CN108362909A - A kind of Multi-functional probe of spherical head - Google Patents
A kind of Multi-functional probe of spherical head Download PDFInfo
- Publication number
- CN108362909A CN108362909A CN201810034961.2A CN201810034961A CN108362909A CN 108362909 A CN108362909 A CN 108362909A CN 201810034961 A CN201810034961 A CN 201810034961A CN 108362909 A CN108362909 A CN 108362909A
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- Prior art keywords
- pressure
- angle
- spherical head
- tube body
- attack
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Classifications
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01P—MEASURING LINEAR OR ANGULAR SPEED, ACCELERATION, DECELERATION, OR SHOCK; INDICATING PRESENCE, ABSENCE, OR DIRECTION, OF MOVEMENT
- G01P13/00—Indicating or recording presence, absence, or direction, of movement
- G01P13/02—Indicating direction only, e.g. by weather vane
- G01P13/025—Indicating direction only, e.g. by weather vane indicating air data, i.e. flight variables of an aircraft, e.g. angle of attack, side slip, shear, yaw
-
- 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
-
- 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
- G01L19/0092—Pressure sensor associated with other sensors, e.g. for measuring acceleration or temperature
-
- 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
- G01L19/14—Housings
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01P—MEASURING LINEAR OR ANGULAR SPEED, ACCELERATION, DECELERATION, OR SHOCK; INDICATING PRESENCE, ABSENCE, OR DIRECTION, OF MOVEMENT
- G01P1/00—Details of instruments
- G01P1/02—Housings
-
- 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
- G01L2019/0053—Pressure sensors associated with other sensors, e.g. for measuring acceleration, temperature
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- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Analytical Chemistry (AREA)
- Measuring Fluid Pressure (AREA)
Abstract
The invention belongs to aircraft atmosphere parameter measurement technologies, are related to a kind of Multi-functional probe of spherical head.The present invention includes spherical head, tube body, support arm, pneumatic circuit and bottom plate；The sphere centre of the spherical head is set along tube body axis direction there are one pitot hole, for experiencing stagnation pressure when aircraft flight；On the spherical surface of the spherical head, a yaw angle pressure port is respectively equipped with the position at tube body axis angle at 45 ° by the centre of sphere along the horizontal plane；On the spherical surface of the spherical head, an angle of attack pressure port is respectively equipped with along the position at vertical plane Yu tube body axis angle at 45 ° by the centre of sphere；True yaw angle when the pressure difference of described two yaw angle pressure ports is used for resolving aircraft flight, the pressure differences of described two angle of attack pressure ports are used for resolving true angle of attack when aircraft flight；The tube body is equipped with static pressure hole, for experiencing static pressure when aircraft flight.
Description
Technical field
The invention belongs to aircraft atmosphere parameter measurement technologies, are related to a kind of Multi-functional probe of spherical head.
Background technology
Atmosphere data probe is the important component of aircraft air data system, and traditional air data system needs
Experience aircraft flight by multiple total, the static pressure pick-ups and the angle of attack, sideslip angle transducer that are installed on head front end or side
The signals such as stagnation pressure, static pressure, the angle of attack, the yaw angle of section, then by air data computer data combination at height, speed, true
The atmospheric parameters such as the angle of attack, true yaw angle.To ensure that the safety and reliability of aircraft, aircraft need to install the big of multiple remainings
Gas data probe, this designs the detectivity energy that can reduce aircraft, while improving aircraft weight.Contemporary aircraft for
Weight indicator, detectivity energy, safety, reliability requirements are higher and higher, and traditional air data system has been unable to meet newly
The manufacture claim of generation aircraft.
Re-entry space vehicle can take off from ground to fly in endoatmosphere, and can speed up into Earth's orbit as space flight
Aircraft.Its maximum flying speed in air can reach 25 times of velocities of sound, and this requires the atmosphere data being mounted thereon to visit
Head quantity is few, reliability is high, while needing to have extremely strong high temperature resistant ablation ability.Traditional atmosphere data probe is surveyed for guarantee
Accuracy of measurement, front end are the design of thin-wall construction, and probe distal end can be concentrated due to heat during high-speed flight causes ablation to become
Shape does not adapt to the manufacture claim of re-entry space vehicle.
Therefore, it is necessary to develop disclosure satisfy that re-entry space vehicle requirement, and conventional aircraft atmosphere data can be replaced to pop one's head in
Multi-functional probe of new generation.
Invention content
The technical problem to be solved by the present invention is to：A kind of Multi-functional probe of spherical head is provided, stagnation pressure, quiet is integrated
The multiple atmosphere data for being distributed in head position can be popped one's head in and be integrated, reduce chain-drive section by the impression of pressure, the angle of attack and yaw angle
Position probe quantity, avoids the angle of attack caused by the probe installation error of different location, yaw angle pressure measurement errors, while can
The detectivity and weight of aircraft are effectively reduced, and in aircraft high-speed flight, the probe of spherical head can avoid out
Existing heat concentrates the deformation for causing ablation.
The technical scheme is that：A kind of Multi-functional probe of spherical head, including spherical head 1, tube body 2, support arm
4, pneumatic circuit 5 and bottom plate 6；The sphere centre of the spherical head is set along tube body axis direction there are one pitot hole 9, for feeling
Stagnation pressure when by aircraft flight；On the spherical surface of the spherical head, by the centre of sphere along the horizontal plane with tube body axis angle at 45 °
Position be respectively equipped with a yaw angle pressure port 8；On the spherical surface of the spherical head, by the centre of sphere along vertical plane and tube body
The position at axis angle at 45 ° is respectively equipped with an angle of attack pressure port 7；The pressure difference of described two yaw angle pressure ports is used for resolving
True yaw angle when aircraft flight, really the attacking when pressure difference of described two angle of attack pressure ports is used for resolving aircraft flight
Angle；The tube body is equipped with static pressure hole 3, for experiencing static pressure when aircraft flight；The Multi-functional probe is internally provided with six tunnels
Airtight pneumatic circuit mutually, wherein being connected all the way with pitot hole, two-way is connected with two angle of attack pressure ports respectively, two-way difference
It connects with two yaw angle pressure ports, is connected all the way with static pressure hole, to which air pressure signal is transferred to air data computer
In respective sensor；The bottom plate is installed on aircraft exterior.
The beneficial effects of the invention are as follows：Compared with using the aircraft of traditional atmosphere data probe, the present invention is using spherical
Five hole Multi-functional probe of head is integrated with the feeling ability of stagnation pressure, static pressure, the angle of attack and yaw angle pressure, and is attacked with higher
Angle, yaw angle measurement accuracy, while probe quantity of the aircraft air data system for experiencing different pressures can be reduced, favorably
In the detectivity and air data system weight that reduce aircraft, when for high speed flight at high altitude, spherical configuration, which can guarantee, to be visited
The not ablated deformation of head, improves the pressure experience precision and reliability of probe.
Description of the drawings
The structural schematic diagram of Fig. 1 Multi-functional probes；
The spherical head left view of Fig. 2 probes；
Spherical head pressure experience cloud atlas when Fig. 3 pops one's head in and windstream angle is 0 °；
Spherical head pressure experience cloud atlas when Fig. 4 pops one's head in and windstream angle is 10 °；
Spherical head pressure experience cloud atlas when Fig. 5 pops one's head in and windstream angle is 20 °；
Spherical head pressure experience cloud atlas when Fig. 6 pops one's head in and windstream angle is 30 °；
Wherein, 1：Spherical head, 2：Tube body, 3：Static pressure hole, 4：Support arm, 5：Pneumatic circuit, 6：Bottom plate, 7：Yaw angle pressure
Hole, 8：Angle of attack pressure port, 9：Pitot hole.
Specific implementation mode
The following further describes the specific embodiments of the present invention with reference to the drawings.
Referring to Fig. 1, Fig. 2, the present invention is a kind of Multi-functional probe of spherical head, including spherical head 1, tube body 2, support arm
4, pneumatic circuit 5 and bottom plate 6；The sphere centre of the spherical head is set along tube body axis direction there are one pitot hole 9, for feeling
Stagnation pressure when by aircraft flight；On the spherical surface of the spherical head, by the centre of sphere along the horizontal plane with tube body axis angle at 45 °
Position be respectively equipped with a yaw angle pressure port 8；On the spherical surface of the spherical head, by the centre of sphere along vertical plane and tube body
The position at axis angle at 45 ° is respectively equipped with an angle of attack pressure port 7；The pressure difference of described two yaw angle pressure ports is used for resolving
True yaw angle when aircraft flight, really the attacking when pressure difference of described two angle of attack pressure ports is used for resolving aircraft flight
Angle；The tube body is equipped with static pressure hole 3, for experiencing static pressure when aircraft flight；The Multi-functional probe is internally provided with six tunnels
Airtight pneumatic circuit mutually, wherein being connected all the way with pitot hole, two-way is connected with two angle of attack pressure ports respectively, two-way difference
It connects with two yaw angle pressure ports, is connected all the way with static pressure hole, to which air pressure signal is transferred to air data computer
In respective sensor；The bottom plate is installed on aircraft exterior.
Aerodynamics simu1ation is carried out to the Multi-functional probe of spherical head of the present invention using simulation software (ANSYS), can be obtained
The probe cloud atlas that surface pressing is experienced in flight course, referring to Fig. 3~Fig. 6.Pop one's head in tube body and windstream 0 °, 10 °,
20 °, under 30 ° of different angle states, symmetrical two pressure ports are in different pressure experience areas on spherical surface, and pressure difference has
Higher angle sensitivity, therefore, the pressure experience hole being arranged on spherical surface disclosure satisfy that Aircraft Angle of Attack, sideslip angular measurement are wanted
It asks.
Inside Multi-functional probe of the present invention comprising six road pressure chambers and appearance and size with tradition includes three tunnel following pressures chambers
Probe it is identical, complicated cavity body structure needs the inner space of bigger, and the internal wall thickness that can cause to pop one's head in becomes smaller, under intensity
Drop；When aircraft high-speed flight, high-speed flow can apply pipeline cavity the pressure of bigger, but sonde configuration intensity can be by
Decline in the frictional heat with air, to solve these problems, the high temperature alloy with excellent high intensity need to be applied to pass through
3D printing technique is manufactured.Total, static pressure pick-up the design method using the changeable tradition of the technology, when design is popped one's head in, really
After determining pick-up shape and position of opening, ensure probe internal cavity can normal transmission pressure, intensity and weight satisfaction want
In the case of asking, air pressure inside cavity can carry out free design, be that an inside possesses complicated chamber by probe principle structural design
After the part of body, the part overall processing is formed using 3D printing technique, then reliability can be produced by following process
High, the good Multi-functional probe of consistency.
Claims (1)
1. a kind of Multi-functional probe of spherical head, including spherical head (1), tube body (2), support arm (4), pneumatic circuit (5) and
Bottom plate (6)；It is characterized in that：The sphere centre of the spherical head is set along tube body axis direction there are one pitot hole (9), for feeling
Stagnation pressure when by aircraft flight；On the spherical surface of the spherical head, by the centre of sphere along the horizontal plane with tube body axis angle at 45 °
Position be respectively equipped with a yaw angle pressure port (8)；On the spherical surface of the spherical head, by the centre of sphere along vertical plane and pipe
The position at body axis angle at 45 ° is respectively equipped with an angle of attack pressure port (7)；The pressure difference of described two yaw angle pressure ports is used for
Resolve true yaw angle when aircraft flight, it is true when the pressure differences of described two angle of attack pressure ports is used for resolving aircraft flight
The angle of attack；The tube body is equipped with static pressure hole (3), for experiencing static pressure when aircraft flight；The Multi-functional probe is internally provided with
The mutual airtight pneumatic circuit in six roads, wherein being connected all the way with pitot hole, two-way is connected with two angle of attack pressure ports respectively, two-way
It connects with two yaw angle pressure ports, is connected all the way with static pressure hole respectively, calculated to which air pressure signal is transferred to atmosphere data
In the respective sensor of machine；The bottom plate is installed on aircraft exterior.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810034961.2A CN108362909A (en) | 2018-01-12 | 2018-01-12 | A kind of Multi-functional probe of spherical head |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810034961.2A CN108362909A (en) | 2018-01-12 | 2018-01-12 | A kind of Multi-functional probe of spherical head |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108362909A true CN108362909A (en) | 2018-08-03 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810034961.2A Pending CN108362909A (en) | 2018-01-12 | 2018-01-12 | A kind of Multi-functional probe of spherical head |
Country Status (1)
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| CN (1) | CN108362909A (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109470401A (en) * | 2018-11-08 | 2019-03-15 | 中国航天空气动力技术研究院 | It is a kind of with meet side angle degree resolving straight rod type pitot |
| CN109738009A (en) * | 2018-12-07 | 2019-05-10 | 武汉航空仪表有限责任公司 | A kind of weathercock type Multi-functional probe |
| CN109877314A (en) * | 2018-12-05 | 2019-06-14 | 太原航空仪表有限公司 | A kind of multifunction atmospheric data probe and increasing material manufacturing method |
| CN110987287A (en) * | 2019-11-20 | 2020-04-10 | 中国航空工业集团公司沈阳飞机设计研究所 | Semi-embedded atmospheric data system for flying wing type airplane |
| CN111024298A (en) * | 2019-12-24 | 2020-04-17 | 太原航空仪表有限公司 | Adjustable total pressure probe |
| CN111157759A (en) * | 2019-12-24 | 2020-05-15 | 太原航空仪表有限公司 | Fixed differential pressure type attack angle sensor and use method |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3318146A (en) * | 1966-02-14 | 1967-05-09 | Rosemount Eng Co Ltd | Pressure sensing instrument for aircraft |
| KR101089989B1 (en) * | 2009-12-24 | 2011-12-05 | 한국항공우주연구원 | Air data sensor device |
| CN103698081A (en) * | 2013-12-01 | 2014-04-02 | 太原航空仪表有限公司 | L-shaped differential pressure type probe |
| CN105987765A (en) * | 2015-03-23 | 2016-10-05 | 罗斯蒙特航天公司 | Air data probes |
| CN106092205A (en) * | 2016-07-29 | 2016-11-09 | 成都凯天电子股份有限公司 | Omnidirectional's atmosphere parameter measurement spheric probe |
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| US3318146A (en) * | 1966-02-14 | 1967-05-09 | Rosemount Eng Co Ltd | Pressure sensing instrument for aircraft |
| KR101089989B1 (en) * | 2009-12-24 | 2011-12-05 | 한국항공우주연구원 | Air data sensor device |
| CN103698081A (en) * | 2013-12-01 | 2014-04-02 | 太原航空仪表有限公司 | L-shaped differential pressure type probe |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109470401A (en) * | 2018-11-08 | 2019-03-15 | 中国航天空气动力技术研究院 | It is a kind of with meet side angle degree resolving straight rod type pitot |
| CN109877314A (en) * | 2018-12-05 | 2019-06-14 | 太原航空仪表有限公司 | A kind of multifunction atmospheric data probe and increasing material manufacturing method |
| CN109877314B (en) * | 2018-12-05 | 2021-11-23 | 太原航空仪表有限公司 | Multifunctional atmospheric data probe and additive manufacturing method |
| CN109738009A (en) * | 2018-12-07 | 2019-05-10 | 武汉航空仪表有限责任公司 | A kind of weathercock type Multi-functional probe |
| CN110987287A (en) * | 2019-11-20 | 2020-04-10 | 中国航空工业集团公司沈阳飞机设计研究所 | Semi-embedded atmospheric data system for flying wing type airplane |
| CN111024298A (en) * | 2019-12-24 | 2020-04-17 | 太原航空仪表有限公司 | Adjustable total pressure probe |
| CN111157759A (en) * | 2019-12-24 | 2020-05-15 | 太原航空仪表有限公司 | Fixed differential pressure type attack angle sensor and use method |
| CN111024298B (en) * | 2019-12-24 | 2021-10-08 | 太原航空仪表有限公司 | Adjustable total pressure probe |
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Application publication date: 20180803 |
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| RJ01 | Rejection of invention patent application after publication |