CN106507935B - A kind of airborne scramjet engine pressure-measuring system - Google Patents
A kind of airborne scramjet engine pressure-measuring systemInfo
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- CN106507935B CN106507935B CN201218008313.3A CN201218008313A CN106507935B CN 106507935 B CN106507935 B CN 106507935B CN 201218008313 A CN201218008313 A CN 201218008313A CN 106507935 B CN106507935 B CN 106507935B
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Abstract
The invention provides a kind of airborne scramjet engine pressure-measuring system, mainly includes electric pressure scaner, pressure acquisition control module, back pressure apparatus and absolute pressure sensor；Back pressure apparatus are that electric pressure scaner 7 and 8 provides reference pressure；Absolute pressure sensor gathers the pressure of back pressure apparatus, and electric pressure scaner outputs signal to pressure acquisition control module；The back pressure apparatus are by absolute pressure sensor is spigot joint, back pressure apparatus cylinder and impermeable steel pipe are constituted；A local atmospheric pressure is sealed inside back pressure apparatus cylinder or is evacuated；The spigot joint one end of absolute pressure sensor connects back pressure apparatus cylinder, and the other end connects absolute pressure sensor；Stainless steel tube one end connects back pressure apparatus cylinder, and the other end is connected to electric pressure scaner by pressure measurement pipeline.Small volume of the present invention, lightweight, high precision are favorably improved payload proportion in Flight Vehicle Structure, provide a kind of effective pressure measxurement means for hypersonic autonomous flight.
Description
Technical field
The present invention relates to space telemetry remote sensing fields, especially, it is related to a kind of airborne scramjet engine pressure measxurement system
System.
Background technology
Space industry be mainly used in the gesture stability of spaceship and aerospace craft, high-speed aircraft, jet engine,
The measurement of the heat-resisting cavity such as rocket, satellite and surface each several part pressure, its performance is by measurement range, measurement accuracy, non-thread
Property and operating temperature are determined.
Space industry working environment is more severe, generally includes thermal etching, refers mainly to hot environment；Mechanical erosion, mainly
Refer to high load capacity, vibration and impact etc.；Chemical erosion, refers mainly to environment of corrosive medium etc..
With developing rapidly for e measurement technology, high-precision hydrodynamics test proposes higher want to pressure-measuring system
Ask, it is desirable to which pressure-measuring system has good dynamic characteristic, the acute variation that internal engine pressures can be obtained in real time becomes
Gesture.In order to not influence flow field state, measurement accuracy is improved, in addition it is also necessary to which pressure-measuring system has minimum profile, can
Engine wall multi-path pressure-measuring-point Simultaneous Pressure is acquired simultaneously.
And apply the pressure-measuring system volume in space industry universal excessively huge at present, be unfavorable for it is integrated, or
The demand of Multipoint synchronous measurement can not be met.
The content of the invention
The technical problem to be solved in the present invention is to provide a kind of airborne scramjet engine pressure-measuring system, the system body
Product is small, lightweight, is favorably improved payload proportion in Flight Vehicle Structure, is that hypersonic autonomous flight is carried
For a kind of effective pressure measxurement means.
A kind of airborne scramjet engine pressure-measuring system of the present invention, is mainly adopted including electric pressure scaner, pressure
Collect control module 6, back pressure apparatus 4 and absolute pressure sensor 5；Back pressure apparatus 4 provides reference pressure for electric pressure scaner；
Absolute pressure sensor 5 gathers the pressure of back pressure apparatus 4, and electric pressure scaner outputs signal to pressure acquisition control module 6；
The back pressure apparatus 4 connects mouth 1, back pressure apparatus cylinder 2 and connecting tube 3 by absolute pressure sensor and constituted；In back pressure apparatus cylinder 2
Face seals a local atmospheric pressure or is evacuated；Absolute pressure sensor connects the one end of mouth 1 connection back pressure apparatus cylinder 2, and the other end connects
Connect absolute pressure sensor 5；The one end of connecting tube 3 connection back pressure apparatus cylinder 2, the other end is connected to electron pressure by pressure measurement pipeline
Scan valve.
Further, the pressure acquisition control module 6 is by function moulds such as data acquisition, scan module control and data communications
Block is constituted；
The data acquisition function module completes the shaping filter and A/D conversion numerals of electric pressure scaner analog signal
Change and be input to the functions such as memory；
The scan module control function module exports the control signal to electric pressure scaner, collection electricity according to sequential
The pressure data of sub- each passage of pressure scanning valve；
The data communication facility module completes the formation of data frame and baud rate on request carries out data transmission to serial ports.
It is preferred that, the electric pressure scaner is ESP-64HD.
The advantage of the invention is that：System compact, lightweight, Multipoint synchronous measurement, improve payload institute accounting
Weight, while pressure measurement accuracy height (≤0.5%), is able to take low latitude stage separation, high dynamic radome fairing and separates and superb
The examination of velocity of sound autonomous flight environment.
Brief description of the drawings
Pressure-measuring system schematic diagram integrated Fig. 1.
Fig. 2 back pressure apparatus structural representations.
Fig. 3 pressure acquisition control module functions realize block diagram.
Embodiment：
The present invention is explained in detail below in conjunction with the accompanying drawings.
The system mainly includes the first electric pressure scaner 7, the second electric pressure scaner 8, pressure acquisition control mould
Block 6, back pressure apparatus 4 and absolute pressure sensor 5, structural representation is as shown in Figure 1.The He of first electric pressure scaner 7
Second electric pressure scaner 8 gathers engine inlets and the flowpath pressure of combustion chamber respectively；Back pressure apparatus 4 is electronics
Pressure scanning valve provides reference pressure；Absolute pressure sensor 5 gathers the pressure of back pressure apparatus 4, and all collection signals enter
Pressure acquisition control module 6, carries out signal transacting.
Electric pressure scaner 7 and 8 is multi-channel high-accuracy miniature electronic pressure scanning valve, such as ESP-64HD, by 64
Individual silicon piezoresistance type pressure sensor array and a temperature sensor composition, with design and environmental pressure amendment
Function.
Back pressure apparatus 4 is mainly that electric pressure scaner 7 and 8 provides reference pressure, reduces ambient pressure variations to measurement
The influence of data, the influence that back pressure apparatus 4 is evacuated rear environmental change can minimize, structural representation such as Fig. 2
It is shown, mouth 1, back pressure apparatus cylinder 2 and impermeable steel pipe 3 are mainly connect by absolute pressure sensor and constituted.Wherein back pressure apparatus cylinder 2
The inside seals a local atmospheric pressure or is evacuated；Absolute pressure sensor connects the one end of mouth 1 connection back pressure apparatus cylinder 2, another
End connection absolute pressure sensor 5, for measuring the pressure of gas in back pressure apparatus cylinder；The one end of stainless steel tube 3 connection back pressure dress
Cylinder 2 is put, the other end is connected to electric pressure scaner 7 and 8, electron pressure scanning valve 7 and 8 by pressure measurement pipeline
Reference pressure is provided.Under 1 local atmosphere pressure state, when environment temperature changes to 70 DEG C by 20 DEG C, pressure
Change turns to 17%, about 17kPa, and very little is influenceed on acquisition precision.Gone to correct each pressure with the data of absolute pressure transducer
Data, can obtain accurate pressure.To simplify system, reduction operation difficulty, back pressure apparatus 4 is typically using sealing one
The measure of local atmospheric pressure.
If being evacuated, when environment temperature changes to 70 DEG C by 20 DEG C, pressure change is substantially zeroed, and acquisition precision is high,
But be evacuated troublesome poeration.
Absolute pressure sensor 5 is connected with back pressure apparatus 4, in real time the amendment each channel pressure data of electric pressure scaner 7 and 8,
Improve measurement accuracy.
Pressure acquisition control module 6 is made using the disposable Cheng Mo of aluminum alloy materials, with lightweight, mechanical strength
High advantage.The size of pressure acquisition control module 6 is 114 × 80 × 38mm, and weight is 0.8kg, small volume, weight
Gently.
Pressure acquisition control module 6 is by functional modules such as data acquisition, scan module control, data processing and data communications
Composition, it is as shown in Figure 3 that it implements block diagram.
Data acquisition function module completes the shaping filter and A/D conversion numerals of the analog signal of electric pressure scaner 7 and 8
Change and be input to the functions such as memory；
Filtering selection voltage controlled voltage source type VCVS type active filters.Whole bandpass filter is respectively by two-stage second order Bart
Butterworth (Butterworth) low pass and high-pass filter cascade composition.
A/D converter selection MAX1166 is 16 low-power consumption moulds of successive approximation of MAXIM companies of U.S. production
Band 4.096V Precision references source in number converter, the converter, while having parallel data output interface.
Scan module control function module exports the control signal to electric pressure scaner 7 and 8, collection according to sequential
The pressure data of each passage of electric pressure scaner 7 and 8；
A series of clock signal, including digital signal processor clock are obtained using a master clock 10M frequency dividing
10MHz, A/D work clock 10MHz, sampling clock 50KHz and refresh clock 20Hz.
Data processing function module completes the functions such as data temperature compensation, environmental pressure amendment；
There is temperature sensor inside electric pressure scaner, according to same pressure signal corresponding pressure at different temperature
Force data is demarcated, and the pressure data measured is multiplied by corresponding calibration coefficient, more accurate pressure data can be obtained.
The pressure acquisition data of electric pressure scaner remove back pressure apparatus 4 and provide reference pressure data, can obtain accurately
Pressure.
Data communication facility module completes the formation of data frame and baud rate on request carries out data transmission to serial ports.Pass through
RS-422 interfaces and the sampler and coder of telemetry system carry out serial communication, and the pressure data of collection is delivered into ground telemetering station.
Because the power supply that hypersonic aircraft is provided to pressure acquisition control module 6 is DC27 ± 4V, one is utilized
The power supply of DC/DC power transfer module electron pressure scannings valve 7 and 8 offers ± 12V ,+15V and+5V, wherein
+ 15V power supplys are used for conventional pressure sensor, and+5V power supply voltage supply power and temperature sensor are used.
The present invention can in less volume integrated pressure measuring system, improve payload proportion, it is lightweight,
Realize Multipoint synchronous measurement, while have higher pressure measurement accuracy (≤0.5%), be able to take low latitude stage separation,
High dynamic pressure radome fairing separates the examination with hypersonic autonomous flight environmental condition.
The preferred embodiments of the present invention are the foregoing is only, are not intended to limit the invention, for the technology of this area
For personnel, the present invention can have various modifications and variations.Within the spirit and principles of the invention, that is made is any
Modification, equivalent, improvement etc., should be included within the scope of the present invention.
Claims (3)
1. a kind of airborne scramjet engine pressure-measuring system, mainly including electric pressure scaner (7,8), pressure
Acquisition control module (6), back pressure apparatus (4) and absolute pressure sensor (5)；Back pressure apparatus (4) is electric pressure scaner (7,8)
Reference pressure is provided；The pressure of absolute pressure sensor (5) collection back pressure apparatus (4), the output letter of electric pressure scaner (7,8)
Number to pressure acquisition control module (6)；
The back pressure apparatus (4) connects mouth (1), back pressure apparatus cylinder (2) and connecting tube (3) by absolute pressure sensor and constituted；Back pressure apparatus
A local atmospheric pressure is sealed inside cylinder (2) or is evacuated；Absolute pressure sensor connects mouth (1) one end connection back pressure apparatus cylinder (2),
Other end connection absolute pressure sensor (5)；Connecting tube (3) one end connection back pressure apparatus cylinder (2), the other end is connected by pressure measurement pipeline
It is connected to electric pressure scaner (7,8).
2. a kind of airborne scramjet engine pressure-measuring system as claimed in claim 1, it is characterised in that the pressure
Power acquisition control module (6) is by data acquisition, scan module control, data processing function module and data communication function module
Composition；
The data acquisition function module completes the shaping filter and A/D conversions of electric pressure scaner (7,8) analog signal
Digitize and be input to memory function；
The data processing function module completes data temperature compensation, environmental pressure debugging functions；
The scan module control function module exports the control signal to electric pressure scaner (7,8) according to sequential,
Gather the pressure data of electric pressure scaner (7,8) each passage；
The data communication facility module completes the formation of data frame and baud rate on request carries out data transmission to serial ports.
3. a kind of airborne scramjet engine pressure-measuring system as claimed in claim 1, it is characterised in that the electricity
Sub- pressure scanning valve (7,8) is ESP-64HD.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201218008313.3A CN106507935B (en) | 2012-12-31 | 2012-12-31 | A kind of airborne scramjet engine pressure-measuring system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201218008313.3A CN106507935B (en) | 2012-12-31 | 2012-12-31 | A kind of airborne scramjet engine pressure-measuring system |
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| Publication Number | Publication Date |
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| CN106507935B true CN106507935B (en) | 2014-04-09 |
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ID=58358321
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| CN201218008313.3A Active CN106507935B (en) | 2012-12-31 | 2012-12-31 | A kind of airborne scramjet engine pressure-measuring system |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109297674A (en) * | 2018-11-08 | 2019-02-01 | 中国航空工业集团公司哈尔滨空气动力研究所 | Pilot system is continuously measured based on pressure scanning valve model surface pressure |
| CN109813520A (en) * | 2019-03-25 | 2019-05-28 | 中国人民解放军国防科技大学 | Flight pneumatic data acquisition system |
| CN112461489A (en) * | 2020-11-25 | 2021-03-09 | 中国空气动力研究与发展中心高速空气动力研究所 | Electronic scanning valve reference pressure control system for low-pressure measurement and application method |
| CN114791330A (en) * | 2022-06-20 | 2022-07-26 | 中国空气动力研究与发展中心低速空气动力研究所 | Multichannel pressure scanning valve system |
| CN116413039A (en) * | 2023-03-29 | 2023-07-11 | 中国航发沈阳发动机研究所 | Sensor signal processing method for ramjet engine |
-
2012
- 2012-12-31 CN CN201218008313.3A patent/CN106507935B/en active Active
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109297674A (en) * | 2018-11-08 | 2019-02-01 | 中国航空工业集团公司哈尔滨空气动力研究所 | Pilot system is continuously measured based on pressure scanning valve model surface pressure |
| CN109813520A (en) * | 2019-03-25 | 2019-05-28 | 中国人民解放军国防科技大学 | Flight pneumatic data acquisition system |
| CN112461489A (en) * | 2020-11-25 | 2021-03-09 | 中国空气动力研究与发展中心高速空气动力研究所 | Electronic scanning valve reference pressure control system for low-pressure measurement and application method |
| CN112461489B (en) * | 2020-11-25 | 2022-09-23 | 中国空气动力研究与发展中心高速空气动力研究所 | Electronic scanning valve reference pressure control system for low-pressure measurement and application method |
| CN114791330A (en) * | 2022-06-20 | 2022-07-26 | 中国空气动力研究与发展中心低速空气动力研究所 | Multichannel pressure scanning valve system |
| CN116413039A (en) * | 2023-03-29 | 2023-07-11 | 中国航发沈阳发动机研究所 | Sensor signal processing method for ramjet engine |
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