CN114508446B - Method for controlling drag reduction of punching Cheng Zhidao bullet - Google Patents
Method for controlling drag reduction of punching Cheng Zhidao bullet Download PDFInfo
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- CN114508446B CN114508446B CN202111653971.2A CN202111653971A CN114508446B CN 114508446 B CN114508446 B CN 114508446B CN 202111653971 A CN202111653971 A CN 202111653971A CN 114508446 B CN114508446 B CN 114508446B
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- engine
- combustion chamber
- period
- chamber pressure
- average value
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
- F02K7/10—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
- F02C7/057—Control or regulation
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Control Of Vehicle Engines Or Engines For Specific Uses (AREA)
- Combined Controls Of Internal Combustion Engines (AREA)
Abstract
The invention discloses a method for controlling drag reduction of a punch Cheng Zhidao bullet, which comprises the following steps: in any period of a set duration, calculating the final average value P of the combustion chamber pressure in the N periods in the forefront of the period 1 The method comprises the steps of carrying out a first treatment on the surface of the At the same time, calculating the final average value P of the combustion chamber pressure in the last N continuous periods of the period 2 The method comprises the steps of carrying out a first treatment on the surface of the According to P 1 And P 2 The logic relation of the difference value and the threshold value is used for judging whether the engine in the ram extended-range missile is flameout or not; if P 1 And P 2 If the difference value of the two is smaller than the threshold value, judging that the engine is flameout to indicate that the operation of the engine is finished, outputting an instruction of the operation of an execution mechanism, and closing an air inlet channel of the engine after the operation of the execution mechanism; if P 1 And P 2 If the difference value of (2) is larger than or equal to the threshold value, judging that the engine is not shut down, indicating that the work of the engine is not finished, and the air inlet channel of the engine cannot be closed. The invention can reduce the flight resistance of the projectile body and increase the range.
Description
Technical Field
The invention belongs to the technical field of control of stamping range-extending shells, and particularly relates to a method for controlling drag reduction of stamping range-extending Cheng Zhidao shells.
Background
Compared with the conventional cannon, the stamping range-extending cannon has the greatest advantage that the stamping engine is adopted as a power system, which can lead the range of the stamping range-extending cannon to reach 90 km or even higher, such as more than 100 km, which is equivalent to twice the maximum effective range of the conventional self-propelled cannon, and has certain advantages in range. The ramjet engine adopts an air suction engine, when the speed of an aircraft reaches a higher level, air entering the engine generates enough compression effect, and the air can be directly mixed with fuel for combustion to generate thrust, but if the engine works, the resistance of an elastomer can be increased due to improper air inlet treatment of an air inlet channel, and the range of the elastomer is influenced.
Disclosure of Invention
In view of this, the invention provides a method for drag reduction control of a ram-increased Cheng Zhidao projectile, which can reduce the flight resistance of the projectile and increase the range.
The invention is realized by the following technical scheme:
a method for controlling drag reduction of a punch Cheng Zhidao bullet comprises the following specific steps:
step one, monitoring a measured value of the pressure of a combustion chamber in real time, and calculating an average value of the pressure of the combustion chamber in one period;
step two, in any period with set duration, calculating the final average value P of the combustion chamber pressure in N periods in the forefront of the period 1 The method comprises the steps of carrying out a first treatment on the surface of the At the same time, calculating the final average value P of the combustion chamber pressure in the last N continuous periods of the period 2 ；
Step three, according to P 1 And P 2 The logic relation of the difference value and the threshold value is used for judging whether the engine in the ram extended-range missile is flameout or not;
if P 1 And P 2 If the difference value of the two is smaller than the threshold value, judging that the engine is flameout to indicate that the operation of the engine is finished, outputting an instruction of the operation of an execution mechanism, and closing an air inlet channel of the engine after the operation of the execution mechanism;
if P 1 And P 2 If the difference value of (2) is larger than or equal to the threshold value, judging that the engine is not shut down, indicating that the work of the engine is not finished, and the air inlet channel of the engine cannot be closed.
Further, the executing mechanism is arranged at the inlet end of the air inlet channel; when the driving executing mechanism does not work, the air inlet channel of the engine is not closed, and the engine can work normally; when the actuating mechanism is driven to work, the air inlet channel of the engine can be closed.
Further, the actuating mechanism is an annular plate.
Further, let 10ms be a cycle, continuously collect 12 combustion chamber pressure measurements in each cycle, remove the maximum and minimum values, and average the remaining 10 data to obtain the combustion chamber pressure average value in the current cycle.
Further, the set duration is 850ms; n=5;
combustion chamber pressure final average value P 1 The calculation method of (2) is as follows: in any period of 850ms, calculating the average value of the combustion chamber pressure in the first five continuous periods of the period, and carrying out average processing on the average value of the combustion chamber pressure in the five periods to obtain P 1 ；
Combustion chamber pressure final average value P 2 The calculation method of (2) is as follows: calculating the average value of the combustion chamber pressure in the last five continuous periods of the period, and carrying out average treatment on the average value of the combustion chamber pressure in the five periods to obtain P 2 。
Further, the threshold value is set to 0.77.
The beneficial effects are that:
(1) According to the real-time monitoring of the pressure of the combustion chamber, when the pressure meets the judging logic of flameout of the engine, the invention outputs the working instruction of the actuating mechanism, after the actuating mechanism works, the air inlet channel of the engine can be closed, the flight resistance after the working of the engine of the punching extended-range shell is reduced, and the range of the punching extended-range shell is increased.
(2) The invention is characterized in that an executing mechanism is arranged at the inlet end of an air inlet channel; when the driving executing mechanism does not work, the air inlet channel of the engine is not closed, and the engine can work normally; when the actuating mechanism is driven to work, the air inlet channel of the engine can be closed, so that the resistance of the pressure-increasing range-increasing missile is prevented from being influenced by the air inlet of the air inlet channel; thus, the present invention converts the method of drag reduction control into a method of actuator drive control.
Drawings
FIG. 1 is a state diagram of an actuator when not in operation;
FIG. 2 is a state diagram of the actuator in operation;
FIG. 3 is a flow chart of the present invention;
wherein, 1-actuating mechanism, 2-intake duct.
Detailed Description
The invention will now be described in detail by way of example with reference to the accompanying drawings.
The embodiment provides a method for controlling drag reduction of a punch increase Cheng Zhidao bullet, referring to fig. 1, an actuating mechanism 1, such as an annular plate, is arranged at the inlet end of an air inlet channel 2; when the driving executing mechanism does not work, the air inlet channel 2 of the engine is not closed, and the engine can work normally; referring to fig. 2, when the actuating mechanism is driven to work, the air inlet channel 2 of the engine can be closed, so that the resistance of the pressure-increasing range-increasing missile is prevented from being influenced by the air inlet of the air inlet channel 2; therefore, the present embodiment converts the method of drag reduction control into a method of driving control of the actuator 1;
referring to fig. 3, the method comprises the following specific steps:
step one, monitoring a measured value P4 of the combustion chamber pressure in real time, taking 10ms as a period, continuously collecting 12 measured values of the combustion chamber pressure in each period, removing the maximum value and the minimum value, averaging the rest 10 data, and taking the obtained data as a combustion chamber pressure average value P4 of the current period i ；
Step two, in any period of 850ms, calculating the combustion chamber pressure average value P4 in the first five continuous periods of the period i And for combustion chamber pressure average value P4 in the five periods i Averaging to obtain final average value P of combustion chamber pressure 1 The method comprises the steps of carrying out a first treatment on the surface of the At the same time, calculating the average value P4 of the combustion chamber pressure in the last five continuous periods of the period i And for combustion chamber pressure average value P4 in the five periods i Averaging to obtain final average value P of combustion chamber pressure 2 ；
Step three, according to P 1 And P 2 The logic relation of the difference value and the threshold value is used for judging whether the engine in the ram extended-range missile is flameout or not;
if P 1 And P 2 If the difference value of the two is smaller than the threshold value, judging that the engine is flameout and indicating that the operation of the engine is finished, and outputting an instruction of the operation of the execution mechanism 1 at the moment, wherein after the operation of the execution mechanism 1, the air inlet channel 2 of the engine can be closed to prevent the resistance of an air inlet channel 2 pressure-increasing and range-increasing missile from influencing the range of the missile;
if P 1 And P 2 If the difference value of (2) is greater than or equal to the threshold value, the engine is judged not to be flameout, and the operation of the engine is not finished, so that the air inlet channel 2 of the engine cannot be closed.
The threshold value of this embodiment is set to 0.77.
In summary, the above embodiments are only preferred embodiments of the present invention, and are not intended to limit the scope of the present invention. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (5)
1. The method for controlling drag reduction of the punch increase Cheng Zhidao bullet is characterized by comprising the following specific steps of:
step one, monitoring a measured value of the pressure of a combustion chamber in real time, and calculating an average value of the pressure of the combustion chamber in one period;
step two, in any period with set duration, calculating the final average value of the combustion chamber pressure in N periods in the forefront of the period
The method comprises the steps of carrying out a first treatment on the surface of the At the same time, the final average value +.about.combustion chamber pressure in the last N consecutive periods of the period is calculated>
；
Step three, according to
And->
The logic relation of the difference value and the threshold value is used for judging whether the engine in the ram extended-range missile is flameout or not;
if it is
And->
If the difference value of the two is smaller than the threshold value, judging that the engine is flameout to indicate that the operation of the engine is finished, outputting an instruction of the operation of an execution mechanism, and closing an air inlet channel of the engine after the operation of the execution mechanism;
if it is
And->
If the difference value of the two is larger than or equal to the threshold value, judging that the engine is not flameout, indicating that the work of the engine is not finished and the air inlet channel of the engine cannot be closed;
the actuating mechanism is arranged at the inlet end of the air inlet channel; when the driving executing mechanism does not work, the air inlet channel of the engine is not closed, and the engine can work normally; when the actuating mechanism is driven to work, the air inlet channel of the engine can be closed.
2. The method of ram up Cheng Zhidao spring drag reduction control of claim 1, wherein said actuator is an annular plate.
3. A method of ram up Cheng Zhidao spring drag reduction control as claimed in claim 1 or 2 wherein 10ms is taken as a period, 12 measurements of the combustion chamber pressure are continuously taken in each period, the maximum and minimum of which are removed, and the remaining 10 data are averaged to calculate the average of the combustion chamber pressure in the current period.
4. A method of ram increasing Cheng Zhidao spring drag reduction control as claimed in claim 1 or 2, wherein the set time period is 850ms; n=5;
final average value of combustion chamber pressure
The calculation method of (2) is as follows: at any one period of 850ms, the time is calculatedThe average value of the combustion chamber pressure in the first five continuous periods of the section is averaged to obtain +.>
；
Final average value of combustion chamber pressure
The calculation method of (2) is as follows: calculating the average value of the combustion chamber pressure in the last five continuous periods of the period, and carrying out average treatment on the average value of the combustion chamber pressure in the five periods to obtain +.>
。
5. A method of ram up Cheng Zhidao spring drag reduction control as claimed in claim 1 or 2, wherein said threshold value is set to 0.77.
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| CN202111653971.2A CN114508446B (en) | 2021-12-30 | 2021-12-30 | Method for controlling drag reduction of punching Cheng Zhidao bullet |
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| CN202111653971.2A CN114508446B (en) | 2021-12-30 | 2021-12-30 | Method for controlling drag reduction of punching Cheng Zhidao bullet |
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| CN114508446A CN114508446A (en) | 2022-05-17 |
| CN114508446B true CN114508446B (en) | 2023-06-27 |
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Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111594348A (en) * | 2020-05-01 | 2020-08-28 | 西北工业大学 | Starting control method for rocket-based combined cycle engine air inlet |
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| FR2840029B1 (en) * | 2002-05-27 | 2004-08-13 | Mbdam | SHUTTERING SYSTEM FOR A PITCH ORIFICE, ESPECIALLY FOR AN ORIFICE OF AN AIR INPUT ROUTE IN THE COMBUSTION CHAMBER OF A STATOREACTOR |
| US6820411B2 (en) * | 2002-09-13 | 2004-11-23 | The Boeing Company | Compact, lightweight high-performance lift thruster incorporating swirl-augmented oxidizer/fuel injection, mixing and combustion |
| JP4134318B2 (en) * | 2005-06-10 | 2008-08-20 | 防衛省技術研究本部長 | Fuel flow control device for flying vehicle and its ram rocket engine |
| CN101017076A (en) * | 2006-12-05 | 2007-08-15 | 周林 | Stamping range increasing ultra-remote guided projectile |
| EP1990521A1 (en) * | 2007-05-09 | 2008-11-12 | Siemens Aktiengesellschaft | Pressure dynamics reduction within a gas turbine engine |
| RU2578012C1 (en) * | 2015-03-23 | 2016-03-20 | Открытое акционерное общество "Авиадвигатель" | Method for determining extinction turbomachine combustion chamber |
| CN104950070A (en) * | 2015-07-14 | 2015-09-30 | 西安近代化学研究所 | Solid propellant flameout critical pressure reduction rate testing method |
| FR3080912B1 (en) * | 2018-05-02 | 2020-04-03 | Nexter Munitions | PROJECTILE POWERED BY STATOREACTOR |
| CN109931185B (en) * | 2019-03-20 | 2021-02-19 | 西北工业大学 | Integral detonation ramjet engine |
| CN112228246B (en) * | 2020-10-30 | 2021-11-02 | 华中科技大学 | Rocket-based detonation and stamping combined cycle engine and use method and application thereof |
| CN112483256B (en) * | 2020-12-06 | 2022-08-23 | 西安长峰机电研究所 | Automatic opening and closing device for air inlet of ramjet engine |
| CN113236443B (en) * | 2021-04-25 | 2022-02-01 | 上海新力动力设备研究所 | Self-tuning method for pressure feedback control parameter of variable thrust engine |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111594348A (en) * | 2020-05-01 | 2020-08-28 | 西北工业大学 | Starting control method for rocket-based combined cycle engine air inlet |
Non-Patent Citations (1)
| Title |
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| 周宏奎.二元高超声速进气道外压段阻力的理论分析及初步减阻研究.长春理工大学学报(自然科学版).2010,第33卷(第3期),第20-25页. * |
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