CN111114762A - Helicopter blade girder inner cavity pressure sensing device and system thereof - Google Patents
Helicopter blade girder inner cavity pressure sensing device and system thereof Download PDFInfo
- Publication number
- CN111114762A CN111114762A CN201911321930.6A CN201911321930A CN111114762A CN 111114762 A CN111114762 A CN 111114762A CN 201911321930 A CN201911321930 A CN 201911321930A CN 111114762 A CN111114762 A CN 111114762A
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- CN
- China
- Prior art keywords
- pressure sensing
- girder
- pressure
- inner cavity
- shell
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/006—Safety devices
- B64C27/007—Safety devices adapted for detection of blade cracks
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q1/00—Details of, or arrangements associated with, antennas
- H01Q1/12—Supports; Mounting means
- H01Q1/22—Supports; Mounting means by structural association with other equipment or articles
- H01Q1/225—Supports; Mounting means by structural association with other equipment or articles used in level-measurement devices, e.g. for level gauge measurement
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q1/00—Details of, or arrangements associated with, antennas
- H01Q1/27—Adaptation for use in or on movable bodies
- H01Q1/28—Adaptation for use in or on aircraft, missiles, satellites, or balloons
- H01Q1/285—Aircraft wire antennas
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Remote Sensing (AREA)
- Physics & Mathematics (AREA)
- Astronomy & Astrophysics (AREA)
- General Physics & Mathematics (AREA)
- Mechanical Engineering (AREA)
- Arrangements For Transmission Of Measured Signals (AREA)
Abstract
The invention relates to a pressure sensing device for an inner cavity of a girder of a helicopter blade, which comprises an antenna part, a power supply part and a pressure sensing part; the antenna part, the power supply part and the pressure sensing part are fixed into an integral structure; the pressure sensing part is used for sensing the real-time pressure of the inner cavity of the helicopter blade girder, the power supply part is used for supplying power to the pressure sensing part, and the antenna part is used for sending out a signal sent by the pressure sensing part; the invention carries out the partition airtight treatment on the pressure detector, and parts with strict airtight requirements are independently welded into a cavity body in a seamless mode, so that the integral function loss caused by the aging problem of the sealing ring is avoided.
Description
Technical Field
The invention relates to the technical field of detection, in particular to a pressure sensing device and a pressure sensing system for an inner cavity of a girder of a blade of a helicopter.
Background
In order to find out hidden danger of blade fracture in time, the helicopter fills gas with 1.6-1.8 times of atmospheric pressure into a cavity of a blade girder, and the gas leakage condition in the cavity is detected by a pressure detector to judge whether the blade has a penetrability crack or not so as to return to the ground in time. The self-sealing properties of the pressure detector are therefore particularly important as a leak detection device. Generally speaking, the whole pressure detector adopts the sealing washer itself to be extruded by the structure and warp to fill the gap between each structure, but because aircraft operational environment is complicated, receives environment influences such as vibration, damp and hot, salt fog, the rubber packing ring can be ageing-accelerated, loses the elasticity of soft medium, consequently must frequently change in order to guarantee good gas tightness.
Disclosure of Invention
The technical problems to be solved by the invention are as follows: the technical problem of real-time detection of the generation of the penetrability crack of the girder of the blade of the helicopter is solved.
The technical scheme is as follows:
the invention provides a pressure sensing device for an inner cavity of a girder of a helicopter blade, which comprises an antenna part, a power supply part and a pressure sensing part, wherein the antenna part is connected with the power supply part; the antenna part, the power supply part and the pressure sensing part are fixed into an integral structure; the pressure sensing part is used for sensing the real-time pressure of the inner cavity of the helicopter blade girder, the power supply part is used for supplying power to the pressure sensing part, and the antenna part is used for sending out a signal sent by the pressure sensing part;
the pressure sensing part comprises a closed shell, a first conductive terminal, a second conductive terminal, a pressure sensing sensor and a signal processing and sending module; an insulating layer and a shielding layer are arranged outside all the conductive terminals; the conductive terminal penetrates through the shell and is solidified with the shell into a whole;
the closed shell is provided with an air inlet interface, the air inlet interface is used for being fixedly and hermetically mounted with a girder of a blade of the helicopter, and the air inlet interface is communicated with an inner cavity of the girder; the pressure sensor and the signal processing and sending module are both arranged in the closed shell, the pressure sensor senses the air inlet pressure of the air inlet interface in real time, and the pressure sensor sends a detection signal to the signal processing and sending module; the pressure sensing sensor and the signal processing and sending module are electrically connected with the power supply part through the first conductive terminal, and the signal processing and sending module is further in signal connection with the antenna part through the second conductive terminal.
Furthermore, the closed shell comprises a first shell and a second shell, the first shell and the second shell enclose a closed cavity, the first shell and the second shell are welded in a seamless mode, and the air inlet interface is arranged on the second shell.
Further, antenna portion includes antenna house and antenna, the antenna setting is inside the antenna house, the antenna house with power supply portion or the sealed fixed connection of pressure sensing portion.
Furthermore, the antenna part, the power supply part and the pressure sensing part are connected in a modularized mode.
Furthermore, the conductive terminal is a wiring terminal or a wiring pin. Preferably copper or a copper alloy.
Furthermore, the second conductive terminal is in signal connection with the antenna in an impedance matching mode.
The invention further provides a pressure sensing device system for the inner cavity of the girder of the helicopter blade, which comprises the pressure sensing device and the girder of the helicopter blade;
the pressure sensing device is fixedly and hermetically connected to the helicopter blade girder through an air inlet interface and is communicated with an inner cavity of the helicopter blade girder; the inflation pressure in the inner cavity is higher than the standard atmospheric pressure;
when the blade girder generates a penetrating crack, gas in the inner cavity can leak through the penetrating crack, and the pressure of the inner cavity is reduced; the pressure sensing device acquires the pressure of the inner cavity in real time and sends the pressure to airborne equipment through the antenna part, so that real-time monitoring is realized.
The invention has the beneficial effects that: the invention carries out the partition airtight treatment on the pressure detector, and parts with strict airtight requirements are independently welded into a cavity body in a seamless mode, so that the integral function loss caused by the aging problem of the sealing ring is avoided.
Drawings
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is a sectional view of the pressure sensing part;
FIG. 3 is a schematic diagram of the connection of the present invention;
FIG. 4 is a schematic diagram of the operation of the invention;
FIG. 5 is a schematic diagram of the operation of the invention;
wherein: 1-an antenna section; 2-a power supply section; 3-pressure sensing part; 4-a closed shell; 5-a first conductive terminal; 6-a second conductive terminal; 7-a pressure-sensitive sensor; 8-a signal processing and transmitting module; 9-an air inlet interface; 10-helicopter blade longeron, 11-through fissures (cracks or holes).
Detailed Description
The following embodiments are given in conjunction with the accompanying drawings
the pressure sensing part 3 comprises a closed shell 4, a first conductive terminal 5, a second conductive terminal 6, a pressure sensing sensor 7 and a signal processing and sending module 8; an insulating layer and a shielding layer are arranged outside all the conductive terminals; the conductive terminal penetrates through the shell and is solidified with the shell into a whole;
the closed shell 4 is provided with an air inlet interface, the air inlet interface is used for being fixedly and hermetically mounted with a girder of a blade of the helicopter, and the air inlet interface is communicated with an inner cavity of the girder; the pressure sensor 7 and the signal processing and sending module 8 are both arranged in the closed shell, the pressure sensor 7 senses the air inlet pressure of the air inlet interface in real time, and the pressure sensor 6 sends a detection signal to the signal processing and sending module 8; the pressure sensing sensor 7 and the signal processing and sending module 8 are electrically connected with the power supply part 2 through the first conductive terminal 6, and the signal processing and sending module 8 is further in signal connection with the antenna part 1 through the second conductive terminal 7.
Claims (8)
1. The utility model provides a helicopter paddle girder inner chamber pressure sensing device which characterized in that: comprises an antenna part, a power supply part and a voltage induction part; the antenna part, the power supply part and the pressure sensing part are fixed into an integral structure; the pressure sensing part is used for sensing the real-time pressure of the inner cavity of the helicopter blade girder, the power supply part is used for supplying power to the pressure sensing part, and the antenna part is used for sending out a signal sent by the pressure sensing part;
the pressure sensing part comprises a closed shell, a first conductive terminal, a second conductive terminal, a pressure sensing sensor and a signal processing and sending module; an insulating layer and a shielding layer are arranged outside all the conductive terminals; the conductive terminal penetrates through the shell and is solidified with the shell into a whole;
the pressure sensing shell is provided with an air inlet interface, the air inlet interface is used for being fixedly and hermetically mounted with a girder of a blade of the helicopter, and the air inlet interface is communicated with an inner cavity of the girder; the pressure sensor and the signal processing and sending module are both arranged in the closed shell, the pressure sensor senses the air inlet pressure of the air inlet interface in real time, and the pressure sensor sends a detection signal to the signal processing and sending module; the pressure sensing sensor and the signal processing and sending module are electrically connected with the power supply part through the first conductive terminal, and the signal processing and sending module is further in signal connection with the antenna part through the second conductive terminal.
2. The pressure sensing device for the inner cavity of the girder of the helicopter blade according to claim 1, wherein: the closed shell comprises a first shell and a second shell, the first shell and the second shell enclose a closed cavity, the first shell and the second shell are welded in a seamless mode, and the air inlet interface is arranged on the second shell.
3. The pressure sensing device for the inner cavity of the girder of the helicopter blade according to claim 1, wherein: antenna portion includes antenna house and antenna, the antenna setting is inside the antenna house, the antenna house with power supply portion or the sealed fixed connection of pressure sensing portion.
4. The pressure sensing device for the inner cavity of the girder of the helicopter blade according to claim 1, wherein: the antenna part, the power supply part and the pressure sensing part are connected in a modularized mode.
5. The pressure sensing device for the inner cavity of the girder of the helicopter blade according to claim 1, wherein: the conductive terminals are binding posts or binding pins.
6. The pressure sensing device for the inner cavity of the girder of the helicopter blade according to claim 5, wherein: the conductive terminal is copper or copper alloy.
7. The pressure sensing device for the inner cavity of the girder of the helicopter blade according to claim 1, wherein: the second conductive terminal is in signal connection with the antenna in an impedance matching mode.
8. The utility model provides a helicopter paddle girder inner chamber pressure sensing device system which characterized in that: the system comprising the pressure sensing device of any one of claims 1-7 and a helicopter blade spar;
the pressure sensing device is fixedly and hermetically connected to the helicopter blade girder through an air inlet interface and is communicated with an inner cavity of the helicopter blade girder; the inflation pressure in the inner cavity is higher than the standard atmospheric pressure;
when the blade girder generates a penetrating crack, gas in the inner cavity can leak through the penetrating crack, and the pressure of the inner cavity is reduced; the pressure sensing device acquires the pressure of the inner cavity in real time and sends the pressure to airborne equipment through the antenna part, so that real-time monitoring is realized.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911321930.6A CN111114762A (en) | 2019-12-19 | 2019-12-19 | Helicopter blade girder inner cavity pressure sensing device and system thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911321930.6A CN111114762A (en) | 2019-12-19 | 2019-12-19 | Helicopter blade girder inner cavity pressure sensing device and system thereof |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111114762A true CN111114762A (en) | 2020-05-08 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911321930.6A Pending CN111114762A (en) | 2019-12-19 | 2019-12-19 | Helicopter blade girder inner cavity pressure sensing device and system thereof |
Country Status (1)
| Country | Link |
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| CN (1) | CN111114762A (en) |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4010708A (en) * | 1975-12-02 | 1977-03-08 | Trodyne Corporation | Differential pressure indicator including remote sensing means |
| US4727251A (en) * | 1986-02-24 | 1988-02-23 | General Nucleonics, Inc. | Detector for helicopter blade crack indicator |
| JPH0624390A (en) * | 1992-07-09 | 1994-02-01 | Mitsubishi Heavy Ind Ltd | Helicopter blade vibration reduction device |
| JPH08201203A (en) * | 1995-01-31 | 1996-08-09 | Kyowa Electron Instr Co Ltd | Pressure transmitter and assembly method of the same |
| JP2000028459A (en) * | 1998-07-14 | 2000-01-28 | Fuji Koki Corp | Pressure sensor |
| US20030101798A1 (en) * | 2001-12-05 | 2003-06-05 | The Entwistle Company | Helicopter hollow blade pressure check and fill apparatus and method to use same |
| US7176812B1 (en) * | 2005-08-04 | 2007-02-13 | The United States Of America As Represented By The Secretary Of The Navy | Wireless blade monitoring system and process |
-
2019
- 2019-12-19 CN CN201911321930.6A patent/CN111114762A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4010708A (en) * | 1975-12-02 | 1977-03-08 | Trodyne Corporation | Differential pressure indicator including remote sensing means |
| US4727251A (en) * | 1986-02-24 | 1988-02-23 | General Nucleonics, Inc. | Detector for helicopter blade crack indicator |
| JPH0624390A (en) * | 1992-07-09 | 1994-02-01 | Mitsubishi Heavy Ind Ltd | Helicopter blade vibration reduction device |
| JPH08201203A (en) * | 1995-01-31 | 1996-08-09 | Kyowa Electron Instr Co Ltd | Pressure transmitter and assembly method of the same |
| JP2000028459A (en) * | 1998-07-14 | 2000-01-28 | Fuji Koki Corp | Pressure sensor |
| US20030101798A1 (en) * | 2001-12-05 | 2003-06-05 | The Entwistle Company | Helicopter hollow blade pressure check and fill apparatus and method to use same |
| US7176812B1 (en) * | 2005-08-04 | 2007-02-13 | The United States Of America As Represented By The Secretary Of The Navy | Wireless blade monitoring system and process |
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