The X-43A Six Degree of Freedom Monte Carlo Analysis

This report provides an overview of the Hyper-X research vehicle Monte Carlo analysis conducted with the six-degree-of-freedom simulation. The methodology and model uncertainties used for the Monte Carlo analysis are presented as permitted. In addition, the process used to select hardware validation test cases from the Monte Carlo data is described. The preflight Monte Carlo analysis indicated that the X-43A control system was robust to the preflight uncertainties and provided the Hyper-X project an important indication that the vehicle would likely be successful in accomplishing the mission objectives. The X-43A inflight performance is compared to the preflight Monte Carlo predictions and shown to exceed the Monte Carlo bounds in several instances. Possible modeling shortfalls are presented that may account for these discrepancies. The flight control laws and guidance algorithms were robust enough as a result of the preflight Monte Carlo analysis that the unexpected in-flight performance did not have undue consequences. Modeling and Monte Carlo analysis lessons learned are presented

Ground-recorded sonic boom signatures of F-18 aircraft formation flight

Two F-18 aircraft were flown, one above the other, in two formations, in order for the shock systems of the two aircraft to merge and propagate to the ground. The first formation had the canopy of the lower F-18 in the inlet shock of the upper F-18 (called inlet-canopy). The flight conditions were Mach 1.22 and an altitude of 23,500 ft. An array of five sonic boom recorders was used on the ground to record the sonic boom signatures. This paper describes the flight test technique and the ground level sonic boom signatures. The tail-canopy formation resulted in two, separated, N-wave signatures. Such signatures probably resulted from aircraft positioning error. The inlet-canopy formation yielded a single modified signature; two recorders measured an approximate flattop signature. Loudness calculations indicated that the single inlet-canopy signatures were quieter than the two, separated tail-canopy signatures. Significant loudness occurs after a sonic boom signature. Such loudness probably comes from the aircraft engines

The X-43A (Hyper-X) Flies Into the Record Books

The goal of the Hyper-X research program, conducted jointly by the NASA Dryden Flight Research Center and the NASA Langley Research Center, was to demonstrate and validate the technology, experimental techniques, and computation methods and tools for design and performance predictions of a hypersonic aircraft with an airframe-integrated, scramjet propulsion system. Three X-43A airframe-integrated, scramjet research vehicles were designed and fabricated to achieve that goal by flight test: two test flights at Mach 7 and one test flight at Mach 10. The first flight, conducted on June 2, 2001, experienced a launch vehicle failure and resulted in a 9-month mishap investigation. A two-year return-to-flight effort ensued and concluded when the second Mach 7 flight was successful on March 27, 2004. Just eight months later, on November 16, the X-43A successfully completed the third and final flight. These two flights were the first flight demonstrations, at Mach 7 and Mach 10 respectively, of an airframe-integrated, scramjet-powered, hypersonic vehicle

Determination of stores pointing error due to wing flexibility under flight load

The in-flight elastic wing twist of a fighter-type aircraft was studied to provide for an improved on-board real-time computed prediction of pointing variations of three wing store stations. This is an important capability to correct sensor pod alignment variation or to establish initial conditions of iron bombs or smart weapons prior to release. The original algorithm was based upon coarse measurements. The electro-optical Flight Deflection Measurement System measured the deformed wing shape in flight under maneuver loads to provide a higher resolution database from which an improved twist prediction algorithm could be developed. The FDMS produced excellent repeatable data. In addition, a NASTRAN finite-element analysis was performed to provide additional elastic deformation data. The FDMS data combined with the NASTRAN analysis indicated that an improved prediction algorithm could be derived by using a different set of aircraft parameters, namely normal acceleration, stores configuration, Mach number, and gross weight

Изучение резонансного взаимодействия в многоатомной молекуле С2Н2D2- cis, основанное на высокоточных экспериментальных данных сильнорезонирующих полос: v10, v8, v7, v4, v6, v12, 2v10

Известно, что молекула этилена является естественной компонентой атмосферного воздуха, участвующей в процессах атмосферной химии и формировании глобального климата. Он играет значительную роль в химии тропосферы и генерации озона. Вследствие вышесказанного в течение многих лет спектры высокого разрешения этилена и его изотопологов являлись предметом пристального внимания. Однако, работ по изучению инфракрасных спектров молекулы cis-C2H2D2 ограниченное количество.Данная работа направлена на изучение спектров высокого разрешения молекулы cis-C2H2D2 в диапазоне 600-1200см-1.В результате исследования спектров определили количество найденных переходов в 2 раза больше с max квант. числами J и Ka, чем были определены в ранних работах. Следует отметить, что полосы ν10, v4 были исследованы впервыеEthylene is a naturally occurring compound in ambient air that affects atmospheric chemistry and the global climate. It plays a significant role in tropospheric chemistry and ozone generation. Therefore in recent years, HR infrared studies of ethylene and eseveral isotopic species have led to a better understanding of its molecular structure. However, high-resolution infrared investigation on cis-C2H2D2 remains limited. This master thesis is focused on the study of high resolution spectra of cis-d2-ethylene molecule in 600-1200 cm-1. As the result of analysis of the experimentally recorded spectra we were able to assign about two times more transitions with higher values of quantum number J and Ka than it was made before. The ν10, v4 and v8 bands were studied at the first time

Анализ влияния физико-химических методов воздействия на продуктивные пласты Ямбургского нефтегазоконденсатного месторождения (ЯНАО)

Во введении раскрывается актуальность выбранной темы, цель и задачи выпускной квалификационной работы. В первой главе изложены теоретические основы методов воздействия, список методов, способы и технологии их проведения и влияние на пласт. Во второй главе дана характеристика изучаемого месторождения. Описана нефтегазоносность месторождения, характеристика коллектора и добываемого газа. В третьей главе проанализированы методы воздействия, применяемые на пласт на ЯНГКМ. В четвертой главе представлен анализ стоимости проведения ГРП. В пятой главе проведен анализ влияния вредных факторов и методы их избежания.The introduction reveals the relevance of the selected topic, the purpose and objectives of the final qualification work. The first chapter sets out the theoretical foundations of impact methods, methods and technologies for their implementation and the effect on the formation. The second chapter describes the studied field. The oil and gas content of the field, the characteristics of the reservoir and produced gas are described. The third chapter analyzes the methods of action applied to the reservoir. The fourth chapter presents an analysis of the cost of hydraulic fracturing. The fifth chapter analyzes the influence of harmful factors and methods of avoidance

The X-43A Hyper-X Mach 7 Flight 2 Guidance, Navigation, and Control Overview and Flight Test Results

The objective of the Hyper-X program was to flight demonstrate an airframe-integrated hypersonic vehicle. On March 27, 2004, the Hyper-X program team successfully conducted flight 2 and achieved all of the research objectives. The Hyper-X research vehicle successfully separated from the Hyper-X launch vehicle and achieved the desired engine test conditions before the experiment began. The research vehicle rejected the disturbances caused by the cowl door opening and the fuel turning on and off and maintained the engine test conditions throughout the experiment. After the engine test was complete, the vehicle recovered and descended along a trajectory while performing research maneuvers. The last data acquired showed that the vehicle maintained control to the water. This report will provide an overview of the research vehicle guidance and control systems and the performance of the vehicle during the separation event and engine test. The research maneuvers were performed to collect data for aerodynamics and flight controls research. This report also will provide an overview of the flight controls related research and results