JPS6055018B2 - Correction device for air pressure detection errors in aircraft, etc. - Google Patents

Description

DETAILED DESCRIPTION OF THE INVENTION The present invention relates to a device for correcting air pressure detection errors in order to obtain correct various outputs from air data processing equipment in an aircraft or the like.

The calculations use the total pressure and apparent static pressure from the detector human system or the detector combined with a pitot tube and flush port as the signal source. Apparent static pressure refers to static pressure that includes errors that occur in the detection unit due to flight conditions of aircraft, etc., but conventional human system signal sources can be corrected as Matsuha functions and have not been implemented in this way. ing. However, the reality is that static pressure detection errors included in the signal source from the flash port detector cannot be corrected using conventional methods. This invention corrects the detection error included in the apparent static pressure from the flash port detector, and corrects the detection error of air pressure in aircraft, etc., so that correct various outputs can be obtained from the air data processing equipment. This was done in an attempt to provide a correction device.

That is, the pneumatic pressure detection error correction device according to the present invention corrects the apparent static pressure signal PS of the signal from the detector flash port.
I and the apparent calibration speed (C, A, S)' or the apparent angle of attack signal, and the static pressure correction amount ΔPs is calculated from the apparent calibration speed or the apparent angle of attack signal and the static pressure correction amount ΔPs is calculated from the apparent calibration speed or the apparent angle of attack signal. A function converter that outputs a voltage proportional to the pressure correction amount ΔPs, and the output from this function converter is used to convert the apparent static pressure signal Psi into a correct static pressure signal Ps or calculate the correct static pressure signal Ps. The air data processing device is characterized in that it includes a means for doing so, so that correct various outputs can be obtained from the air data processing device. In the first embodiment of the present invention, the air pressure itself of the signal source is corrected and used for subsequent calculations, so that a correct signal is supplied to the air data processing equipment, and the output does not include the influence of static pressure errors. FIG. 1 is a system diagram of the first embodiment, and FIG. 2 is a principle diagram of the first embodiment. In explaining the first embodiment using these two figures, the symbols used in the figures and their correlations are as follows. Psi... Apparent static pressure, Ps.
...Correct static pressure, Pt...Total pressure, ΔPs
...Static pressure detection error, Psi/Pt...
Apparent Matsuha function, Ps/Pt...Example 1 of correct Matsuha function: The total pressure signal Pt input from the detector can be directly input into the air data processing equipment, but regarding static pressure, the apparent static pressure The signal Psi is divided into two signals, the apparent calibration speed or the apparent angle of attack signal, and the former Psi is received by the pneumatic pressure converters A and C and outputted as a static pressure signal Ps corrected thereby, and the latter is a function The converter outputs a voltage proportional to the amount of correction to be added to the static pressure, that is, the static pressure detection error ΔPs, and the corrected static pressure A S taken out from the pneumatic pressure converters A and C, air, and data processing. The pressure sensor built into the device converts it into a voltage proportional to the static pressure Ps, which is reversed in sign by the inverter I and input to the (-) side of the operational amplifier A2, which is proportional to the above ΔPs. The resulting voltage is input to the (10) side of the amplifier A2, and the calculation is performed, and the resultant voltage is taken out as an output.

Furthermore, the correction amount ΔP to be added to the static pressure on the X side of the next divider
Insert a voltage proportional to s, input the Psi obtained above to the Y side, perform a division operation, and get ΔPS/P as the result of z=Φ.
Take out Si as an output signal. This ΔPS/Psi is sent to the (-) side of the servo amplifier A1 as a fulcrum position setting signal, and sets the position of the movable fulcrum S as a feedback signal to the pneumatic converters A and C.

Next, we will explain the structure and function of the air pressure transducers A and C. These are sealed box-shaped containers with an air intake port connected to a pressure difference detection diaphragm D, into which an apparent static pressure Psi is introduced, and a corrected static pressure Psi is introduced from the exhaust port. The static pressure Ps is discharged as an output.

In addition, there are control valves C and V connected to the pressurizing air source and the depressurizing vacuum source from the sides of the center of the container, respectively, and the inner walls of the control valves C and ■ are the valve opening/closing plates V integrated into the balance beam BB as shown in the figure. , P. The central balance beam BB is supported so as to be able to rotate around a fulcrum S, and the upper surface of the balance beam BB is connected to a vacuum bellows B and the contact points 7 of the pressure difference detector diaphragm D at a distance L from the vacuum bellows B. The movable fulcrum S of the variable resistor R7 for fulcrum position detection comes into contact with the lower surface and serves as a fulcrum that supports pressure from above. Now, the servo motor M is driven by the fulcrum position setting signal ΔPS/Psi to the (-) side of the servo amplifier A1, and the movable fulcrum S is moved to a designated position by the operation of the gear train GT. Accordingly, the contact point of the moving fulcrum S runs on the variable resistor R for fulcrum position detection, and detects the fulcrum position. When the position of the fulcrum S is determined as described above, the following relationship is established between the vacuum bellows B and the double edge points of the diaphragm D. Here, L is the distance between the contact point of the vacuum bellows B and the contact point of the pressure difference detection section diaphragm D, and is constant.

1 is the distance from the zero starting point to the fulcrum S at the contact point of the vacuum bellows B, including the direction. Now, for example, the apparent static EEPsi that has entered the intake side of the pressure difference detection part diaphragm D
When is larger than the pressure on the opposite side, the balance beam ship moves downward to the right due to the pressing force of the contact point D, and the valve opening/closing plate at the right end descends to open the valve connected to the pressure source.

As a result, the air pressure inside the container rises, and when it balances with Psi, the equilibrium beam BB returns to the equilibrium position, and the valve opening/closing plate ■
, P also closes the pressurizing valve. As a result, the air pressure inside the container becomes the corrected static pressure Ps and is led to the outside as an output. Conversely, if Psi is smaller than the internal pressure, the valve on the pressure reducing side is opened and the operation is continued until the air pressure is balanced. The static pressure corrected in this way is supplied to the air data processing equipment and is supplied as a correct output. Next, a second embodiment of the invention will be described.

In the second embodiment, various input signals are directly input to the air data processing equipment, the amount of correction necessary for each system is calculated, and the correction calculation is performed within the equipment to supply correct results. FIG. 3 is a system diagram of the second embodiment, and FIG. 4 is a principle diagram of the second embodiment.

The symbols used in the explanation of FIGS. 3 and 4 and their correlations are exactly the same as in the first embodiment. That is (1)
The formula also applies in this case. First, the total pressure signal Pt from the detector pitot tube enters the speed sensor in the air data processing equipment, and the apparent static pressure signal Psi from the detector flash boat is divided into two parts, one of which is sent to the upper speed sensor. It is taken out as a Mach function (1) multiplied by Psi and input as an input signal to the (+) side of the operational amplifier for Pt for addition.

Note that the remaining signal of PSi enters the static pressure sensor and is taken out as a voltage signal Psi proportional to the pneumatic signal of Psi.
One of the divided signals is input to the X side of the divider 1MD1, and the other input is input to the (+) side of the operational amplifier input.

Next, the apparent calibration velocity or apparent angle of attack signal input from the detector flash boat is converted by a function converter into a voltage ΔPs proportional to the static pressure detection error, and this voltage ΔPs is proportional to the static pressure detection error.
Ps is divided into two parts and one part is put into the X side of the divider 2MD2, and the other part is led to the (-) side of the operational amplifier A4. Furthermore, on the Y side of the divider 1r01, there is a signal that comes out from the speed sensor.
A voltage (100) proportional to Psi's apparent Matsuha function is inputted, and z=Y=Pt is obtained as the output signal, which is
When x is input to the Y side of the divider 2MD2, it comes out as Z=Y=ΔPs-.

When this signal voltage is introduced into the (-) side of the operation intensifier PsO, the operation PsiΔP is as shown in equation (1).
sPs calculation is performed.

In other words, a new Matsuha function with a positive 0PtPtPt is obtained.

Note that the signal voltages input to the (+) and (-) sides of the operational amplifier A4 are taken out as the correct static pressure signal Ps. Is the Matsuha function correct based on the above? Thus, the correct static pressure function Ps can be obtained. Next, the portion surrounded by a broken line in FIG. 4 can be replaced with the principle diagram in FIG. 5. FIG. 5 is a principle diagram for obtaining a correct static pressure signal when the apparent static pressure signal is given as a highly proportional signal. In addition, static pressure detection error Δ
An embodiment will be described in which PSl, in other words, a static pressure correction amount is generated. This can be used in common with Embodiments 1 and 2 described above, but for example, by utilizing the characteristics of the potentiometer, the function of the apparent angle of attack or the apparent calibration speed is plotted on the horizontal axis as shown in FIG. If we take the rotation angle θ of the potentiometer shaft that is proportional to , and take the voltage ΔPs that is proportional to the atmospheric pressure as the static pressure 3 correction amount on the vertical axis, we can obtain a function given for each type of aircraft, for example, in the form of a T curve. FIG. 7 is a diagram showing the principle of generation of the static pressure correction amount by a potentiometer. When a shaft rotation angle θ proportional to a function of the apparent angle of attack or apparent calibration speed is set to a potentiometer to which a reference voltage is applied, the static pressure correction amount ΔPs is obtained in the form of a voltage. A piezoelectric element may be used instead of the potentiometer used in this). As explained above using the two embodiments, by correcting the apparent calibration speed or apparent angle of attack, it is possible to obtain a correct static pressure signal by adding the correct correction to the signal from the flash boat. This allows us to obtain the correct output along with the correct Matsuha function.

[Brief explanation of the drawing]

Fig. 1 System diagram of Embodiment 1 of this invention, Fig. 2 Principle diagram of Embodiment 1 of this invention, Fig. 3 Embodiment 2 of this invention
Systematic diagram, Fig. 4 Principle diagram of Embodiment 2 of this invention, Fig. 5
Figure 6: Diagram of the correct static pressure signal generation given by a signal proportional to altitude; Figure 6: Potentiometer axis rotation angle and static pressure correction amount diagram; Figure 7: Generation principle of static pressure compensation using a potentiometer. Each symbol used in the drawings indicates a supplementary part.

Claims (1)

[Claims] 1. Means for dividing the signal from the detector flush port into two: an apparent static pressure signal Psi and an apparent calibration speed or apparent angle of attack signal; A function converter that calculates a static pressure correction amount ΔPs from the signal and outputs it as a voltage proportional to the static pressure correction amount ΔPs, and converts the apparent static pressure signal Psi into a correct static pressure signal using the output from this function converter. A correction device for air pressure detection error in an aircraft, etc., comprising means for converting the static pressure signal Ps into a correct static pressure signal Ps or calculating a correct static pressure signal Ps, so that correct various outputs can be obtained from an air data processing device. 2. A correction device for a detection error in air pressure of an aircraft, etc. as claimed in claim 1, wherein a correct static pressure signal Ps after converting an apparent static pressure signal Psi is introduced into an air data processing device. 3. A correction device for a detection error in air pressure of an aircraft, etc. as claimed in claim 1, wherein an apparent static pressure signal Psi is introduced into an air data processing device to calculate a correct static pressure signal Ps.