CN112504547A - High-precision dynamic pressure measuring method and system with long-term stability - Google Patents
High-precision dynamic pressure measuring method and system with long-term stability Download PDFInfo
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Abstract
The invention discloses a high-precision dynamic pressure measuring method and system with long-term stability. Calculating the zero offset b of the measured dynamic pressure Qc2 of the wide range differential pressure sensor when the Qc1 is close to 0 Pa; when the Qc1 is close to the range end value of the small-range differential pressure sensor, calculating the error correction slope k of the dynamic pressure Qc 2; when the dynamic pressure Qc is within the measuring range of the small-range differential pressure sensor, the measured dynamic pressure Qc1 of the small-range differential pressure sensor is a real dynamic pressure, that is, Qc = Qc 1; otherwise, the real dynamic pressure is obtained by correcting the dynamic pressure Qc 2. The invention constructs the measuring configurations of the small-range differential pressure sensor and the large-range differential pressure sensor, and realizes the measuring precision and the long-term stability in the dynamic pressure full pressure range through the cooperative work of the small-range differential pressure sensor and the large-range differential pressure sensor.
Description
Technical Field
The invention belongs to the technical field of atmospheric data measurement, and particularly relates to a high-precision dynamic pressure measuring method and system with long-term stability.
Background
The atmospheric data system is used for measuring parameters such as the height, the speed and the like of aircrafts such as airplanes, helicopters, missiles and the like in real time by utilizing the principle of measuring the air pressure, is safety key equipment of the airplanes, belongs to an airplane avionics system, provides important navigation and flight control parameters for an airplane navigation system, a flight control system, a comprehensive fire control system and an airplane engine control system, and is an essential important system for influencing the flight safety of the airplanes and realizing autonomous navigation.
The atmospheric data system realizes the calculation of atmospheric parameters such as the air pressure altitude, the indicated airspeed, the Mach number, the vacuum speed, the lifting speed and the like of the aircraft by measuring the total pressure (static pressure + speed pressure) and the static pressure signal of a flow field where the aircraft is located, so that dynamic pressure measurement is the basis of atmospheric data measurement, and the measurement precision and the long-term stability of the dynamic pressure measurement directly determine the performance and the long-term stability of the atmospheric data measurement device.
According to the bernoulli equation:
when the ideal gas which is non-viscous and incompressible flows along the flow pipe at a constant speed, the flow speed is increased, and the static pressure of the fluid is reduced; conversely, the flow velocity decreases and the static pressure of the fluid will increase. But the sum of the hydrostatic and hydrodynamic pressures of the fluid, referred to as the total pressure, remains constant at all times. Therefore, the dynamic pressure equation of an ideal gas is as follows:
wherein:
v: space velocity, unit: m/s2；
qc: dynamic pressure, unit: pa;
ρ: gas density, unit: kg/m3Sea level air density ρ n is 1.225kg/m3；
According to the ideal gas dynamic pressure equation, the derivative of the dynamic pressure equation is as follows:
qc' (V) ═ ρ V type (3)
According to the dynamic pressure derivative equation, the dynamic pressure resolution is in a direct proportional relation with the speed point, so that for the atmospheric data measurement principle, when the airspeed error is constant, the lower the speed measurement point is, the smaller the dynamic pressure error is required to be, and the higher the measurement precision requirement on the pressure sensor is.
At present, low-speed aircrafts such as helicopters, airships and the like have higher low-speed measurement precision requirements on air data airspeed measurement, and the airspeed measurement precision requirements are shown in the following table 1.
TABLE 1 airspeed and dynamic pressure measurement accuracy requirements
Dynamic pressure measurement can be achieved in two ways:
(1) measuring total pressure (Pt) and static pressure (Ps) by two absolute pressure sensors respectively, and indirectly obtaining dynamic pressure Qc which is Pt-Ps;
(2) the dynamic pressure (Qc) is measured directly using a differential pressure sensor.
At present, a silicon resonance pressure sensor is generally adopted to realize absolute pressure acquisition, the long-term stability of the sensor is good (10Pa/10 years), the relative measurement precision is high (0.02 percent F.S), but the measurement range of the sensor is wider relative to the dynamic pressure low-speed measurement range (the measurement range: 140.0kPa), and therefore, the absolute precision of the sensor is lower relative to the low-speed measurement section. The absolute pressure sensor with the accuracy of 0.02 percent F.S (measuring range: 140.0kPa) can only achieve the highest measuring accuracy of 0.01 percent F.S (measuring range: 140.0kPa), namely, the delta P is +/-14 Pa, through system screening and secondary correction. According to the formula Qc-Pt-Ps, Qc maximum measurement error Δ Qc ═ 14 × 2 ═ 28 Pa. According to the requirement (delta Qc is less than or equal to 9.19Pa) of low-speed measurement on the measurement error of the dynamic pressure Qc in the table 1, the absolute pressure sensor can not meet the requirement of low-speed measurement of the airspeed.
When the airspeed measurement accuracy requirement is that delta V is less than or equal to 0.5m/s, when an absolute pressure sensor is used for measuring the dynamic pressure, the airspeed measurement accuracy requirement can be met only when V is more than or equal to 28/(0.5 x 1.225) ═ 45.7 m/s.
The differential pressure sensor directly realizes dynamic pressure measurement, eliminates the maximum measurement error caused by inconsistent directions of total pressure and static pressure measurement errors, generally adopts a piezoresistive principle (silicon pressure group differential pressure sensor), has flexible measurement range, and can select the differential pressure sensor with a proper dynamic pressure range according to the airspeed measurement range, thereby improving the measurement resolution of the dynamic pressure and improving the measurement precision of the dynamic pressure.
The silicon pressure group differential pressure sensor generally has large time drift and temperature drift, so the long-term stability of the silicon pressure group differential pressure sensor is poor, and the requirement of long-term stability of airborne equipment cannot be met.
The specifications and characteristics of a conventional silicon pressure cell differential pressure sensor are shown in table 2 below.
TABLE 2 silicon pressure set differential pressure sensor specification and characteristics
According to the analysis, because low-speed aircrafts such as helicopters, airships and the like have higher requirements on the measurement precision of air data airspeed at low speed, have strict requirements on the measurement precision and long-term stability of the pressure sensor, and cannot be realized by adopting the traditional measurement method, the invention realizes the real-time correction of the large-range differential pressure sensor by changing the dynamic pressure measurement configuration (small-range and large-range combined measurement) and by using the small-range differential pressure sensor with long-term stability (almost no time drift and temperature drift) and good performance, thereby realizing the dynamic pressure full-range measurement precision and long-term stability.
The small-range differential pressure sensor adopts a heat flow penetration principle, has the performances of low pressure difference, low drift and high precision, has excellent long-term stability, and has a small measurement range.
The main technical properties of the heat flux penetration principle small range differential pressure sensor are shown in table 3.
Table 3 main technical properties of small-range differential pressure sensor based on heat flux penetration principle
| Serial number | Parameter(s) | Index (I) | Remarks for note |
| 1 | Measuring range | -500Pa～500Pa | |
| 2 | Zero point accuracy | 0.1Pa | |
| 3 | Accuracy of measurement range | 3% reading | |
| 4 | Repeatability of zero point | 0.03Pa | |
| 5 | Measurement Range repeatability | 0.5% reading | |
| 6 | Long term stability | Less than or equal to 0.01 Pa/year | Almost no drift |
| 7 | Allowing over-pressure capability | 100kPa (typical value) | Overpressure capacity can contain dynamic pressure measurement range |
| 8 | Pressure of breakage | ≥300kPa |
Disclosure of Invention
The invention aims to provide a high-precision dynamic pressure measuring method with long-term stability, and aims to solve the problems.
The invention also aims to provide a high-precision dynamic pressure measuring system with long-term stability, which constructs a measuring configuration of a small-range differential pressure sensor and a large-range differential pressure sensor, and realizes the measuring precision and long-term stability in a dynamic pressure full pressure range through the cooperative work of the small-range differential pressure sensor and the large-range differential pressure sensor.
The invention aims at the requirements of low-speed air data airspeed low-speed measurement precision and long-term stability of low-speed aircrafts such as helicopters, airships and the like, overcomes the defects of the prior measurement technology, fully utilizes the advantages of two different differential pressure sensors, and constructs a small-range differential pressure sensor, a large-range differential pressure sensor measurement configuration and a large-range differential pressure sensor real-time calibration method by changing the prior measurement configuration so as to realize the measurement precision and long-term stability in a dynamic pressure full pressure range.
The invention is mainly realized by the following technical scheme:
a high-precision dynamic pressure measuring method with long-term stability comprises a large-range differential pressure sensor and a small-range differential pressure sensor, wherein the small-range differential pressure sensor is high in precision and long-term stability; the measuring range of the wide-range differential pressure sensor covers the dynamic pressure measuring range; the overpressure capacity of the small-range differential pressure sensor covers a dynamic pressure measurement range;
when Qc1 approaches 0Pa, the null offset b of the measured dynamic pressure Qc2 of the wide range differential pressure sensor is calculated:
b＝Qc1-Qc2
when the Qc1 is close to the range end value of the small-range differential pressure sensor, calculating the error correction slope k of the dynamic pressure Qc 2:
when the dynamic pressure Qc is within the measuring range of the small-range differential pressure sensor, the measured dynamic pressure Qc1 of the small-range differential pressure sensor is a real dynamic pressure, that is, Qc is Qc 1;
when the dynamic pressure Qc exceeds the measuring range of the small-range differential pressure sensor, then:
Qc＝k×Qc2+b。
to better implement the present invention, further, when | Qc1| ≦ 495Pa, then Qc ≦ Qc 1; when | Qc1| > 495Pa, then:
Qc＝k×Qc2+b。
in order to better realize the invention, further, when the absolute value of Qc1 is less than or equal to 5Pa, the zero deviation b of the measured dynamic pressure Qc2 of the wide-range differential pressure sensor is calculated. When Qc1 is within the range of ± 5Pa from the end of the range of the small-range differential pressure sensor, the error correction slope k of dynamic pressure Qc2 is calculated.
To better implement the present invention, further, when 470Pa ≦ Qc1 ≦ 495Pa, an error correction slope k of the dynamic pressure Qc2 is calculated.
In order to better implement the invention, further, the dynamic pressure obtained by the test is used for indicating the airspeed resolution:
when M is less than or equal to 1,
when M is greater than 1, the compound is,
wherein:
m: mach number;
and Qc: dynamic pressure;
and Vi: indicating an airspeed;
pn: sea level standard atmospheric pressure, 101.325 kPa;
cn: sea level standard speed of sound, 340.294 m/s;
k: adiabatic index, 1.4.
In order to better implement the invention, further, the dynamic pressure obtained by the test is used for indicating the airspeed resolution:
when M is less than or equal to 1,
when M is greater than 1, the compound is,
wherein:
m: mach number;
and Qc: dynamic pressure;
ps: carrying out static pressure;
k: adiabatic index, 1.4.
In order to better implement the invention, further, the dynamic pressure obtained by the test is used for vacuum speed calculation:
when Vt is ≦ c for the first time,
when Vt > c is greater than the value of c,
wherein:
vt: vacuum speed;
and Qc: dynamic pressure;
ps: carrying out static pressure;
k: adiabatic index, 1.4;
r: specific gas constant, 287.05287m2/K.s2；
Ts: and (5) keeping the atmosphere at a static temperature.
The invention is also realized by the following technical scheme: a high-precision dynamic pressure measuring system with long-term stability comprises a small-range differential pressure sensor, a large-range differential pressure sensor and an acquisition and correction module which are serially arranged on a total pressure pipeline, wherein a static pressure pipeline is arranged between the small-range differential pressure sensor and the large-range differential pressure sensor, and the small-range differential pressure sensor and the large-range differential pressure sensor are respectively connected with the acquisition and correction module; the precision and the long-term stability of the small-range differential pressure sensor are high; the measuring range of the wide-range differential pressure sensor covers the dynamic pressure measuring range.
The technical scheme of the high-precision full-pressure-range dynamic pressure measuring method for realizing the long-term stability of atmospheric data comprises the following steps:
1. the dynamic pressure Qc is measured by adopting differential pressure sensors with two measuring ranges (1 small measuring range and 1 large measuring range) simultaneously, so that the dynamic pressure Qc covers a dynamic pressure measuring range, wherein the small-measuring-range differential pressure sensor has high precision and good long-term stability, the overpressure capacity covers the dynamic pressure measuring range, and a large range differential pressure sensor needs to cover the dynamic pressure measuring range.
2. Two paths of dynamic pressure Qc1 (small range) and Qc2 (large range) are collected simultaneously.
3. When the dynamic pressure Qc is in the measuring range of the small-range differential pressure sensor, the static pressure Qc is Qc1, and the airspeed and mach number are calculated by using Qc1 (small range) as it is.
4. When the dynamic pressure Qc1 is near 0Pa (margin is adjustable), the null deviation b of the dynamic pressure Qc2 (wide range) is calculated.
5. When the dynamic pressure Qc1 is near the full scale of the differential pressure sensor (margin is adjustable), the error correction slope k of the dynamic pressure Qc2 (wide scale) is calculated.
The dynamic pressure zero position and full range allowance value are adjusted according to the characteristics of the platform.
The invention has the beneficial effects that:
(1) the invention aims at the requirements of low-speed air data airspeed low-speed measurement precision and long-term stability of low-speed aircrafts such as helicopters, airships and the like, overcomes the defects of the prior measurement technology, fully utilizes the advantages of two different differential pressure sensors, and constructs a small-range differential pressure sensor, a large-range differential pressure sensor measurement configuration and a large-range differential pressure sensor real-time calibration method by changing the prior measurement configuration so as to realize the measurement precision and long-term stability in a dynamic pressure full pressure range.
(2) The method is obtained through a large number of mathematical deductions and tests according to performance indexes and long-term stability characteristics of various differential pressure sensors, is actually applied to a certain product, obtains good effects, realizes the problems of low-speed and high-precision measurement of atmospheric data airspeed and time drift of a large-range differential pressure sensor, ensures the long-term stability of atmospheric data measurement, has the characteristics of low cost, easiness in implementation and the like, and has strong practical application value and economic benefit.
(3) The invention adopts the differential pressure sensor without time drift to realize the real-time automatic correction of the differential pressure sensor with time drift, the correction is automatically realized without manual intervention and periodic maintenance of an atmospheric data measuring device, and the maintainability of the equipment is greatly improved.
Drawings
FIG. 1 is a schematic block diagram of the system of the present invention;
fig. 2 is a block flow diagram of the present invention.
Detailed Description
Example 1:
a high-precision dynamic pressure measuring method with long-term stability is disclosed, as shown in figure 1, comprising a large-range differential pressure sensor and a small-range differential pressure sensor, wherein the small-range differential pressure sensor has higher precision and long-term stability; the measuring range of the wide-range differential pressure sensor covers the dynamic pressure measuring range.
When Qc1 approaches 0Pa, the null offset b of the measured dynamic pressure Qc2 of the wide range differential pressure sensor is calculated:
b＝Qc1-Qc2
when the Qc1 is close to the range end value of the small-range differential pressure sensor, calculating the error correction slope k of the dynamic pressure Qc 2:
when the dynamic pressure Qc is within the measuring range of the small-range differential pressure sensor, the measured dynamic pressure Qc1 of the small-range differential pressure sensor is a real dynamic pressure, that is, Qc is Qc 1;
when the dynamic pressure Qc exceeds the measuring range of the small-range differential pressure sensor, then:
Qc＝k×Qc2+b。
the invention aims at the requirements of low-speed air data airspeed low-speed measurement precision and long-term stability of low-speed aircrafts such as helicopters, airships and the like, overcomes the defects of the prior measurement technology, fully utilizes the advantages of two different differential pressure sensors, and constructs a small-range differential pressure sensor, a large-range differential pressure sensor measurement configuration and a large-range differential pressure sensor real-time calibration method by changing the prior measurement configuration so as to realize the measurement precision and long-term stability in a dynamic pressure full pressure range.
Example 2:
the present embodiment is optimized on the basis of embodiment 1, and when | Qc1| ≦ 495Pa, Qc ≦ Qc 1; when | Qc1| > 495Pa, Qc ═ k × Qc2+ b. As shown in fig. 2, dynamic pressures Qc1 and Qc2 are collected by a small-range differential pressure sensor and a large-range differential pressure sensor, respectively, and when | Qc1| ≦ 495Pa, Qc1 is adopted as a real dynamic pressure, and Qc ═ Qc1 is provided; otherwise, the corrected dynamic pressure Qc2 obtains a true dynamic pressure, which is k × Qc2+ b.
Further, when the absolute value of Qc1 is less than or equal to 5Pa, the zero deviation b of the measured dynamic pressure Qc2 of the wide-range differential pressure sensor is calculated.
The invention adopts the differential pressure sensor without time drift to realize the real-time automatic correction of the differential pressure sensor with time drift, the correction is automatically realized without manual intervention and periodic maintenance of an atmospheric data measuring device, and the maintainability of the equipment is greatly improved.
Other parts of this embodiment are the same as embodiment 1, and thus are not described again.
Example 3:
a high-precision dynamic pressure measuring system with long-term stability is disclosed, as shown in figure 1, and comprises a small-range differential pressure sensor, a large-range differential pressure sensor and an acquisition and correction module which are arranged on a total pressure pipeline in series, wherein a static pressure pipeline is arranged between the small-range differential pressure sensor and the large-range differential pressure sensor, and the small-range differential pressure sensor and the large-range differential pressure sensor are respectively connected with the acquisition and correction module; the precision and the long-term stability of the small-range differential pressure sensor are high; the measuring range of the wide-range differential pressure sensor covers the dynamic pressure measuring range.
The method is obtained through a large number of mathematical deductions and tests according to performance indexes and long-term stability characteristics of various differential pressure sensors, is actually applied to a certain product, obtains good effects, realizes the problems of low-speed and high-precision measurement of atmospheric data airspeed and time drift of a large-range differential pressure sensor, ensures the long-term stability of atmospheric data measurement, has the characteristics of low cost, easiness in implementation and the like, and has strong practical application value and economic benefit. The invention adopts the differential pressure sensor without time drift to realize the real-time automatic correction of the differential pressure sensor with time drift, the correction is automatically realized without manual intervention and periodic maintenance of an atmospheric data measuring device, and the maintainability of the equipment is greatly improved.
Example 4:
the embodiment adopts a dynamic pressure atmospheric parameter recalibration example for measuring an atmospheric data measuring device on an airplane to describe, and the dynamic pressure original parameter is obtained by measuring a differential pressure type silicon piezoresistive sensor.
As shown in fig. 1, the dynamic pressure measurement method adopted in the present embodiment is directly implemented by using a differential pressure sensor, and the small-range and large-range dynamic pressure measurements are respectively implemented by using two differential pressure sensors with different ranges, so as to be used for resolving the following indicated airspeed, mach number and vacuum speed. The two differential pressure sensors are respectively: 1, a small-range differential pressure sensor; 2, a wide range differential pressure sensor.
The atmospheric dynamic pressure described in the embodiment is obtained by subtracting the static pressure from the total pressure, and is a basic parameter for calculating atmospheric data such as the indicated airspeed, Mach number, vacuum speed and the like of the airplane through direct measurement of a differential pressure sensor.
As shown in fig. 2, after being powered on, the atmospheric data measurement device executes periodic tasks according to a program cycle, where the program cycle of software is 20ms, and the internal dynamic pressure correction process is as follows:
1. the atmospheric data measuring device acquires dynamic pressures Qc1 and Qc 2;
2. judging the range of Qc1, if | Qc1| is less than or equal to 495Pa, calculating the real dynamic pressure Qc according to the formula (8);
qc ═ Qc1 formula (8)
3. If the absolute value of Qc1 is less than or equal to 5Pa, calculating the zero deviation b of the dynamic pressure Qc2 according to the formula (9);
b-Qc 1-Qc2 type (9)
4. If 470Pa ≦ Qc1 ≦ 495Pa, calculating an error slope k of the dynamic pressure Qc2 according to equation (10);
5. if the absolute value Qc1 is less than or equal to 495Pa, calculating a real dynamic pressure Qc according to the formula (11);
qc ═ k × Qc2+ b formula (11)
6. The atmospheric data measuring device completes calculation of the indicated airspeed Vi according to the obtained real Qc according to the formula (12) and the formula (13);
when M is less than or equal to 1
When M >1
Wherein:
m: mach number;
and Qc: dynamic pressure;
and Vi: indicating an airspeed;
pn: sea level standard atmospheric pressure, 101.325 kPa;
cn: sea level standard speed of sound, 340.294 m/s;
k: adiabatic index, 1.4;
7. the atmospheric data measuring device completes Mach number M calculation according to the obtained real Qc according to the formula (14) and the formula (15);
when M is less than or equal to 1
When M >1
Wherein:
m: mach number;
and Qc: dynamic pressure;
ps: carrying out static pressure;
k: adiabatic index, 1.4.
8. The atmospheric data measurement device completes the vacuum velocity Vt calculation according to equations (16) and (17) from the obtained true Qc.
When Vt is ≦ c
When Vt > c
Wherein:
vt: vacuum speed;
and Qc: dynamic pressure;
ps: carrying out static pressure;
k: adiabatic index, 1.4;
r: specific gas constant, 287.05287m2/K.s2；
Ts: and (5) keeping the atmosphere at a static temperature.
The invention aims at the requirements of low-speed air data airspeed low-speed measurement precision and long-term stability of low-speed aircrafts such as helicopters, airships and the like, overcomes the defects of the prior measurement technology, fully utilizes the advantages of two different differential pressure sensors, and constructs a small-range differential pressure sensor, a large-range differential pressure sensor measurement configuration and a large-range differential pressure sensor real-time calibration method by changing the prior measurement configuration so as to realize the measurement precision and long-term stability in a dynamic pressure full pressure range.
The method is obtained through a large number of mathematical deductions and tests according to performance indexes and long-term stability characteristics of various differential pressure sensors, is actually applied to a certain product, obtains good effects, realizes the problems of low-speed and high-precision measurement of atmospheric data airspeed and time drift of a large-range differential pressure sensor, ensures the long-term stability of atmospheric data measurement, has the characteristics of low cost, easiness in implementation and the like, and has strong practical application value and economic benefit.
The invention adopts the differential pressure sensor without time drift to realize the real-time automatic correction of the differential pressure sensor with time drift, the correction is automatically realized without manual intervention and periodic maintenance of an atmospheric data measuring device, and the maintainability of the equipment is greatly improved.
The above description is only a preferred embodiment of the present invention, and is not intended to limit the present invention in any way, and all simple modifications and equivalent variations of the above embodiments according to the technical spirit of the present invention are included in the scope of the present invention.
Claims (8)
1. A high-precision dynamic pressure measuring method with long-term stability is characterized by comprising a large-range differential pressure sensor and a small-range differential pressure sensor, wherein the small-range differential pressure sensor has higher precision and long-term stability; the measuring range of the wide-range differential pressure sensor covers the dynamic pressure measuring range;
when the measured dynamic pressure Qc1 of the small-range differential pressure sensor is close to 0Pa, calculating the zero deviation b of the measured dynamic pressure Qc2 of the large-range differential pressure sensor:
b＝Qc1-Qc2
when the Qc1 is close to the range end value of the small-range differential pressure sensor, calculating the error correction slope k of the dynamic pressure Qc 2:
when the dynamic pressure Qc is within the measuring range of the small-range differential pressure sensor, the measured dynamic pressure Qc1 of the small-range differential pressure sensor is a real dynamic pressure, that is, Qc is Qc 1;
when the dynamic pressure Qc exceeds the measuring range of the small-range differential pressure sensor, then:
Qc＝k×Qc2+b。
2. the method of claim 1, wherein when | Qc1| ≦ 495Pa, Qc ═ Qc 1; when | Qc1| > 495Pa, then:
Qc＝k×Qc2+b。
3. the method for measuring dynamic pressure with high precision and long-term stability as claimed in claim 1 or 2, wherein the null deviation b of the dynamic pressure measured by the wide-range differential pressure sensor Qc2 is calculated when the | Qc1| ≦ 5 Pa.
4. The method of claim 2, wherein the slope k of error correction of dynamic pressure Qc2 is calculated when 470Pa ≦ Qc1 ≦ 495 Pa.
5. The high-precision dynamic pressure measurement method for long-term stability according to claim 1, wherein the dynamic pressure obtained by the test is used for indicating airspeed calculation:
when M is less than or equal to 1,
when M is greater than 1, the compound is,
wherein:
m: mach number;
and Qc: dynamic pressure;
and Vi: indicating an airspeed;
pn: sea level standard atmospheric pressure, 101.325 kPa;
cn: sea level standard speed of sound, 340.294 m/s;
k: adiabatic index, 1.4.
6. The high-precision dynamic pressure measurement method for long-term stability according to claim 1, wherein the dynamic pressure obtained by the test is used for indicating airspeed calculation:
when M is less than or equal to 1,
when M is greater than 1, the compound is,
wherein:
m: mach number;
and Qc: dynamic pressure;
ps: carrying out static pressure;
k: adiabatic index, 1.4.
7. The high-precision dynamic pressure measuring method for long-term stability according to claim 1, wherein the dynamic pressure obtained by testing is used for vacuum speed calculation:
when Vt is ≦ c for the first time,
when Vt > c is greater than the value of c,
wherein:
vt: vacuum speed;
and Qc: dynamic pressure;
ps: carrying out static pressure;
k: adiabatic index, 1.4;
r: specific gas constant, 287.05287m2/K.s2；
Ts: and (5) keeping the atmosphere at a static temperature.
8. A high-precision dynamic pressure measuring system with long-term stability is characterized by comprising a small-range differential pressure sensor, a large-range differential pressure sensor and a collecting and correcting module which are serially arranged on a total pressure pipeline and a static pressure pipeline, wherein the static pressure pipeline is arranged between the small-range differential pressure sensor and the large-range differential pressure sensor, and the small-range differential pressure sensor and the large-range differential pressure sensor are respectively connected with the collecting and correcting module; the precision and the long-term stability of the small-range differential pressure sensor are high; the measuring range of the wide-range differential pressure sensor covers the dynamic pressure measuring range.
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