We discuss the various problems occurring when trying to fix a geoid or geopotential model using sea level observations sampled
during a limited time span from a bounded geographical domain. Such problems are on the one hand aliasing and spectral leakage,
and on the other, the non-conservation of matter over only part of the world ocean.
In the light of these issues we discuss whether it is sensible to include in a definition of the global geoid the radially
symmetric part of either the mean sea level field itself, or its linear or nonlinear time dependence, arriving at a negative
conclusion.
This revised version was published online in August 2006 with corrections to the Cover Date. 相似文献
Pair creation in relativistic double layers in shown to have consequences for the charge density in the double layer and the current flowing through it. 相似文献
Some sites for solar flares are known to develop where new magnetic flux emerges and becomes abutted against opposite polarity pre-existing magnetic flux (review by Galzauskas/1/). We have identified and analyzed the evolution of such flare sites at the boundaries of a major new and growing magnetic flux region within a complex of active regions, Hale No. 16918. This analysis was done as a part of a continuing study of the circumstances associated with flares in Hale Region 16918, which was designated as an FBS target during the interval 18 – 23 June 1980. We studied the initiation and development of both major and minor flares in Hα images in relation to the identified potential flare sites at the boundaries of the growing flux region and to the general development of the new flux. This study lead to our recognition of a spectrum of possible relationships of growing flux regions to flares as follows: (1) intimate interaction with adjacent old flux — flare sites centered at new/old flux boundary, (2) forced or “intimidated” interaction in which new flux pushes old field having lower flux density towards a neighboring old polarity inversion line where a flare then takes place, (3) “influential” interaction — magnetic lines of force over an old polarity inversion line, typically containing a filament, reconnect to the new emerging flux; a flare occurs with erupting filament when the magnetic field overlying the filament becomes too weak to prevent its eruption, (4) inconsequential interaction — new flux region is too small or has wrong orientation for creating flare conditions, (5) incidental — flare occurs without any significant relationship to new flux regions. 相似文献
General Dynamics has now flown all four versions of the Atlas commercial launch vehicle, which cover a payload weight capability to geosynchronous transfer orbit (GTO) in the range of 5000–8000 lb. The key analyses to set design and environmental test parameters for the vehicle modifications and the ground and flight test data that validated them were prepared in paper IAF-91-170 for the first version, Atlas I.
This paper presents similar data for the next two versions, Atlas II and IIA. The Atlas II has propellant tanks lengthened by 12 ft and is boosted by MA-5A rocket engines uprated to 474,000 lb liftoff thrust. GTO payload capability is 6225 lb with the 11-ft fairing. The Atlas IIA is an Atlas II with uprated RL10A-4 engines on the lengthened Centaur II upper stage. The two 20,800 lb thrust, 449 s specific impulse engines with an optional extendible nozzle increase payload capability to GTO to 6635 lb. The paper describes design parameters and validated test results for many other improvements that have generally provided greater capability at less cost, weight and complexity and better reliability. Those described include: moving the MA-5A start system to the ground, replacing the vernier engines with a simple 50 lb thrust on-off hydrazine roll control system, addition of a POGO suppressor, replacement of Centaur jettisonable insulation panels with fixed foam, a new inertial navigation unit (INU) that combines in one package a ring-laser gyro based strapdown guidance system with two MIL-STD-1750A processors, redundant MIL-STD-1553 data bus interfaces, robust Ada-based software and a new Al-Li payload adapter. Payload environment is shown to be essentially unchanged from previous Atlas vehicles. Validation of load, stability, control and pressurization requirements for the larger vehicle is discussed.
All flights to date (five Atlas II, one Atlas IIA) have been successful in launching satellites for EUTELSAT, the U.S. Air Force and INTELSAT. Significant design parameters validated by these flights are presented. Particularly noteworthy has been the performance of the INU, which has provided average GTO insertion errors of only 10 miles apogee, 0.2 miles perigee and 0.004 degrees inclination. It is concluded that Atlas II/IIA have successfully demonstrated probably the largest number of current state-of-the-art components of any expendable launch vehicle flying today. 相似文献
Space motion sickness has been estimated as affecting between 1/3 and 1/2 of all space flight participants. NASA has at the moment proposed a combination of promethazine and ephedrine (P/E) and one of scopolamine and dextroamphetamine (S/D), both given orally, as well as a transdermally applied scopolamine (TAS), as preventive and ameliorative measures. The reported double-blind study, tests the early phase actions and efficacy of the transdermal scopolamine (Transderm (TM)-V of ALZA Corporation) and compares these in detail to the oral medications. Motion sickness resistance was tested by standardized head movements while accelerating at 0.2 degree/sec2 to a maximum rotation of 240 degrees/sec, with an intermediate plateau of 10 min at 180 degrees/sec. To permit weighting motion sickness protection against other system influences, cardiovascular, psychological (subjective and objective), and visual parameter changes were documented for the three therapeutic modes. The relative impact of the various modalities on operational and experimental components of space missions is discussed. A comparison to intramuscularly administered promethazine (a backup therapeutic mode suggested for Space Shuttle use) is also included. 相似文献
The paper summarizes research into cost-effective propulsion system options for small satellites. Research into the primary cost drivers for propulsion systems is discussed and a process for resolving them is advanced. From this analysis, a new paradigm for understanding the total cost of propulsion systems is defined that encompasses nine dimensions – mass, volume, time, power, system price, integration, logistics, safety and technical risk. This paradigm is used to characterize all near-term propulsion technology options. From this effort, hybrid rockets emerges as a promising but underdeveloped technology with great potential for cost-effective application. A dedicated research program was completed to characterize this potential. This research demonstrated that hybrid rockets offer a safe, reliable upper stage option that is a versatile, cost-effective alternative to solid rocket motors. Finally, an innovative technique was derived to parametrically combine the diverse cost dimensions into a useful, quantifiable figure of merit for mission and research planning. Overall, it is shown that the most cost-effective solution is found by weighing all options along the nine dimensions of the cost paradigm within the context of a specific mission. 相似文献
Responding to the demand for a ‘faster, cheaper, better’ implementation of space related services. Dornier Satellitensysteme GmbH has established and exercised an approach for the development and production of satellites and the corresponding ground equipment for small missions, referred to as Flexbus. It allows to support space service customers starting from mission engineering via design, development and manufacturing of the necessary hardware, the launch service and ending with the hand-over of the operational system. Flexbus harmonises a modular component concept with a sound design and development approach, as a whole providing the means to offer high quality products in a fairly short time and for competitive pricing. This paper will outline the major features of the Flexbus approach and describe application examples. 相似文献
An overview of the solar wind termination shock is presented including: its place in the heliosphere and its origin; its structure including the role of interstellar pickup ions and galactic and anomalous cosmic rays; its inferred location based on Lyman- backscatter, Voyager radio signals, and anomalous cosmic rays; its shape and movement. 相似文献
The Advanced X-ray Astrophysics Facility (AXAF) planned for launch in the middle of the next decade will be a powerful new tool to enhance our understanding of the Universe. In this paper we describe the principal elements: the optics and the instruments. We review the instrument capabilities in order that potential users of AXAF may plan supporting research in the years prior to launch. We also review several of the scientific questions which AXAF is well suited to address. 相似文献
A method for measuring model forces in the shock tunnel by means of an acceleration-compensated balance has been reported by the authors.1 Since that time, a continuing program of research and development on advanced shock-tunnel instrumentation at Cornell Aeronautical Laboratory, Inc. has led to a promising new balance configuration. This balance is inherently more compact than previous designs, and allows testing of higher lift/drag (L/D) configurations than before. The increased high-pressure capability of the shock tunnel, and the growing recognition of the importance of the shock tunnel as a means of generating large Reynolds number flow, have thus added to the importance of this new higher load, more compact balance concept. An experimental balance has been built and calibrated. The performance of this balance is presented in this paper. 相似文献