Двигательная установка. RL 10A-4-2. [Редактировать]

Ракетный двигатель RL-10A-4-2 произведен компанией Pratt & Whitney Rocketdyne и обеспечивает тягу в размере 99.2 кНьютон. Двигатель имеет высоту 3.53 метра и диаметр 1.53 метра. Особенностью установки является ее оснащение сдвижным сопловым насадком. Двигатель сертифицирован на работу в течении 740 секунд и может включаться несколько раз. Сухая масса установки составляет 166 кг. Степень расширения сопла 84. Отношение тяга к весу составляет 61. Система управления вектором тяги является электро-механической.

Новостная лента[Найти информацию в новостях] [Найти информацию в документах]

#Новостная лента.
12016-03-25. ULA подтвердила проблемы с двигательными установками при последнем запуске РН Атлас.
ULA подтвердила, что верхняя ступень РН Атлас 5 работала на одну минуту дольше чем было запланировано. При этом компания, пока что, не называет причины этого, однако по данным СМИ основной причиной такого поведения ракеты являлось преждевременное выключение двигательной установки первой ступени. К настоящему времени ULA не перенесла запуск в разряд частично неудачных, но отметила, что по данным телеметрии, Cygnus был успешно выведен на орбиту. Из обнародованных данных телеметрии необходимо отметить, что:
1. ДУ RL 10A-4-2 должен был работать 18 минут 9 секунд (фактически отработал 19 минут 20 секунд).
2. Возможно что подобное отклонение было вызвано ошибкой в прогнозных значениях длительности работы первой ступени. При этом, в самой компании отметили, что подобные неточности бывают сплошь и рядом поскольку траектория выведения просчитывается за несколько недель до запуска.
3. Двигатель РД-180 работал всего-лишь на пять секунд меньше чем было запланировано.Тэги: 2016-019RL 10A-4-2РД-180Атлас 5 401

Технические характеристики

#ХарактеристикаЗначение
1Длина (двигателя), метра3.53
2Топливоводород + кислород
3Тяга, кН99.2
4Удельный импульс (вакум), секунд451
5Масса (сухая), кг167
6Диаметр, метра1.53
7Давление (в камере сгорания), бар39

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... Validation: RL-10 design and analysis 6.1. Overview of the RL-10A-3-3A rocket... simulation: validation at nominal conditions . 6.4. RL-10 Engine start-up . . . . . . . . . . . . . . . 6.4.1. Description... start-up sequences . . 6.4.2. Start transient . . . . . . . . . . . . . . . 6.5. RL-10 engine shut-down . . . . . . . . . . . . . . 6.5.1. Description... Figures 4.10. Schematic of the RL-10 engine . . . . . . . . . . . . . . . . . . . . 111 5.1. 5.2. 5.3. 5.4. 5.5. Schematic illustration... 139 140 141 6.1. 6.2. 6.3. 6.4. 6.5. 6.6. 6.7. 6.8. RL-10A-3-3A engine schematic [115] . . . . . . . . . . RL-10A-3-3A engine diagram... from P&W [15] . . . . . . Turbine performance maps . . . . . . . . . . . . . . . RL-10A-3-3A chamber contour [15] and.... Venturi nozzle profile . . . . . . . . . . . . . . . . . . . . RL-10A-3-3A schematic model . . . . . . . . . . . . . . . RL-10A-3-3A Valve schedule for... Figures 6.17. 6.18. 6.19. 6.20. RL-10A-3-3A Valve schedule for Shut... 4.19. RL-10A-3-3A input and initial data . . . . . . . . . . . . . . . . . . 110 4.20. RL-10A-3-3A engine... . . . . . . . . . . . . . . . . . . . . . 134 5.3. Positioning of themocouples . . . . . . . . . . . . . . . . . . . . . 135 6.1. RL-10A-3-3A construction data [15] . . . . . . . . . . . . . . . . . 146... parameters . . . . . . . . . . . . . Oxidiser line valves parameters . . . . . . . . . . . RL-10A-3-3A engine system output data... simulation of a real engine, the RL-10A-3-3A. 1.4. Organization of this Thesis... main test case examined: the RL-10A-3-3A rocket engine which presents... application of ROCETS is the RL-10A-3-3A rocket engine [13, 14... State Library RL-10A-3-3A rocket engine system The RL-10 is an... test case a model of the RL-10A-3-3A rocket engine system has... [-] 180 [-] 1000 [K] 2 [kg/s] Table 4.19.: RL-10A-3-3A input and initial data...% 0.39% 3.68% 2.89% 2.5% Table 4.20.: RL-10A-3-3A engine system output data... altitude into Earth orbit. The RL-10A-3-3A developed by Pratt & Whitney... with respect to the initial RL-10A-1 engine. A cryogenic expander cycle engine... 1-D discretised chamber 142 6. Integrated Validation: RL-10 design and analysis and... data available. 6.1. Overview of the RL-10A-3-3A rocket engine The RL10A.... Figure 6.1.: RL-10A-3-3A engine schematic [115] 145 6. Integrated Validation: RL-10 design... 1.476 216 6.72 [m] [m] [-] [m] [-] [kg] Table 6.1.: RL-10A-3-3A construction data [15] a values... 6. Integrated Validation: RL-10 design and analysis Figure 6.2.: RL-10A-3-3A engine diagram 6.2. Design procedure The development of the RL-10... follows: θ = π + arctan(ν/n) 147 (6.1) 6. Integrated Validation: RL-10 design and analysis where... total dynamic 148 6. Integrated Validation: RL-10 design and analysis (a) Extended... insert that creates a sharp Figure 6.7.: RL-10A-3-3A chamber contour [15] and... 1 2 + v − ρ 2 Pcav ρ 1 = − ζv 2 2 155 ⇒ ∆P = (1 + ζ) m ˙2 2ρA2 6. Integrated Validation: RL-10 design and analysis The... channels profiles 157 6. Integrated Validation: RL-10 design and analysis 6.2.3. Lines... valves parameters 161 6. Integrated Validation: RL-10 design and analysis 6.3. Subsystem... conditions Each component of the RL-10A-3-3A engine has been previously... together to create the complete RL-10A-3-3A engine model (see Figure...% Table 6.5.: RL-10A-3-3A engine system output data 163 6. Integrated Validation: RL-10 design and analysis Figure 6.10.: RL-10A-3-3A schematic model 164 6. Integrated Validation: RL-10 design and analysis 6.4. RL... 6. Integrated Validation: RL-10 design and analysis Figure 6.11.: RL-10A-3-3A Valve... Simulation [15] 166 6. Integrated Validation: RL-10 design and analysis turbopumps... the previous model of the RL-10A-3-3A transient start-up [15... chamber temperature. 170 6. Integrated Validation: RL-10 design and analysis (a) Chamber... results - part 3 173 6. Integrated Validation: RL-10 design and analysis (a) Venturi... 6. Integrated Validation: RL-10 design and analysis Figure 6.17.: RL-10A-3-3A Valve... Simulation [15] 176 6. Integrated Validation: RL-10 design and analysis 6.5.2. Shut... present model. 179 6. Integrated Validation: RL-10 design and analysis (a) Chamber... results - part 3 182 6. Integrated Validation: RL-10 design and analysis (a) Venturi... results - part 4 183 6. Integrated Validation: RL-10 design and analysis 6.6. Dynamic... ±10% operation 186 6. Integrated Validation: RL-10 design and analysis (a) Chamber... results - part 3 189 6. Integrated Validation: RL-10 design and analysis (a) Turbine... results - part 4 190 6. Integrated Validation: RL-10 design and analysis Oxidiser... ±10% operation 192 6. Integrated Validation: RL-10 design and analysis (a) Chamber... results - part 3 195 6. Integrated Validation: RL-10 design and analysis (a) Turbine... liquid propellant rocket engine, the RL-10A-3-3A. The construction of a model... also well estimated. Moreover the RL-10A-3-3A model accurately predicts the... be calculated: 0.4 λl hl = 0.023 Re0.8 (C.7) l P rl D where the sub index l makes...



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... I. Engine meng,1 [kg] RL-50 500 499 RL-60 550 RD-57A...-down version of Pratt & Whitney’s RL-10A-3A is used, retaining the...-B HM7-B HM7-B HM7-B RL-10A-1 RL-10A-3 RL-10A-3A RL-10A-3A RL-10A-3A RL-10A-3A RL-10A-4 RL-10A-3A RD-56... considered in this study, RL-50 and RL-60 (Table 4), do not... first-stage engine selection. Engine RL-50 RL-60 RD-57A-1 LR87...-down version of the original RL-10A-3A engine is used. Stage...] HAV-I RL-10A-3A∗ 103 100 ∗ 109 100 HAV-IIa RL-10A-3A 100 HAV-IIb RL-10A-3A∗ 107 Launch...



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..., the S-IV Stage and it’s RL 10 Engines, the J-2 Engine and... on the Saturn V, and the RL 10 on the Centaur vehicle... S-IV Stage simulating a LO2/LH2 RL 10 This was a lengthy calibration.../Saturn), J-2S (Apollo/ Saturn upgrades), RL-10, and TR-201 (all... mixture buildup. The LO2/LH2 RL 10 Engine, used on the... the new Pratt and Whitney RL 10B-2 Engine. The J-4 Test Cell... up to 300 sec. THE RL 10 ENGINE Probably the longest... in the U.S. has been the RL 10 Engine. Pratt and Whitney..., 1963 was powered by two RL 10A-3 engines. Our Centaur testing was... rotation at Engine Start. The RL 10 has been used in... I/S-IV Stage. There were six RL 10A-3 Engines on the Saturn 1/S-IV...-11 Engine Page32 The first RL 10A-1 Engine at 15,000 lbf... the major milestones in the RL 10’s illustrious history of applications... First Saturn flight with six RL-10A-3 engines (Saturn S-I / S-IV Stage) October... Atlas V. Two configurations of the RL 10 Engine are shown in Figure 35. Applications: RL 10B-2 used on Delta III... RL 10A-5 used on the McDonnell Douglas DC-X (throttleable down to 30 %) RL 10A-4-2 used as an Upper Stage engine on Atlas V RL 10A-4 used... Upper Stage RL 10A-3-3A used on Titan Centaur The RL 10 has... numerous NASA robotic missions. The RL 10 has placed more than... such a record. RL10B-2 The first RL 10A-1 Engine at 15,000 lbf... 35. Two Configurations of the RL 10 Engine Page34 Facility Supersonic... two test entries of the RL 10 Engine in AEDC’s J-4 Test.... The second entry tested the RL 10B-2 (FS1-10) version with... this test Figure 36. The RL 10B-2 Engine in J-4 Test Cell..., both of which use the RL 10 Engine. The Delta III... Cryogenic Engine (CECE) of the RL 10 family is shown being.... The DC-X, with its four RL 10 Engines, and the X-33... Stage Engine, Upper Stages with RL 10 Engines, see, e.g., [30], future... recently in successfully testing the RL 10B-2 Engine, benefitted the design...



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... pounds thrust each. The two RL-10 engines on Centaur produce... Two 16,500 pound thrust RL-10 en­ gines, 12 small... extensive earth Figure 2, Centaur stage: / — RL-10 engines; 2 — liquid oxygen tank... by Pratt & Whitney Aircraft, each RL-10 engine produces 16,500... a fuel pump but with the RL-10 en­ gines this step... produce added thrust. 11. The RL-10 has proven to be.... Another important feature of the RL-10 engines is that they.... CENTAUR ENGINE SYSTEM (ROCKET ENGINE RL-10) I. Look through the text...-180. 1. The Pratt & Whitney company's RL-10 (fig. 5), initially fired in... for a future Space Transfer Vehicle. RL-10 design work began in... satellites. By end 1990, 178 RL-lOs of all types had... gantry procedures and not on RL-10's operation. General Dynamics' review... penetrate. Before the second failure, RL-10 had achieved 190 flights.... By end of 1995, 246 RL-lOs of all types had... Centaur applications, clusters of six RL-10A-3 powered Saturn l's stage on six... during 1964/65. The original RL-10A-I model generated 66.72 kN....4 atm chamber pressure. The current RL-10 is available in the... transfer vehicles. The 93.4 kN RL-10B-2 gives improvement by increasing... 466.5 s; expansion ratio 285:1. The RL-10C-1, providing 156 kN using... simplifies the engine configuration. V" Figure 5. RL-10 propulsion system schematic: / — thrust... oxygen; с — liquid helium; d — gaseous helium 8. RL-10 has the turbopump feed... of its remaining energy. In RL-10 is used expander cycle... won a contract to provide four RL-10A-5 for single stage rocket technology... Atlas 2A/2AS versions incorporate RL-lOs improved to 92.5 kN... USAF XLR-129 engine The RL-10E version is developed for... rocket engine RL-10 Type RL10A-3-A3 specifications RL-IOA-4 - - RL-10A-5 RL-10 B-2 RL-10C... the questions. i. What type of RL-10 engine does carbon-carbon... closed cycle is used in RL-10 engine? 5. How is combustion.... 1. Когда началась разработка ракетного двигателя RL-10? 2. Что явилось причиной первых аварий двигателя RL-10? 3. Какие основные особенности двигательной... цикл используется в работе ракетного двигателя RL-10? 5. Какие факторы ограничивают повышение... турбины? 6. Какая модель ракетного двигателя RL-10 содержит выдвижной углепластиковый насадок.... Compare the main characteristics of RL-10 models and SSME. SUPPLEMENTARY.... Centaur Engine System (Rocket Engine RL-10) Supplementary Texts -^ ,Q 15 ~л Терминологический...



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... 7 MSW Pratt & Whitney RL-10 Engine Description • Created RL-10 model – Hard... 1% full thrust in testing – Used RL-10A-4 info . • Isp = 449 s, O/F = 5.5, p0 = 39... 8 MSW Descent Engine Comparisons • Altair RL-10 vs. Apollo LM Descent... • Logarithmic mass flux contour map RL-10A-4 PLUME CROSS SECTION, FIRST ATTEMPT... = 300 K) RL-10A-4 LUNAR SURFACE IMPINGEMENT SURFACE PRESSURE FROM 100 m ALTITUDE RL-10A-4 LUNAR....3 m RL-10A-4 LUNAR SURFACE IMPINGEMENT SURFACE SHEAR STRESS r FROM 100 m ALTITUDE RL-10A-4 LUNAR... possibility of incorporating – high-fidelity RL-10 lunar plume impingement computational...



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... эксплуатации фирмой Pratt&Whitney двигателя RL-10 и многочисленные проекты новых безгенераторных...:1 260 США (Pratt and Whitney) RL-60 267 4561 5,85 8 Centaur... двигателей: RL -10A-4-2, РД-0146Э, РД-0146, RL-10B-2, Vinci, MB-60, RL-60... на двух ЖРД: на RL-10B-2 (Рисунок 7) и RL-10A-4-2 (Рисунок 8). Еще на одном.... В ЖРД RL-10A-4-2 выдвижной насадок выполнен из ниобиевого сплава [6], а в двигателях RL-10B-2 [7] и РД... применен в 1998 году на двигателе RL-10B-2. Этот насадок изготавливается фирмой... перспективного европейского двигателя Vinci и американского RL-60 будут также разработаны и произведены... насадка из УУКМ ЖРД RL-10B-2 [7]. Рисунок 8. Двигатель RL-10A-4-2 с выдвижным сопловым насадком...



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... launch vehicle, and Pratt & Whitney’s RL-10A-4 engine used in the Atlas... LE-5B (left) and the RL-10A-4 (right). 3 American Institute of Aeronautics...,865 5.0 552 110 534 593 5.6 8.6 RL-10A-4 LOX/LH2 451 22,289... HPSS LE-5B LE-5B RL-10A-4 RL-10A-4 (Hohmann) (Grav (Hohmann) (Grav Assist... required 2,300 lb for the RL-10A-4 engine and 2,400 lb for...) LE-5B (Grav Assist) RL-10A-4 (Hohmann) RL-10A-4 (Grav Assist) XIPS Hall Thruster... LE-5B (Hohmann) LE-5B RL-10A-4 RL-10A-4 (Grav (Hohmann) (Grav Assist) Assist... LE-5B (Hohmann) LE-5B RL-10A-4 RL-10A-4 (Grav (Hohmann) (Grav Assist) Assist... times less propellant for the RL-10A-4 and LE-5B engines respectively... (Hohmann) LE-5B (Grav Assist) RL-10A-4 RL-10A-4 (Hohmann) (Grav Assist) Hall Thruster... lb of propellant for the RL-10A-4 and LE-5B respectively. The... LE-5B LE-5B (Grav RL-10A-4 RL-10A-4 (Hohmann) Assist) (Hohmann) (Grav Assist...



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... Engine Development – J-2S, XRS-2200, RL-60, MB-60 • Flight Engine Qualification, Certification – J-2, F-1, SSME, RS-68, RL-10, etc. • Flight Engine Acceptance... Prior to First Flight LMDE (U/S) RL-10A-1 (U/S) (Lander) 700 Klbf 250 Klbf... s 6,810 s in-work (i/w) Upgraded to RL-10A-3 N/A 726 2805 188 1730 707... Prior to First Flight LMDE (U/S) RL-10A-1 (U/S) (Lander) 700 Klbf 250 Klbf... s 6,810 s in-work (i/w) Upgraded to RL-10A-3 N/A 726 2805 188 1730 707...



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... one or two Pratt & Whitney RL-10A-4-2 engines. Selection for the SEC... launch vehicle to meet. The RL-10A-4-2 engine has the capability for... Second Stage (DCSS) with a single RL-10B-2 engine. Each Delta IV... DCSS design; 5-m fairing uses two RL-10B-2 engines **Rocket-grade kerosene... ULA – Common Centaur Upper Stage RL-10A4-2 30,384.03 kg...,631.77 kg ULA – DCSS RL-10B-2 29,418.24 kg... ULA – Common Centaur Upper Stage RL-10A4-2 117,169.94 kg...,820.59 kg ULA – DCSS RL-10B-2 111,013.20 kg... ULA – Common Centaur Upper Stage RL-10A4-2 51,114.93 kg...,426.14 kg ULA – DCSS RL-10B-2 48,839.41 kg... ULA – Common Centaur Upper Stage RL-10A4-2 12,502.06 kg...,023.79 kg ULA – DCSS RL-10B-2 12,067.44 kg... ULA – Common Centaur Upper Stage RL-10A4-2 70,492.94 kg...,349.28 kg ULA – DCSS RL-10B-2 66,948.93 kg... – Common Centaur Upper Stage RL-10A4-2 ULA – DCSS RL-10B-2 SpaceX – Falcon... – Common Centaur Upper Stage RL-10A4-2 ULA – DCSS RL-10B-2 SpaceX – Falcon... – Common Centaur Upper Stage RL-10A4-2 ULA – DCSS RL-10B-2 SpaceX – Falcon... this study, the Pratt & Whitney RL-10B-2 propulsion system required the... both mission profiles. Using the RL-10B-2 propulsion system, the required... Mars-direct approach. Using the RL-10B-2 propulsion system, the gross...



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... the analysis. Historic RS–68, RL–10, and SSME data was... altitude-start or an RL–10. The RL–10 was ruled out... were assumed necessary for the RL10A–4–2 engine to meet reliability and... be a new design utilizing the RL10A–4–2 engine modified as discussed in...–180 in a 4.3-m core, with four RL–10–4–A engines in the upper... 24,750 1 RL-10B-2 24,750 100.0 44,600 2 RL-10A-4-2 22,300... modified existing engines or designs (RL10A–4, 73-percent J–2S+, 81-percent... phase of comparison included the RL–10, LR–60, LR–85... LR-60 Exp Exp SBORSC RL-10A RD-180 SRB 4-Seg SRB... ExpExp SBORSC Exp Exp Exp RL-10A RD-180 Engine in Cycle... appropriate. Various versions of the RL–10 have more than 2 million... Cuts due to engine anomoly RL-10 35 30 25 RD... Exp LR-60 Exp Exp RL-10A SBORSC RD-180 Figure 6-71... Table 6-28. Uncertainty Measures Engine RL–10 LR–60 LR–85... that the SSME and the RL–10 are both operational and... containing the SSME, RS–68, J–2, RL–10, LR–60, and LR...–180 booster engines and four RL–10 upper stage engines, and...–68 booster engines and four RL–10 upperstage engines. Each system... upper stage outfitted with four RL–10 engines (designated LV 2) was... needed to human rate the RL–10 and current vehicle designs... by the MPS and the RL–10. This vehicle was not... a new upper stage with four RL–10 engines (designated LV 4), are... human rating the RS–68, RL–10, and overall vehicle. The.... Critical path items included the RL–10 engine, the MPS, and... various engines (LR–85, J–2, J–2S, RL–10), and • EELV options: Delta..., such as J–2, SSME, and the RL–10. The schedule analysis focused...