RU2450279C2 - Test device for checking signal lines of flight control system controlling electric motor operation in aircraft - Google Patents

Abstract

FIELD: physics.

SUBSTANCE: test device has at least one pilot relay (52, 54) for connection with the relay socket of the flight control system when checking signal lines of the flight control system, and at least one indicator (60, 70, 80, 90) which is electrically connected to at least one pilot relay (52, 54) for indicating whether voltage applied to the pilot relay (52, 54) is greater than or equal to a predetermined voltage. The disclosed method involves operations for connecting at least one pilot relay (52, 54) of the test device (1) instead of the operating relay to the relay socket of the flight control system, applying voltage to at least one pilot relay (52, 54) and determining whether voltage applied to at least one pilot relay (52, 54) is greater than or equal to a predetermined voltage.

EFFECT: easier checking.

12 cl, 2 dwg

Description

FIELD OF THE INVENTION

The present invention relates to a test device, its use, and to a method for checking the signal lines of a flight control system that controls the operation of the trimmable horizontal stabilizer (THS) of an aircraft.

State of the art

The engine responsible for actuating the trimmed horizontal stabilizer (THS) on board the aircraft must not start under certain circumstances, even if, for example, a pilot sends a control signal in the aircraft cockpit that would otherwise trigger the THS engine. Such special circumstances include flight situations in which starting the THS engine would have a negative or even catastrophic effect on aircraft safety.

The THS engine is usually controlled by a radio-electronic unit or flight control system that contains two relays (relay 51CE and relay 52CE), and depending on the voltage (usually 28 V) applied to the control contacts (winding contacts) of each of the two relays, starting the THS engine blocked even when control signals are transmitted, for example, from the cockpit of an aircraft through an electronic unit to both relays. Thus, depending on the voltage applied to the control contacts of the two relays, the THS motor cannot be started independently of any other control signals present in the electronic unit.

Flight safety has always been and remains a factor of paramount importance. Therefore, it is often necessary to carry out maintenance and control tests of aircraft. One such test involves testing the electronic control infrastructure of a flight control system that provides THS engine control. The purpose of such checks is, in particular, to determine the presence of a certain voltage on the control contacts of two relays contained in the electronic unit, which provides control of the THS engine. Thus, in the event of the successful completion of these tests, it can be guaranteed that the start of the THS engine will be blocked in situations where it could have a negative impact on flight safety.

During ground tests of the aircraft, the so-called Environmentally Sustainable Airport Operation (ESAO) system is used to simulate predefined flight situations in the electronic flight control system and to double-check the operation of the components of the flight control system in accordance with the technical specifications. The ESAO system generates control signals, which are then transmitted through the conductors of the flight control system to the THS engine. On the basis of the modeling signals that the ESAO system generates, they verify the correctness of the processing of the modeling signals by the flight control system and their conversion into the corresponding control signals to apply the corresponding voltages, for example, to two relays 51CE and 52CE, responsible for controlling the THS engine.

In particular, for flight situations that require THS engine start blocking, the ESAO system generates simulation signals, as a result of which voltage is applied to relay 51CE and relay 52CE to ensure that the THS engine cannot be started, regardless of any other control signals that can be generated on board an aircraft.

Until now, the voltage applied to the 51CE and 52CE relays (28 Volts) had to be measured manually. For this purpose, the first operator using the ESAO system simulated various flight situations, and the second operator communicating with the first operator using the radio communication system had to be in close proximity to the 51CE and 52CE relays to make sure that depending on the simulated flight In situations, the voltage applied to the two relays 51CE and 52CE is within a certain range. Therefore, such control tests were quite laborious and expensive.

Disclosure of invention

Thus, it is an object of the present invention to provide a test device that greatly simplifies ground testing of an aircraft, in particular ground testing, during which control logic circuits that control a THS engine are tested.

This and other tasks are accomplished with a test device for checking the signal lines of a flight control system that monitors the operation of the trimmable horizontal stabilizer (THS) engine of an aircraft, the flight control system comprising at least one relay installed in the corresponding relay socket. The test device comprises at least one control relay for connecting to the relay socket when checking the signal lines of the flight control system, and at least one indicator that is electrically connected to at least one control relay so that indicate whether the voltage applied to at least one monitoring relay is greater than or equal to a predetermined voltage.

With the test device according to the invention, only one operator can carry out ground tests of an aircraft, in particular tests related to THS engine control. The operator can start the ESAO system to provide simulation signals to the relays contained in the THS engine control system, and at the same time test the THS engine control system. For this purpose, the operator removes two working relays (51CE and 52CE) from the corresponding relay sockets and inserts plugs into these sockets that are electrically connected to the control relays of the test device. Thus, the tests are carried out not of the working relays themselves, but of the components and control logic circuits installed before the two working relays. The indicator of the test device immediately shows the operator whether the corresponding voltage is applied to the control contacts of the monitoring relay. Thus, the operator can check whether the working relay will interrupt the flow of current to the THS engine in those flight situations when the THS engine start must be blocked.

The test device according to the invention preferably comprises a first indicator and a second indicator, wherein the first indicator shows whether the voltage applied to the monitoring relay is greater than or equal to a predetermined voltage, and the second indicator indicates whether this voltage is less than preset voltage. Thus, depending on the activity of the first or second indicator, the operator will immediately find out whether the voltage applied to the working relay is sufficient to block the start of the THS engine.

In another preferred embodiment of the present invention, the test device comprises a first monitoring relay and a second monitoring relay. In this case, the first monitoring relay and the second monitoring relay are electrically connected to their own first and second indicators, i.e. the first monitoring relay is connected to the first and second indicators, and the second monitoring relay is electrically connected to the first and second indicators. Thus, for each control relay, two indicators are provided in order to indicate whether the correct voltage is applied to each of the control relays, and whether the applied voltage is greater than or equal to the preset voltage.

Each indicator of the relay socket test apparatus of the present invention preferably provides a visual signal. According to a preferred embodiment of the present invention, each indicator is a light emitting diode. In order to distinguish between the failure and the positive result of a ground test of the logic circuits that control the THS engine, light emitting diodes emit light of different colors. In this case, the operator can immediately establish whether the components of the electronic unit installed in front of the working relay comply with the technical requirements.

The test device according to the invention preferably comprises a monitoring relay plug which is installed in the relay socket of the flight control system to be tested. Thus, the 51SE and 52CE working relays can be easily replaced by installing two plugs of the monitoring relays in the corresponding relay sockets, and the test device will immediately show whether the voltage applied to the monitoring relays blocks the starting of the THS engine in predefined flight situations.

The pre-set voltage, which must be applied to the control contacts of the relay sockets to block the starting of the THS engine in certain flight situations, is preferably 28 volts.

Another aspect of the invention is the use of the test device described above for checking the signal lines of a flight control system that monitors the engine's trimmable horizontal stabilizer (THS) of an aircraft.

Another aspect of the invention is a method for checking the signal lines of a flight control system that controls the operation of the trimmed horizontal stabilizer aircraft engine, said flight control system comprising at least one relay mounted in a corresponding relay socket. The method according to the invention includes operations in which at least one control relay of the test device is connected, instead of at least one relay of the flight control system with a relay socket of the flight control system, voltage is applied to said at least one control relay and determining whether the voltage applied to the specified monitoring relay is greater than or equal to the predetermined voltage.

To apply voltage to at least one monitoring relay, an ESAO system is preferably used.

According to a preferred embodiment, the method includes an operation in which it is simultaneously determined whether the voltages applied to the two monitoring relays that are installed in two corresponding flight control relay relays in series are equal to or greater than the predetermined voltage.

Other characteristics and advantages of the invention are apparent from the following detailed description of a preferred embodiment of the invention with reference to the accompanying drawings.

Brief Description of the Drawings

Figure 1 is a schematic perspective view of a test device with relay sockets according to the present invention.

Figure 2 is a circuit diagram of a test device with relay sockets shown in Figure 1.

The implementation of the invention

1 shows a preferred embodiment of a test device according to the invention. Test device 1 is particularly suitable for testing the signal lines of a flight control system monitoring the operation of the trimmed horizontal stabilizer (THS) engine of an aircraft. More specifically, the test device 1 according to the invention is particularly suitable for use to test components, signal lines, terminals, and the like. flight control systems located in front of the THS engine during ground tests of the aircraft using the ESAO system, which is capable of simulating various flight situations.

The test device 1 contains two plugs 10, 20, which are inserted into the corresponding relay sockets (not shown), thereby replacing the working relays, in particular 51CE and 52CE, of the electronic unit. The plugs 10, 20 are connected to the housing 50 of the test device using cable 30. Cable 30 can be of any length, in particular 10 meters, in order to increase the degree of freedom of use of the test device.

As can be seen in FIG. 1, indicators are installed in the housing 50, in particular light emitting diodes 60, 70, 80, 90. In a preferred embodiment, the light emitting diodes 60, 80 and the light emitting diodes 70, 90 have radiation of various colors, in particular red and green. During operation of the test device 1, the light emitting diodes 60, 80 and the light emitting diodes 70, 90 indicate whether the voltage applied to the signal lines of the flight control system is equal to a predetermined voltage. If this voltage is equal to the preset voltage, the light emitting diodes 60, 80 will be active, while the light emitting diodes 70, 90 will be active if the voltage is less than the preset voltage.

Figure 2 presents a schematic diagram of the electrical connections of the test device 1 of Figure 1. The same reference numbers denote identical or similar components of the test device shown in Fig.1.

Two control relays 52, 54 are installed in the housing 50 of the test device, each of which is electrically connected by current conductors with plugs 10, 20. X1, X2 mean control contacts (winding contacts) of the control relays 52, 54, and A2, A3 are the contacts of the control relay armature 52, 54. In addition, the light emitting diodes 60, 70 and 80, 90 are connected to the respective conductors passing between the plugs 10, 20 and the control relays 52, 54. In particular, the light emitting diodes 60, 80 are connected to the corresponding conductors of the control contacts X1 and X2 while ak light emitting diodes 70, 90 connected to conductive contacts A2 and A3 armature control relays 52, 54.

If the plugs 10, 20 are inserted into the corresponding relay sockets of the electronic block and the voltage applied by the ESAO system through the electronic block to the contacts X1, X2 (X2 is a grounded contact) is equal to or greater than the preset voltage, the light-emitting diodes 60, 80 will be active. In other words, the light emitting diodes 60, 80 will emit light if the voltage applied to the contacts X1 and X2 is equal to or greater than 28 V. In this situation, the light emitting diodes 70, 90 will be inactive, since the contacts A2, A3 are not closed by the control relays 52, 54. However, if the voltage applied to the contacts X1 and X2 is less than 28 V, the control relays are closed by the contacts A2, A3 of the armature, so the light-emitting diodes 70, 90 will be active, while the light-emitting diodes 60, 80 will be inactive .

The essence of the invention is to provide technical personnel serving the aircraft, a simple and convenient way to check the signal lines of the flight control system, monitoring, for example, the operation of the engine THS aircraft. For this purpose, the working relays (51CE and 52CE) are removed from the respective relay sockets and plugs 10, 20 of the test device according to the present invention are installed in their place. After starting the ESAO system, which simulates various flight situations, it is necessary to determine whether the voltage applied during this test to the signal lines of the flight control system and, therefore, to the control contacts X1 and X2 of the control relays 52, 54 is equal to the preset voltage 28 B. This voltage corresponds to the voltage that is applied to the control contacts of the working relays 51CE and 52CE during aircraft operation and which blocks the start of the THS engine in the pre-determined divided flight situations. Thus, instead of checking the working relays 51CE and 52CE themselves, the test device according to the invention allows you to check components, signal lines, terminals, etc. of the electronic unit located in front of the THS engine in order to determine whether the corresponding voltage will be applied to the control contacts of the working relays 51CE and 52CE during aircraft operation, which blocks the start of the THS engine in preset flight situations. As a result, flight safety is greatly increased.

When using the test device according to the invention, one operator will be able to start the ESAO system and carry out the necessary ground tests of the radio electronic unit responsible for controlling the THS engine.

Claims (12)

1. A test device (1) for checking the signal lines of a flight control system monitoring the operation of the engine of the trimmed horizontal stabilizer of an aircraft, said flight control system comprising at least one relay mounted in a corresponding relay socket; comprising: at least one control relay (52, 54) for connecting to the relay socket when checking the signal lines of the flight control system, at least one indicator (60, 70, 80, 90), electrically connected at least with one monitoring relay (52, 54) to indicate whether the voltage applied to at least one monitoring relay (52, 54) is greater than or equal to a predetermined voltage. 2. The test device according to claim 1, characterized in that at least one indicator comprises a first indicator (60, 80) and a second indicator (70, 90), while the first indicator (60, 80) is intended to indicate whether the voltage applied to at least one control relay (52, 54) is greater than or equal to a predetermined voltage, and the second indicator (70, 90) is intended to indicate whether the voltage is less, than the pre-set voltage. 3. The test device according to claim 2, characterized in that at least one control relay comprises a first control relay (52) and a second control relay (54) for connecting to the respective relay control relay sockets when checking the signal lines of the control system flight, while the first control relay (52) and the second control relay (64) are electrically connected to the first indicator (60, 80) and the second indicator (70, 90), respectively. 4. The test device according to claim 3, characterized in that each of the first indicators (60, 80) is electrically connected to the control contacts (X1, X2) of the first (52) and second (54) control relays, respectively, with each of the second indicators (70, 90) are electrically connected to the contact (A2, A3) of the armature of the first (52) and second (54) monitoring relays, respectively. 5. The test device according to claim 1, characterized in that each indicator (60, 70, 80, 90) is configured to supply a visual signal. 6. The test device according to claim 2, characterized in that each indicator is a light emitting diode, while the first (60, 80) and second (70, 90) light emitting diodes emit light of a different color. 7. The test device according to claim 1, characterized in that each control relay (52, 54) is connected to a control relay plug (10, 20) installed in the corresponding relay socket of the flight control system under test. 8. The test device according to claim 1, characterized in that the pre-set voltage is 28 V. 9. The use of the test device (1) according to one of the preceding paragraphs for checking the signal lines of a flight control system that monitors the operation of the engine trimmed horizontal stabilizer of the aircraft. 10. A method for checking the signal lines of a flight control system that controls the operation of the engine trimmed horizontal stabilizer of the aircraft; moreover, the flight control system contains at least one relay installed in the corresponding relay socket; comprising the following operations: at least one control relay (52, 54) of the test device (1) is connected according to one of claims 1 to 8, instead of the flight control system relay, a voltage of at least at least one monitoring relay (52, 54) determines whether the voltage applied to at least one monitoring relay (52, 54) is greater than or equal to a predetermined voltage. 11. The method according to claim 10, characterized in that the system of environmentally balanced operation of the airport initiates the application of voltage to at least one control relay (52, 54). 12. The method according to claim 10 or 11, characterized in that it includes an operation in which it is simultaneously determined whether the voltages applied to the two monitoring relays (52, 54) are connected to two corresponding relay control system relay sockets connected in series, greater than or equal to the preset voltage.

Images