CN203502168U - Hypersonic aerocraft pressure valve calibration system before transmission - Google Patents
Hypersonic aerocraft pressure valve calibration system before transmission Download PDFInfo
- Publication number
- CN203502168U CN203502168U CN201320615794.3U CN201320615794U CN203502168U CN 203502168 U CN203502168 U CN 203502168U CN 201320615794 U CN201320615794 U CN 201320615794U CN 203502168 U CN203502168 U CN 203502168U
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- Prior art keywords
- pressure
- valve
- pressure valve
- storage tank
- pressure vessel
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Lifetime
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Abstract
The utility model relates to a hypersonic aerocraft pressure valve calibration system before transmission. The hypersonic aerocraft pressure valve comprises a pressure storage tank provided with a plurality of mutually communicated air outlet channels; a high-pressure air cylinder is connected with an inlet of the pressure storage tank through a pressure reducing valve, a hand valve and an air inlet pipeline so as to provide an air source for the pressure storage tank; a pressure meter is connected to the pressure storage tank and measures the pressure of air inside the pressure storage tank; flexible pipe of channels of a pressure valve are connected with the air outlet channels respectively; output signals of the pressure valve are connected with a missile-borne computer so as to carry out storage and calibration on a measurement value of the pressure valve. The system provided by the utility model carries out calibration before transmission on a plurality of pressure valves installed on a hypersonic aerocraft, and ensures the pressure valves on the aerocraft to be reliable and accurate.
Description
Technical field
The utility model relates to hypersonic aircraft fields of measurement, is specifically related to hypersonic aircraft and penetrates front pressure valve demarcation.
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 system that carry-on pressure valve is demarcated.
Utility model content
The problem that the utility model exists for prior art, has proposed a kind of hypersonic aircraft and has penetrated front pressure valve calibration system, and a plurality of pressure valve that are arranged on hypersonic aircraft are tried to front demarcation, guarantees that carry-on pressure valve is reliable, accurate.
Hypersonic aircraft is penetrated a front pressure valve calibration system, it is characterized in that comprising pressure vessel, comprises the outlet passageway that several communicate on pressure vessel; Gas cylinder is connected with the entrance of pressure vessel by reduction valve, hand valve, air inlet pipeline, for pressure vessel provides source of the gas; Tensimeter is connected on pressure vessel, the gaseous tension in gaging pressure storage tank; The flexible pipe of each passage of pressure valve is connected with outlet passageway respectively; The output signal of pressure valve is connected with missile-borne computer, and the measured value of pressure valve is stored, demarcated.
The utility model 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: the utility model pressure valve calibration principle figure;
Fig. 2: pressure vessel connection diagram in the utility model;
Embodiment
Below in conjunction with accompanying drawing, the utility model is 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.
This system 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 utility model that instructions is described, various not illustrating is construed as limiting the flesh and blood of utility model, 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 and the scope of utility model.
Claims (1)
1. hypersonic aircraft is penetrated a front pressure valve calibration system, it is characterized in that comprising pressure vessel (5), comprises the outlet passageway that several communicate on pressure vessel; Gas cylinder (1) is connected with the entrance of pressure vessel (5) by reduction valve (2), hand valve (3), air inlet pipeline (11), for pressure vessel provides source of the gas; It is upper that tensimeter (12) is connected in pressure vessel (5), the gaseous tension in gaging pressure storage tank; The flexible pipe of each passage of pressure valve (6) is connected with outlet passageway respectively; The output signal of pressure valve (6) is connected with missile-borne computer (8), and the measured value of pressure valve is stored, demarcated.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320615794.3U CN203502168U (en) | 2013-09-30 | 2013-09-30 | Hypersonic aerocraft pressure valve calibration system before transmission |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320615794.3U CN203502168U (en) | 2013-09-30 | 2013-09-30 | Hypersonic aerocraft pressure valve calibration system before transmission |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203502168U true CN203502168U (en) | 2014-03-26 |
Family
ID=50333139
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201320615794.3U Expired - Lifetime CN203502168U (en) | 2013-09-30 | 2013-09-30 | Hypersonic aerocraft pressure valve calibration system before transmission |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203502168U (en) |
-
2013
- 2013-09-30 CN CN201320615794.3U patent/CN203502168U/en not_active Expired - Lifetime
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