the cabin fittings is presented on the visual information displaying unit 139, the control of which ensures the development of a failure situation and the message" Reduce the speed M <0.9 "is displayed - (release the brake brushes, turn off the "Fast and the Furious", set the "ORE" to the position below the "Maximum").

 An example of displaying the cockpit of an aircraft in distress according to the CEP on the visual information display unit 139 is shown in FIG. 17. In FIG. 18. an example of a forecast of the development of a failure situation (Fig. 17) is given 6 seconds ahead according to statistics from a data bank of analysis unit 10.

 As block 140 speech recognition can be used known device [15]. As a speech synthesizer 141, a known device [10] is used. As block 139 display visual information uses a standard graphical SVGA monitor [16]. A well-known device [17] is used as a statistical processing unit 136 and a priority generation unit 137. As a data bank 138, a known device is used [18]. As the transmitter 11 and the receiver 12 of the first channel of the on-board radio station, the transmitter 16 and the receiver 15 of the first channel of the ground-based radio station, the transmitter and receiver of a known radio station are used, respectively [12]. As the transmitter 14 and the receiver 13 of the second channel of the on-board radio station, the transmitter 18 and the receiver 17 of the second channel of the ground-based radio station, the transmitter and receiver of the known radio station are used, respectively [19]. As the first encoder 20 and the first decoder 19, the second encoder 22 and the second decoder 21, the encoder and decoder of the known P-099M system are used, respectively [20]. As a logical element 23 OR, the well-known 564 CT3 microcircuit is used [6].

 Block 37 accounting history (BUP) (Fig. 4 and 11). From the output of block 36 BFKOOS situation codes that require taking into account the time spent in the active (triggered) state are received at the input of block 37 BUP (Fig. 11). These codes are fed to the inputs "A" of the comparison circuits 142.1, ..., 142.N BUP. Hardwired codes from block 148 for setting comparison codes are supplied to the second inputs ("B") of these comparison schemes. The failure code of a certain system triggers the comparison circuit corresponding to the given failure code and the active signal of the triggered comparison circuit is fed to the information input of the corresponding counter 143.1, ..., 143.N ECU, and to the clock inputs of the counters 143.1, ..., 143.N ECU at the same time, clock pulses with a frequency of 1 Hz are supplied, which ensure the calculation of the time spent by the corresponding failure code in the active state with an accuracy of up to a second. Codes from the outputs of the counters 143.1, ..., 143.N of the control unit, which are the time spent by the codes of the generalized failure situation in the active state, are supplied to the address inputs of the block 36 BFKOOS, thus causing a change in the code of the generalized failure situation depending on the time of the presence of this situation at the input of the unit 37 BUP, i.e. the time of the existence of the failure situation for the entire flight is provided, or the history of failures at any moment of the current time, including at the time of the end of the flight. To install the counters 143.1, ..., 143.N FCU in its initial state, an initial start-up circuit is used, assembled on the basis of a single-vibrator 144 of the initial installation of the FCU. Two modes are offered. Initial installation at power-up (work on the ground). In this case, the on-delay is determined by the charge time of the capacitor 145 of the FCU through the resistor 146 of the FCU. Upon completion of the charge of the capacitor 145 BUP, the one-shot 144 of the initial installation is activated and sets all the counters 143.1, ..., 143.N of the BUP through the logic element 147 OR of the BUP to the initial state. The second mode (work in the air). When generating the signal "Start 0" (see table. 1, 2), the initial installation of the counters is provided to them through the logical element 147 OR BUP. As comparison schemes 142.1, ..., 142.N BUP are used known IC type 533SP1, [5]. As the counters 143.1, ..., 143.N of the control unit, the well-known IC 564 IE10 is used [6]. As a single-vibrator 144 of the BUP initial installation, the well-known IC type 564 AG1 is used [6]. As a logical element 524 OR - IC type 533LL1 [5]. Block 148 setting comparison codes is implemented by soldering the conclusions of the "In" circuits 142.1, ..., 142.N comparison to the potentials of a logical zero or one, depending on the value of the corresponding category of the comparison code.

 Block 44 operational reprogrammable read-only memory (Fig. 4 and 12). The main component of the EPROM unit 44 is the IC Electrically Erasable Reprogrammable Read-Only Memory (EEPROM) device, for example, 1601 PP3 [5]. Information is fed to the address inputs of the EEPROM 149 from the output of the counters 150.1, ..., 150.N of the addresses of the EEPROM, which provides sequential enumeration of addresses from AO by Amakh upon receipt of the next “Write to EEPROM” pulse from block 36 BFKOOS of the first memory unit 3. The control code for ensuring the mode of erasing, writing or reading is generated using the ROM 151 write ERPZU, ROM 152 read ERPZU, ROM 153 erase ERPZU. The choice of ROM 151 recording ERPZU is carried out by the signal "Record in ERPZU", coming from block 36 BFKRS first block 3 memory through a single-shot 158 recording ERPZU. The one-shot provides the required signal length of the sample ROM 151 recording the EEPROM, which provides the necessary diagram of control signals for recording in the EEPROM 149. At the same time, the signal "Recording in the EEPROM" through the second logic element 161 OR EEPROM is supplied to the trigger 162 of the EEPROM, ensuring its installation in the active state . The signal level of the logical unit from the output of the trigger 162 ERPZU provides the passage of clock pulses from the generator 164 clock pulses of the EEPROM through the element 163 AND EEPROM to the counter 165 programs EEPROM. The formation of the recording diagram occurs due to enumeration of the addresses of the ROM 151 of the ERPZU recording by the counter 165 of the ERPZU programs. To set the counter 165 of the EEPROM program and the trigger 162 of the EEPROM to its initial state at the end of the recording cycle, the transfer signal of the counter 165 of the EPROM program is used, which, through the NO 16 EEPROM element 166 and the third logical element OR OR EEPROM, resets the EEPROM trigger 162 (initialization). At the same time, the signal from the output of logic element 166 is NOT through the single-vibrator 167 of resetting the program counter of the EEPROM, the delay circuit (the second resistor 168 EEPROM and the second capacitor 169 EEPROM) and the first element 154 OR EPROM resets the counter 165 of the program EPROM (sets to initial state). The circuit works similarly to the described one upon receipt of the signals “Reading ERPZU” from element 42 OR of the first memory unit 3, or “Erasure” (“Start” signal from block 33 of the BFCEP). In this case, a single-vibrator 159 of reading an EEPROM and a read-only memory 152 of reading an EEPROM are used to implement reading and a single-vibrator 160 of erasing an EEPROM together with a ROM 153 of erasing an EEPROM when organizing erasing information from an EEPROM. The information to be recorded comes from the block of registers 39.1, ..., 39.J of the first block 3 of the memory to block 149 RPZU. The read information from the block 149 RPZU arrives at the block of multiplexers 38.1,. . ., 38.K, which are controlled by the "Read EEPROM" signal. The initial installation of counters 165 of the program of the EEPROM, 150.1, ..., 150.N addresses of the EEPROM 149, of the trigger 162 of the EEPROM is carried out by the signal of the one-shot 155 of the initial installation of the EEPROM, which is started when the power is turned on through the delay circuit, consisting of the first resistor 157 of the EEPROM and the first capacitor 156 ERPZU. As block 149 RPZU used IC type 1601 PP3 [13, p. one hundred] ; generator 164 clock pulses - a known scheme [7, p. 125, fig. 9.15a]; logical element 163 and the EEPROM - 533L1 [5]; counter 165 programs ERPZU - 564IE11 [6]; single-vibrator 158 ERPZU records, 159 ERPZU reads, 160 erase ERPZUs, 167 zeroing the program counter of ERPZU, 165 initial setting of ERPZU - 564 AG1 [6]; logical element 166 NOT ERPZU - 564 LN2 [6]; the first and third logical elements 154, 170 OR ERPZU - 533 LL1 [5]; the second element 161 OR ERPZU - 533 LE4 [5]; flip-flop 162 ERPZU - 564TM2 [6]; counters 150.1, ..., 150.N addresses of the ERPZU - 564IE10 [6]; ROM 151 records, 152 reads, 153 erase ERPZU - 556 RT4 [5].

 Using the proposed device on board the aircraft will improve the efficiency of the fleet on the ground and in the air, reduce accident rate and improve flight safety. It should also be noted the moral factor, which will additionally affect the efficiency of operation and flight safety. The crew has the ability to maintain contact (via ether) with the Earth (Mission Management Group) automatically (by acting by the CEP) and objectively (without human intervention in the description of the failure situation). This gives the crew confidence in the correctness of its assessment on Earth and the issuance of recommendations or orders for appropriate action. A further development of the proposed device is to increase the depth of the description of the situation on board the aircraft, expand the volume of secondary statistical processing of information on Earth, and use global satellite communication systems. This will allow to achieve the potential operational efficiency of the fleet and raise flight safety to a whole new level.

Sources of information
1. A device for collecting and analyzing data on the operation of an information-computing system. Auto St USSR N 1795476, G 06 F 15/36, 01/08/1990
2. The system of registration of flight modes MSRP-64. 142.20.00. Manual for technical operation. Prototype.

 3. Flight information processing system "Mayak-85MS". 7YU1.583.001RE1. Manual for technical operation.

 4. The program of express analysis on the product "Mayak-85M" flight information recorded "Tester UZ series L" on products 9.12, 9-13, 9-15. Directory of controlled events. 688.85002-03 90.

 5. Catalog of integrated circuits, part 1. Dayton Central Design Bureau, 1990.

 6. Industry standard. Integrated circuits 564 series. Application Guide. OST 11 340.907-80.

 7. MRB B. I. Gorshkov Elements of electronic devices. M .: Radio and communications, 1989.

 8. To help the radio amateur. M .: DOSAAF, issue 95, 1986.

 9. Sign-synthesizing indicators, group 6349. Collection of information sheets. RM 11.073.071.1-82.

 10. J. Cater. Computers - speech synthesizers. M .: Mir, 1985.

 11. Equipment RI-65 Manual for technical operation 3.838.003 OM.

 12. Radio station R-862; Manual for technical operation of YaIDI1.101.013 RE. Maintenance Schedule ЯДЖ1.101.013 РО.

 13. The journal "Radio", N 5, 1986.

 14. The equipment P-500. Technical description and Operation Instructions СЫ3.838.008ТО.

 15. Tarabunov I.M. Hardware-software complex for analysis and recognition of speech signals based on micro-computers. -In the book. Automatic recognition of auditory images: Abstracts of reports and messages of the 13th All-Union School-Seminar "Automatic recognition of auditory images." (ARSO-13). Siberian Branch of the Academy of Sciences. Novosibirsk 1984.

 16. Operating Manual Bedienungsanletung. 14 "Color monitor, 1993, Taiwan.

 17. ALI 386DX MINI ISA SYSTEM BOARD. User's manual, 1993, Taiwan.

 18. Personal computing complex "Electronics MS0585". Drive "Electronics МС 54011". 0.305.098.TU.

 19. The radio station R-800 L2. Guidelines for the technical operation of IZh1.101.021 RE1. Maintenance schedule IZH21.101.021 RO. 1984.

 20. The equipment R-099M. Manual for technical operation. 31.600.000 RE.

Claims (1)

 A device for collecting and recording flight information, containing an analysis unit, a memory unit, a control unit and a timer, characterized in that it further includes a multiplexer, a speech synthesizer, a switch, an information flow distribution unit, a voice information input unit, a second memory unit, a transmitter the first channel of the on-board radio station, the receiver of the first channel of the on-board radio station, the transmitter of the second channel of the on-board radio station, the receiver of the second channel of the on-board radio station, the first decoder, the first encoder, logic OR element, a transmitter of a first channel of a terrestrial radio station, a receiver of a first channel of a terrestrial radio station, a transmitter of a second channel of a terrestrial radio station, a receiver of a second channel of a terrestrial radio station, a second decoder, a second encoder, wherein the first group of information inputs of the device is the first group of information inputs of the multiplexer, the second group the information inputs of which is the first timer output connected to the information input of the switch, the control input of which is connected to the first output the control unit, the start input of which is connected to the second output of the timer, the second output of the control unit is connected to the control input of the multiplexer, the input of which is connected to the information input of the first memory unit, the first control input of which is connected to the third output of the control unit, the fourth output of which is connected to the first control the input of the distribution block of information flows, the first and second information inputs of which are connected to the outputs of the same name of the first memory block, the third output of which is connected connected to the input of the speech synthesizer, the readiness output of which is connected to the second control input of the first memory block, the corresponding bit of the third output of the first memory block is connected to the input of the transmitter of the first channel of the on-board radio station, the output of which is connected to the first input of the OR logic element, the second input of which is connected with the information output of the speech synthesizer connected to the first information input of the second memory unit and to the information input of the transmitter of the first channel of the onboard radio tance, the output of the receiver of the second channel of the onboard radio station through the first decoder is connected to the second control input of the information flow distribution unit, the output of which is connected to the information input of the first encoder, the synchronization input of which is connected to the fifth output of the control unit, the output of the first encoder is connected to the input of the transmitter of the second channel of the onboard radio stations, the output of the switch is connected to the control input of the second memory unit, the second information input of which is connected to the output of the input unit voice speech radio, the output of the receiver of the first channel of the ground radio station is connected to the first information input of the analysis unit, the first output of the analysis unit is connected to the input of the transmitter of the first channel of the ground radio station, the output of the receiver of the second channel of the ground radio station through the second decoder is connected to the second information input of the analysis unit, the second output of which the second encoder is connected to the input of the transmitter of the second channel of the terrestrial radio station.

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