RU2453858C2 - Device and method to simulate power supply system failure at air craft - Google Patents

Abstract

FIELD: electricity.

SUBSTANCE: device for testing flight controls is designed so that at least one flight control device can be tested. Besides, the flight control device is manufactured so that it can supply warning signal or aircraft flight control disconnection signal and/or connection interlocking signal as a response to power supply system failure. The device for testing flight controls is comprised of a connection element 1 implemented so that it can be installed in the first line of power supply direction, which is connected to the first flight control device. Besides, the first line of power supply direction generates a signal describing the state of the first power source and in addition, includes the first switching device which is connected during operation so that power supply direction line signal is switched for the first flight control device.

EFFECT: advanced functionalities.

10 cl, 3 dwg

Description

Technical field

The present invention relates to a device and method for simulating a power failure in an aircraft. In the event of such a failure of the power supply system, a warning should be displayed, in response to which the devices of the aircraft should be turned off automatically or manually and / or their inclusion should be automatically blocked.

State of the art

In normal flight operations, two generators generate electricity for the aircraft control and a flight convenience tool for passengers, each of which is connected to one aircraft engine, and for safety reasons, power backup is provided. In the event of a failure of one generator, the other generator provides electricity to all aircraft systems, but does not provide redundancy. A warning is displayed, and some devices in the aircraft may be turned off. In particular, if a single engine generator fails, some aircraft systems, such as an aircraft entertainment system, should be automatically turned off and / or turned on. Deactivating such systems ensures flight safety, since failure of a single engine generator reduces available power, and disabling certain systems reduces overall energy consumption. In particular, an aircraft belongs to the third category if a backup power source is provided. The third category allows for automatic approach and landing. If one generator fails, the aircraft no longer has a backup power source, and accordingly the aircraft category is reduced to the second. The second category warns the pilot that in the event of a further failure in the aircraft system, the pilot will be forced to operate the aircraft in manual mode. If the aircraft is assigned the second category, for safety reasons the pilot is forbidden to use the autopilot for automatic landing, therefore, the autopilot must be turned off when landing, and it must not be turned on. In the event of a failure of both generators, an auxiliary power source, such as a retractable external turbine, provides emergency power to the aircraft, a warning is displayed, and devices that are unnecessary in emergency operation can be automatically turned off.

When conducting ground tests to check the shutdown and / or inability to turn on some aircraft systems when a power failure occurs, for example, an entertainment system or kitchens, it is necessary to simulate the failure of the first generator driven by the first engine, or the second generator driven by the second engine , and the failure of both generators, leading to the inclusion of an emergency power source. In addition, a warning should be displayed to the pilot to indicate that certain systems, such as autopilot, should not be and / or cannot be used.

Disclosure of invention

An object of the present invention is to provide an easy-to-implement method for simulating generator failure driven by a motor to perform testing.

The purpose of the invention is achieved by a method of checking at least one flight control means and wiring connected to it, and the flight control means is configured to alert, turn off the means of the aircraft and / or block its inclusion when a certain condition of at least one power source in an aircraft. The method includes the following steps. The switching means is installed in the power indicating line connected to the first flight control means, and the power indicating line transmits a signal indicative of the state of the power source. The signal in the power indicating line is changed by activating the switching means. Check the response of the flight controls.

The flight control means may be a flight and guidance computer or a navigation computer. The flight control means may control at least one aircraft means. The specified means of the aircraft can be any device in the aircraft, for example, an aircraft entertainment system, an air conditioning system, a kitchen, and the like, regardless of whether the device needs electricity. Switching means may be installed in the power indication lines using an adapter-connector. The activation of the switching means leads to a change in the signal in the power indicating line, which indicates, that is, models, distortion or failure of the power supply of the flight control system or other component of the aircraft. The response of the flight control means can be checked by signals supplied by the flight control means, for example, on an indicating device, or by turning off and / or the inability to turn on the means of the aircraft. In another embodiment, the signals provided by the flight control may be measured. Power indication lines do not transfer electricity to any aircraft device. More specifically, the power indication lines transmit a signal indicative of the state of the power source. When working in the flight control system, there is a backup power source, so it cannot determine the failure of the power system without external information. The term "wiring" may include cable harness and power bus, as well as parts thereof.

An advantage of the present invention is that testing of other components of the aircraft can be continued while checking the response of the flight control to a power failure. In traditional test methods, the power source is turned off and the flight control response is tested. In the proposed method for testing the response of flight control devices to a power supply failure, they only change the signal in the power supply indication line and do not turn off the power source, so that testing of other aircraft components can continue, regardless of the reaction of the flight control to a power supply failure.

A power line signal may indicate a redundant power source from multiple power sources. If the aircraft contains multiple power supplies, a signal on the power indicating line may indicate that a backup power supply is available for multiple flight controls. If there is such a redundant power source for multiple flight controls, the aircraft is assigned a third category that allows for automatic landing.

The signal on the power indicating line may be transmitted to a plurality of flight controls.

The step of changing the signal in the power indicating line may include the step of simulating a power supply interruption, for example, electrical breakdown, short circuit, or overload condition. The step of installing the switching means in the power indicating line may include installing the switching means in the plurality of power indicating lines and / or installing the plurality of switching means in the plurality of power indicating lines connected to the plurality of flight control means, and the step of changing the signal in the power indicating line includes a step of changing the plural signals in a plurality of power indicating lines. Thus, by performing simple and error-free actions, you can test the correct wiring of the complex cable harness of the aircraft and the operation of the flight control.

The purpose of the present invention is also achieved by means of a device for checking the operation of the flight control means, configured to check at least one flight control means and the wiring connected thereto; moreover, the flight control means is configured to issue a warning, turn off the means of the aircraft and / or block its inclusion in response to a state of failure (source) of power supply. The device for verifying the operation of the flight control means comprises first connecting means adapted to be installed in a first power indicating line connected to the first flight control means, the first power indicating line transmitting a signal indicative of the state of the first power source, and further comprises a first switching means connected during operation in such a way as to ensure switching of the signal of the first power indicating line connected to first flight control tool.

As indicated above, the flight control means may be a flight and guidance computer or a navigation computer. The flight control means may control at least one aircraft means. The specified means of the aircraft can be any device in the aircraft, for example, an aircraft entertainment system, an air conditioning system, a kitchen, and the like, regardless of whether the device needs electricity. The connecting means may be an adapter connector that can be connected to a suitable aircraft cable harness connector and / or aircraft device connector.

The activation of the switching means leads to a change in the signal in the power indicating line, which indicates a distortion or failure of the aircraft power supply and / or its part. The response of the flight control means can be checked by a signal supplied by the flight control means, for example, on an indicating device, or by turning off and / or the inability to turn on the means of the aircraft.

The device for checking the operation of the flight control means may include second switching means connected during operation in such a way as to provide switching of the signal of the second power indicating line connected to the second flight control means. The second flight control may be a flight control backup to the first flight control, which is a prerequisite for the aircraft to work in the third category, for example, for automatic approach and landing.

The device for verifying the operation of the flight control means may further comprise second connecting means configured to install power indications in the third and fourth lines connected to the first and second flight controls, respectively, wherein the third and fourth power indicating lines transmit a signal indicative of the state of the second power supply, and the third switching means connected during operation in such a way as to ensure the switching of the signal a power indicating line connected to the first flight control means and a fourth switching means connected during operation so as to provide switching of a signal of the fourth power indicating line connected to the second flight control means. A signal indicating the state of the first and / or second power source may indicate a state of the power source such as normal operation, low voltage, power failure, overload condition, and the like. During normal operation, the second power source provides power to the second flight control means, which provides a backup power source for the second flight control means, and such a backup power source for the second flight control means is necessary, as described above, for the flight in the third category.

With the help of the device for checking the operation of the flight control means, the aircraft safety systems providing a backup power supply can be checked. Two power supplies and two aircraft flight controls provide dual redundancy, which creates a very complex harness system and a very sophisticated control tool for the associated power bus. However, the device for verifying the operation of the flight control means in accordance with the present invention is configured to verify such a complex cable harness system, to mount it in an aircraft, the associated power bus and / or power bus control device.

The device for verifying the operation of the flight control means may further comprise third connecting means configured to install power indications in the fifth and sixth power lines connected to the first and second power control means, respectively, the fifth and sixth power supply indicating lines transmitting a signal indicative of the state of the third power supply, and the fifth switching means connected during operation in such a way as to ensure switching of the signal of the fifth line a power supply connected to the first flight control means and a sixth switching means connected during operation so as to provide switching of a signal of the sixth power indicating line connected to the second flight control means. The first power source may be a first generator driven by rotation by the first engine of the aircraft, the second power source may be a second generator driven by rotation by the second engine of the aircraft, and the third power source may be an emergency power source for the aircraft, such as a battery a battery or a retractable auxiliary turbine that turns on or extends in the event of a failure of both generators in. The term "power supply" may also include a power bus and part thereof.

In the event of a failure of both the first and second power sources, the flight control means may disable the aircraft flight comfort system, such as an air conditioning system, aircraft entertainment system, and the like, to save aircraft battery power. In addition, as indicated above, a warning should be displayed.

One skilled in the art will recognize that cable harnesses and the associated power bus providing such a high level of redundancy and disaster recovery have a complex structure. However, as indicated above, the device for checking the operation of the flight control means is configured to test such a complex system of cable harnesses and power bus. Using the device to verify the operation of the flight control tool is simple, and therefore an error in the operation is extremely unlikely.

The above device can be used to test flight controls, cable harnesses and / or power bus. The device for verifying the operation of the flight control means may be a device for simulating a power system failure and can be used to simulate any state of a power system failure in an aircraft.

Brief Description of the Drawings

The invention is further described in more detail with reference to the accompanying drawings, in which:

figure 1 is a pictorial view of a device for checking the operation of flight control in accordance with the present invention;

FIG. 2 is an example of a backup power supply scheme of two flight controls in an aircraft; FIG.

figure 3 is a diagram of a device for checking the operation of the flight control means in accordance with the present invention.

The implementation of the invention

Figure 1 shows a device 1 for checking the operation of the flight control means, containing six switches 14, 16, 18, 20, 22, 24. The first connecting means includes a plug connector 2 and a female connector 4, the second connecting means contains a plug connector 8 and a female connector 6, and the third connecting means comprises a plug connector 12 and a female connector 10. The device 1 for checking the operation of the flight control means further comprises a cable 26 for connecting a plurality of connectors and switching ents.

As shown in FIG. 2, the aircraft comprises a first generator 30, a second generator 34, and an emergency power supply 32, which may be a battery or a retractable external turbine. The first flight control means 36 and / or the second flight control means 38 displays messages on the display device 40 and can further control the air conditioning system 42 and the entertainment system 68. A power bus 46 distributes electrical energy from the first generator 30, the emergency power supply 32 and the second the generator 34 into the first flight control means 36 and / or the second flight control means 38 depending on the state of the power sources 30, 32, 34. Using a plurality of lines 50, the power bus control device 48 determines the operating states of the first generator 30, the emergency power supply 32, and the second generator. The power bus control device 48 transmits signals to the first flight control means 36 and the second flight control means 38 over a plurality of power supply lines 52, 54, respectively.

In normal flight operation, the first generator 30 provides power to the first flight control means 36, and the second generator 34 provides power to the second flight control means 38. If a power supply failure in the first generator 30 is detected by the power bus control 48, the power bus control 48 opens the key 56 and closes the key 58, so that the second generator 34 provides power to the first flight control means 36 and the second flight control means 38. However, in this case, there is no backup power source for the first and second flight control means 36, 38, and the aircraft category is reduced from the third to the second. In the second category, automatic landing is prohibited, and, for security reasons, certain devices must be turned off, for example, entertainment system 68. Accordingly, the flight control means 36, 38 display a warning on the display device 40 and may further disable the entertainment system 68 and / or block inclusion of entertainment system 68.

If another failure of the power supply system is detected, the power bus control device 48 may switch additional keys 60, 62, 64, 66 on the power bus in the second generator 34 and / or emergency power supply 32 in the same way as the keys 56 and 58, as described above, in order to provide power to the first and second flight controls 36, 38 without redundancy, and can transmit the type of failure of the power system via a plurality of power indicating lines 52 to the first flight control means 36 and the second plurality of lines 54 power supply to the second flight control means 38. However, FIG. 2 shows only a simplified diagram for explaining the invention. The cable harness, power bus, and power bus control in the aircraft are very complex and distributed throughout the aircraft, so testing and complete operation verification is a difficult task.

FIG. 3 shows a diagram of a device 1 for checking the operation of a flight control means connected to the first flight control means 36 and the second flight control means 38, for example via a power bus, cable bundle and the like, in test mode. To simplify the description, the power bus 46 and cable harness of the aircraft are not shown in FIG. 3. As indicated above, the device 1 for checking the operation of the flight control means includes switches 14, 20, 16, 22, 18, 24. Each switch contains a main switching means indicated by the letter "a" and an additional switching means indicated by the letter "b", moreover, both switching means are switched simultaneously when the corresponding switch is activated.

To simulate normal operation, the first switching means 14a, the second switching means 20a, the third switching means 18a, the fourth switching means 24a, the fifth switching means 16a and the sixth switching means 22a are closed to provide a signal to the first flight control means 36 and the second flight control means 38 Vnorm, indicating that the aforementioned redundant power supply is available from the first power supply 30 and the second power supply 34. A warning message by the first and second flight control means 36, 38 is not provided. The Vnorm signal is typically an earth voltage and indicates the absence of a power failure condition to signal. When the switch 14 is activated, the first switching means 14a opens, and the Vnorm signal is not supplied to the first power indicating line 74, and accordingly, an abnormal power state signal is supplied to the first flight control means 36. The first flight control means 36 displays a warning, disables the aircraft means such as the entertainment system 68, and / or blocks its inclusion. When the second switch 20 is activated, the second switching means 20a opens, and the Vnorm signal is not supplied to the second power supply line 76, thereby signaling an abnormal power state to the second flight control means 38. The second flight control means 38 also displays a warning, disables the means of the aircraft and / or blocks its inclusion.

When the third switch 18 is activated, the third switching means 18a is opened, and accordingly, the Vnorm signal is not provided on the third power indicating line 82, and therefore, an abnormal power state signal is supplied to the first flight control means 36, which leads to the above-described reaction of the first flight control means 36 . When the fourth switch 24 is activated, the fourth switching means 24a is opened, and the Vnorm signal is not supplied through the fourth power indicating line 84 to the second flight control means 38, which leads to the reaction of the second flight control means 38 described above.

When the fifth switch 16 is activated, the fifth switching means 16a is opened, and accordingly, the Vnorm signal is not supplied through the fifth power indicating line 78, which is an indication of the abnormal power state for the first flight control means 36 and leads to the reaction of the first flight control means 36 described above. When the sixth switch 22 is activated, the sixth switching means 22a is opened, and therefore, the Vnorm signal is not supplied through the sixth power indication line 80. Accordingly, an abnormal power state signal is supplied to the second flight control means 38, which responds as described above.

The first switch 14 and the second switch 20 simulate an error in the first generator driven by the first engine. The third switch 18 and the fourth switch 24 simulate an error in a second generator driven by a second engine. The fifth switch 16 and the sixth switch 22 simulate the inclusion of an emergency power source, such as a battery or a retractable auxiliary power source. A plurality of power indication lines 74, 78, 82, and 76, 80, 84 are connected to the first flight control means 38 and the second flight control means, respectively. However, it will be understood by one of ordinary skill in the art that signals indicative of a plurality of error conditions may be transmitted along a single power indication line.

In normal flight operation, the function of the first and second switches 14 and 20 is performed by the first relay, the function of the third and fourth switches 18 and 24 is performed by the second relay, and the function of the fifth and sixth switches 16 and 22 is performed by the third relay. If a power failure condition occurs during normal flight operation, the first, second and third relays are energized to signal the power failure condition to the first and second flight control means 36, 38. Thus, if only one of the lines 74, 76, 78, 80, 82, 84 does not provide a Vnorm signal to the first flight control means 36 or the second flight control means 38, a message is displayed on the display device 40 and the aircraft means, for example entertainment system 68, is turned off. Testing such a complex design, including multiple redundancy, is a complex task and does not exclude errors.

If the simulated error signal of the power supply system is supplied to the system during testing from the generator side, the first, second and third relays are energized, and due to multiple redundancy, it is impossible to perform testing.

In addition, when the first relay is turned on in test mode, the power failure signal is transmitted to the first and second flight control means 36, 38 along the first power indicating line 74 and the second power indicating line 76. Both flight control systems 36, 38 will display a warning and disconnect any aircraft device. Due to the availability of redundancy, an error on the first power supply line 74 and / or an error of the first flight control means 36 is not detected since the second power supply line 76 does not provide a Vnorm signal to the second flight control means 38, and thus the second flight control means 38 displays a warning on the display device 40 and / or disables the entertainment system 68. The Vnorm signal is typically a ground voltage. If the first 74 power supply indicating line is accidentally connected to ground, the first power supply indicating line 74 cannot signal a power failure condition to the first flight control means 36.

Without the device and method in accordance with the present invention, the multi-level redundancy in accordance with the present invention can only be checked by checking the integrity of each line and sending signals indicating a failure state of the power supply system directly to the first and second flight control means 36, 38.

Additional switching means 14b, 20b, 16b, 22b, 18b and 24b may be used for additional testing and indication. These additional switching means 14b, 20b, 16b, 22b, 18b and 24b are connected to a device that displays in the aircraft cabin a simplified diagram of the actual state of the power supply system at the moment. A simplified diagram of the actual state of the power supply system includes the actual state of the generators 30, 34, the power bus and the cable harness. This simplified design is available to pilots and testing professionals.

The proposed device 1 for checking the operation of the flight control device is easily connected to the power bus and / or cable harness in a large commercial aircraft, since it contains only a few connectors. In addition, an easy-to-use device for testing flight control tools allows testing of a complex multiple-redundant power distribution scheme. An error in operation is unlikely, since the proposed device 1 for checking the operation of the flight control means contains only six switches. When performing the above tests, the power is not turned off, so other tests of the aircraft are not interrupted.

Claims (10)

1. A method of checking at least one means (36, 38) of flight control and wiring connected to it, moreover, means (36, 38) of flight control is configured to alert, turn off means (42, 44) of the aircraft and / or blocking its inclusion in response to a certain state of at least one power supply source (30, 32, 34) in an aircraft, comprising the following steps:
installing switching means (14a, 16a, 18a, 20a, 22a, 24a) in the line (74, 76, 78, 80, 82, 84; 52, 54) indicating the power supply connected to the first flight control means (36, 38), moreover, the line (74, 76, 78, 80, 82, 84; 52, 54) indicating the power supply transmits a signal indicating the state of the power source (30, 32, 34); changing the signal in the power indication line (74, 76, 78, 80, 82, 84; 52, 54) by activating the switching means (14a, 16a, 18a, 20a, 22a, 24a); and
checking the reaction of the flight control means (36, 38);
moreover, the step of installing the switching means (14a, 16a, 18a, 20a, 22a, 24a) in the power indication line (74, 76, 78, 80, 82, 84; 52, 54) includes installing the switching means in a plurality of power indication lines and / or installation of a plurality of switching means (14a, 16a, 18a, 20a, 22a, 24a) in a plurality of lines (74, 76, 78, 80, 82, 84; 52, 54) indicating power supply connected to the plurality of means (36, 38) flight control, and the step of changing the signal in the line (74, 76, 78, 80, 82, 84; 52, 54) indicating the power supply includes the step of changing many signals in many lines (74, 76, 78, 80, 82 , 84; 52, 54) power instructions. 2. The method according to claim 1, characterized in that the signal in the line (74, 76, 78, 80, 82, 84; 52, 54) indicating the power supply indicates a backup power source from a plurality of power sources. 3. The method according to claim 1, characterized in that the signal is transmitted along the line (74, 76, 78, 80, 82, 84; 52, 54) indicating the power supply to a variety of flight control means (36, 38). 4. The method according to claim 1, characterized in that the step of changing the signal in the line (74, 76, 78, 80, 82, 84; 52, 54) of the power supply includes the step of modeling the state of interruption or overload of the source (30, 32, 34 ) power supply. 5. A device (1) for checking the operation of the flight control means, configured to check at least one means (36, 38) of the flight control and the wiring connected to it, moreover, the means (36, 38) of the flight control is arranged to feed warning, turning off the means (42, 44) of the aircraft and / or blocking its inclusion in response to a failure condition of the power supply, containing:
a first connecting means (2, 4) configured to install a power indication in a first line (74) connected to a first flight control means (36), the first power indicating line (74) transmitting a signal indicating the state of the first source (30 ) power supply;
first switching means (14a) connected during operation so as to provide switching of the signal of the first power indicating line (74) connected to the first flight control means (36); and
second switching means (20a), connected during operation so as to provide switching of the signal of the second power indicating line (76) connected to the second flight control means (38). 6. The device according to claim 5, characterized in that it contains a second connecting means (10, 12), configured to install in the third and fourth lines (82, 84) indications of power connected to the first and second means (36, 38) flight control, respectively, with the third and fourth power supply lines (82, 84) transmitting a signal indicating a state of the second power supply source (34); third switching means (18a), connected during operation in such a way as to provide switching of the signal of the third power supply indicating line (82) connected to the first flight control means (36); and a fourth switching means (24a) connected during operation so as to provide switching of a signal of the fourth power indicating line (84) connected to the second flight control means (38). 7. The device according to claim 6, characterized in that it contains a third connecting means (6, 8) made with the possibility of installing in the fifth and sixth lines (78, 80) indications of power connected to the first and second means (36, 38) flight control, respectively, with the fifth and sixth power supply lines (78, 80) transmitting a signal indicating a state of the third power source (32); the fifth switching means (16a) connected during operation so as to provide switching of the signal of the fifth line (78) indicating the power supply connected to the first means (36) of flight control; and a sixth switching means (22a) connected during operation so as to provide switching of a signal of the sixth power supply indicating line (80) connected to the second flight control means (38). 8. The device according to claim 5, characterized in that the first power source is a first generator (30), driven into rotation by the first engine of the aircraft. 9. The device according to claim 6, characterized in that the second power source is a second generator (30), driven into rotation by the second engine of the aircraft. 10. The device according to claim 7, characterized in that the third source (32) of power supply is an emergency power source of the aircraft.

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