CN111239526B - Aircraft communication controller testing arrangement - Google Patents
Aircraft communication controller testing arrangement Download PDFInfo
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- CN111239526B CN111239526B CN202010129212.5A CN202010129212A CN111239526B CN 111239526 B CN111239526 B CN 111239526B CN 202010129212 A CN202010129212 A CN 202010129212A CN 111239526 B CN111239526 B CN 111239526B
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- communication controller
- power supply
- supply circuit
- voltage divider
- airplane
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
- G01R31/00—Arrangements for testing electric properties; Arrangements for locating electric faults; Arrangements for electrical testing characterised by what is being tested not provided for elsewhere
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B23/00—Testing or monitoring of control systems or parts thereof
- G05B23/02—Electric testing or monitoring
- G05B23/0205—Electric testing or monitoring by means of a monitoring system capable of detecting and responding to faults
- G05B23/0208—Electric testing or monitoring by means of a monitoring system capable of detecting and responding to faults characterized by the configuration of the monitoring system
- G05B23/0213—Modular or universal configuration of the monitoring system, e.g. monitoring system having modules that may be combined to build monitoring program; monitoring system that can be applied to legacy systems; adaptable monitoring system; using different communication protocols
Abstract
The invention relates to a testing device for an aircraft communication controller. The aircraft communication controller testing arrangement includes: the device comprises a signal source, a multi-path voltage divider and a display instrument; the multi-way voltage divider comprises a plurality of output ports; the output end of the signal source is connected with the input end of the multi-path voltage divider, each output port of the multi-path voltage divider is connected with the input end of a control element in the communication controller of the airplane to be tested, and the output ports correspond to the input ends of the control elements one to one; the output end of the communication controller of the airplane to be tested is connected with a display instrument; the multi-path voltage divider is used for dividing the voltage signal sent by the signal source into a plurality of test voltage signals; the plurality of test voltage signals differ in amplitude. The invention can realize the simultaneous test of various elements in the communication controller of the airplane, saves the cost and is convenient to operate.
Description
Technical Field
The invention relates to the field of detection of communication controllers, in particular to a testing device for an aircraft communication controller.
Background
The communication controller is a communication interface device which is arranged between a data circuit and a host computer in a data communication system and is used for controlling data transmission. The existing communication controller testing device of the airplane can only test one control element such as radio voice, and needs a plurality of devices when the various control elements such as the radio voice and the compass need to be tested simultaneously, so that the testing cost is high, the needed devices are more, and the operation is inconvenient.
Disclosure of Invention
The invention aims to provide a testing device for an aircraft communication controller, which is used for simultaneously testing various elements in the aircraft communication controller, saves cost and is convenient to operate.
In order to achieve the purpose, the invention provides the following scheme:
an aircraft communications controller testing device comprising: the device comprises a signal source, a multi-path voltage divider and a display instrument;
the multi-way voltage divider comprises a plurality of output ports; the output end of the signal source is connected with the input end of the multi-path voltage divider, each output port of the multi-path voltage divider is connected with the input end of a control element in the communication controller of the airplane to be tested, and the output ports correspond to the input ends of the control elements one by one; the output end of the communication controller of the airplane to be tested is connected with the display instrument; the multi-path voltage divider is used for dividing the voltage signal sent by the signal source into a plurality of test voltage signals; the amplitudes of a plurality of test voltage signals are different; the communication controller of the airplane to be tested is used for obtaining the output voltage of each control element according to the plurality of test voltage signals; and the display instrument is used for displaying the output voltage of all control elements in the communication controller of the airplane to be tested.
Optionally, the aircraft communication controller testing device further includes: and the signal source is connected with the multi-path voltage divider through the isolator.
Optionally, the aircraft communication controller testing device further includes: a panel on which the display is disposed; and the panel is provided with a test hole, and the output port of the multi-path voltage divider is connected with the input end of the communication controller of the airplane to be tested through the test hole.
Optionally, the aircraft communication controller testing device further includes: the switches are arranged on the panel, one switch is connected with one output port of the multi-path voltage divider, the switches correspond to the output ports one by one, and the switches are used for controlling the on or off of the output ports.
Optionally, the aircraft communication controller testing device further includes: and the power supply circuit is respectively connected with the signal source and the communication controller of the airplane to be tested.
Optionally, the power supply circuit includes a first power supply circuit and a second power supply circuit, and the first power supply circuit includes a first rectification circuit, a first linear voltage regulator and a first filter, which are connected in sequence; the second power supply circuit comprises a second rectifying circuit, a second linear voltage stabilizer and a second filter which are connected in sequence; the first power supply circuit is used for supplying power to the signal source, and the second power supply circuit is used for supplying power to the communication controller of the airplane to be tested.
Optionally, the power circuit further includes: and the input end of the first power supply circuit and the input end of the second power supply circuit are connected with the mains supply through the transformer.
Optionally, the signal source is a two-channel sinusoidal signal generator.
Optionally, the dual-channel sinusoidal signal generator includes an oscillator group, a preamplifier, a compensation limiter, and a linear amplifier, which are connected in sequence.
Optionally, the oscillator group is composed of two oscillators connected in parallel.
According to the specific embodiment provided by the invention, the invention discloses the following technical effects: the invention divides the signal source into signals with various amplitudes by arranging the multi-path voltage divider, realizes the integration of the test functions of various control elements such as radio station voice and compass, and saves the cost compared with the prior art that each device can only detect one control element such as compass.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed to be used in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings without inventive exercise.
FIG. 1 is a schematic structural diagram of a testing device for an aircraft communication controller according to an embodiment of the present invention;
FIG. 2 is a schematic structural diagram of a panel of an aircraft communication controller testing apparatus according to an embodiment of the present invention;
FIG. 3 is a schematic diagram illustrating the connection between a button and a testing hole of the testing device of the aircraft communication controller according to the embodiment of the present invention;
FIG. 4 is a block diagram of a power circuit in the testing apparatus for an aircraft communication controller according to the embodiment of the present invention;
fig. 5 is a block diagram of a circuit connection structure of a dual-channel sinusoidal signal generator of the aircraft communication controller testing device according to the embodiment of the invention.
Description of the symbols:
the test device comprises a panel 1, a voltmeter 2, an ammeter 3, an integrated AC meter 4, a switch 5, a test hole 6, a power switch 7, a socket 8, a signal source 9, an isolator 10, a multi-path voltage divider 11, a power circuit 12 and a fuse 13.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The invention aims to provide a testing device for a communication controller. The invention divides the signal source into signals with various amplitudes by arranging the multi-path voltage divider, realizes the integration of the test functions of various control elements such as radio station voice and compass, and saves the cost compared with the prior art that each device can only detect one control element such as compass
In order to make the aforementioned objects, features and advantages of the present invention comprehensible, embodiments accompanied with figures are described in further detail below.
Example 1
As shown in fig. 1, an aircraft communication controller testing apparatus includes: a signal source 9, a multi-path voltage divider 11 and a display instrument;
the multi-way voltage divider 11 includes a plurality of output ports; the output end of the signal source 9 is connected with the input end of the multi-path voltage divider 11, each output port of the multi-path voltage divider 11 is connected with the input end of a control element in the communication controller of the airplane to be tested, and the output ports correspond to the input ends of the control elements one by one; the output end of the communication controller of the airplane to be tested is connected with the display instrument, and the multi-path voltage divider 11 is used for dividing the voltage signal sent by the signal source 9 into a plurality of test voltage signals; the amplitude values of the test voltage signals are different and are divided into eight amplitude value signals; the communication controller of the airplane to be tested is used for obtaining the output voltage of each control element according to the plurality of test voltage signals; and the display instrument is used for displaying the output voltage of all control elements in the communication controller of the airplane to be tested.
As an alternative embodiment, as shown in fig. 2, the display instrument includes a voltmeter 2, an ammeter 3 and a comprehensive ammeter 4.
As an optional implementation manner, the signal source 9 is provided with a metal shielding box, a shielding wire is used in signal transmission, and a shielding layer is arranged on a circuit board of the aircraft communication controller testing device.
As an alternative embodiment, a socket 8 is provided on the display, and the socket 8 is used for connecting the aircraft communication controller to be tested, providing an excitation source for the CCU, and collecting a feedback signal of the CCU.
As an optional implementation manner, the aircraft communication controller testing device further includes: an isolator 10, wherein the signal source 9 is connected with the multi-way voltage divider 11 through the isolator 10.
As an optional implementation manner, the aircraft communication controller testing device further includes: the display device comprises a panel 1, wherein the display device is arranged on the panel 1; the panel 1 is provided with a test hole 6, the output port of the multi-path voltage divider 11 is connected with the input end of the communication controller of the airplane to be tested through the test hole 6, and the test hole 6 sends the signal to the corresponding contact of the communication controller of the airplane to be tested through the adapter cable.
As an optional implementation manner, the aircraft communication controller testing device further includes: a plurality of switches 5, a plurality of said switches 5 being provided on said panel 1. As shown in fig. 3, one of the switches 5 is connected to one output port of the multi-path voltage divider 11, and the switches 5 correspond to the output ports one by one, the switch 5 is used to control the on or off of the output port, and a fuse 13 is connected between the output port and the switch for protection. Each switch 5 corresponds to a voltage signal with a corresponding amplitude, when the required switch 5 is pressed, the corresponding signal is sent to an earphone signal amplifier or a microphone amplifier of the communication controller of the airplane to be tested, and the voltmeter 2, the ammeter 3 and the comprehensive alternating current meter 4 are used for displaying the output voltage and current of the communication controller.
As an optional implementation manner, the aircraft communication controller testing device further includes an equivalent load of the aircraft communication controller to be tested, the testing hole 6 is connected with the comprehensive alternating current meter 4 through the equivalent load of the aircraft communication controller to be tested, and the equivalent load of the aircraft communication controller to be tested is used for simulating and recording the capacitive reactance and the impedance of the communication device.
As an optional implementation manner, the aircraft communication controller testing device further includes: and the power supply circuit 12 is connected with the signal source 9 and the communication controller of the airplane to be tested respectively.
As an alternative implementation, as shown in fig. 4, the power supply circuit 12 includes a first power supply circuit and a second power supply circuit, and the first power supply circuit includes a first rectification circuit, a first linear regulator and a first filter, which are connected in sequence; the second power supply circuit comprises a second rectifying circuit, a second linear voltage stabilizer and a second filter which are connected in sequence; the first power supply circuit is used for supplying power to the signal source 9, and the second power supply circuit is used for supplying power to the communication controller of the airplane to be tested.
As an optional implementation manner, the first power circuit and the second power circuit are linear dc power supplies, and the two circuits are not affected by each other and are isolated independent power supplies.
As an alternative embodiment, the panel 1 further comprises a power switch 7, which is connected to the first power circuit and the second power circuit.
As an optional implementation manner, the power supply of the signal source 9 is 50V dc voltage, and the working power supply of the aircraft communication controller to be tested is 27V dc voltage.
As an alternative embodiment, the power circuit 12 further includes: and the input end of the first power supply circuit and the input end of the second power supply circuit are connected with the mains supply through the transformer.
As an alternative embodiment, the signal source 9 is a two-channel sinusoidal signal generator.
As an alternative embodiment, as shown in fig. 5, the two-channel sinusoidal signal generator includes an oscillator group, a preamplifier, a compensation limiter and a linear amplifier, which are connected in sequence.
As an alternative embodiment, the oscillator group consists of two oscillators connected in parallel. The two oscillators are respectively a first oscillator and a second oscillator, the first oscillator and the second oscillator are both temperature-compensated PLL oscillators, the output frequency of the first oscillator is 400Hz, the output frequency of the second oscillator is 1000Hz, the frequency band passing characteristic of the aircraft communication controller can be detected by selecting signals representing 1000Hz of high pitch and 400Hz of low pitch, and the waveform of the signals is a standard sine wave.
The invention adopts the technical scheme, and has the advantages that:
on the basis of intensive and serious investigation, the full technical demonstration is carried out on the aspects of the reliability, operability, practicability and the like of the equipment, and the design is further improved and optimized from the actual requirement. In addition, the operation is simpler by adopting the built-in signal source, the detection method is optimized, and the panel structure is clear.
Aiming at the problem that small alternating current signals used in the measuring process are easily interfered by the outside and a power supply of the scheme, the scheme reduces the influence of interference in two aspects of adopting a linear direct current power supply and a signal source circuit shielding design.
The device is simple and practical to operate, can meet the requirements of the operation and use of crew members with high school culture and is portable and easy to use.
The embodiments in the present description are described in a progressive manner, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other.
The principles and embodiments of the present invention have been described herein using specific examples, which are provided only to help understand the method and the core concept of the present invention; meanwhile, for a person skilled in the art, according to the idea of the present invention, the specific embodiments and the application range may be changed. In view of the above, the present disclosure should not be construed as limiting the invention.
Claims (7)
1. An aircraft communication controller testing device, comprising: the device comprises a signal source, a multi-path voltage divider and a display instrument;
the multi-way voltage divider comprises a plurality of output ports; the output end of the signal source is connected with the input end of the multi-path voltage divider, each output port of the multi-path voltage divider is connected with the input end of a control element in the communication controller of the airplane to be tested, and the output ports correspond to the input ends of the control elements one by one; the output end of the communication controller of the airplane to be tested is connected with the display instrument; the multi-path voltage divider is used for dividing the voltage signal sent by the signal source into a plurality of test voltage signals; the amplitudes of a plurality of test voltage signals are different; the communication controller of the airplane to be tested is used for obtaining the output voltage of each control element according to the plurality of test voltage signals; the display instrument is used for displaying the output voltages of all control elements in the communication controller of the airplane to be tested; the signal source is a two-channel sinusoidal signal generator; the dual-channel sinusoidal signal generator comprises an oscillator group, a preamplifier, a compensation amplitude limiter and a linear amplifier which are connected in sequence; the oscillator group consists of two oscillators connected in parallel.
2. An aircraft communication controller testing device according to claim 1, further comprising: and the signal source is connected with the multi-path voltage divider through the isolator.
3. An aircraft communication controller testing device according to claim 1, further comprising: a panel on which the display is disposed; and the panel is provided with a test hole, and the output port of the multi-path voltage divider is connected with the input end of the communication controller of the airplane to be tested through the test hole.
4. An aircraft communication controller testing device according to claim 3, further comprising: the switches are arranged on the panel, one switch is connected with one output port of the multi-path voltage divider, the switches correspond to the output ports one by one, and the switches are used for controlling the on or off of the output ports.
5. An aircraft communication controller testing device according to claim 1, further comprising: and the power supply circuit is respectively connected with the signal source and the communication controller of the airplane to be tested.
6. The aircraft communication controller testing device of claim 5, wherein the power supply circuit comprises a first power supply circuit and a second power supply circuit, and the first power supply circuit comprises a first rectifying circuit, a first linear voltage regulator and a first filter which are connected in sequence; the second power supply circuit comprises a second rectifying circuit, a second linear voltage stabilizer and a second filter which are connected in sequence; the first power supply circuit is used for supplying power to the signal source, and the second power supply circuit is used for supplying power to the communication controller of the airplane to be tested.
7. An aircraft communications controller testing device according to claim 6, wherein the power supply circuit further comprises: and the input end of the first power supply circuit and the input end of the second power supply circuit are connected with the mains supply through the transformer.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010129212.5A CN111239526B (en) | 2020-02-28 | 2020-02-28 | Aircraft communication controller testing arrangement |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010129212.5A CN111239526B (en) | 2020-02-28 | 2020-02-28 | Aircraft communication controller testing arrangement |
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| CN111239526A CN111239526A (en) | 2020-06-05 |
| CN111239526B true CN111239526B (en) | 2022-02-18 |
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