CN103712770A - Monitoring system for carrier-rocket launch fuel-gas flow field - Google Patents
Monitoring system for carrier-rocket launch fuel-gas flow field Download PDFInfo
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- CN103712770A CN103712770A CN201210373253.4A CN201210373253A CN103712770A CN 103712770 A CN103712770 A CN 103712770A CN 201210373253 A CN201210373253 A CN 201210373253A CN 103712770 A CN103712770 A CN 103712770A
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Abstract
The invention discloses a monitoring system for a carrier-rocket launch fuel-gas flow field. The monitoring system includes a first test main array group and a second test main array group, wherein the first test main array group includes an in-diversion-hole fuel-gas flow field test array, a table-board fuel-gas flow field test array and an on-cross-beam fuel-gas flow field test array. The second test main array group includes a near-diversion-trench-entrance fuel-gas flow field parameter test array, a diversion-trench-drainage-guide-face fuel-gas flow field parameter test array, a guide-trench-top fuel-gas flow field parameter test array and a diversion-trench-side-face fuel-gas flow field parameter test array. The test scheme of the carrier-rocket launch fuel-gas flow field is applicable to carrier-rocket launch fuel-gas flow field testing and fuel-gas-flow ablation characteristic assessment and capable of being transplanted conveniently into a shrinkage-scale launch simulation test or fuel-gas flow field testing and fuel-gas ablation characteristic assessment in a special simulation test.
Description
Technical field
The present invention relates to rocket launching field, relate in particular to a kind of carrier rocket transmitting gas flow field monitoring field.
Background technology
Rocket launching gas-flow is the problem that the fields such as the special equipment development of rocket launching technical research, emission coefficient, the special thermal protection of rocket and gas flow field control are paid close attention on the ablation impact of emission coefficient, rocket always, all voted and carried out special thermal protection technology, principle of products and checking research into huge fund in these fields, in correlative study, a very important job is to detect and assess rocket launching gas flow field parameter, has proposed a lot of simple and easy or system detecting methods to adapt to the rocket launching gas-flow ablation communication environments of different technologies form for this reason.
At present, the main carrier rocket emission coefficient structural condition of relying on of rocket launching gas flow field monitoring is carried layout limited measure node test specific position gas flow field parameter in emission coefficient structure, this test is subject to emission coefficient structural condition (as transmitting station structural condition) interference-limited, the combustion parameter of test is often difficult to reflect rocket launching gas-flow gas flow field characteristic, under some conditions, be subject to the restriction of emission coefficient structural condition to cause obtaining actual gas flow field parameter, simultaneously because measuring point is limited, high temperature and high speed gas-flow very easily causes testing sensor to damage, thereby System in Small Sample Situation test data is difficult to reflect the true transmitting gas-flow regularity of distribution, thereby can not system, assess subtly the impact on gas-flow gas flow field of rocket body and emission coefficient.
In addition, the field of gas flow field monitoring is at present detected, is assessed mainly for single spraying pipe rocket launching gas-flow ablation and gas flow field, carrier rocket particularly strap-on vehicle transmitting gas-flow ablation and gas flow field detection field relates to less, mainly contain the reason of three aspects: the one, the mutual disturbing effect of carrier rocket multi nozzle gas-flow is obvious, causes particularly gas-flow ablation characteristics parameter and the gas flow field parameter testing of gas flow field parameter, analyzes difficulty especially; The 2nd, carrier rocket often adopts different types of engine to adapt to special lift-off technology Capability Requirement, this core stage motor, booster rocket engine application aspect at strap-on vehicle is particularly more outstanding, cause gas-flow ablation characteristics and gas flow field characteristic test, analyze difficulty, for example the research of gas-flow ablative mechanism need to be determined ablation intensity and incoming flow Reynolds number relation, under engine gas stream phase mutual interference and the non-single condition of gas-flow incoming flow composition, obviously increased test and analyzed difficulty; The 3rd, carrier rocket flat pad disturbance effect is outstanding, and the ablation of gas-flow and gas flow field impact must take into full account the structural perturbation effect of flat pad.
Summary of the invention
Fundamental purpose of the present invention is to provide particularly strap-on vehicle transmitting gas flow field monitoring system of a kind of applicable carrier rocket.
Above-mentioned purpose realizes by following proposal:
A carrier rocket transmitting gas flow field monitoring system, is characterized in that, described monitoring system comprises the main array group of the first test and the main array group of the second test; Wherein,
The main array group of described the first test comprises: gas flow field hot-wire array on gas flow field hot-wire array, table top gas flow field hot-wire array, cross beam in pod apertures; In described pod apertures, gas flow field hot-wire array consists of the gas flow field hot-wire array group that is arranged on the inside surface of each pod apertures; Described table top gas flow field hot-wire array is that the gas flow field hot-wire array group arranging on pod apertures periphery, flat pad table top forms; On described cross beam, gas flow field hot-wire array is that the gas flow field hot-wire array that is arranged on flat pad cross beam upper surface forms;
The main array group of described the second test comprises: gas flow field parameter testing array, diversion trench row guide face gas flow field parameter testing array, diversion trench top gas flow field parameter testing array, diversion trench side gas flow field parameter testing array near diversion trench entrance; Near described diversion trench entrance, gas flow field parameter testing array is arranged on diversion trench entrance section; Described diversion trench row guide face gas flow field parameter testing array is arranged based on row's guide face surface normal; Gas flow field parameter testing array in described diversion trench top is arranged based on showing normal direction in diversion trench groove top and water conservancy diversion entrance; Gas flow field parameter testing array in described diversion trench side is symmetricly set on diversion trench two sides.
Monitoring system according to above-mentioned, is characterized in that, the main array group of described the first test also comprises: gas flow field hot-wire array on tower, it is evenly arranged on umbilical tower inside surface on flat pad.
Monitoring system according to above-mentioned, is characterized in that, the built-in measurement of flow parameter array of described pod apertures is divided into upper and lower two-layer layout.
Monitoring system according to above-mentioned, is characterized in that, in described pod apertures, gas flow field hot-wire array forms " mouth " shape or " O " shape.
Monitoring system according to above-mentioned, is characterized in that, near described diversion trench entrance, gas flow field parameter testing array forms " mouth " shape or " O " shape.
Monitoring system according to above-mentioned, is characterized in that, the sensor that described the first main array group of test and the main array group of the second test are used is for pressure transducer, temperature sensor, heat flux sensor, flow sensor, ablation sensor is independent or its combination.
Beneficial effect of the present invention:
(1) based on the present invention, can launch gas-flow at distribution, the Changing Pattern of flat pad table top, cross beam, pod apertures, umbilical tower by testing evaluation carrier rocket, based on gas-flow, at flat pad table top, cross beam, pod apertures, umbilical tower distribution, further systematic analysis of Changing Pattern, assessment flat pad gas-flow ablation characteristics, flat pad Thermal Synthetic protectiving scheme is proposed.
(2) based on the present invention, can launch distribution, the Changing Pattern of gas-flow in diversion trench by testing evaluation carrier rocket, gas-flow ablation characteristics can further be analyzed, be assessed to distribution based on gas-flow in diversion trench, Changing Pattern, proposes launching site diversion trench Thermal Synthetic protectiving scheme.
(3) based on the present invention, can test and analyze the distribution of carrier rocket transmitting gas-flow, ablation impact simultaneously, can instruct also verification carrier rocket transmitting gas flow field numerical value to indicate and experimental study.
Accompanying drawing explanation
Fig. 1 is flat pad stage body organization plan schematic diagram;
Fig. 2 is the vertical view of flat pad stage body structure;
Fig. 3 is the left side view of flat pad stage body structure;
Fig. 4 is the schematic diagram (A-A of Fig. 1 to) of transmitting stage body pod apertures internal flow field parameters hot-wire array;
Fig. 5 is the schematic diagram (A-A of Fig. 1 to) of the transmitting stage body pod apertures internal flow field parameters hot-wire array that amplify to show;
Fig. 6 is that the B-B of Fig. 2 is to view;
Fig. 7 is flat pad table top measurement of flow parameter array approaches schematic diagram;
Fig. 8 is measurement of flow parameter array approaches schematic diagram on flat pad cross beam;
Fig. 9 is guide trough structure scheme subdivision schematic diagram;
Figure 10 is the measurement of flow parameter array approaches schematic diagram of settling on diversion trench wall;
Figure 11 is the vertical view of Figure 10;
Figure 12 is near the partial structurtes schematic diagram of measurement of flow parameter array diversion trench entrance.
Embodiment
With reference to figure 1 ~ Figure 12, emission coefficient comprises multi-function service platform 1 and movable launch platform 13.Carrier rocket transmitting gas flow field testing scheme builds based on the emission coefficient emission coefficient body structure surface that particularly gas-flow affects, and adopts the main array group of two large tests to realize carrier rocket and launches gas flow field test.Wherein, the main array group of carrier rocket transmitting gas flow field the first test utilizes the primary structure windward side that relates to gas-flow impact on flat pad to set up, and mainly tests near the transmitting of flat pad stage body gas flow field parameter; The main array group of carrier rocket transmitting gas flow field the second test utilizes the primary structure windward side that relates to gas-flow impact in the diversion trench of launching site to set up, and mainly tests transmitting gas flow field parameter in diversion trench.Gas flow field parameter based on the main array group test of carrier rocket transmitting gas flow field two test can be supplemented mutually, with near gas flow field absolutely proving emission coefficient, distribute and attenuation law, also can mutually reflect card, to reject the pseudo-data of distortion, verification affects the gas flow field Parameter Variation of emission coefficient, can revise the transmitting pre-representation model of gas flow field and numerical algorithm simultaneously.
With reference to figure 1 ~ Fig. 8, the main array group of carrier rocket transmitting gas flow field the first test is further comprised of four transmitting gas flow field hot-wire arrays again, be respectively gas flow field hot-wire array 7 on the upper gas flow field hot-wire array 2 of tower (be umbilical tower 1, also claim high-order service tower 1), the interior gas flow field hot-wire array 3 of pod apertures, table top gas flow field hot-wire array 6, cross beam.
With reference to figure 3, on tower gas flow field hot-wire array based on umbilical tower inside surface on flat pad (near the body structure surface of carrier rocket one side, also be the directly windward side of impact of gas-flow and injection air-flow thereof) build, due to umbilical tower up and down each composition section inside surface be planar structure, in building process directly based on each planar process to arranging serial gas flow field parameter testing hole, cloth position in space in each plane, series of tests hole becomes matrix array, the umbilical tower up and down row of the submatrix on each composition section is combined and forms gas flow field test matrix on tower, all or part of supporting necessary testing sensor of each instrument connection of emission test process, cable, collecting device can carry out gas flow field integration test on tower.At present, the flow field parameter type of assessment gas flow field or combustion gas ablation characteristics comprises gas-flow pressure, temperature, hot-fluid, flow velocity, ablation etc., in emission test process, according to the supporting type of umbilical tower size, test number (TN) and sensor, quantity, pressure, temperature, hot-fluid, flow velocity, ablation sensor independence or combination can be structured the formation, realize the flow field parameter such as pressure, temperature, hot-fluid, flow velocity, ablation separately or integration test.On process of the test tower, gas flow field hot-wire array group is laid sensor and be can be changed into gas flow field sensor, and this position test data type becomes test carrier rocket transmitting gas-flow gas flow field like this.For the emission coefficient that umbilical tower is not set, do not exist gas-flow ablation on tower to affect problem, can cancel this hot-wire array.
With reference to figure 2, Fig. 4 ~ Fig. 6, in pod apertures, gas flow field hot-wire array builds based on flat pad pod apertures inside surface, final, and in pod apertures, gas flow field hot-wire array 3 comprises the gas flow field hot-wire array being arranged in each pod apertures.Each pod apertures horizonally split cross section of Fig. 8, Fig. 9 signal is " mouth " shape, in each pod apertures, gas flow field hot-wire array is " mouth " shape hot-wire array thus, when each pod apertures horizonally split cross section is " O " shape, in each pod apertures, gas flow field hot-wire array is " O " shape hot-wire array.During each array test hole of actual implementation, equally based on each guide face planar design direct method to cloth hole, during emission test, according to the supporting type of pod apertures size, test number (TN) and sensor, quantity, pressure, temperature, hot-fluid, flow velocity, ablation sensor independence or combination can be structured the formation, realize the flow field parameter such as pressure, temperature, hot-fluid, flow velocity, ablation separately or integration test.In pod apertures gas flow field hot-wire array group consider carrier rocket take off moment gas-flow directly to affect position be pod apertures bottom, then along with carrier rocket takes off, gas-flow starts to affect gradually pod apertures middle part, top, low level and high-order " O " shape or " mouth " shape hot-wire array (upper and lower two-layer layout are set respectively for this reason in each pod apertures, referring to 4 of Fig. 6,5), testing successively differing heights position pod apertures inside surface gas flow field dynamic state of parameters distributes and Changing Pattern.Equally, according to low level, high-order gas flow field hot-wire array sensor type, quantity in the alternative coupling of experimental scale or adjustment pod apertures.
With reference to figure 8, on cross beam, gas flow field parameter testing array 7 is directly built into " well " shape hot-wire array based on cross beam upper surface, for testing cross beam upper surface gas-flow parameter.
With reference to figure 9 ~ Figure 12, the main array group of carrier rocket transmitting gas flow field the second test is gas flow field hot-wire array group in diversion trench, based on diversion trench 8 guide faces, build, mainly by four subarrays, become, be respectively near the gas flow field parameter testing array 9 of diversion trench entrance, diversion trench row guide face (also directly bearing gas-flow shock surface, is also diversion trench bottom surface) gas flow field parameter testing array 12, diversion trench top gas flow field parameter testing array 10, diversion trench side gas flow field parameter testing array 11.
With reference to Figure 12, near diversion trench entrance, gas flow field parameter testing array 9 arranges based on diversion trench entrance section, hole, gas flow field testing sensor cloth position forms " mouth " shape or " O " shape hot-wire array, be mainly used in monitoring diversion trench entrance section place gas-flow injection air-flow situation and gas-flow heat radiation situation, also can, for monitoring diversion trench entrance gas-flow gas flow field situation, also monitor diversion trench porch gas flow field bottleneck effect situation.
With reference to figure 9 ~ Figure 10, diversion trench row guide face gas flow field parameter testing array 12 sensors arrange based on row's guide face surface normal, according to diversion trench row lead gas-flow trend and and water conservancy diversion entrance determine whole array shape.Figure 10 shows that " L shaped " diversion trench row guide face gas flow field parameter testing array totally becomes " L shaped ", and corresponding " W shape " diversion trench row guide face gas flow field parameter testing array totally becomes " W shape ".With reference to Figure 10 ~ Figure 11, according to emission test research needs, along diversion trench row guide face laterally (being that vertical gas-flow row leads direction) can arrange and lead center line symmetry (or asymmetric) and set up " L shaped " (or " W shape ") gas flow field parameter testing array, be that actual diversion trench row guide face gas flow field parameter testing array can be comprised of several groups " L shaped " (or " W shape ") gas flow field parameter testing array, increase gas flow field parameter and analyze increment, improve gas flow field distribution resolution.
With reference to figure 9 ~ Figure 11, gas flow field parameter testing array in diversion trench top is similar to diversion trench row guide face gas flow field parameter testing array, testing sensor is arranged based on showing normal direction in diversion trench groove top and water conservancy diversion entrance, according to the groove top molded line of groove top symmetric section demonstration, is determined whole array shape.Figure 10 shows has set up " L " shape gas flow field parameter testing array based on " L shaped " diversion trench top " L shaped " molded line, similar Figure 10, and corresponding " W shape " water conservancy diversion top " W shape " molded line can be set up " W " shape gas flow field parameter testing array.According to emission test research needs, gas flow field parameter testing array in diversion trench top also can be comprised of several groups " L shaped " or " W shape " gas flow field parameter testing subarray, to increase gas flow field parameter, analyzes increment, improves gas flow field distribution resolution.Diversion trench top gas flow field parameter testing array can be used for testing gas-flow gas flow field rule in diversion trench.
With reference to figure 9 ~ Figure 11, gas flow field parameter testing array in diversion trench side is from row's guide face certain altitude, based on diversion trench two sides are symmetrical, build, main test affects the gas flow field rule of diversion trench side from diversion trench row guide face certain altitude place, with reference to the similar structure of diversion trench row's guide face gas flow field parameter testing array shape, i.e. chute side gas flow field parameter testing array also becomes " L shaped " or " W shape " for this reason.
The actual test of similar carrier rocket transmitting gas flow field the first main array of test is selected and deployment scenarios, according to actual needs, each subarray of the main array of carrier rocket transmitting gas flow field the second test can carry out reasonable combination to gas flow field testing sensor quantity, type, realizes integration test and the analysis of gas flow field one-parameter or multiparameter.
The present invention proposes carrier rocket transmitting gas flow field testing scheme and can be used for the test of carrier rocket emission test gas flow field and the assessment of gas-flow ablation characteristics, and also the value of moving is assessed with gas-flow ablation characteristics in special simulation test research (as reduced scale degree jet test or engine run test) process gas flow field test easily.
Claims (6)
1. a carrier rocket transmitting gas flow field monitoring system, is characterized in that, described monitoring system comprises the main array group of the first test and the main array group of the second test; Wherein,
The main array group of described the first test comprises: gas flow field hot-wire array on gas flow field hot-wire array, table top gas flow field hot-wire array, cross beam in pod apertures; In described pod apertures, gas flow field hot-wire array consists of the gas flow field hot-wire array group that is arranged on the inside surface of each pod apertures; Described table top gas flow field hot-wire array is that the gas flow field hot-wire array group arranging on pod apertures periphery, flat pad table top forms; On described cross beam, gas flow field hot-wire array is that the gas flow field hot-wire array that is arranged on flat pad cross beam upper surface forms;
The main array group of described the second test comprises: gas flow field parameter testing array, diversion trench row guide face gas flow field parameter testing array, diversion trench top gas flow field parameter testing array, diversion trench side gas flow field parameter testing array near diversion trench entrance; Near described diversion trench entrance, gas flow field parameter testing array is arranged on diversion trench entrance section; Described diversion trench row guide face gas flow field parameter testing array is arranged based on row's guide face surface normal; Gas flow field parameter testing array in described diversion trench top is arranged based on showing normal direction in diversion trench groove top and water conservancy diversion entrance; Gas flow field parameter testing array in described diversion trench side is symmetricly set on diversion trench two sides.
2. monitoring system according to claim 1, is characterized in that, the main array group of described the first test also comprises: gas flow field hot-wire array on tower, it is evenly arranged on umbilical tower inside surface on flat pad.
3. monitoring system according to claim 1, is characterized in that, the built-in measurement of flow parameter array of described pod apertures is divided into upper and lower two-layer layout.
4. monitoring system according to claim 1, is characterized in that, in described pod apertures, gas flow field hot-wire array forms " mouth " shape or " O " shape.
5. monitoring system according to claim 1, is characterized in that, near described diversion trench entrance, gas flow field parameter testing array forms " mouth " shape or " O " shape.
6. according to the monitoring system one of claim 1-5 Suo Shu, it is characterized in that, the sensor that described the first main array group of test and the main array group of the second test are used is for pressure transducer, temperature sensor, heat flux sensor, flow sensor, ablation sensor is independent or its combination.
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| CN104296995A (en) * | 2014-10-09 | 2015-01-21 | 中国运载火箭技术研究院 | Engine jet flame characteristic test device and method in atmospheric absorption wave band |
| CN104296995B (en) * | 2014-10-09 | 2017-01-04 | 中国运载火箭技术研究院 | Engine flame characteristic test device and test method in atmospheric absorption waveband |
| CN109900154A (en) * | 2019-03-13 | 2019-06-18 | 北京航天发射技术研究所 | A kind of rocket launching gas flow field quasi-steady state predicting method and device |
| CN109933849A (en) * | 2019-02-01 | 2019-06-25 | 北京航天发射技术研究所 | A kind of complexity gas flow field calculates fast calibration method and medium |
| CN109974541A (en) * | 2019-03-26 | 2019-07-05 | 北京航天发射技术研究所 | Multi nozzle rocket dynamic jet test system |
| CN109974847A (en) * | 2019-03-26 | 2019-07-05 | 北京航天发射技术研究所 | Carrier rocket emits jet noise detection method |
| CN109974542A (en) * | 2019-03-26 | 2019-07-05 | 北京航天发射技术研究所 | A kind of carrier rocket takes off power thermal environment detection system and method |
| CN111562189A (en) * | 2020-05-31 | 2020-08-21 | 太原理工大学 | Ultrahigh-temperature gas jet erosion test device for diversion trench material |
| CN111795828A (en) * | 2020-06-05 | 2020-10-20 | 湖北航天技术研究院总体设计所 | Horizontal simulation launch test device and method |
| CN111964527A (en) * | 2020-07-14 | 2020-11-20 | 北京航天发射技术研究所 | High-efficient low-cost transmission platform heat protection system |
| CN112966354A (en) * | 2021-03-29 | 2021-06-15 | 湖北三江航天江北机械工程有限公司 | Anti-scouring capability assessment method for gas flow drainage device |
| CN113295047A (en) * | 2021-05-06 | 2021-08-24 | 北京航天发射技术研究所 | Driving distributed heavy carrier rocket vertical transfer system |
| CN116629028A (en) * | 2023-07-19 | 2023-08-22 | 东方空间技术(山东)有限公司 | Method and device for determining parameters of flow guide groove of petal-shaped launching pad |
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| CN104296995A (en) * | 2014-10-09 | 2015-01-21 | 中国运载火箭技术研究院 | Engine jet flame characteristic test device and method in atmospheric absorption wave band |
| CN104296995B (en) * | 2014-10-09 | 2017-01-04 | 中国运载火箭技术研究院 | Engine flame characteristic test device and test method in atmospheric absorption waveband |
| CN109933849A (en) * | 2019-02-01 | 2019-06-25 | 北京航天发射技术研究所 | A kind of complexity gas flow field calculates fast calibration method and medium |
| CN109900154A (en) * | 2019-03-13 | 2019-06-18 | 北京航天发射技术研究所 | A kind of rocket launching gas flow field quasi-steady state predicting method and device |
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| CN109974542A (en) * | 2019-03-26 | 2019-07-05 | 北京航天发射技术研究所 | A kind of carrier rocket takes off power thermal environment detection system and method |
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| CN109974847A (en) * | 2019-03-26 | 2019-07-05 | 北京航天发射技术研究所 | Carrier rocket emits jet noise detection method |
| CN111562189B (en) * | 2020-05-31 | 2022-06-28 | 太原理工大学 | Ultrahigh-temperature gas jet erosion test device for diversion trench material |
| CN111562189A (en) * | 2020-05-31 | 2020-08-21 | 太原理工大学 | Ultrahigh-temperature gas jet erosion test device for diversion trench material |
| CN111795828A (en) * | 2020-06-05 | 2020-10-20 | 湖北航天技术研究院总体设计所 | Horizontal simulation launch test device and method |
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| CN111964527B (en) * | 2020-07-14 | 2022-07-29 | 北京航天发射技术研究所 | High-efficient low-cost transmission platform heat protection system |
| CN112966354A (en) * | 2021-03-29 | 2021-06-15 | 湖北三江航天江北机械工程有限公司 | Anti-scouring capability assessment method for gas flow drainage device |
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