SU382002A1 - METHOD FOR DETERMINING STATIC PRESSURE ON AIRCRAFT - Google Patents
METHOD FOR DETERMINING STATIC PRESSURE ON AIRCRAFTInfo
- Publication number
- SU382002A1 SU382002A1 SU1611228A SU1611228A SU382002A1 SU 382002 A1 SU382002 A1 SU 382002A1 SU 1611228 A SU1611228 A SU 1611228A SU 1611228 A SU1611228 A SU 1611228A SU 382002 A1 SU382002 A1 SU 382002A1
- Authority
- SU
- USSR - Soviet Union
- Prior art keywords
- static pressure
- aircraft
- pressure
- determining static
- temperature
- Prior art date
Links
Landscapes
- Measuring Fluid Pressure (AREA)
Description
1one
Изобретение относитс к области аэродинамических исследований.This invention relates to the field of aerodynamic research.
Известные способы определени истинного статического давлени на летательном аппарате Hia высоте полета путем измерени полного давлени требуют применени сложных оптических или радиотехнических устройств.The known methods for determining the true static pressure on an Hia aircraft altitude by measuring the total pressure require the use of complex optical or radio devices.
Дл упрощени процесса измерени по предложенному способу одновременно измер ют температуру заторможенного потока и выполн ют зон/ифоваиие атмосферы в корилоре пролета аппарата.To simplify the measurement process according to the proposed method, the temperature of the inhibited flow is simultaneously measured and the zones / atmosphere shaping are performed in the passage corilor.
Сущность способа основава на сравнении измеренного статического давлени испытываемым приемником давлени с истинным статическим давлением на высоте полета. Дл определени истинного статического давлени необходимо измерить вертикальный температурный градиент атмосферы. Дл этого, любым известным способом производ т зондирование атмосферы. Непосредствевно на летательном аппарате измер ют температуру и давление заторможенного потока. Измер ют температуру и давление у земли.The essence of the method is based on comparing the measured static pressure with the pressure receiver being tested with the true static pressure at flight altitude. To determine the true static pressure, it is necessary to measure the vertical temperature gradient of the atmosphere. For this, atmospheric sounding is produced by any known method. The temperature and the pressure of the inhibited flow are measured directly on the aircraft. Measure the temperature and pressure at the ground.
Затем определ ют истинное статическое давлеи е по формуле:Then, the true static pressure is determined by the formula:
р K-1-KR- .p K-1-KR-.
Рп -Т,Pn -T,
Я I
А:-1A: -1
Л-ЛLL
кto
где РЗ - давление у земли,where RZ is the pressure at the ground,
Гз - температура у земли, /С-коэффициент адиабаты, т - вертикальный температурный градиент ,Gz - temperature at the ground, / С-coefficient of adiabat, t - vertical temperature gradient,
R - газова посто нна , РП - давление заторможенного потока, Гт - температура заторможенного потока .R is the gas constant, RP is the pressure of the inhibited flow, Gt is the temperature of the inhibited flow.
Далее путем сравнени определ ют аэродинамические погрешности.Next, the aerodynamic errors are determined by comparison.
Предмет изобретени Способ определени статического давлени The subject of the invention. Method for determining static pressure
на летательном аппарате путем измерени полного давлени , отличающийс тем, что, с целью упрощени процесса измерени , одновременно измер ют температуру заторможенного потока и выполн ют зондирование атмосферы в коридоре пролета аппарата.on an aircraft by measuring the total pressure, characterized in that, in order to simplify the measurement process, the temperature of the inhibited flow is simultaneously measured and the atmosphere is sensed in the passage corridor of the device.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| SU1611228A SU382002A1 (en) | 1971-01-05 | 1971-01-05 | METHOD FOR DETERMINING STATIC PRESSURE ON AIRCRAFT |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| SU1611228A SU382002A1 (en) | 1971-01-05 | 1971-01-05 | METHOD FOR DETERMINING STATIC PRESSURE ON AIRCRAFT |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| SU382002A1 true SU382002A1 (en) | 1973-05-22 |
Family
ID=20463620
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| SU1611228A SU382002A1 (en) | 1971-01-05 | 1971-01-05 | METHOD FOR DETERMINING STATIC PRESSURE ON AIRCRAFT |
Country Status (1)
| Country | Link |
|---|---|
| SU (1) | SU382002A1 (en) |
-
1971
- 1971-01-05 SU SU1611228A patent/SU382002A1/en active
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