RU166823U1 - APPARATUS FOR CHECKING THE HELICOPTER AUTOPILOT - Google Patents

Abstract

1. Equipment for checking the autopilot of a helicopter, comprising a control unit with built-in software, equipped with an indicator and a keyboard for issuing information to the operator and receiving commands from him, a switching device for transmitting signals to the control object and a measuring unit containing a microcontroller with non-volatile memory for storing data and controlling the process of measuring and generating test signals by issuing commands to the transducers, meters, which are part of the measuring unit and a signal switch, in addition, the measuring unit contains amplifiers that amplify the test signals, and normalizers, bringing the input signals to the range of meters. 2. The equipment for checking the autopilot of a helicopter according to claim 1, characterized in that the control unit comprises a digital interface for transmitting data to a computer.

Description

The utility model relates to measuring equipment, namely, devices for performing checks and adjusting autopilot on board a helicopter during routine maintenance, in particular the AP-34B electro-hydraulic autopilot and autopilot components.

Currently, the control and measurement of the parameters of the electro-hydraulic autopilot of the helicopter and the components of the autopilot are carried out at specialized stands, in accordance with current methods.

A device for checking the quality of operation of autopilots is known (patent No. 2181681, 1999, patent holder of the State Unitary Enterprise "Instrument Design Bureau"). The known solution describes a device for implementing a method for checking the quality of the operation of the steering unit and the autopilot of guided projectiles, based on measuring the time of the equivalent delay of the steering gear or autopilot in certain conditions. The measured parameter during verification is the angle of rotation of the rudders. Information is removed from the actuator of the system - the steering drive, and the device provides the supply of test electrical signals to the system, the functioning of the actuator (pneumatic system) and creates mechanical loads for it. The disadvantage of this solution is that it is designed to record only one of the characteristics of the automatic control system.

The closest, taken as a prototype is the calibration apparatus PAA 34B. - operating instructions 6C1.410.000TO, 2003, Federal State Institution “Ufa Instrument-Making Production Association” (see Appendix), intended for checking and adjusting the units and set of the AP-34B autopilot in a helicopter, in a laboratory, and in aircraft workshops. The equipment includes a control panel for checking compensation sensors and angular velocity sensors, a control unit for controlling the control unit and autopilot AP-34B, a control panel for checking the control unit and autopilot AP-34, a control panel for checking the height corrector KV-P, an adapter, an arm that verify the parameters of individual units and autopilot complex. The disadvantage of this equipment is the high complexity of the verification process, the significant dimensions of the installation for verification, as well as low measurement accuracy due to the influence of the human factor and the use of obsolete equipment.

Taking into account the significant range of equipment under test and taking into account the fact that well-known test benches and test equipment are designed to perform manual checks, it takes a long time to carry out checks during routine maintenance, requires highly qualified personnel, as well as significant production facilities for organizing workplaces . In addition, for verification, it is necessary to dismantle the equipment and deliver it to the inspection site.

The objective of the claimed solution is the creation of mobile equipment for testing autopilots and its components directly on board the helicopter, as well as reducing the complexity, time of verification and improving the accuracy of measurements.

This goal is achieved due to the fact that the equipment for checking the autopilot of the helicopter is made up of a control unit with built-in software, equipped with an indicator and a keyboard for issuing information to the operator and receiving commands from him, a switching device for transmitting signals to the control object and a measuring unit containing microcontroller with non-volatile memory for storing data and controlling the process of measuring and generating test signals by issuing commands to incoming Technical contents are subject transducers measuring unit, measuring instruments and signal switch furthermore comprises a measuring unit amplifiers amplifying test signals and normalizers resulting signals to the band gauges. And also due to the fact that the control unit may contain a digital interface for transmitting data to a computer.

The technical result of the solution is achieved through the use of the claimed combination of essential features and consists in the creation of mobile control and testing equipment for carrying out checks of the helicopter’s autopilots and its constituent elements in semi-automatic mode and directly on board the helicopter, which ensures the convenience of checks, increasing the reliability and reliability of the results of a comprehensive check parameters of the equipment under test in all operating modes, the possibility of semi-automatic iCal checks. The claimed test equipment through software and mathematics that implements an operating algorithm using a database of tests, in accordance with the technical conditions for the object of verification, generates a set of signals. Each set of test signals corresponds to a set of reference signals at the outputs of the test objects. The technical result also consists in the possibility of maintaining an electronic database of inspections, expanding the list of equipment being checked. Diagnostics and verification of equipment is carried out in a semi-automatic mode, using software, which ensures high accuracy of equipment quality control and diagnostics of its malfunctions, and also reduces the influence of the human factor on measurement accuracy and reduces the time required to verify equipment operability, since it does not require costs for dismantling and subsequent installation of the equipment under test. The claimed solution is illustrated by the following drawings.

In FIG. 1 shows a functional diagram of the equipment for checking the autopilot.

The equipment includes, located in a single housing, a control unit 1, a measuring unit 2, a signal switching device 3.

The digital part of measuring unit 2 consists of a microcontroller 4 and non-volatile memory 5. The microcontroller 4 is connected via inputs and outputs to transducers 6, meters 7, and a signal switcher 10. Measuring unit 2 contains amplifiers 8, amplifying test signals and normalizers 9, leading the input signals to range of meters.

The control unit 1 (CU) is used to perceive the operator’s commands through the built-in keyboard and issue control actions to the measuring unit 2, as well as to receive the measured data from the measuring unit 2, display information on the built-in screen, and write the measurement data to the built-in memory.

Measuring unit 2 (BI) is used to perceive commands from control unit 1, to execute sequences of actions specified by control unit 1 (primary conversion, measurement, digitization of measured signals; automatic tuning; digital-to-analogue conversion and amplification of test signals; switching of measuring lines to the control object).

The switching device 3 is used to transmit test signals to the control object from the measuring unit 2 and the measured signals from the control object to the measuring unit 2.

To transfer the accumulated data to software (software) to a personal computer (PC), control unit 1 has a standard digital data transfer interface, through which data is transferred for subsequent conversion, systematization, and storage.

The work of the complex is built on the principle of a machine-man interface.

The required operations and calculations occur in semi-automatic mode under the control of the operator.

The control unit 1 is used to enter the operator commands to control the test process, as well as to provide the operator with the necessary information on the process and test results.

The commands entered by the operator are processed in the control unit 1, converted by means of the embedded algorithm into a sequence of elementary commands for the measuring unit 2.

At the command of the control unit 1, the measuring unit 2 generates the required voltage ratings with the specified characteristics, which are supplied through the switching device 3 to the control object.

The signals from the control object through the switching device 3 enter the measuring unit 2, where they are converted, measured (digitized), and transferred to the control unit 1 for display and storage, as well as for the automatic control system in closed control loops of the control object. The data received from the measuring unit 2 are displayed on the control unit 1, forming the operator information field.

The operation of the measuring unit 2 is based on the implementation of simple algorithms and computational operations. The digital part of the measuring unit consists of a microcontroller 4 and non-volatile memory 5. The non-volatile memory 5 is used to store the executable part of the embedded software (loaded into the microcontroller 4 when the equipment is turned on) and calibration coefficients for the correct conversion of signals from a digital to an analog domain and vice versa.

The microcontroller 4 executes the program code. At the same time providing:

a. data exchange with control unit 1;

b. receiving and interpreting top-level commands from control unit 1;

c. the issuance of elementary commands to converters 6, meters 7 and the switch 10;

d. mathematical transformations over the received data;

e. data exchange with non-volatile memory 5;

f. data exchange with meters 7 and converters 6.

Converters 6 are used to convert, at the command of the microcontroller 4, input voltage signals from external power sources to multiple output signals of the required amplitudes and phasing. In this case, both digital signals and the signals of analog sensors interpreted by the control object as Euler angles (position of the object in space), angular velocities, altitude and airspeed are simulated.

The signals after conversion are amplified by amplifiers 8 to provide the required amplitude amplitude and increase the line power and are fed to the signal switch 10.

The signal switch 10 redirects the signals along the required line at the command of the microcontroller 4 for supply to the control object.

The reaction in the form of electrical signals from the control object through the interrogated line of the signal switch 10 is supplied to one of the meters 7 through the normalizer 9, where it is converted to a digital signal form.

Normalizers 9 are used to coordinate the measuring lines between the control object and meters 7, preliminary conversion of the analog signal (attenuation, amplification or filtering).

The digitalized signals from the meters 7 are fed to the microcontroller 4 to perform further mathematical operations and transmit the results to the control unit.

In measuring block 2, in addition to open loops (formation / measurement), closed control loops, which are required for the object control process, are also implemented (when the output signals of the shapers are automatically adjusted according to the results of the data received from the meters to achieve the desired criterion).

The software product included in the equipment can be deployed on a personal computer under the control of the operating system, for reading the data accumulated in the control unit 1, forming a database, generating a report on the work done, generating statistical calculations, graphs, etc., as well as programming of control unit 1 (recording in the memory of control unit 1 of the list of serial numbers of the aircraft of the user to bind the stored data to the board number).

The inventive control and verification equipment for checking autopilots allows for objective monitoring, to increase accuracy, reduce the complexity and cost of control and does not require the use of expensive and bulky instruments and equipment. Testing equipment is a mobile automated device for monitoring and measuring autopilot parameters, it is used directly on board the helicopter and monitors and measures all the necessary parameters of the equipment under test in a semi-automatic mode in accordance with current regulatory documents, collecting, processing, accumulating and storing the results of checks, output results of checks, maintaining a database for each tested device. All measured values using the software for each type of device are stored in a database for this type of device and can be used to verify its operability during operation.

Claims (2)

1. Equipment for checking the autopilot of a helicopter, comprising a control unit with built-in software, equipped with an indicator and a keyboard for issuing information to the operator and receiving commands from him, a switching device for transmitting signals to the control object and a measuring unit containing a microcontroller with non-volatile memory for storing data and controlling the process of measuring and generating test signals by issuing commands to the transducers, meters, which are part of the measuring unit and a signal switch, in addition, the measuring unit contains amplifiers that amplify the test signals, and normalizers, bringing the input signals to the range of meters. 2. Equipment for checking the autopilot of a helicopter according to claim 1, characterized in that the control unit comprises a digital interface for transmitting data to a computer.

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