CN205246692U - A static pressure probe for little speed measurement of gyroplane - Google Patents
A static pressure probe for little speed measurement of gyroplane Download PDFInfo
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- CN205246692U CN205246692U CN201521090574.9U CN201521090574U CN205246692U CN 205246692 U CN205246692 U CN 205246692U CN 201521090574 U CN201521090574 U CN 201521090574U CN 205246692 U CN205246692 U CN 205246692U
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- static pressure
- gyroplane
- pitot
- speed
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Abstract
The utility model belongs to the technical field of the static pressure probe, concretely relates to a static pressure probe for little speed measurement of gyroplane has solved general gyroplane and has gone up traditional airspeed tube and can't make effectual impression to the undercut air current, and simultaneously because the influence of undercut air current, the pressure that the baroport was experienced when gyroplane hovered with low -speed flight is not accurate static pressure, problem that the static pressure signal can not normal use. It includes the airspeed tube, and the airspeed tube body adopts spindle streamline profile, and it has two baroports to open on the airspeed tube body, and the orientation is just installed upwards on lieing in spindle streamline profile to two baroports. The utility model discloses compare with general static pressure probe, its data utilization is rateed has had very big promotion. It is interval to be 0-V1 in gyroplane speed, the utility model discloses can effectively experience undercut stream pressure signal, separate from this and calculate the undercut air speed. After speed is greater than V2, the utility model discloses fuselage static pressure signal be can effectively experience, height and speed isoparametric are resolved.
Description
Technical field
The utility model belongs to the technical field of probe head of static pressure, is specifically related to a kind of probe head of static pressure for the little tachometric survey of gyroplane, directly applies to gyroplane hovering and the low-speed operations measurement of gas washing Flow Velocity at present.
Background technology
Total static pressure pitot is the important component part of gyroplane air data system. Total static pressure pitot is generally arranged on gyroplane down side top, can impression machine on stagnation pressure and static pressure pressure signal is transferred to atmospheric engine, be counted as the atmospheric parameters such as pressure altitude, indicator air speed, true air speed, Mach number, rising or falling speed through atmospheric engine solution.
Gyroplane is in the time of flight, and air-flow can be pressed towards oblique below, and rotor below produces downward air-flow, is called downwash flow. Gyroplane is in the time of flight, pitot is positioned at rotor below, owing to there being the impact of rotor downwash air-flow, before the existing aircraft of air velocity at pitot baroport place, fly the horizontal velocity component of generation, the vertical velocity component and the horizontal velocity component that also have downwash flow to produce. When aircraft high-speed flight, downwash flow can be ignored the measurement impact of static pressure, and baroport can be experienced the static pressure of fuselage exactly. In the time of gyroplane hovering or low-speed operations; the velocity component that baroport place downwash flow produces accounts for principal element to the impact of static pressure impression; the static pressure that now pitot is experienced is greater than stagnation pressure; the air speed going out by this data solver is negative value; flying speed is less; negative value is larger, and the pressure signal that therefore static-pressure system is experienced is unavailable.
In the time of gyroplane hovering or low-speed operations condition, downwash flow has a great impact the measurement of atmospheric parameter. Due to the concrete identical magnitude of rocket projectile initial velocity and gyroplane downwash flow, downwash flow produces very strong aerodynamic interference to rocket projectile, stronger impact the initial trajectory of rocket projectile. Therefore,, in hang or low-speed condition, need to measure downwash flow speed.
Traditional pitot baroport is generally circumferential perforate design, and baroport is generally positioned at etc. on straight straightway, is the degree of accuracy that ensures static pressure measurement, and pitot body length is generally long. Typical traditional pitot profile and static pressure perforate figure are as shown in Figure 2,3.
Summary of the invention
The utility model cannot be made effective impression to downwash flow in order to solve traditional pitot on general gyroplane, while is due to the impact of downwash flow, the pressure that when gyroplane hovering and low-speed operations, baroport is experienced is not static pressure accurately, the problem that static pressure signal can not normally use, provides a kind of probe head of static pressure for the little tachometric survey of gyroplane.
Static-pressure system in the utility model can gather pressure by baroport in the time of gyroplane hovering and low speed, and pressure signal calculates downwash flow speed thus. And this invention effectively utilizes gyroplane in hovering and the static pressure signal that cannot use when low speed.
The utility model adopts following technical scheme to realize:
For the probe head of static pressure of the little tachometric survey of gyroplane, comprise pitot, it is characterized in that pitot body adopts spindle streamline surface, on pitot body, have two baroports, two baroports be positioned on spindle streamline surface and installation direction upwards.
Described spindle streamline surface comprises three sections that connect as one successively, and first paragraph is parabola profile section; Second segment is straight line conical surface section, and the 3rd section is straightway. Two baroports are positioned at straight line conical surface section, and the angle between two baroport center lines is 32 °, when installation one towards top, one is tilted to fuselage direction.
Pitot is installed on the fuselage left and right sides, apart from approximately 1/3～2/3 rotor diameter place of aircraft rotary wing oar disk center, and left pitot and right pitot position symmetry.
The utility model is compared with general probe head of static pressure, and its data user rate is greatly improved. As shown in Figure 1, be 0～V in gyroplane speed1Interval, the utility model can effectively be experienced downwash flow pressure signal, calculates thus downwash flow speed. When speed is greater than V2After, the utility model can effectively be experienced fuselage static pressure signal, separates the parameters such as calculated altitude and speed. And traditional pitot is at gyroplane speed 0～V2Interval, the pressure signal that its depressurizing system is experienced is all not spendable. By fluid simulation software (CFD) emulation, speed is greater than to V in addition2On rear gyroplane, the static pressure error value of pitot baroport is calculated, and static pressure error of the present utility model is also in error allowed band.
Brief description of the drawings
Fig. 1 is the utility model and existing static pressure pitot rate curve comparison diagram,
Fig. 2 is existing pitot outline drawing,
Fig. 3 is the A-A profile of Fig. 2,
Fig. 4 is profile figure of the present utility model,
Fig. 5 is left pitot baroport perforate schematic diagram,
Fig. 6 is right pitot baroport perforate schematic diagram.
Detailed description of the invention
By reference to the accompanying drawings detailed description of the invention of the present utility model is described further.
For the probe head of static pressure of the little tachometric survey of gyroplane, comprise pitot, it is characterized in that pitot body adopts spindle streamline surface, on pitot body, have two baroports, two baroports be positioned on spindle streamline surface and installation direction upwards.
Described spindle streamline surface comprises three sections that connect as one successively, and first paragraph is parabola profile section; Second segment is straight line conical surface section, and the 3rd section is straightway. Two baroports are positioned at straight line conical surface section, and the angle between two baroport center lines is 32 °, when installation one towards top, one is tilted to fuselage direction.
Pitot is installed on the fuselage left and right sides, apart from approximately 1/3～2/3 rotor diameter place of aircraft rotary wing oar disk center, and left pitot and right pitot position symmetry.
Embodiment: on certain class gyroplane, we,, by analyzing fuselage impact and the rotor airflow influence of certain class gyroplane, have carried out profile as shown in Figure 3 to pitot and improved, and use profile of the present utility model and position of opening, mode.
According to fuselage impact and the rotor airflow influence of gyroplane, pitot body has adopted unique spindle streamline surface, the aerodynamic effects of this profile uniqueness can realize lower unit static pressure error in shorter unit profile, effectively shortens body length loss of weight.
As shown in Figure 3, first paragraph is parabola profile section to pitot spindle streamline surface, and second segment is straight slope section, and the 3rd section is normal straight section.
The profile formula of first paragraph parabola profile L1 is as follows: φ D=(a+bX+cX2+dX3+eX4+……)×2,（0≤X≤81）,
a=3.7530997、b=0.15652095、c=-0.0019875442、d=3.0398042X10-5、e=-5.057283X10-7。
Second segment straight slope section L2: φ D=(a+bx) X2, (81≤X≤103),
a=2.7272451、b=0.07006917。
The 3rd section is normal straight section L3: φ D=19.88, (103≤X≤171).
Pitot baroport people as shown in Figure 5,6, pitot baroport is positioned in spindle profile and by traditional circumferential openings and is improved to only top perforate, the downwash flow velocity that the angle of perforate should produce according to baroport place rotor designs, angle between two baroport center lines is 32 °, the pressure experience signal error occurring when two baroports can effectively avoid single hole to be blocked. Pitot is installed on fuselage upside and is subject to rotor downwash airflow influence greatly and the position nearer apart from rotor, left pitot and right pitot position symmetry, and the different perforate direction of left and right pitot is that the fuselage of gyroplane own and rotor airflow influence are determined.
Use fluid simulation software (CFD) to carry out emulation to gyroplane floating state flow field, can obtain the pressure of baroport position in flow field, can obtain effective downwash flow velocity amplitude through resolving.
Claims (4)
1. for a probe head of static pressure for the little tachometric survey of gyroplane, comprise pitot, it is characterized in that pitot body adopts spindle streamline surface, on pitot body, have two baroports, two baroports be positioned on spindle streamline surface and installation direction upwards.
2. the probe head of static pressure for the little tachometric survey of gyroplane according to claim 1, is characterized in that described spindle streamline surface comprises three sections that connect as one successively, and first paragraph is parabola profile section; Second segment is straight line conical surface section, and the 3rd section is straightway.
3. the probe head of static pressure for the little tachometric survey of gyroplane according to claim 2, it is characterized in that two described baroports are positioned at straight line conical surface section, angle between two baroport center lines is 32 °, when installation one towards top, one is tilted to fuselage direction.
4. according to a kind of probe head of static pressure for the little tachometric survey of gyroplane described in claim 1 or 2 or 3, it is characterized in that described pitot is installed on the fuselage left and right sides, apart from approximately 1/3～2/3 rotor diameter place of aircraft rotary wing oar disk center, left pitot and right pitot position symmetry.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201521090574.9U CN205246692U (en) | 2015-12-24 | 2015-12-24 | A static pressure probe for little speed measurement of gyroplane |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201521090574.9U CN205246692U (en) | 2015-12-24 | 2015-12-24 | A static pressure probe for little speed measurement of gyroplane |
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| CN205246692U true CN205246692U (en) | 2016-05-18 |
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| CN201521090574.9U Expired - Fee Related CN205246692U (en) | 2015-12-24 | 2015-12-24 | A static pressure probe for little speed measurement of gyroplane |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105424971A (en) * | 2015-12-24 | 2016-03-23 | 太原航空仪表有限公司 | Static pressure probe used for gyroplane low speed measurement |
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2015
- 2015-12-24 CN CN201521090574.9U patent/CN205246692U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105424971A (en) * | 2015-12-24 | 2016-03-23 | 太原航空仪表有限公司 | Static pressure probe used for gyroplane low speed measurement |
| CN105424971B (en) * | 2015-12-24 | 2019-08-16 | 太原航空仪表有限公司 | A kind of probe head of static pressure for the small tachometric survey of gyroplane |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20160518 Termination date: 20201224 |