CN101718627B - Terminal shock wave detecting method and device - Google Patents
Terminal shock wave detecting method and device Download PDFInfo
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- CN101718627B CN101718627B CN2009103122226A CN200910312222A CN101718627B CN 101718627 B CN101718627 B CN 101718627B CN 2009103122226 A CN2009103122226 A CN 2009103122226A CN 200910312222 A CN200910312222 A CN 200910312222A CN 101718627 B CN101718627 B CN 101718627B
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Abstract
The invention relates to a terminal shock wave detecting method and a terminal shock wave detecting device. The method comprises the following steps: 1) putting a detecting device with a detecting channel in a supersonic inlet, wherein the detecting channel is a shrinkable and expandable channel; 2) when the supersonic inlet works, detecting the pressure Pa on a throat of the detecting channel 20 and the pressure Pb on an outlet of the detecting channel; and 3) calculating and judging, namely calculating a difference value delta P between the Pb and Pa, judging the terminal shock wave is positioned on the upstream of the inlet of the detecting device if the delta P is greater than zero, judging the terminal shock wave is positioned on the downstream of the outlet of the detecting device if the delta P is smaller than zero, and judging the sonic flow is positioned at the position of the detecting device if delta P is equal to zero. The method and the device solve the technical problem that the traditional terminal shock wave detecting method and terminal shock wave detecting device have poor measuring accuracy and cannot meet the requirements on accuracy and sensitivity of a ramjet control system; and the method and the device have high accuracy, high sensitivity and high robustness, and can achieve the effect of optimal control of the ramjet control system.
Description
Technical field
The present invention relates to the method and the device of terminal shock wave position sensing in a kind of supersonic inlet, help control system to determine and control air intake duct duty.
Background technology
One of developing direction of punching engine control system is exactly optimum control.The scheme of optimum control is a lot, no matter which kind of scheme all needs to accurately measure air intake duct inlet and outlet pressure ratio or terminal shock wave position.The measurement of air intake duct inlet and outlet pressure ratio and terminal shock wave position is the difficult problem during punching engine is measured.For the detection of terminal shock wave position, be exactly existing measurement mechanism utilizes Pitot tube to measure the static pressure and the stagnation pressure of local air-flow, total judge the terminal shock wave position by static pressure.Problem with the gas velocity in the Pitot tubular type probe measurement supersonic inlet is, existing supersonic inlet interior flow field complexity, when gas velocity is near velocity of sound, precision is very low, and this interval is the threshold value of judging the terminal shock wave position for the control system particular importance because gas velocity is a velocity of sound.The precision and the sensitivity requirement of punching engine control system can not be satisfied in the terminal shock wave position that records in this way.
Summary of the invention
For measuring method that solves existing terminal shock wave and the technical matters that measurement device low precision, the precision that can't satisfy the punching engine control system and sensitivity require, the invention provides a kind of terminal shock wave detecting method and device.
Technical solution of the present invention:
A kind of terminal shock wave detecting method, its special character is: may further comprise the steps:
1) sniffer 2 with a band detection channels 20 is positioned in the supersonic inlet 1; Described detection channels 20 is the passage of shrinkage expansion shape;
2) when supersonic inlet 1 work, measure the pressure Pa at detection channels 20 venturi places and the pressure P b in detection channels exit;
3) calculate and judgement: calculate the difference DELTA P of Pb Pa, greater than zero, then terminal shock wave is positioned at the upstream of sniffer porch as Δ P; Less than zero, then terminal shock wave is positioned at the downstream in sniffer exit as Δ P; P equals zero as Δ, and then the sniffer place is a sonic flow.
Above-mentioned steps 2) also to measure the pressure P c of detection channels 20 porch in; Described step 3) should be mutually: calculate the ratio K of (Pb Pa)/Pc, greater than zero, then terminal shock wave is positioned at the upstream of sniffer porch as K; Less than zero, then terminal shock wave is positioned at the downstream in sniffer exit as K; Equal zero as K, then the sniffer place is a sonic flow.
Above-mentioned detection channels 20 is a Rafael nozzle.
A kind of terminal shock wave sniffer comprises air intake duct 1, sniffer 2, pressure guiding pipe and the sensor that links to each other with pressure guiding pipe; Described sniffer 2 is arranged in the air intake duct 1; Described sniffer 2 has detection channels 20; Described detection channels 20 is the passage of shrinkage expansion shape; The quantity of described pressure guiding pipe is at least two, all is arranged in the detection channels 20.
Above-mentioned detection channels 20 is a Rafael nozzle.
The quantity of above-mentioned pressure guiding pipe is two, and it comprises throat's pressure guiding pipe 21 that is arranged on detection channels 20 venturi places and the outlet pressure guiding pipe 22 that is arranged on detection channels 20 exits.
The quantity of above-mentioned pressure guiding pipe is three, and it comprises the inlet pressure guiding pipe that is arranged on detection channels 20 porch, the outlet pressure guiding pipe 22 that is arranged on throat's pressure guiding pipe 21 at detection channels 20 venturi places and is arranged on detection channels 20 exits.
Beneficial effect of the present invention: the present invention is a miniature pneumatic device, the device internal channel is a detection channels, by measuring the static pressure in detection channels venturi place, exit, perhaps measure the static pressure of detection channels venturi place, exit and porch, just can judge the position of terminal shock wave in the air intake duct.Shock wave detection method in the supersonic inlet that the present invention proposes has overcome Pitot tube is measured the terminal shock wave position in supersonic inlet technological deficiency, than Pitot tubular type measuring method higher precision, sensitivity and robustness are arranged, can realize the optimum control of punching engine control system.
Description of drawings
Fig. 1 is the structural representation of the sniffer of invention and the position view of terminal shock wave;
Fig. 2 is the position view of terminal shock wave of the present invention;
Wherein: the 1-supersonic inlet, the 2-sniffer, the 20-detection channels, 21-throat pressure guiding pipe, 22-exports pressure guiding pipe, the 23-pressure guiding pipe that enters the mouth, the terminal shock wave of A, B-diverse location.
Embodiment
The terminal shock wave sniffer that uses in the supersonic inlet that the present invention proposes, the position of terminal shock wave in the detectable supersonic inlet, be used to help control system to determine and control air intake duct duty, comprise air intake duct 1, sniffer 2, pressure guiding pipe and the sensor that links to each other with pressure guiding pipe; Sniffer 2 is arranged in the air intake duct 1; Sniffer 2 has detection channels 20; Detection channels 20 is the passage of shrinkage expansion shape, preferably adopts Rafael nozzle; The quantity of pressure guiding pipe can be two, comprises the throat's pressure guiding pipe 21 that is arranged on detection channels 20 venturi places and the outlet pressure guiding pipe 22 in exit; In order to improve accuracy of measurement, can also be at detection channels 20 porch inlet porting pressure guiding pipes 23; Can also increase pressure tap on this basis.
Sniffer is installed in supersonic inlet runner central authorities, measures the pressure Pa at detection channels 20 venturi places and the pressure P b in exit; When terminal shock wave has been crossed sniffer, for example at position A place, then sniffer 2 is in the subsonic flow, and at this moment, Pb-Pa is greater than zero; When terminal shock wave behind sniffer, for example at position B place, then sniffer 2 is in the supersonic airstream, this moment, Pb-Pa was less than zero, when Pb-Pa equals zero, then sniffer 2 is in the velocity of sound air-flow.
If measured the pressure P c of detection channels porch simultaneously; Then only need to calculate the value K of (Pb-Pa)/Pc, deterministic process is the same.
Claims (7)
1. terminal shock wave detecting method is characterized in that: may further comprise the steps:
1) sniffer (2) with a band detection channels (20) is positioned in the supersonic inlet (1); Described detection channels (20) is the passage of shrinkage expansion shape;
2) when supersonic inlet (1) is worked, measure the pressure Pa at detection channels (20) venturi place and the pressure P b in detection channels exit;
3) calculate and judgement: calculate the difference DELTA P of Pb-Pa, greater than zero, then terminal shock wave is positioned at the upstream of sniffer porch as Δ P; Less than zero, then terminal shock wave is positioned at the downstream in sniffer exit as Δ P; P equals zero as Δ, and then the sniffer place is a sonic flow.
2. terminal shock wave detecting method according to claim 1 is characterized in that:
Described step 2) also to measure the pressure P c of detection channels (20) porch in; Described step 3) replaces with: calculate the ratio K of (Pb-Pa)/Pc, greater than zero, then terminal shock wave is positioned at the upstream of sniffer porch as K; Less than zero, then terminal shock wave is positioned at the downstream in sniffer exit as K; Equal zero as K, then the sniffer place is a sonic flow.
3. terminal shock wave detecting method according to claim 1 and 2 is characterized in that: described detection channels (20) is a Rafael nozzle.
4. a terminal shock wave sniffer is characterized in that: comprise air intake duct (1), sniffer (2), pressure guiding pipe and the sensor that links to each other with pressure guiding pipe; Described sniffer (2) is arranged in the air intake duct (1); Described sniffer (2) has detection channels (20); Described detection channels (20) is the passage of shrinkage expansion shape; The quantity of described pressure guiding pipe is at least two, all is arranged in the detection channels (20).
5. terminal shock wave sniffer according to claim 4 is characterized in that: described detection channels (20) is a Rafael nozzle.
6. according to claim 4 or 5 described terminal shock wave sniffers, it is characterized in that: the quantity of described pressure guiding pipe is two, the outlet pressure guiding pipe (22) that it comprises the throat's pressure guiding pipe (21) that is arranged on detection channels (20) venturi place and is arranged on detection channels (20) exit.
7. according to claim 4 or 5 described terminal shock wave sniffers, it is characterized in that: the quantity of described pressure guiding pipe is three, and it comprises the inlet pressure guiding pipe that is arranged on detection channels (20) porch, the outlet pressure guiding pipe (22) that is arranged on throat's pressure guiding pipe (21) at detection channels (20) venturi place and is arranged on detection channels (20) exit.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009103122226A CN101718627B (en) | 2009-12-24 | 2009-12-24 | Terminal shock wave detecting method and device |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009103122226A CN101718627B (en) | 2009-12-24 | 2009-12-24 | Terminal shock wave detecting method and device |
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| Publication Number | Publication Date |
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| CN101718627A CN101718627A (en) | 2010-06-02 |
| CN101718627B true CN101718627B (en) | 2011-06-01 |
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| CN2009103122226A Active CN101718627B (en) | 2009-12-24 | 2009-12-24 | Terminal shock wave detecting method and device |
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Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105841882B (en) * | 2016-03-17 | 2018-08-03 | 中国人民解放军国防科学技术大学 | Shock train leading edge detection device in a kind of distance piece |
| CN107576446B (en) * | 2017-08-02 | 2020-10-20 | 南京航空航天大学 | Active detection method for front edge of shock wave string of isolation section of scramjet engine |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4186590A (en) * | 1978-05-02 | 1980-02-05 | Egorov Alexandr F | Method of determining the quantitative content of gaseous or vaporous impurity in a gas mixture and a device for accomplishing same |
| SU1474489A1 (en) * | 1987-03-16 | 1989-04-23 | Уфимский авиационный институт им.Серго Орджоникидзе | Probe for locating a shock wave |
| CN1384794A (en) * | 1999-08-25 | 2002-12-11 | 波音公司 | Supersonic external-compression diffuser and method for designing same |
-
2009
- 2009-12-24 CN CN2009103122226A patent/CN101718627B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4186590A (en) * | 1978-05-02 | 1980-02-05 | Egorov Alexandr F | Method of determining the quantitative content of gaseous or vaporous impurity in a gas mixture and a device for accomplishing same |
| SU1474489A1 (en) * | 1987-03-16 | 1989-04-23 | Уфимский авиационный институт им.Серго Орджоникидзе | Probe for locating a shock wave |
| CN1384794A (en) * | 1999-08-25 | 2002-12-11 | 波音公司 | Supersonic external-compression diffuser and method for designing same |
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| CN101718627A (en) | 2010-06-02 |
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