CN219077500U - Helicopter rotor state detection equipment - Google Patents
Helicopter rotor state detection equipment Download PDFInfo
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- CN219077500U CN219077500U CN202221412841.XU CN202221412841U CN219077500U CN 219077500 U CN219077500 U CN 219077500U CN 202221412841 U CN202221412841 U CN 202221412841U CN 219077500 U CN219077500 U CN 219077500U
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
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- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
Abstract
The utility model discloses helicopter rotor wing state detection equipment, and relates to the technical field of helicopter fault detection. The method is used for solving the technical problems of real-time acquisition of the strain parameters of the existing rotor wing, data transmission, equipment installation and the like. Comprising the following steps: a rotor strain measurement unit, which is arranged at the top end of the rotor hub and is used for measuring the stress of helicopter rotor vibration and transmitting the stress to the static component receiver unit; a static component receiver unit disposed within the chamber for converting the received stress into a standard data stream.
Description
Technical Field
The utility model relates to the technical field of helicopter fault detection, in particular to helicopter rotor wing state detection equipment.
Background
The helicopter is more and more widely used in military and civil work occasions due to the characteristics of vertical take-off and landing, hovering, small speed and the like which are not possessed by the fixed wing aircraft. The helicopter has a plurality of rotating parts, including a rotor system, a transmission system, a main speed reducer, a tail rotor system and the like, so that the whole helicopter works in the coordinated operation of a plurality of rotating systems and parts, wherein a rotor serves as a key part of the helicopter, the load test flight of the rotor in the helicopter shaping test flight is a key subject of the helicopter test flight, and the acquisition of rotor load test data about the fatigue life of the helicopter is an indispensable task for helicopter load and strength flight test.
The rotor can produce very big centrifugal overload and mix with abominable operational environment such as high temperature air current at high-speed rotatory in-process, and the test equipment of installing on the rotor if handle mishandling then directly can influence the control system of aircraft and then endanger flight safety. The test equipment applied to the test equipment has the characteristics of firmness, reliability, accurate measurement, small volume and the like, and not only is real and reliable high-precision flight data required to be obtained in real time, but also the flight safety is required to be ensured.
At present, the rotor testing equipment applied to the helicopter in China only realizes the basic function of data acquisition, and cannot realize real-time rotor state detection and fault diagnosis. Therefore, a set of special test equipment for monitoring the vibration stress real-time state of the helicopter rotor is urgently needed to be developed, wherein the rotor strain measurement is taken as a research target, the real-time online monitoring method for the running state strain parameters of the rotating part is researched, the technical problems of real-time acquisition of the rotor strain parameters, data transmission, equipment installation and the like are solved, and the special test equipment is used for monitoring the vibration stress real-time state of the helicopter rotor.
Disclosure of Invention
The embodiment of the utility model provides helicopter rotor state detection equipment, which can realize real-time detection and fault diagnosis of the helicopter rotor state.
The embodiment of the utility model provides helicopter rotor wing state detection equipment, which comprises the following components:
a rotor strain measurement unit, which is arranged at the top end of the rotor hub and is used for measuring the stress of helicopter rotor vibration and transmitting the stress to the static component receiver unit;
a static component receiver unit disposed within the chamber for converting the received stress into a standard data stream.
Preferably, the rotor strain measurement unit comprises a strain sensor, a first processor and a first wireless data transmission unit;
the strain sensor is arranged at the top end of the rotor hub and is used for measuring the torque value of the rotor hub;
the first processor is electrically connected with the strain sensor and is used for receiving the torque value and sending the torque value to the static part receiving unit through a first wireless data transmission unit;
wherein the first wireless data transmission unit is arranged in the fairing.
Preferably, the stationary part receiver unit comprises a second wireless data transmission unit, a second processor;
the second wireless data transmission unit is arranged in the cabin, is electrically connected with the first wireless data transmission unit, and is used for receiving the torque value and sending the received torque value to the second processor;
the second processor is arranged in the cabin, is electrically connected with the second wireless data transmission unit, converts the received torque value into a standard data stream, and sends the standard data stream to the rear end through an RS422 data interface.
Preferably, the fairing is located above the strain sensor;
the first wireless data transmission unit is electrically connected with the strain force processor through a coaxial radio frequency cable;
the first wireless data transmission unit is of a monopole antenna columnar structure.
Preferably, the second wireless data transmission unit is arranged on the tail boom of the machine body, and the installation plane is higher than the rotation plane of the rotor blade.
Preferably, the rotor strain measurement unit is shown as a disc-shaped package structure.
The embodiment of the utility model provides helicopter rotor wing state detection equipment, which comprises the following components: a rotor strain measurement unit, which is arranged at the top end of the rotor hub and is used for measuring the stress of helicopter rotor vibration and transmitting the stress to the static component receiver unit; a static component receiver unit disposed within the chamber for converting the received stress into a standard data stream. The device can determine the vibration stress of the helicopter rotor through the rotor strain measurement unit and transmit the vibration stress to the static part receiver unit through wireless transmission aiming at the requirement of the helicopter rotor vibration stress real-time monitoring, and the static part receiver unit calculates the received stress in real time, converts the received stress into a standard data stream and transmits the standard data stream to the rear end. The technical problems of real-time acquisition of the strain parameters of the existing rotor, data transmission, equipment installation and the like are solved, and special test equipment for monitoring the vibration stress real-time state of the helicopter rotor is provided.
Drawings
In order to more clearly illustrate the embodiments of the utility model or the technical solutions in the prior art, the drawings that are required in the embodiments or the description of the prior art will be briefly described, it being obvious that the drawings in the following description are only some embodiments of the utility model, and that other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
Fig. 1 is a schematic structural diagram of a helicopter rotor state detection apparatus according to an embodiment of the present utility model;
fig. 2 is a schematic structural diagram of a rotor strain measurement unit according to an embodiment of the present utility model;
fig. 3 is a schematic structural diagram of a static component receiver unit according to an embodiment of the present utility model;
fig. 4 is a schematic diagram of an installation structure of a rotor strain measurement unit according to an embodiment of the present utility model;
fig. 5 is a schematic diagram of an installation structure of a second wireless data transmission unit according to an embodiment of the present utility model;
the strain sensor-101, the first wireless data transmission unit-102 and the second wireless data transmission unit-201.
Detailed Description
The following description of the embodiments of the present utility model will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present utility model, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the utility model without making any inventive effort, are intended to be within the scope of the utility model.
Fig. 1 schematically illustrates a structural diagram of a helicopter rotor state detection apparatus according to an embodiment of the present utility model, where, as shown in fig. 1, the helicopter rotor state detection apparatus mainly includes a rotor strain measurement unit and a static component receiver unit. The rotor wing strain measurement unit is arranged at the top end of the rotor wing hub, the static part receiver unit is arranged in the helicopter cabin, and data transmission is realized between the rotor wing strain measurement unit and the static part receiver unit in a radio mode.
In the embodiment of the utility model, the rotor wing strain measurement unit is arranged at the top end of the rotor hub and can perform rotary motion along with the rotor hub, and is used for measuring the stress of helicopter rotor wing vibration and transmitting the measured stress to the static part receiver unit; further, the static part receiver unit is arranged in the cabin and is in data transmission with the rotor wing strain measurement unit in a radio mode, when the static part receiver unit receives the ground stress sent by the rotor wing strain measurement unit, the ground stress is converted into a standard data stream, and further, the standard data stream is sent to a remote measuring/warning system at the rear end through an RS422 data interface for use in state monitoring.
According to the helicopter rotor state detection equipment provided by the embodiment of the utility model, the stress of helicopter rotor vibration can be determined through the rotor strain measurement unit and transmitted to the static part receiver unit through wireless transmission, and the static part receiver unit calculates the received stress in real time, converts the received stress into a standard data stream and transmits the standard data stream to the rear end. The technical problems of real-time acquisition of the strain parameters of the existing rotor, data transmission, equipment installation and the like are solved, and special test equipment for monitoring the vibration stress real-time state of the helicopter rotor is provided.
Fig. 2 is a schematic structural diagram of a rotor strain measurement unit according to an embodiment of the present utility model; fig. 3 is a schematic structural diagram of a static component receiver unit according to an embodiment of the present utility model; fig. 4 is a schematic diagram of an installation structure of a rotor strain measurement unit according to an embodiment of the present utility model; fig. 5 is a schematic diagram of an installation structure of a second wireless data transmission unit according to an embodiment of the present utility model. The following describes in detail the helicopter rotor status detecting apparatus provided by the embodiment of the present utility model with reference to fig. 2 to 5.
As shown in fig. 2, an embodiment of the present utility model provides a ground rotor strain measurement unit, which mainly includes a strain sensor, a first processor, and a first wireless data transmission unit.
Specifically, as shown in fig. 3, a strain sensor 101 is disposed at the top of the rotor hub, and performs rotational movement with the rotor hub, for measuring a torque value of the rotor hub. In practical applications, the number of strain sensors 101 may be plural.
In an embodiment of the present utility model, the strain sensor has the following functions: providing a maximum of 10 analog signal channels and providing excitation signals for an external sensor; providing an analog front end, and amplifying, filtering and gain adjusting an external signal; realizing A/D conversion of the processed analog signals; responding to the heartbeat beat sent out by the R_CCU (first processor) to realize synchronous data acquisition of all analog channels; according to the heartbeat cycle of the bus, the acquired data is added with verification information and then sent to an R_CCU (first processor) unit; state management, detecting the running state of the unit and reporting abnormal state information to the r_ccu (first processor).
Further, as shown in fig. 3, the first wireless data transmission unit 102 is disposed in a fairing, and the fairing is located above a housing where the strain sensor is disposed, and the first wireless data transmission unit is electrically connected to the strain processor through a coaxial radio frequency cable.
Illustratively, the first wireless data transmission unit includes a ground transceiver antenna, which may be of the monopole antenna mast antenna type, which may be fixedly mounted in a central location outside the fairing above the rotor strain measurement unit device, connected to the antenna interface of the rotor strain measurement unit panel by a coaxial radio frequency cable. The monopole columnar antenna is installed in a direction vertically upwards.
In the embodiment of the present utility model, the first wireless data transmission unit has the following functions: receiving a serial code stream sent by a first processor (R_CCU), and judging the accuracy of data; 2) Frame format processing, namely filling data in a data buffer according to the requirement of a frame format, calculating checksum information of a full frame and filling the information into the frame format; 3) The data is code modulated and transmitted.
In an embodiment of the present utility model, the first processor has the following functions: 1) Heart beat control: and controlling the signal acquisition unit of the whole upper rotor wing testing system to be in a synchronous working state. In a continuous data acquisition mode, different acquisition units need to convert and initiate output transmission according to the heartbeat beat; 2) Device state management: the embedded two processors realize state management of a strain sensor (R_DAU), a first processor (R_CCU) and a power module (R_RFU) through a SerLink bus, and the state management comprises working temperature alarming of equipment, whether a channel is normal, whether a unit self-checking state is normal, a wireless link state and the like. 3) And initializing management, configuring channel gain, oversampling configuration, zero adjustment configuration and the like of the strain sensor (R_DAU), and configuring an operating frequency point, an operating mode and the like of the first wireless data transmission unit (R_RFU). 4) Part of state information can be added into a data stream, and an abnormal state is given to a second processor (G_CCU) in the cabin through a wireless link, and all information of equipment DHM is acquired through an external serial port; 5) Data flow control: in a data acquisition mode, all channel information and partial state information of equipment are obtained by controlling a SerLink bus, the information is combined according to a preset format to form a data frame, after timestamp information, P_ID information and P_CNT information of the data frame are added, a check value of a full frame is calculated to form a complete data full frame, the data full frame is converted into a serial code stream, and the serial code stream is transmitted to an R_RFU unit through an LVDS interface to realize data transmission; 6) Implementation of the timestamp function: the system receives the uplink time information from the wireless link, relies on a time synchronization algorithm unit to obtain local time, operates an internal high-stability RTC time (the RTC time correction depends on external time), finally realizes the synchronization with the on-board IRIG-B time, obtains the time stamp of the event type action of the equipment by responding to the heartbeat beat, and adds a time stamp label to the acquired data; 7) Device health status management (DHM): the unit is mainly used for health management of equipment, detecting bus state and time sequence, acquiring state information transmitted by the equipment, processing the state information, acquiring the working environment temperature of R_CCU, and comprehensively obtaining the overall running state of the equipment. The overheat protection threshold of the device is enabled by DHM.
As shown in fig. 3, an embodiment of the present utility model provides a geostationary receiver unit, which mainly includes a second wireless data transmission unit and a second processor.
The second processor is arranged in the cabin, is electrically connected with the second wireless data transmission unit, converts the received torque value into a standard data stream, and sends the standard data stream to the rear end through the RS422 data interface. Specifically, the second processor needs torque value to be converted into RS422 and Ethernet number format required by the system to be sent to the back-end onboard test main system for recording or telemetry. The second processor needs to have the functions of data real-time processing and algorithm secondary development, can process the acquired data in real time, and sends the state information after the calculation to a remote sensing/alarming system at the rear end through an RS422 data interface for state monitoring.
The second wireless data transmission unit is arranged in the cabin, is electrically connected with the first wireless data transmission unit, and is used for receiving the torque value and sending the received torque value to the second processor. In practical applications, the second wireless data transmission unit includes a transceiver antenna 201, which may adopt a single antenna or a 2-antenna mode according to practical measurement requirements. Specifically, as shown in fig. 5, when a single antenna mode is adopted, the stationary transceiver antenna 201 can be directly installed and fixed on the usable part of the tail section oblique beam of the aircraft, and the installation plane needs to be higher than the rotation plane of the rotor blade. When the static antenna adopts a 2-antenna mode, the 2 static receiving and transmitting antennas are symmetrically distributed on two sides of the rotating part receiving and transmitting antenna, and an angle of 180 degrees is formed between every two static receiving and transmitting antennas. The antenna bracket is installed at the corresponding position of the aircraft skin, and the monopole antenna columnar structure is adopted, so that the installation direction faces the direction of the antenna of the rotating part.
It should be noted that, the second processor included in the embodiment of the present utility model processes the received data, and also includes a telemetry/alarm system that cooperates with the interface unit to send the resolved status information to the back end through the RS422 data interface. In practical application, the second processor and the interface unit mainly realize the following functions:
1) Data flow control: receiving data transmitted by a second wireless data transmission unit (G_RFU), extracting effective data according to a set frame format, calculating full-frame check information, comparing whether the data are normal, marking an abnormal flag bit if the data are abnormal, analyzing the normal data according to the set frame format, and extracting the effective data; 2) Generating PCM data according to a PCM frame format, and finally outputting the PCM data and a clock through serial-parallel conversion; 3) Generating Ethernet data conforming to an IENA frame format according to the configuration requirement of an IENA message, and outputting the Ethernet data through an Ethernet output interface, wherein the message is a UDP multicast message; 4) Generating an Ethernet data message conforming to the iNET-X frame format according to the configuration requirement of the iNET-X message, and outputting the Ethernet data message through an Ethernet output interface, wherein the message is a UDP multicast message; 5) Time information analysis: analyzing signals output by an IRIG-B (AC/DC) demodulation circuit, extracting time information contained in the signals, correcting and calibrating local RTC time, transmitting the time information to a first processor (R_CCU) through a wireless link, and realizing the time consistency of a real upper rotor wing test system and the like. Performing time stamping on event type information in the second processor (G_CCU); 6) Device configuration display: the configuration of the test system is realized through an Ethernet interface, and the configuration information comprises gain adjustment of all channels, channel sampling rate selection, channel zero setting, radio frequency working frequency point, PCM frame format selection, modification of PCM synchronous words, equipment network address, equipment IP address configuration, ethernet message IENA parameter configuration, ethernet message iNET-X parameter configuration, network output type selection and equipment high-stability protection alarm threshold setting. The display function comprises hexadecimal code value of the channel, converted physical quantity information, core temperature (junction temperature for reference) information of each functional unit of the equipment, internal environment temperature information of the equipment, data timestamp information, wireless link state and other information; 7) The method has the functions of data real-time processing and algorithm secondary development, and can process the acquired data in real time.
In practical application, in order to avoid the problem of influencing the rotation motion characteristics of the rotor due to the new installation device on the rotor moving part of the helicopter, it is preferable that the helicopter rotor state detection device provided by the embodiment of the utility model has a mechanical structure following the following principles:
1) The volume is as small as possible, the weight is as light as possible, and materials with lighter mass are selected on the basis of ensuring the structural strength for the selection of raw materials;
2) The strain sensor, the first processor, the second processor and the first wireless data transmission unit, the second wireless data transmission unit and the power module are independently packaged, so that the maintenance of a later failure mode is facilitated, the maintenance of equipment is realized by directly replacing the module, and the persistence of a flight task is ensured;
3) The modules are arranged on the base, and the positions of the modules are symmetrically arranged, so that the mass center of the whole mass is as close to the central origin as possible, the mass of the symmetrically placed modules is as close as possible in the processing stage, and the mass distribution of the central disc is as uniform as possible;
4) And a balancing structure is reserved on the outer layer structure of the equipment, so that balancing work of a later-stage dynamic balance test is facilitated. The installation position for installing the balancing weight is reserved around the equipment, so that balancing adjustment in the static and dynamic balance test process is facilitated, and the balancing difficulty is reduced.
Preferably, the packaging structure of the rotor wing strain measurement unit provided by the embodiment of the utility model is disc-shaped, and the integrity of the whole structure of the device can be ensured under the condition that the internal functional module is abnormal through the outer disc-shaped structure packaging. The rotor wing strain measurement unit is composed of modules with different functions, each functional module is of an independent packaging structure, a high-strength PCB circuit board is adopted inside the rotor wing strain measurement unit, the rotor wing strain measurement unit is fully attached to a module shell through a sealing glue filling packaging technology, and the requirements of high strength and heat dissipation inside the rotor wing strain measurement unit are met through special glue filling and sealing.
In summary, an embodiment of the present utility model provides a helicopter rotor state detection apparatus, including: a rotor strain measurement unit, which is arranged at the top end of the rotor hub and is used for measuring the stress of helicopter rotor vibration and transmitting the stress to the static component receiver unit; a static component receiver unit disposed within the chamber for converting the received stress into a standard data stream. The device can determine the vibration stress of the helicopter rotor through the rotor strain measurement unit and transmit the vibration stress to the static part receiver unit through wireless transmission aiming at the requirement of the helicopter rotor vibration stress real-time monitoring, and the static part receiver unit calculates the received stress in real time, converts the received stress into a standard data stream and transmits the standard data stream to the rear end. The technical problems of real-time acquisition of the strain parameters of the existing rotor, data transmission, equipment installation and the like are solved, and special test equipment for monitoring the vibration stress real-time state of the helicopter rotor is provided.
While preferred embodiments of the present utility model have been described, additional variations and modifications in those embodiments may occur to those skilled in the art once they learn of the basic inventive concepts. It is therefore intended that the following claims be interpreted as including the preferred embodiments and all such alterations and modifications as fall within the scope of the utility model.
It will be apparent to those skilled in the art that various modifications and variations can be made to the present utility model without departing from the spirit or scope of the utility model. Thus, it is intended that the present utility model also include such modifications and alterations insofar as they come within the scope of the appended claims or the equivalents thereof.
Claims (6)
1. Helicopter rotor state check out test set, its characterized in that includes:
a rotor strain measurement unit, which is arranged at the top end of the rotor hub and is used for measuring the stress of helicopter rotor vibration and transmitting the stress to the static component receiver unit;
a static component receiver unit disposed within the chamber for converting the received stress into a standard data stream.
2. The helicopter rotor status detecting apparatus of claim 1 wherein the rotor strain measurement unit comprises a strain sensor, a first processor, and a first wireless data transmission unit;
the strain sensor is arranged at the top end of the rotor hub and is used for measuring the torque value of the rotor hub;
the first processor is electrically connected with the strain sensor and is used for receiving the torque value and sending the torque value to the static part receiving unit through a first wireless data transmission unit;
wherein the first wireless data transmission unit is arranged in the fairing.
3. The helicopter rotor status detection apparatus of claim 1 wherein said stationary component receiver unit comprises a second wireless data transmission unit, a second processor;
the second wireless data transmission unit is arranged in the cabin, is electrically connected with the first wireless data transmission unit, and is used for receiving the torque value and sending the received torque value to the second processor;
the second processor is arranged in the cabin, is electrically connected with the second wireless data transmission unit, converts the received torque value into a standard data stream, and sends the standard data stream to the rear end through an RS422 data interface.
4. The helicopter rotor condition detection apparatus of claim 2 wherein said fairing is located above said strain sensor;
the first wireless data transmission unit is electrically connected with the first processor through a coaxial radio frequency cable;
the first wireless data transmission unit is of a monopole antenna columnar structure.
5. A helicopter rotor status detecting apparatus as claimed in claim 3 wherein said second wireless data transmission unit is disposed on the body tail boom with the mounting plane being higher than the plane of rotation of the rotor blade.
6. The helicopter rotor state detection apparatus of claim 1 wherein the rotor strain measurement unit is a disc-shaped package structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202221412841.XU CN219077500U (en) | 2022-06-07 | 2022-06-07 | Helicopter rotor state detection equipment |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202221412841.XU CN219077500U (en) | 2022-06-07 | 2022-06-07 | Helicopter rotor state detection equipment |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN219077500U true CN219077500U (en) | 2023-05-26 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202221412841.XU Active CN219077500U (en) | 2022-06-07 | 2022-06-07 | Helicopter rotor state detection equipment |
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| CN (1) | CN219077500U (en) |
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2022
- 2022-06-07 CN CN202221412841.XU patent/CN219077500U/en active Active
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