CN111024302A - Front end structure of multidirectional atmospheric pressure probe - Google Patents
Front end structure of multidirectional atmospheric pressure probe Download PDFInfo
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- CN111024302A CN111024302A CN201911301848.7A CN201911301848A CN111024302A CN 111024302 A CN111024302 A CN 111024302A CN 201911301848 A CN201911301848 A CN 201911301848A CN 111024302 A CN111024302 A CN 111024302A
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- column body
- supporting seat
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- air
- upper column
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
- G01L19/00—Details of, or accessories for, apparatus for measuring steady or quasi-steady pressure of a fluent medium insofar as such details or accessories are not special to particular types of pressure gauges
- G01L19/0007—Fluidic connecting means
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Abstract
The invention relates to a front end structure of a multidirectional atmospheric pressure probe, which comprises a supporting seat, an upper column body and a lower column body; the upper cylinder and the lower cylinder are triangular prisms; the upper column body, the lower column body and the supporting seat are sequentially fixed into an integral structure, and the axial projections of the upper column body and the lower column body are staggered by 60 degrees; six axially parallel channel cavities are integrally formed in the upper cylinder and the lower cylinder and are uniformly distributed in the circumferential direction; the three cylindrical surfaces of the upper cylinder and the three cylindrical surfaces of the lower cylinder are provided with air inlets, and the air inlet of each cylindrical surface is correspondingly communicated with one channel cavity; the supporting seat is provided with six air guide joints, and each air guide joint is correspondingly communicated with one channel cavity. The structure of the invention can measure pressure to the opening in multiple directions, a plurality of pressure sensing curved surfaces with certain pneumatic characteristics are distributed along the center of the column in a circumferential array manner, and a pressure sensing hole is arranged in the center of each pneumatic curved surface, so that the pressure sensing curved surfaces can sense and output the air pressure in multiple directions around the probe.
Description
Technical Field
The invention relates to the technical field of airborne atmospheric data detection, in particular to a front end structure of a multidirectional atmospheric pressure probe.
Background
At present, all omnidirectional atmospheric data probes matched with domestic helicopters use movable total static pressure probes, the probes are kept parallel to synthetic airflow by means of empennages and universal joints and sense total pressure and static pressure in the flight process, an angle sensor is utilized to measure the deflection angle of the probes, and the atmospheric parameters of the helicopters, such as triaxial six-directional speed, rotor wing lower washing airflow speed, attack angle, sideslip angle and the like, can be solved through the total pressure, the static pressure and the deflection angle of the probes of the synthetic airflow.
The probe is formed by combining a conventional total static pressure sensor and a steering mechanism, and in order to reduce the influence of the appearance of the airplane on the measurement of the total static pressure, the probe needs to be arranged at a position far away from an airplane body through a strut and an external pipeline, the integral mass is not less than 1.5kg, and the weight is overlarge; the total static pressure sensor has large volume and mass, and the required deicing power is large; the probe has a complex structure and contains movable parts, so that clamping stagnation faults are easy to occur, the reliability is low, and the maintainability is poor; the steering joint is limited by the structure, the range of the deflection angle of the total static pressure probe is small, the measurement ranges of the attack angle and the sideslip angle are +/-90 degrees, and the omnidirectional measurement cannot be realized; the probe can only simultaneously sense the total pressure and the static pressure in one direction, the pressure sensing direction is single, and the velocity vector resolving error is large.
Disclosure of Invention
The technical problems to be solved by the invention are as follows: the defect that atmospheric environment data cannot be collected in multiple directions at the same time is overcome, and introduction of atmospheric gas in multiple directions can be achieved.
The technical scheme is as follows: the front end structure of the multidirectional atmospheric pressure probe comprises a supporting seat, an upper column body and a lower column body; the upper cylinder and the lower cylinder are triangular prisms; the upper column body, the lower column body and the supporting seat are sequentially fixed into an integral structure, and the axial projections of the upper column body and the lower column body are staggered by 60 degrees;
six axially parallel channel cavities are integrally formed in the upper cylinder and the lower cylinder and are uniformly distributed in the circumferential direction; the three cylindrical surfaces of the upper cylinder and the three cylindrical surfaces of the lower cylinder are provided with air inlets, and the air inlet of each cylindrical surface is correspondingly communicated with one channel cavity; the supporting seat is provided with six air guide joints, and each air guide joint is correspondingly communicated with one channel cavity.
In addition, a front end structure of the multi-directional atmospheric pressure probe is provided, which comprises a supporting seat, an upper column body and a lower column body; the upper column body and the lower column body are both quadrangular; the upper column body, the lower column body and the supporting seat are sequentially fixed into an integral structure, and the axial projections of the upper column body and the lower column body are staggered by 45 degrees;
eight axially parallel channel cavities are integrally formed in the upper cylinder body and the lower cylinder body, and the eight channel cavities are uniformly distributed in the circumferential direction; the four cylindrical surfaces of the upper cylinder and the four cylindrical surfaces of the lower cylinder are provided with air inlets, and the air inlet of each cylindrical surface is correspondingly communicated with one channel cavity; the supporting seat is provided with eight air guide joints, and each air guide joint is correspondingly communicated with one channel cavity.
For the front end structure of the multi-directional atmospheric pressure probe, the following further improvements or structural limitations exist:
furthermore, a central cavity is formed in the centers of the upper column body and the lower column body, and a heating device is arranged in the central cavity and used for heating the front end structure of the multi-directional atmospheric pressure probe. The condensed liquid can be prevented from freezing by heating, or the liquid can be discharged by vaporization.
Further, a partition plate extends axially at the bottom of each channel cavity, and the height of the partition plate of each channel cavity is higher than that of the air inlet of each channel cavity. Because the partition plate is higher than the air inlet, impurities or liquid mist in the air inlet are blocked, attached or deposited by the partition plate and cannot be brought to the air guide joint by the air.
Further, the air inlet is an air hole or an air gap.
Furthermore, the heating device is an electric heating device, and a power line and an electric connector are arranged in the supporting seat, the upper column body or the lower column body and used for supplying power to the electric heating device.
Furthermore, the material of supporting seat, upper cylinder or lower cylinder is heat conduction metal. Preferably nickel, copper or an aluminium alloy.
The using method comprises the following steps:
the front end structure of the multi-directional atmospheric pressure probe is mounted on the surface of a streamline shell, the multi-directional atmospheric pressure probe is mounted at the tail ends of wings on two sides of a helicopter along with the streamline shell when in use, sensed air pressure in 6 (or 8) directions around the probe can be transmitted to an on-board atmospheric data calculating device through an air pressure pipeline in the shell, and the calculating device can directly and accurately calculate atmospheric parameters such as triaxial six-directional speed, downwash airflow speed, +/-180-degree attack angle, sideslip angle and the like of the helicopter by utilizing the pressure. The electric heating device in the front end structure is connected with a cable in the shell, and the power supply on the machine is utilized to realize the anti-icing and deicing functions of the front end structure.
The invention has the beneficial effects that: the structure of the invention can measure pressure to the opening in multiple directions, a plurality of pressure sensing curved surfaces with certain pneumatic characteristics are distributed along the center of the column in a circumferential array manner, and a pressure sensing hole is arranged in the center of each pneumatic curved surface, so that the pressure sensing curved surfaces can sense and output the air pressure in multiple directions around the probe. The probe has small volume and light weight, is made of heat conduction materials (such as nickel), and can realize higher anti-icing and deicing effects with smaller heating power. The probe has a regular polyhedral structure and has the advantage of low RCS (radar cross section) appearance. The probe has no movable part, high reliability and good maintainability. The probe is vertically arranged on the surface of the streamline shell, is arranged at the tail ends of wings at two sides of the helicopter along with the shell when in use, can directly calculate the three-axis six-direction speed, the lower washing air speed, the +/-180-degree attack angle, the sideslip angle and other atmospheric parameters of the helicopter by utilizing the pressure sensed by the probes at different positions at the two sides, and the pneumatic characteristic of the probe only depends on the self and the shape of the shell, can adapt to various machine body shapes, is suitable for various helicopters, and has obvious technical progress compared with the prior art.
Drawings
FIG. 1 is a partial sectional view of the present invention (embodiment 1); (exposed channel cavity)
FIG. 2 is a partial sectional view of embodiment 2; (exposed channel cavity)
FIG. 3 is a schematic view of the gas flow direction in the channel chamber (without the partition);
FIG. 4 is a cross-sectional view of a baffle plate and a channel chamber;
FIG. 5 is a schematic view of the gas flow direction in the channel chamber (with the baffle);
wherein: 1-upper column; 2-lower column; 3-a support seat; 4-an air guide joint; 5-an air inlet; 6-channel cavity; 7-an electric heating device; 8-a separator.
Detailed Description
The following embodiments are given in conjunction with the accompanying drawings
six axially parallel channel cavities are integrally formed in the upper cylinder and the lower cylinder and are uniformly distributed in the circumferential direction; the three cylindrical surfaces of the upper cylinder and the three cylindrical surfaces of the lower cylinder are provided with air inlets, and the air inlet of each cylindrical surface is correspondingly communicated with one channel cavity; the supporting seat is provided with six air guide joints, and each air guide joint is correspondingly communicated with one channel cavity.
eight axially parallel channel cavities are integrally formed in the upper cylinder body and the lower cylinder body, and the eight channel cavities are uniformly distributed in the circumferential direction; the four cylindrical surfaces of the upper cylinder and the four cylindrical surfaces of the lower cylinder are provided with air inlets, and the air inlet of each cylindrical surface is correspondingly communicated with one channel cavity; the supporting seat is provided with eight air guide joints, and each air guide joint is correspondingly communicated with one channel cavity.
six axially parallel channel cavities are integrally formed in the upper cylinder and the lower cylinder and are uniformly distributed in the circumferential direction; the three cylindrical surfaces of the upper cylinder and the three cylindrical surfaces of the lower cylinder are provided with air inlets, and the air inlet of each cylindrical surface is correspondingly communicated with one channel cavity; the supporting seat is provided with six air guide joints, and each air guide joint is correspondingly communicated with one channel cavity.
And the centers of the upper column body and the lower column body are provided with central cavities, and the heating device is arranged in the central cavities and used for heating 7 the front end structure of the multi-directional atmospheric pressure probe. The condensed liquid can be prevented from freezing by heating, or the liquid can be discharged by vaporization.
A partition 8 extends axially at the bottom of each channel chamber, the height of the respective channel chamber partition being higher than the inlet opening of the respective channel chamber. Because the partition plate is higher than the air inlet, impurities or liquid mist in the air inlet are blocked, attached or deposited by the partition plate and cannot be brought to the air guide joint by the air.
Claims (8)
1. The utility model provides a multidirectional atmospheric pressure probe's front end structure which characterized in that: comprises a supporting seat, an upper column body and a lower column body; the upper cylinder and the lower cylinder are triangular prisms; the upper column body, the lower column body and the supporting seat are sequentially fixed into an integral structure, and the axial projections of the upper column body and the lower column body are staggered by 60 degrees;
six axially parallel channel cavities are integrally formed in the upper cylinder and the lower cylinder and are uniformly distributed in the circumferential direction; the three cylindrical surfaces of the upper cylinder and the three cylindrical surfaces of the lower cylinder are provided with air inlets, and the air inlet of each cylindrical surface is correspondingly communicated with one channel cavity; the supporting seat is provided with six air guide joints, and each air guide joint is correspondingly communicated with one channel cavity.
2. The utility model provides a multidirectional atmospheric pressure probe's front end structure which characterized in that: comprises a supporting seat, an upper column body and a lower column body; the upper column body and the lower column body are both quadrangular; the upper column body, the lower column body and the supporting seat are sequentially fixed into an integral structure, and the axial projections of the upper column body and the lower column body are staggered by 45 degrees;
eight axially parallel channel cavities are integrally formed in the upper cylinder body and the lower cylinder body, and the eight channel cavities are uniformly distributed in the circumferential direction; the four cylindrical surfaces of the upper cylinder and the four cylindrical surfaces of the lower cylinder are provided with air inlets, and the air inlet of each cylindrical surface is correspondingly communicated with one channel cavity; the supporting seat is provided with eight air guide joints, and each air guide joint is correspondingly communicated with one channel cavity.
3. An axial displacement adjustment device for an instrument shaft component according to claim 1 or 2, wherein: the center of the upper column body and the center of the lower column body are provided with central cavities, and the heating device is arranged in the central cavities and used for heating the front end structure of the multi-directional atmospheric pressure probe.
4. An axial displacement adjustment device for an instrument shaft component according to claim 1 or 2, wherein: and a partition plate extends axially at the bottom of each channel cavity, and the height of the partition plate of each channel cavity is higher than that of the air inlet of each channel cavity.
5. An axial displacement adjustment device for an instrument shaft component according to claim 1 or 2, wherein: the air inlet is an air hole or an air gap.
6. An axial displacement adjustment device for an instrument shaft component according to claim 1 or 2, wherein: the heating device is an electric heating device, and a power line and an electric connector are arranged in the supporting seat, the upper column body or the lower column body and used for supplying power to the electric heating device.
7. An axial displacement adjustment device for an instrument shaft component according to claim 1 or 2, wherein: the supporting seat, the upper column body or the lower column body is made of heat conducting metal. Preferably nickel, copper or an aluminium alloy.
8. An axial displacement adjustment device for an instrument shaft component, as set forth in claim 6, wherein: the air guide joints are uniformly arranged in an annular mode by taking the electric heating device as an axis.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911301848.7A CN111024302A (en) | 2019-12-17 | 2019-12-17 | Front end structure of multidirectional atmospheric pressure probe |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911301848.7A CN111024302A (en) | 2019-12-17 | 2019-12-17 | Front end structure of multidirectional atmospheric pressure probe |
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| Publication Number | Publication Date |
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| CN111024302A true CN111024302A (en) | 2020-04-17 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201911301848.7A Pending CN111024302A (en) | 2019-12-17 | 2019-12-17 | Front end structure of multidirectional atmospheric pressure probe |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112649622A (en) * | 2020-12-04 | 2021-04-13 | 中国航空工业集团公司沈阳飞机设计研究所 | Pressure sensing probe and fixed-wing aircraft atmospheric data system |
-
2019
- 2019-12-17 CN CN201911301848.7A patent/CN111024302A/en active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112649622A (en) * | 2020-12-04 | 2021-04-13 | 中国航空工业集团公司沈阳飞机设计研究所 | Pressure sensing probe and fixed-wing aircraft atmospheric data system |
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