CN103542980A - Hypersonic aircraft pre-shooting pressure valve calibration method - Google Patents
Hypersonic aircraft pre-shooting pressure valve calibration method Download PDFInfo
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- CN103542980A CN103542980A CN201310460836.5A CN201310460836A CN103542980A CN 103542980 A CN103542980 A CN 103542980A CN 201310460836 A CN201310460836 A CN 201310460836A CN 103542980 A CN103542980 A CN 103542980A
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Abstract
A hypersonic aircraft pre-shooting pressure valve calibration method includes that 1, a high pressure gas source is connected with a pressure storage tank, and the pressure storage tank is provided with a plurality of gas discharging channels; 2, each channel soft pipe of a pressure valve is connected with the gas discharging channels of the pressure storage tank, and outputted signals are connected with an onboard computer; 3, the high pressure gas source is opened, and the pressure in the pressure storage tank is measured; when the pressure in the pressure storage tank is stable, the onboard computer is started to perform collection of the pressure valve, and measuring records are stored; 4, if data values measured by the pressure valve and pressure values of the pressure storage tank are in the allowed error range, the operation state of the pressure valve mounted on the aircraft is determined to be normal, and a calibration curve during flying tests is calculated; if the data values measured by the pressure valve and the pressure values of the pressure storage tank 5 are out of the allowed error range, the pressure valve is required to change. By the aid of the method, pre-testing calibration can be performed on a plurality of pressure valves mounted on the hypersonic aircraft, and the pressure valves on the aircraft can be guaranteed to be reliable and accurate.
Description
Technical field
The present invention relates to hypersonic aircraft fields of measurement, be specifically related to hypersonic aircraft and penetrate front pressure valve scaling method.
Background technology
The hypersonic aircraft that the scramjet engine of take is power has the feature of body/engine integration, under hypersonic flight condition, air-flow is through the compression of air intake duct, and the burning of firing chamber, in air intake duct and firing chamber, produce high temperature and high pressure gas, the data that high temperature and high pressure gas is measured are the important evidence that whether air intake duct starts, whether light a fire firing chamber.
Can pressure valve truly, the pressure of Measurement accuracy high temperature and high pressure gas is particularly crucial.Must before test transmitting, to pressure valve, finally demarcate.Generally, pressure valve is to demarcate before being arranged on aircraft, but due to the reason such as installation, transportation may build-up of pressure valve damage or drift, and the accuracy that impact is measured.
In the prior art, not yet find can be simultaneously to a plurality of, to be arranged on the method that carry-on pressure valve is demarcated.
Summary of the invention
The present invention is directed to the problem that prior art exists, proposed a kind of hypersonic aircraft and penetrated front pressure valve scaling method, a plurality of pressure valve that are arranged on hypersonic aircraft are tried to front demarcation, guarantee that carry-on pressure valve is reliable, accurate.
Penetrate a front pressure valve scaling method, comprise the following steps:
If the data value that step 4 pressure valve is measured and the force value of pressure vessel are in allowed error range, to be arranged on carry-on pressure valve duty intact in explanation, calculates the calibration curve making a flight test; If the data value that pressure valve is measured and the force value of pressure vessel have exceeded error range, need to change pressure valve.
The present invention utilizes on aircraft existing pipeline and measures passage pressure valve is demarcated.Verify truely and accurately the reliability of pressure-measuring system.The inherent error of having eliminated test macro, has improved measuring accuracy.
Accompanying drawing explanation
Fig. 1: pressure valve calibration principle figure of the present invention;
Fig. 2: pressure vessel connection diagram in the present invention;
Embodiment
Below in conjunction with accompanying drawing, the present invention will be further described.
A plurality of pressure valve are arranged on aircraft, the gas access of pressure valve is connected with the last pressure measurement point pipeline of aircraft, the output signal of pressure valve is connected with missile-borne computer, pressure valve inputs in missile-borne computer the measured value of each pressure-measuring-point, and missile-borne computer stores, demarcates the measured value of pressure valve.
As shown in Figure 1, 2, the flexible pipe of pressure valve 6 each passages is connected with the outlet passageway on pressure vessel respectively; The output signal of pressure valve 6 is connected with computing machine 8.
Pressure valve missile-borne calibration principle figure as shown in Figure 1.By the valve open of gas cylinder 1 self, the effect by reduction valve 2 is decompressed to the air pressure in pipeline to demarcate required atmospheric pressure value.By hand valve, gas is directed in pressure vessel 5, and reads the pressure in pressure vessel 5 by tensimeter 12.After pressure stability in pressure vessel 5, start 8 pairs of pressure valve 6 of computing machine and gather, and preserve survey record.
After test completes, measurement data is carried out to interpretation, data value as measured in pressure valve 6 and the force value on tensimeter 12 are in the error range being allowed, pressure valve 6 duties that explanation is arranged on aircraft 7 are intact, according to pressure valve 6 and the force value of tensimeter 12, obtain calibration curve, be used for making a flight test; If the force value on the data value that pressure valve 6 is measured and tensimeter 12 has exceeded error range, need the pressure valve 6 on aircraft 7 to change.
The method can be simultaneously to a plurality of pressure valve 6 gather, save data, interpretation data.To pressure valve, can meet flight test and require to provide foundation.
The just embodiment of this invention that instructions is described, various not illustrating limited essence of an invention Composition of contents, person of ordinary skill in the field read after instructions can to before described embodiment make an amendment or be out of shape, and do not deviate from essence of an invention and scope.
Claims (1)
1. hypersonic aircraft is penetrated a front pressure valve scaling method, comprises the following steps:
Step 1, high-pressure air source are that pressure vessel (5) provides source of the gas; On pressure vessel, comprise several outlet passageways;
Step 2, the flexible pipe that is arranged on each passage of each pressure valve (6) on aircraft are connected with the outlet passageway on pressure vessel respectively, and the output signal of pressure valve is connected with missile-borne computer;
Step 3, open high-pressure air source, the pressure in gaging pressure storage tank (5); After pressure stability in pressure vessel (5), start missile-borne computer (8) pressure valve (6) is gathered, and preserve survey record.
If the force value of the data value that step 4 pressure valve (6) is measured and pressure vessel (5) is in allowed error range, pressure valve (6) duty that explanation is arranged on aircraft (7) is intact, calculates the calibration curve making a flight test;
If the force value of the data value that pressure valve (6) is measured and pressure vessel (5) has exceeded error range, need to change pressure valve (6).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310460836.5A CN103542980A (en) | 2013-09-30 | 2013-09-30 | Hypersonic aircraft pre-shooting pressure valve calibration method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310460836.5A CN103542980A (en) | 2013-09-30 | 2013-09-30 | Hypersonic aircraft pre-shooting pressure valve calibration method |
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| Publication Number | Publication Date |
|---|---|
| CN103542980A true CN103542980A (en) | 2014-01-29 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201310460836.5A Pending CN103542980A (en) | 2013-09-30 | 2013-09-30 | Hypersonic aircraft pre-shooting pressure valve calibration method |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2828776Y (en) * | 2005-06-21 | 2006-10-18 | 上海威尔泰工业自动化股份有限公司 | Static pressure drift testing device of differential transmitter |
| CN102323006A (en) * | 2011-08-29 | 2012-01-18 | 际华三五零二职业装有限公司 | Portable pressure calibrator |
| CN102410904A (en) * | 2011-08-10 | 2012-04-11 | 南车石家庄车辆有限公司 | CO2 pressure reducer overall calibration method |
| US20130031949A1 (en) * | 2010-02-18 | 2013-02-07 | Snecma | Method and a device for correcting a measurement of the pressure of a gas stream flowing in an aircraft engine |
| CN103353373A (en) * | 2013-07-12 | 2013-10-16 | 中国人民解放军91663部队 | Calibration device used for multi-medium spring-tube pressure gauge |
-
2013
- 2013-09-30 CN CN201310460836.5A patent/CN103542980A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2828776Y (en) * | 2005-06-21 | 2006-10-18 | 上海威尔泰工业自动化股份有限公司 | Static pressure drift testing device of differential transmitter |
| US20130031949A1 (en) * | 2010-02-18 | 2013-02-07 | Snecma | Method and a device for correcting a measurement of the pressure of a gas stream flowing in an aircraft engine |
| CN102410904A (en) * | 2011-08-10 | 2012-04-11 | 南车石家庄车辆有限公司 | CO2 pressure reducer overall calibration method |
| CN102323006A (en) * | 2011-08-29 | 2012-01-18 | 际华三五零二职业装有限公司 | Portable pressure calibrator |
| CN103353373A (en) * | 2013-07-12 | 2013-10-16 | 中国人民解放军91663部队 | Calibration device used for multi-medium spring-tube pressure gauge |
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Application publication date: 20140129 |