RU136609U1 - DEVICE FOR FORECASTING PILOT PERFORMANCE IN ALTITUDE FLIGHT - Google Patents

Abstract

A device for predicting the pilot’s performance in high-altitude flight, characterized in that it includes blocks connected to the aircraft’s flight data acquisition system through the receiving and collecting information block: determining the pressure drop in the cockpit, collecting information about the flight profile, analyzing the health of the pressurized cabin, analyzing operating mode of oxygen-breathing equipment, diagnostics of the state of a set of oxygen equipment, the outputs of which are connected to the input of the calculation unit the ability of a pilot whose output is connected to the aircraft’s on-board digital computer.

Description

The claimed technical solution relates to measuring equipment, namely to systems for automated monitoring, control and rescue of the aircraft and crew.

The on-board active flight safety system is known (patent for invention RU No. 2223542, published February 10, 2004), containing blocks of functional meters and measurements of biomedical parameters connected via an information reception and collection unit to an analysis and control unit, to to which an output unit is connected, characterized in that an electronic computer connected to an analysis and control unit and an onboard digital computer connected to it, a system control panel, an optical o-sighting navigation system, fire alarm system, electronic control system connected to the electronic computer, remote control system connected to the information receiving and collection unit, on-board electronic equipment monitoring system, general-purpose equipment system and mass measuring system connected to the optical-sighting navigation system and an electronic computer, a system of fuel level sensors, while the data reception and collection unit and the output unit are connected to the electronic computer an optical machine and an on-board digital computer, and an optical-sighting navigation system and a fire alarm system are connected to an automatic control system included in the output unit, and the remote control system is connected to the system control panel.

The technical task of the proposed utility model is to increase the safety of high-altitude flights by predicting the health of the pilot and transmitting the forecast to the on-board digital computer of the aircraft for accounting when implementing control.

The solution to the technical problem is achieved by the fact that the device for predicting the pilot’s operability in high-altitude flight includes blocks connected to the aircraft’s flight parameters registration system via the receiving and collecting information block: determining the pressure drop in the cockpit, collecting information about the flight profile, analyzing the health of the pressurized cabin, analysis of the operating mode of oxygen-breathing equipment, diagnostics of the state of the set of oxygen equipment - the outputs of which are connected to the input of the p the calculation of the efficiency of the pilot, whose output is connected to the on-board digital computer of the aircraft.

The technical result provided by the given set of features is to increase the safety of high-altitude flights by providing real-time forecasting of the pilot’s operability in high-altitude flight and the ability to take into account prognostic estimates in the laws of controlling an aircraft, life support system and protective equipment of its crew.

The essence of the developed device for predicting the health of the pilot in high altitude flight is illustrated by the figure (Fig. - Diagram of the functional relationship of the components of the device for predicting the health of the pilot in high altitude flight), which are schematically indicated:

1 - On-board system for recording flight parameters of an aircraft.

2 - A device for predicting the health of the pilot in high altitude flight.

3 - On-board digital computer.

4 - Block receiving and collecting information.

5 - Block analysis of the mode of operation of oxygen-respiratory equipment.

6 - Block diagnostics of the state of the set of oxygen equipment.

7 - Block for determining the differential pressure in the cabin.

8 - Flight profile information collection unit.

9 - Block analysis of serviceability pressurized cabin.

10 - Calculator.

11 - Block calculating the height of flight.

12 - Block for calculating the "height" and barometric pressure in the cabin with a working pressurized cabin.

13 - Unit for calculating the "height" and barometric pressure in the cabin with a faulty pressure chamber.

14 - Block for calculating the concentration of oxygen.

15 - Block calculation of excess pressure.

16 - Block calculation of tracheal pressure.

17 - Unit for calculating the backup time to maintain health.

18 - Block calculating the performance assessment of the pilot

A device for predicting the pilot’s operability in high-altitude flight (see Fig., 2), characterized in that it includes blocks connected to the aircraft’s flight parameters registration system (1) through the data receiving and collecting unit (4): analyzing the oxygen operation mode respiratory equipment (5), diagnostics of the state of the set of oxygen equipment (6), determination of the pressure drop in the cabin (7), collection of information about the flight profile (8), analysis of the health of the pressure chamber (9) - the outputs of which are connected to the input the computer (10), the output of which is connected to the on-board digital computer (3) of the aircraft.

The functioning of the developed device for predicting the health of the pilot in high-altitude flight is as follows.

1) The device input is connected to the information bus of the aircraft’s flight parameters registration system (1), and its output is connected to the aircraft’s onboard digital computer (3).

2) Data from the information bus (1) enters the unit for receiving and collecting information (4) of the device.

3) Based on the analysis of the received data, the analysis unit of the operating mode of oxygen-breathing apparatus (5) generates a binary tuple X consisting of three elements at the output:

X = <x ₁ , x ₂ , x ₃ >,

where x ₁ = {1 if the switch “100% О ₂ ” is in the “On” position and 0 otherwise;}, x ₂ = {1 if the switch “Emergency” is in the “On” position and 0 - in otherwise}, x ₃ = {1, if the switch "VUSh" is in the "On" position and 0 otherwise}.

4) Based on the analysis of the data received, the unit for diagnosing the state of the set of oxygen equipment (6) generates a binary tuple Y consisting of five elements at the output:

Y = <y ₁ , y ₂ , y ₃ , y ₄ , y ₅ >,

where y ₁ = {1 if the event "Oxygen is absent" is recorded and 0 otherwise;} y ₂ = {1 if the event "Oxygen respiratory equipment failure" is recorded and 0 otherwise}, y ₃ = { 1, if the event “Oxygen mask is not connected” is recorded and 0 otherwise;} y ₄ = {1, if the event “Oxygen mask tightness compensator is not connected” is recorded and 0 otherwise}, y ₅ = {1, if the event “Failure of a high-altitude compensating suit” is recorded and 0 otherwise;}.

5) Based on the analysis of the received data, the unit for determining the pressure drop in the cockpit (7) generates the pressure drop in the cockpit of the aircraft (Δp, Pa) at the output.

6) Based on the analysis of the received data, the flight profile information collection unit (8) generates at the output a description of the flight profile of the aircraft in the form of a sequence of pairs: flight altitude (it is usually determined with a resolution of 100 m) - flight time at this altitude ( in seconds).

7) Based on the analysis of the received data, the pressurized cabin serviceability analysis unit (9) generates a binary signal z = {1 if the event “Aircraft's pressurized cabin” is detected and 0 otherwise).

8) Based on the information from the outputs of blocks (5) - (9), the calculator (10) calculates the performance assessment.

9) The unit for calculating the flight altitude (11) calculates the atmospheric pressure (p, Pa) from the current altitude (altitude h _n , m) based on a typical table stored in the unit’s internal memory linking the values of h, m and p , Pa using the piecewise linear interpolation algorithm:

,

,

where h _i and h _i-1 are interpolation nodes, ah _i-1 ≤h _n <h _i .

10) The unit for calculating the "height" and the barometric pressure in the cabin with a functioning pressurized cabin (12) is activated when the signal z = 1 appears at the output of the pressurized cabin analyzing unit (9) and calculates:

- “heights” in the cabin (h _k , m) depending on the current altitude (h, m) based on a typical table stored in the unit’s internal memory linking the values of h, m and h _k , m taking into account the pressure regulation mode in a pressurized cabin of a specific aircraft, using the piecewise linear interpolation algorithm:

,

,

where h _i and h _i-1 are interpolation nodes, ah _i-1 ≤h _n ≤h _i .

- barometric cabin pressure (p _k Pa), depending on the current altitude (h, m) based on the stored linking the value h in the block internal memory model table, m and h _k, m in view mode pressure regulation in pressurized cabin of a specific aircraft, using piecewise linear interpolation algorithm:

,

,

where h _i and h _i-1 are interpolation nodes, and h _i-1 ≤h _n <h _i .

12) The unit for calculating the oxygen concentration (14) calculates the oxygen concentration in the oxygen-breathing apparatus of the aircraft (s, unit) according to the formula:

,

,

where c (h) is the functional dependence of the oxygen concentration in the oxygen-breathing apparatus of the aircraft (s, units) depending on the current altitude (h, m) based on the type table stored in the unit’s internal memory that relates the values of s, units and h, m, using the piecewise linear interpolation algorithm:

,

,

where h _i and h _i-1 are the interpolation nodes, h _i-1 ≤h _n <h _i .

13) The unit for calculating the excess pressure (15) calculates the excess pressure (p _ID , Pa) in the oxygen-breathing apparatus of the aircraft, depending on the current altitude (h, m):

where p _ID (h) is the functional dependence of the excess pressure (p _ID , Pa) in the oxygen-breathing apparatus of the aircraft on altitude (h, m) based on the type table stored in the unit’s internal memory linking the values of p _ID , Pa and h, m, taking into account the serviceability / malfunction of the high-altitude compensating suit (determined by the value of the signal y ₅ from the output of the unit for diagnosing the state of the set of oxygen equipment (6)), using the piecewise linear interpolation algorithm:

,

,

where h _i and h _i-1 are interpolation nodes, ah _i-1 ≤h _n <h _i .

The tracheal pressure calculation unit (16) calculates the partial oxygen pressure in the tracheal air (p _mp , Pa) according to the formula:

P _mp = s (p- _cabin -47 + p _ID ).

15) The unit for calculating the backup time for maintaining health (17) calculates the minimum (t _min , s), modal (t _mod , s) and maximum (t _max , s) values of the backup time for maintaining health by the value of the partial pressure of oxygen in tracheal air ( p _mp , Pa) according to the formulas:

,

,

,

,

.

.

16) The calculation unit for assessing the health of the pilot (18) calculates the probability of loss of health (w, units) from the minimum (t _min , s), modal (t _mod , s) and maximum (t _max , s) values of the backup time the health and duration of the flight phase (t _stage , s) obtained from the output of the block, the flight profile information collection unit (8), based on the piecewise linear interpolation algorithm of the truncated normal distribution:

,

,

where Φ is the Laplace function (a table of its values, which is standard, is stored in the internal memory of the unit for calculating the pilot's health assessment).

17) The calculated estimate of the probability of loss of working capacity (w, units) is transmitted to the on-board digital computer (3) for further use in the laws of controlling the aircraft and the crew life support system.

Thus, the described elements of the claimed device for predicting the health of the pilot in high-altitude flight are functionally interconnected and are in constructive unity, and the combination of its essential features is unknown from the prior art. Therefore, according to the applicants, the inventive device for predicting the performance of a pilot in high-altitude flight is a new technical solution that belongs to the class of systems for automated control, management and rescue of an aircraft and crew.

The correctness of the developed approach to predicting the pilot’s performance in high-altitude flight was confirmed when solving several problems in the framework of studies under the grant of the Russian Foundation for Basic Research “Research on improving the technology of adaptive control of human-machine systems operating at high risk of operator hypoxic conditions” (No. 12- 08-01273-a).

In particular, in the investigation of the crash of the Su-27p aircraft, which was flying after replacing two engines in simple weather conditions. In the period from 15:49:17 to 15:51:51 (hh: mm: ss) of the flight at the stage of “Mach overclocking”, the pilot experienced a rapid loss of working capacity. The reason for the rapid (within 1-1.5 min) and severe disruption of the pilot’s performance, apparently, was the effect of altitude flight factors and, in the first place, a pronounced degree of oxygen starvation (hypoxia).

Explosive decompression, complicated by abnormal operation of oxygen equipment and high-altitude equipment, could be the reason for the sharp decrease in oxygen supply. However, taking into account the fact that the pilot was in protective equipment (VKK-6, ZSh-7 and KM-34D series 2), which guarantees protection against lung barotrauma and remains operational for 3 minutes when the cabin of this type of aircraft is depressurized ( and, above all, during explosive decompression) over the entire range of heights it was believed that along with the depressurization factor, another dangerous factor also acted - a violation of the rules for the use of protective equipment and the life support system. Possible causes of the accident were analyzed using the mathematical model of the claimed device, as a result of which, based on the calculated prognostic estimates of the pilot’s working ability in high-altitude flight, it was established that the aircraft’s cabin was depressurized (modeling of flight conditions with a pressurized cabin showed that the oxygen partial pressure in tracheal air during the flight, it remains in the normal range and the value of w remains equal to zero), and the gap in the altitude compensating suit and it would lead to disaster only in combination with some other reason, since flying with an leaky cabin and a torn high-rise compensating suit in the absence of other damage to the life support system in the conditions under consideration was not dangerous. Therefore, the catastrophe occurred due to one of the following physiologically equivalent reasons: the oxygen maxi did not seal tightly to the face due to its displacement due to aerobatic overload, the oxygen mask fitting and the protective helmet pre-tensioner were not connected, and the compensated expiration valve failed. These circumstances are reflected in the act of investigation of the disaster.

If the inventive device was installed on board the aircraft, the catastrophe could have been prevented by timely receiving a predictive assessment of the pilot’s flight performance, on the basis of which a signal is given to the pilot or the autopilot is turned on with the aircraft automatically flying into a horizontal flight at an altitude of 3000 m before recovery health pilot.

The inventive device for predicting the performance of a pilot in high-altitude flight is industrially applicable, since it can be implemented by enterprises (organizations) of the aviation industry in the industrial production of information-measuring, computing, information systems and software and hardware complexes of aircraft.

Claims (1)

A device for predicting the pilot’s health in high altitude flight, characterized in that it includes blocks connected to the aircraft’s flight data acquisition system via the receiving and collecting information block: determining the pressure drop in the cockpit, collecting information about the flight profile, analyzing the health of the pressurized cabin, analyzing operating mode of oxygen-breathing equipment, diagnostics of the state of a set of oxygen equipment, the outputs of which are connected to the input of the calculation unit the ability of a pilot whose output is connected to the aircraft’s on-board digital computer.

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