阅读说明：本技术 一种罗盘原位综合检测系统 (Compass in-situ comprehensive detection system ) 是由 赵长彦 软会英 车建鹏 闫亮 车建 东钊 于 2019-11-18 设计创作，主要内容包括：本发明提供一种罗盘原位综合检测系统,包括电源模块、信号产生组件、辐射器组件以及显控组件,电源模块的输出端与信号产生组件、辐射器组件以及显控组件的输入端连接,所述信号产生组件的输出端与辐射器组件的输入端连接,所述信号产生组件的输出端还与显控组件的输入端连接,与现有技术相比,本发明具有如下的有益效果：无需拆卸设备即可实现对无线电罗盘的原位检查,实现对无线电罗盘系统接收灵敏度、定向灵敏度、罗盘罗差等指标的定量测试,判断该设备工作是否正常,另外还可以对环形天线单元进行性能检测。(The invention provides a compass in-situ comprehensive detection system, which comprises a power module, a signal generating assembly, a radiator assembly and a display control assembly, wherein the output end of the power module is connected with the input ends of the signal generating assembly, the radiator assembly and the display control assembly, the output end of the signal generating assembly is connected with the input end of the radiator assembly, and the output end of the signal generating assembly is also connected with the input end of the display control assembly, and compared with the prior art, the compass in-situ comprehensive detection system has the following beneficial effects: the radio compass can be checked in situ without disassembling the equipment, so that the quantitative test of the indexes of the radio compass system, such as receiving sensitivity, directional sensitivity, compass error and the like, is realized, whether the equipment works normally is judged, and in addition, the performance detection can be carried out on the annular antenna unit.)

1. The utility model provides a compass normal position integrated detection system, includes power module, signal generation subassembly, radiator subassembly and shows accuse subassembly, its characterized in that: the output of power module and signal production subassembly, radiator subassembly and show the input of accuse subassembly and be connected, the output of signal production subassembly is connected with radiator subassembly's input, the output of signal production subassembly still is connected with the input that shows the accuse subassembly.

2. The compass in-situ comprehensive detection system of claim 1, wherein: the signal generating assembly adopts an FPGA + DAC structure (DDS) to complete signal generation and signal amplitude and phase adjustment, and the signal frequency range is 100-1799.5 KHz.

3. The compass in-situ comprehensive detection system of claim 1, wherein: the radiator assembly is used for completing the size ratio matching of the vertical antenna signal and the annular antenna signal and the matching of the corresponding interface.

4. The compass in-situ comprehensive detection system of claim 1, wherein: the display control assembly is composed of a compass check module, an antenna measuring module, an equipment self-checking module and a system sensitivity measuring module, wherein the compass check module is used for finishing the setting and displaying of signal frequency, amplitude and direction, the antenna measuring module is used for measuring inductance and Q value of a transverse coil and a longitudinal coil of the loop antenna in a fixed frequency mode of 500KHz or a frequency sweep mode, and the system sensitivity measuring module is used for realizing receiving sensitivity measurement and directional sensitivity measurement and recording in a table; and the equipment self-checking module is used for self-checking each module.

5. The compass in-situ comprehensive detection system of claim 1, wherein: the power module is used for supplying power to the signal generating assembly, the radiator assembly and the display control assembly.

Technical Field

The invention relates to a compass in-situ comprehensive detection system, belongs to the technical field of detection type instruments and meters, relates to in-situ detection of an airborne radio compass, and is suitable for series type radio compasses which take vertical antenna signals as reference signals and cooperate with loop antenna signals to resolve navigation angles as a navigation principle.

Background

The radio compass is used for measuring the direction of an aircraft relative to a navigation station, can continuously and automatically output a navigation angle to realize flight navigation, and is one of necessary navigation equipment of an airplane. In order to ensure the normal operation and flight safety of the equipment, the airplane maintenance regulation or the airplane maintenance outline stipulates the inspection contents at various times. At present, for daily inspection and periodic maintenance of an airborne radio compass, dislocation performance test inspection and airplane traction to a special site to push an airplane to correct the compass error are needed to complete the work contents, the workload is large, time and labor are consumed, faults such as circuit faults and module cross-linking will increase along with the increase of dislocation disassembly and detection times, the reliability is reduced, and the accuracy of the system is also influenced by personnel operation errors. Particularly, in the traditional error calibration, an airplane is towed to a special field or runway, a towing vehicle and a large amount of manpower are needed for assistance, strict requirements on the field, the environment and time are required, and the measurement method is complicated, long in time consumption and poor in precision.

Disclosure of Invention

Aiming at the defects in the prior art, the invention aims to provide a compass in-situ comprehensive detection system to solve the problems in the background technology, and the compass in-situ comprehensive detection system can solve the following problems: 1. the system performance test has the defect that the machine parts are required to be out of position. The technology and the method have the basic conditions of system performance test, and the airborne equipment parts can complete the equipment system performance test without being out of position. 2. The radio compass check is limited by special place and time. The traditional method for checking the radio compass offset of the airplane needs to drag the airplane to a special place for correcting the offset, and has the disadvantages of large workload, time and labor consumption, and influence by time and weather. 3. The influence of the off-position disassembly and assembly times of the machine parts on the reliability of the system. Often along with the increase of off-position dismantlement and detection number of times, faults such as circuit trouble, module cross-linking will increase, and the reliability descends. 4. Influence of human operation errors on system accuracy. The traditional method needs to push the airplane to rotate for 360 degrees, needs a large amount of personnel and various vehicles to guarantee, is complex in measuring method, and can cause the problem of influence on measuring precision in each link.

In order to achieve the purpose, the invention is realized by the following technical scheme: the utility model provides a compass normal position integrated detection system, includes power module, signal generation subassembly, radiator subassembly and shows the accuse subassembly, power module's output and signal generation subassembly, radiator subassembly and show the input of accuse subassembly and be connected, the output that the signal generated the subassembly is connected with radiator subassembly's input, the output that the signal generated the subassembly still is connected with the input that shows the accuse subassembly.

Furthermore, the signal generation assembly adopts an FPGA + DAC structure (DDS) to complete signal generation and signal amplitude and phase adjustment, frequency points, output voltage and azimuth angle digital display, functions are selectable, parameters are adjustable, three internal signals are independently output, output signal intensity is quantitative and controllable, one signal is taken as a vertical antenna signal (standard signal), the other signal is taken as a longitudinal signal (output amplitude is changed along with azimuth) of the loop antenna, the other signal is taken as a transverse signal (output amplitude is changed along with azimuth) of the loop antenna, the system has a power-on self-detection function, the signal frequency range is 100 KHz-1799.5 KHz, three external independent signals (vertical antenna and external output signal of the loop antenna) are led to a chassis panel socket, can replace an onboard compass antenna, are directly connected with a receiver, and are used for performance test of the compass receiver.

Further, the radiator assembly is used for completing the size ratio matching of the vertical antenna signal and the loop antenna signal and the matching of the corresponding interface, and the electromagnetic compatibility is as follows: shielding, isolating and preventing crosstalk.

Furthermore, the display control assembly is composed of a compass check module, an antenna measurement module, an equipment self-checking module and a system sensitivity measurement module, so that man-machine interaction is realized, and functions of compass check, antenna measurement, system sensitivity measurement and equipment self-checking are completed; the antenna measurement module is used for measuring the inductance and the Q value of the transverse coil and the longitudinal coil of the loop antenna in a constant frequency mode of 500KHz or a frequency sweep mode, displaying the inductance and the Q value on the upper computer software and displaying a measurement result and a conclusion; the system sensitivity measurement module is used for realizing receiving sensitivity measurement and directional sensitivity measurement and recording the measurement in a table; and the equipment self-checking module is used for self-checking each module and can display the fault codes of each component of the whole machine.

Further, the power module is used for supplying power to the signal generating assembly, the radiator assembly and the display control assembly, and when the onboard 28V power supply is used, the voltage reduction module can be adopted to generate corresponding required voltage.

The invention has the beneficial effects that: according to the compass in-situ comprehensive detection system, in-situ detection of the radio compass can be realized without disassembling equipment, quantitative tests of indexes such as receiving sensitivity, directional sensitivity and compass error of the radio compass system are realized, whether the equipment works normally is judged, and in addition, performance detection can be carried out on the loop antenna unit.

Drawings

Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:

FIG. 1 is a schematic structural diagram of an in-situ comprehensive detection system for a compass according to the present invention;

in the figure, 1 is a power supply module, 2 is a signal generating assembly, 3 is a radiator assembly, and 4 is a display control assembly.

Detailed Description

In order to make the technical means, the creation characteristics, the achievement purposes and the effects of the invention easy to understand, the invention is further described with the specific embodiments.

Referring to fig. 1, the present invention provides a technical solution: the utility model provides a compass normal position integrated detection system, includes power module 1, signal generation subassembly 2, radiator subassembly 3 and show accuse subassembly 4, power module 1's output and signal generation subassembly 2, radiator subassembly 3 and show the input of accuse subassembly 4 and be connected, and signal generation subassembly 2's output is connected with radiator subassembly 3's input, and signal generation subassembly 2's output still is connected with the input that shows accuse subassembly 4.

The signal generation assembly 2 adopts an FPGA + DAC structure (DDS) to complete signal generation and signal amplitude and phase adjustment, frequency points, output voltage and azimuth angle digital display, functions are selectable, parameters are adjustable, three internal signals are independently output, the intensity of the output signals is quantitative and controllable, one signal is taken as a vertical antenna signal (standard signal), the other signal is taken as a longitudinal signal (the output amplitude is changed along with the azimuth) of the loop antenna, the other signal is taken as a transverse signal (the output amplitude is changed along with the azimuth) of the loop antenna, the system has a power-on self-detection function, the signal frequency range is 100 KHz-1799.5 KHz, the external three independent signals (the vertical antenna and the external output signal of the loop antenna) are led to a chassis panel socket, an onboard antenna can replace an onboard compass and is directly connected with a receiver to perform performance test.

The radiator component 3 is used for completing the matching of the size proportion of the vertical antenna signal and the annular antenna signal and the matching of the corresponding interface, and the electromagnetic compatibility is as follows: shielding, isolating and preventing crosstalk.

The display control assembly 4 is composed of a compass error checking module, an antenna measuring module, an equipment self-checking module and a system sensitivity measuring module, realizes man-machine interaction, and completes functions of compass error checking, antenna measuring, system sensitivity measuring and equipment self-checking, wherein the compass error checking module is used for completing the setting and displaying of signal frequency, amplitude and direction, displaying compass direction in a dial form, inputting compass values in real time, and generating a drop table and a compass curve; the antenna measurement module is used for measuring the inductance and the Q value of the transverse coil and the longitudinal coil of the loop antenna in a constant frequency mode of 500KHz or a frequency sweep mode, displaying the inductance and the Q value on the upper computer software and displaying a measurement result and a conclusion; the system sensitivity measurement module is used for realizing receiving sensitivity measurement and directional sensitivity measurement and recording the measurement in a table; and the equipment self-checking module is used for self-checking each module and can display the fault codes of each component of the whole machine.

The power module 1 is used for supplying power to the signal generating assembly 2, the radiator assembly 3 and the display control assembly 4, and when the onboard 28V is used, the voltage reduction module can be adopted to generate corresponding required voltage.

As an embodiment of the present invention: according to the compass in-situ comprehensive detection system, in-situ detection of the radio compass can be realized without disassembling equipment, quantitative tests of indexes such as receiving sensitivity, directional sensitivity and compass error of the radio compass system are realized, whether the equipment works normally is judged, and in addition, performance detection can be carried out on the loop antenna unit.

1. The working efficiency is obviously improved. The airplane is in situ and the equipment parts are in situ, when relevant content is checked, other resources are not occupied, other maintenance and guarantee work can be carried out as usual, and two persons can complete the work which can be completed by one guarantee unit within 4 hours. 2. The detection result is more objective and real. Due to in-situ detection, the whole operation state of the system can be more comprehensively reflected, and the system can be adjusted to work in the best state. 3. The method has great significance for improving the guarantee capability and the flight safety. The main contents of test and inspection are moved forward, and test data analysis is realized, so that fault prediction and prevention can be realized, the guarantee capability is obviously improved, the fault hidden danger is found in time, and the flight safety is guaranteed. 4. The economic benefit is remarkable. Various special guarantee resources are saved, and various consumptions are reduced.

Although the present invention has been described with reference to the preferred embodiments, it should be understood that various changes, substitutions and alterations can be made herein without departing from the spirit and scope of the invention as defined by the appended claims.