CN101985904B - Control method of detonation pipe for high-frequency pulse detonation engine - Google Patents
Control method of detonation pipe for high-frequency pulse detonation engine Download PDFInfo
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- CN101985904B CN101985904B CN 201010527539 CN201010527539A CN101985904B CN 101985904 B CN101985904 B CN 101985904B CN 201010527539 CN201010527539 CN 201010527539 CN 201010527539 A CN201010527539 A CN 201010527539A CN 101985904 B CN101985904 B CN 101985904B
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- solenoid valve
- inlet solenoid
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- igniter
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- 238000005474 detonation Methods 0.000 title claims abstract description 69
- 238000000034 method Methods 0.000 title claims abstract description 12
- 239000000446 fuel Substances 0.000 claims abstract description 35
- 239000007800 oxidant agent Substances 0.000 claims abstract description 29
- 230000001590 oxidative effect Effects 0.000 claims abstract description 26
- 238000002955 isolation Methods 0.000 claims description 37
- 239000007789 gas Substances 0.000 description 28
- 230000008676 import Effects 0.000 description 25
- 239000003350 kerosene Substances 0.000 description 5
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 description 4
- MYMOFIZGZYHOMD-UHFFFAOYSA-N Dioxygen Chemical group O=O MYMOFIZGZYHOMD-UHFFFAOYSA-N 0.000 description 3
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 2
- 238000011161 development Methods 0.000 description 2
- 230000018109 developmental process Effects 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 229910052757 nitrogen Inorganic materials 0.000 description 2
- 239000001301 oxygen Substances 0.000 description 2
- 229910052760 oxygen Inorganic materials 0.000 description 2
- 239000003380 propellant Substances 0.000 description 2
- 238000011160 research Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 229910001882 dioxygen Inorganic materials 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 238000006213 oxygenation reaction Methods 0.000 description 1
- 230000010349 pulsation Effects 0.000 description 1
- 210000000664 rectum Anatomy 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
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Abstract
The invention provides a detonation pipe for a high-frequency pulse detonation engine and a control method thereof. The detonation pipe is characterized in that two fuel inlet solenoid valves are connected at a fuel inlet of the detonation pipe; two oxidant inlet solenoid valves are connected at an oxidant inlet of the detonation pipe; two insolated gas inlet solenoid valves are connected at an insolated gas inlet of the detonation pipe; and two igniters are mounted on the detonation pipe, wherein in one control period, a set of the solenoid valves are used for running and one igniter is used for igniting in the front half period and the other set of the solenoid valves are used for running and the other igniter is used for igniting in the latter half period. The invention can efficiently increase the work frequency of the pulse detonation engine and greatly decrease the demand on the solenoid valve response frequency. The solenoid valve which has the response frequency as half as the work frequency of the engine can be used, in order to decrease the load of the solenoid valve and help prolonging the service life of the solenoid valve.
Description
Technical field
The invention belongs to technical field of engines, be specially a kind of detonation tube and controlling method thereof of high-frequency pulse pinking engine.
Background technique
Pulse-knocking engine (Pulse Detonation Engine is called for short PDE) is that a kind of pulse-knocking ripple that utilizes produces the periodically non-permanent propulsion system of momentum.Different from conventional engines is, pulse-knocking engine is based on the power plant of the intermittent work on the knocking combustion basis.Therefore how producing reliably rapidly the key problem that detonation wave is the pulse-knocking engine design in detonation tube, is also simultaneously the key factor that determines pulse-knocking engine performance quality.
Studies show that, the performance parameter of the frequency of okperation pulse detonation engine of pulse-knocking engine has material impact.Ideally, the thrust of pulse-knocking engine linear increase along with the increase of frequency of okperation.Therefore, the practical application of the frequency of okperation pulse detonation engine of increase pulse-knocking engine is significant.When the frequency of okperation of pulse-knocking engine reached 100Hz, the thrust that motor produces can be considered continuous.
In order to improve the frequency of okperation of pulse-knocking engine, widely used in the laboratory at present is solenoid valve.The opening and closing of solenoid valve needs certain response time, and this has a upper limit with regard to the frequency of okperation that has determined solenoid valve, and the frequency of okperation of common pulse-knocking engine can't surmount or even reach this upper frequency limit.Therefore, all there is the shortcoming of underfrequency in the frequency of okperation of pulse-knocking engine.At the pulse-knocking engine development initial stage, both at home and abroad mainly with the control unit of high-frequency electromagnetic valve as the pulse-knocking engine Propellant Supply, response frequency can reach 60Hz or higher.But the research level of at present domestic and international high-frequency electromagnetic valve has determined high-frequency electromagnetic valve and can only accomplish can't satisfy the need of work of pulse-knocking engine under large flow below latus rectum Φ 2mm.And the frequency that the solenoid valve that can satisfy the requirement of pulse-knocking engine working flow can reach is generally not high, and the bottleneck factor that this has become the research of Limited Pulses detonation engine has seriously restricted the follow-up developments of pulse-knocking engine.
Summary of the invention
The technical problem that solves
In order to improve the frequency of okperation of pulse-knocking engine, the present invention proposes a kind of detonation tube and controlling method thereof of high-frequency pulse pinking engine, can under the prerequisite of not improving solenoid valve, effectively improve work frequency of pulse knocking engine.
Technological scheme
The technical solution used in the present invention is:
The detonation tube of described a kind of high-frequency pulse pinking engine, it is characterized in that: be connected with two fuel inlet solenoid valves in detonation tube fuel inlet place, the place is connected with two oxidant inlet solenoid valves at the detonation tube oxidant inlet, inlet is connected with two isolation gas import solenoid valves at detonation tube isolation gas, and the two-way igniter also is housed on detonation tube.
The preferred version of described a kind of high-frequency pulse pinking engine detonation tube: it is characterized in that: the two-way igniter is arranged on detonation tube horizontal both sides relatively, and is 1～3 times of detonation tube internal diameter apart from detonation tube closed end distance.
The preferred version of described a kind of high-frequency pulse pinking engine detonation tube: it is characterized in that: detonation tube oxidant inlet and relative installation of isolation gas import, and all be in the middle of igniter and detonation tube closed end, be 0.5～1 times of detonation tube internal diameter apart from detonation tube closed end distance, circumferential air inlet; Fuel inlet is positioned at detonation tube closed end center, axial admission.
the controlling method of described a kind of high-frequency pulse pinking engine detonation tube, it is characterized in that: in the front half period of a control cycle, the first fuel inlet solenoid valve, the first oxidant inlet solenoid valve, the first igniter and the first isolation gas import electromagnetic valve work, and the dutycycle of the first fuel inlet solenoid valve and the first oxidant inlet solenoid valve is 0.1～0.3, phase place is 0 °, the dutycycle of the first igniter is 0.01～0.04, phase place is 360 ° of dutycycles that multiply by the first fuel inlet solenoid valve, the dutycycle of the first isolation gas import solenoid valve is 0.1～0.3, phase place is that 180 ° of dutycycles that deduct the first isolation gas import solenoid valve multiply by 360 °, and the dutycycle sum of the first fuel inlet solenoid valve, the first igniter and the first isolation gas import solenoid valve is less than 0.5, in the rear half period of a control cycle, the second fuel inlet solenoid valve, the second oxidant inlet solenoid valve, secondary igniter and the second isolation gas import electromagnetic valve work, and the dutycycle of the second fuel inlet solenoid valve and the second oxidant inlet solenoid valve is identical with the dutycycle of the first fuel inlet solenoid valve, phase place is 180 °, the dutycycle of secondary igniter is identical with the dutycycle of the first igniter, phase place is that the first igniter phase place adds 180 °, the dutycycle of the second isolation gas import solenoid valve is identical with the dutycycle of the first isolation gas import solenoid valve, phase place is that the phase place of the first isolation gas import solenoid valve adds 180 °.
Beneficial effect
adopt detonation tube and the controlling method thereof of a kind of high-frequency pulse pinking engine of the present invention's proposition, fuel inlet at same detonation tube, oxidant inlet, adopt respectively two-way electromagnetic valve to control in the import of isolation gas, and adopted the two-way igniter, by each half period before and after control cycle is divided into, each is by one group of solenoid valve and waypoint firearm work within per halftime, can effectively improve the frequency of okperation of pulse-knocking engine, greatly reduce the requirement to the solenoid valve response frequency, can adopt response frequency is half solenoid valve of engine operation frequency, reduced the load of solenoid valve, be conducive to the solenoid valve life-time dilatation.
Description of drawings
Fig. 1: structural representation of the present invention;
Fig. 2: two cover solenoid valves and two-way igniter working timing figure;
Fig. 3: the pressure waveform figure when the electromagnetic valve frequency is 6Hz;
Fig. 4: the pressure waveform figure when the electromagnetic valve frequency is 8Hz;
Fig. 5: the pressure waveform figure when the electromagnetic valve frequency is 10Hz;
Fig. 6: the tonogram at Three pressures measuring point place under different control frequencies;
Fig. 7: the average velocity of wave figure under different control frequencies between p1-p2 and p2-p3;
Wherein: 1, the first fuel inlet solenoid valve; 2, the second fuel inlet solenoid valve; 3, the first isolation gas import solenoid valve; 4, the second isolation gas import solenoid valve; 5, the first igniter; 6, secondary igniter; 7, the first oxidant inlet solenoid valve; 8, the second oxidant inlet solenoid valve; 9, detonation tube.
Embodiment
Illustrate the present invention below in conjunction with embodiment:
Embodiment 1:
With reference to accompanying drawing 1, the detonation tube 9 of described a kind of high-frequency pulse pinking engine, fuel inlet place at detonation tube 9 is connected with the first fuel inlet solenoid valve 1 and the second fuel inlet solenoid valve 2, inlet is connected with the first isolation gas import solenoid valve 3 and the second isolation gas import solenoid valve 4 at isolation gas, the place is connected with the first oxidant inlet solenoid valve 7 and the second oxidant inlet solenoid valve 8 at oxidant inlet, and also has the first igniter 5 and relative being arranged on detonation tube of secondary igniter 6 levels on detonation tube 9.The oxidant inlet of detonation tube 9 and relative installation of isolation gas import, and all be in the middle of igniter and detonation tube closed end, be 0.5 times of detonation tube internal diameter apart from detonation tube closed end distance, circumferentially air inlet; Fuel inlet is positioned at detonation tube closed end center, axial admission.
In the present embodiment, the fuel of employing is aviation kerosine, and oxygenant is compressed oxygen, and isolation gas is compressed nitrogen, and igniter is automobile spark plug.Detonation tube internal diameter 30mm wherein, long 0.76m, the motor propellant feed system is furnished with 2 spark plug fitting seats for detonation tube provides two-way kerosene, oxygen and isolation nitrogen on detonation tube, spark plug is 75mm apart from detonation tube 9 closed end distances, namely 2.5 of the detonation tube internal diameter times.Adopt the general-utility car spark plug to light a fire, ignition energy is 50mJ.Three pressures measuring point on detonation tube is p1, p2, p3, respectively apart from ignition location 450mm, 530mm and 610mm.
In the present embodiment, the supply pressure of compressed oxygen and kerosene is respectively 1.5MPa and 0.5MPa.The equivalent proportion of liquid kerosene/oxygen mixture is about 1.0.External pressure and ambient temperature are respectively 1.01325 * 105Pa and 288.15K.Under this experimental condition, the kerosene that is calculated by pinking general-purpose computations software CEA program (Chemical Equilibrium and Applications)/oxygen gas phase detonation pressure P
0With speed V
0Be respectively 4.36MPa and 2357.5m/s.
The present embodiment is tested on pulse-knocking engine, and control system output eight road square signals are controlled two cover solenoid valve and two-way igniters, as shown in Figure 2.In the front half period of a control cycle, the first fuel inlet solenoid valve 1, the first oxidant inlet solenoid valve 7, the first igniter 5 and the first isolation gas import solenoid valve 3 work, and the dutycycle of the first fuel inlet solenoid valve 1 and the first oxidant inlet solenoid valve 7 is 0.15, phase place is 0 °, the dutycycle of the first igniter 5 is 0.01, phase place is 54 °, and the dutycycle of the first isolation gas import solenoid valve 3 is 0.2, and phase place is 108 °.In rear half period, the second fuel inlet solenoid valve 2, the second oxidant inlet solenoid valve 8, secondary igniter 6 and the second isolation gas import solenoid valve 4 work, and the dutycycle of the second fuel inlet solenoid valve 2 and the second oxidant inlet solenoid valve 8 is 0.15, phase place is 180 °, the dutycycle of secondary igniter 6 is 0.01, phase place is 234 °, and the dutycycle of the second isolation gas import solenoid valve 4 is 0.2, and phase place is 288 °.
3 groups of control frequencies have been adopted in the present embodiment, be respectively 6Hz, 8Hz, 10Hz, the pressure that collects at p1, p2, p3 Three pressures measuring point over time curve for respectively as Fig. 3, Fig. 4, shown in Figure 5, the time span of intercepting is 1s, pressure pulsation curves in time can be found out from figure, and the fluctuating frequency of pressure is the twice of engine control frequency.When control frequency was 6Hz, 8Hz, 10Hz, the frequency of okperation of motor was followed successively by 12Hz, 16Hz, 20Hz.
According to the experimental pressure data, count the pressure average peak at the place of Three pressures measuring point under different control frequencies, as shown in Figure 6.According to the pressure-wave emission speed between each cycle measuring point, statistics draws the average velocity of wave between p1-p2 and p2-p3 under different control frequencies, as shown in Figure 7.When control frequency was 6Hz, 8Hz and 10Hz, p3 place pressure peak mean value was respectively that between 97%, 79.7% and 70.2%, p2-p3 of aforementioned calculated value, average velocity of wave is respectively 74.6%, 71.0% and 71.8% of calculated value.The size of the pressure peak that obtains according to test and average velocity of wave, can judge under these three kinds of control frequencies, all obtained full-blown detonation wave after igniting in detonation tube, full-blown pinking occurs between p2～p3, and detonation frequency is 2 times of control frequency.And as long as solenoid valve can satisfy the requirement of control frequency, this method can obtain the pinking of 2 times that detonation frequency is control frequency.
Above-mentioned experimental result shows, this novel detonation tube and controlling method thereof are feasible, and single electromagnetic valve work frequency is only half of detonation frequency, greatly reduces work frequency of pulse knocking engine to the dependence of solenoid valve response frequency.
Embodiment 2:
The structure of detonation tube 9 and embodiment's 1 difference are: oxidant inlet and the import of isolation gas be 1 times for the detonation tube internal diameter apart from detonation tube closed end distance; Spark plug is 90mm apart from detonation tube 9 closed end distances, namely 3 of the detonation tube internal diameter times.
The present embodiment is tested on pulse-knocking engine, and control system output eight road square signals are controlled two cover solenoid valve and two-way igniters.In the front half period of a control cycle, the first fuel inlet solenoid valve 1, the first oxidant inlet solenoid valve 7, the first igniter 5 and the first isolation gas import solenoid valve 3 work, and the dutycycle of the first fuel inlet solenoid valve 1 and the first oxidant inlet solenoid valve 7 is 0.3, phase place is 0 °, the first igniter 5 dutycycles are 0.04, phase place is 108 °, and the first isolation gas import solenoid valve 3 dutycycles are 0.1, and phase place is 144 °.In rear half period, the second fuel inlet solenoid valve 2, the second oxidant inlet solenoid valve 8, secondary igniter 6 and the second isolation gas import solenoid valve 4 work, and the dutycycle of the second fuel inlet solenoid valve 2 and the second oxidant inlet solenoid valve 8 is 0.3, phase place is 180 °, the dutycycle of secondary igniter 6 is 0.04, phase place is 288 °, and the dutycycle of the second isolation gas import solenoid valve 4 is 0.1, and phase place is 324 °.
Adopted equally 3 groups of control frequencies in the present embodiment, be respectively 6Hz, 8Hz, 10Hz, collected pressure curve over time at p1, p2, p3 Three pressures measuring point, result shows that the fluctuating frequency of pressure is the twice of engine control frequency.
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| CN 201010527539 CN101985904B (en) | 2010-10-28 | 2010-10-28 | Control method of detonation pipe for high-frequency pulse detonation engine |
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| CN101985904B true CN101985904B (en) | 2013-06-05 |
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| CN103075271B (en) * | 2013-01-21 | 2015-04-22 | 西北工业大学 | High-frequency conical spiral tube type pulse detonation engine |
| CN103195613B (en) * | 2013-04-15 | 2015-04-22 | 西北工业大学 | Pulse detonation rocket engine frequency doubling work control device and control method thereof |
| CN105003353B (en) * | 2015-07-14 | 2017-01-18 | 王星睿 | Valvula type pulse jet engine |
| CN109252980B (en) * | 2018-11-13 | 2020-11-20 | 西北工业大学 | A fuel injection system for adaptive pulse detonation engine |
| CN109404165B (en) * | 2018-12-26 | 2019-11-19 | 中国人民解放军战略支援部队航天工程大学 | Continuous detonation rocket-based engine and aircraft with thrust vector control |
| CN115045776B (en) * | 2022-04-28 | 2024-04-30 | 西北工业大学 | A dual-fuel non-isolated pulse detonation engine device and control method thereof |
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| US5901550A (en) * | 1993-04-14 | 1999-05-11 | Adroit Systems, Inc. | Liquid fueled pulse detonation engine with controller and inlet and exit valves |
| US5873240A (en) * | 1993-04-14 | 1999-02-23 | Adroit Systems, Inc. | Pulsed detonation rocket engine |
| US6584765B1 (en) * | 2001-12-21 | 2003-07-01 | United Technologies Corporation | Pulse detonation engine having an aerodynamic valve |
| US7131260B2 (en) * | 2004-06-18 | 2006-11-07 | General Electric Company | Multiple detonation initiator for frequency multiplied pulsed detonation combustion |
| GB0425901D0 (en) * | 2004-11-25 | 2004-12-29 | Rolls Royce Plc | Combuster |
| US7669406B2 (en) * | 2006-02-03 | 2010-03-02 | General Electric Company | Compact, low pressure-drop shock-driven combustor and rocket booster, pulse detonation based supersonic propulsion system employing the same |
| US7950219B2 (en) * | 2006-10-31 | 2011-05-31 | General Electric Company | Dual mode combustion operation of a pulse detonation combustor in a hybrid engine |
| CN201858045U (en) * | 2010-10-28 | 2011-06-08 | 西北工业大学 | Detonation tube of high-frequency pulse detonation engine |
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