Готові списки джерел за темами / Space mechanism in-flight testing

Зміст

Статті в журналах

Добірка наукової літератури з теми "Space mechanism in-flight testing"

Автор: Grafiati

Опубліковано: 11 березня 2023

Оформте джерело за APA, MLA, Chicago, Harvard та іншими стилями

Оберіть тип джерела:

Ознайомтеся зі списками актуальних статей, книг, дисертацій, тез та інших наукових джерел на тему "Space mechanism in-flight testing".

Біля кожної праці в переліку літератури доступна кнопка «Додати до бібліографії». Скористайтеся нею – і ми автоматично оформимо бібліографічне посилання на обрану працю в потрібному вам стилі цитування: APA, MLA, «Гарвард», «Чикаго», «Ванкувер» тощо.

Також ви можете завантажити повний текст наукової публікації у форматі «.pdf» та прочитати онлайн анотацію до роботи, якщо відповідні параметри наявні в метаданих.

Статті в журналах з теми "Space mechanism in-flight testing"

Taylor, Gerald R., and Robert P. Janney. "In vivo testing confirms a blunting of the human cell-mediated immune mechanism during space flight." Journal of Leukocyte Biology 51, no. 2 (1992): 129–32. http://dx.doi.org/10.1002/jlb.51.2.129.

Повний текст джерела

Стилі APA, Harvard, Vancouver, ISO та ін.

Huber, F. W., P. D. Johnson, O. P. Sharma, J. B. Staubach, and S. W. Gaddis. "Performance Improvement Through Indexing of Turbine Airfoils: Part 1—Experimental Investigation." Journal of Turbomachinery 118, no. 4 (1996): 630–35. http://dx.doi.org/10.1115/1.2840918.

Повний текст джерела

Анотація:

This paper describes the results of a study to determine the performance improvements achievable by circumferentially indexing successive rows of turbine stator airfoils. An experimental/analytical investigation has been completed that indicates significant stage efficiency increases can be attained through application of this airfoil clocking concept. A series of tests was conducted at the National Aeronautics and Space Administration’s (NASA) Marshall Space Flight Center (MSFC) to experimentally investigate stator wake clocking effects on the performance of the Space Shuttle Main Engine Alternate Fuel Turbopump Turbine Test Article. Extensive time-accurate Computational Fluid Dynamics (CFD) simulations have been completed for the test configurations. The CFD results provide insight into the performance improvement mechanism. Part one of this paper describes details of the test facility, rig geometry, instrumentation, and aerodynamic operating parameters. Results of turbine testing at the aerodynamic design point are presented for six circumferential positions of the first stage stator, along with a description of the initial CFD analyses performed for the test article. It should be noted that first vane positions 1 and 6 produced identical first to second vane indexing. Results obtained from off-design testing of the “best” and “worst” stator clocking positions, and testing over a range of Reynolds numbers are also presented. Part two of this paper describes the numerical simulations performed in support of the experimental test program described in part one. Time-accurate Navier–Stokes flow analyses have been completed for the five different turbine stator positions tested. Details of the computational procedure and results are presented. Analysis results include predictions of instantaneous and time-average midspan airfoil and turbine performance, as well as gas conditions throughout the flow field. An initial understanding of the turbine performance improvement mechanism is described.

Стилі APA, Harvard, Vancouver, ISO та ін.

Z˙bikowski, Rafał, Cezary Galin´ski, and Christopher B. Pedersen. "Four-Bar Linkage Mechanism for Insectlike Flapping Wings in Hover: Concept and an Outline of Its Realization." Journal of Mechanical Design 127, no. 4 (2005): 817–24. http://dx.doi.org/10.1115/1.1829091.

Повний текст джерела

Анотація:

This paper describes the concept of a four-bar linkage mechanism for flapping wing micro air vehicles and outlines its design, implementation, and testing. Micro air vehicles (MAVs) are defined as flying vehicles ca. 150 mm in size (handheld), weighing 50–100 g, and are developed to reconnoiter in confined spaces (inside buildings, tunnels, etc.). For this application, insectlike flapping wings are an attractive solution and, hence, the need to realize the functionality of insect flight by engineering means. Insects fly by oscillating (plunging) and rotating (pitching) their wings through large angles, while sweeping them forward and backward. During this motion, the wing tip approximately traces a figure eight and the wing changes the angle of attack (pitching) significantly. The aim of the work described here was to design and build an insectlike flapping mechanism on a 150 mm scale. The main purpose was not only to construct a test bed for aeromechanical research on hover in this mode of flight, but also to provide a precursor design for a future flapping-wing MAV. The mechanical realization was to be based on a four-bar linkage combined with a spatial articulation. Two instances of idealized figure eights were considered: (i) Bernoulli’s lemniscate and (ii) Watt’s sextic. The former was found theoretically attractive, but impractical, while the latter was both theoretically and practically feasible. This led to a combination of Watt’s straight-line mechanism with a drive train utilizing a Geneva wheel and a spatial articulation. The actual design, implementation, and testing of this concept are briefly described at the end of the paper.

Стилі APA, Harvard, Vancouver, ISO та ін.

Merriam, E. G., J. E. Jones, S. P. Magleby, and L. L. Howell. "Monolithic 2 DOF fully compliant space pointing mechanism." Mechanical Sciences 4, no. 2 (2013): 381–90. http://dx.doi.org/10.5194/ms-4-381-2013.

Повний текст джерела

Анотація:

Abstract. This paper describes the conception, modeling, and development of a fully compliant two-degree-of-freedom pointing mechanism for application in spacecraft thruster, antenna, or solar array systems. The design objectives and the advantages of a compliant solution are briefly discussed. Detailed design decisions to meet project objectives are described. Analytical and numerical models are developed and subsequently verified by prototype testing and measurements in several iterations. A final design of the 3-D printed titanium monolithic pointing mechanism is described in detail and its performance is measured.

Стилі APA, Harvard, Vancouver, ISO та ін.

ZHAO Hai-bo, 赵海波, 赵伟国 ZHAO Wei-guo, 董吉洪 DONG Ji-hong, et al. "Accuracy analysis and testing for secondary mirror adjusting mechanism in large space telescope." Optics and Precision Engineering 27, no. 11 (2019): 2374–83. http://dx.doi.org/10.3788/ope.20192711.2374.

Повний текст джерела

Стилі APA, Harvard, Vancouver, ISO та ін.

Michaels, Dan, and Alon Gany. "Modeling and testing of a tube-in-tube separation mechanism of bodies in space." Acta Astronautica 129 (December 2016): 214–22. http://dx.doi.org/10.1016/j.actaastro.2016.09.013.

Повний текст джерела

Стилі APA, Harvard, Vancouver, ISO та ін.

Wang, Junwei, Lei Zhang, Guohua Li, et al. "Research and Verification of Key Techniques in the Simulation of Space Extremely Rapid Decompression in Millisecond." International Journal of Aerospace Engineering 2021 (April 5, 2021): 1–11. http://dx.doi.org/10.1155/2021/6634468.

Повний текст джерела

Анотація:

The research of rapid decompression with its effect assessment and protection technology is the problem that must be faced by the future exploration projects such as near space exploration, deep space exploration, and long-term lunar or Mars base. A new reusable quick opening mechanism which can be opened in millisecond is designed to meet the testing requirement of ground simulator for extremely rapid decompression, and the testing results show that the quick opening mechanism can be opened within 0.1 s. The mathematical formulation is also developed, and the comparisons with the results from the literature demonstrate its validity. The CFD simulation and the verification system are established for the airflow in the rapid decompression process under different opening degrees. The simulation results show that the effect of the opening on the decompression process is very obvious and the decompression time corresponding to 50%, 75%, and 100% opening is 479.1 ms, 320.7 ms, and 290.1 ms, respectively. The testing results also show a consistent trend which is 583 ms, 450 ms, and 384 ms, respectively, to reach the equilibrium state.

Стилі APA, Harvard, Vancouver, ISO та ін.

Hymer, W. C., R. E. Grindeland, T. Salada, P. Nye, E. J. Grossman, and P. K. Lane. "Experimental modification of rat pituitary growth hormone cell function during and after spaceflight." Journal of Applied Physiology 80, no. 3 (1996): 955–70. http://dx.doi.org/10.1152/jappl.1996.80.3.955.

Повний текст джерела

Анотація:

Space-flown rats show a number of flight-induced changes in the structure and function of pituitary growth hormone (GH) cells after in vitro postflight testing (W. C. Hymen, R. E. Grindeland, I. Krasnov, I, Victorov, K. Motter, P. Mukherjee, K. Shellenberger, and M. Vasques. J. Appl. Physiol. 73, Suppl.: 151S-157S, 1992). To evaluate the possible effects of microgravity on growth hormone (GH) cells themselves, freshly dispersed rat anterior pituitary gland cells were seeded into vials containing serum +/- microM hydrocortisone (HC) before flight. Five different cell preparations were used: the entire mixed-cell population of various hormone-producing cell types, cells of density < 1.071 g/cm3 (band 1), cells of density > 1.071 g/cm3 (band 2), and cells prepared from either the dorsal or ventral part of the gland. Relative to ground control samples, bioactive GH released from dense cells during flight was reduced in HC-free medium but was increased in HC-containing medium. Band 1 and mixed cells usually showed opposite HC-dependent responses. Release of bioactive GH from ventral flight cells was lower; postflight responses to GH-releasing hormone challenge were reduced, and the cytoplasmic area occupied by GH in the dense cells was greater. Collectively, the data show that the chemistry and cellular makeup of the culture system modifies the response of GH cells to microgravity. As such, these cells offer a system to identify gravisensing mechanisms in secretory cells in future microgravity research.

Стилі APA, Harvard, Vancouver, ISO та ін.

Konovalov, A. M., and V. I. Kugushev. "Mechanism of excitatioon of natural vibrations of fireclay products and its application in flaw detection." NOVYE OGNEUPORY (NEW REFRACTORIES), no. 10 (November 25, 2022): 55–62. http://dx.doi.org/10.17073/1683-4518-2022-10-55-62.

Повний текст джерела

Анотація:

In this article, using the example of developing a technique for non-destructive testing of a fireclay product («asterisks») using the natural vibrations of the object of control, a mathematical model is presented that allows us to specifically describe the process of converting an external dynamic effect into the natural vibrations of the part. The peculiarity of the model is that, firstly, it is a carrier of the free energy of elastic deformation and the process of natural oscillations is formed in it. Secondly, the model is a Riemannian space in which all dynamic parameters are constant and reduced to zero, i.e. the model does not exist physically, but only as a functional space. The proposed model can serve as an effective tool for analyzing the processes observed during non-destructive testing and vibration diagnostics. Ill. 7. Ref. 22.

Стилі APA, Harvard, Vancouver, ISO та ін.

Zhou, Hongming, Peiyuan Li, Longfei Wu, and Qiankun Gao. "A wavelet analysis-based matching pursuit algorithm for an accurate ultrasonic TOFD measurement." Insight - Non-Destructive Testing and Condition Monitoring 62, no. 11 (2020): 662–68. http://dx.doi.org/10.1784/insi.2020.62.11.662.

Повний текст джерела

Анотація:

The time-of-flight diffraction (TOFD) technique is used as an important non-destructive testing method in weld integrity evaluation and failure analysis. However, an accurate measurement of the time-of-flight (TOF) has proven to be difficult due to the low time resolution of the measured signal. Conventional deconvolution techniques have been used to improve the time resolution of the signal but are not effective for ultrasonic TOFD signals because the frequency contents of the signals are non-static in space-frequency distribution. To overcome this problem, a method is proposed in this paper that estimates the TOF in two steps. In the first step, the measured signal is decomposed into a series of narrowband signals using a wavelet transform and an atom dictionary is adaptively established according to the characteristics of a selected narrowband signal. In the second step, matching pursuit (MP) is used to derive a sparse representation of the selected narrowband signal. A steel specimen with artificial defects is prepared, experiments are carried out and the results confirm the efficacy of the proposed algorithm.

Стилі APA, Harvard, Vancouver, ISO та ін.

Більше джерел

Ми пропонуємо знижки на всі преміум-плани для авторів, чиї праці увійшли до тематичних добірок літератури. Зв'яжіться з нами, щоб отримати унікальний промокод!