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Details of astronaut zero gravity performance evaluation program including publication of handbook, fabrication of prototype hardware, and worksite performance data
Technical analyses and computer programs in support of optimization of liquid hydrogen thermal protection systems for nuclear Mars spacecraft
ObjectivesThe purpose of this study is to discuss technical aspects and rationales of magnetic resonance (MR)-guided cryoablation (CA) of Morton’s neuroma (MN); preliminary clinical experience is also retrospectively reviewed.MethodsProcedures were performed under local anaesthesia on an outpatient basis. Lesion size and location, procedural (technical success, procedural time, complications) and clinical outcomes (patient satisfaction according to a four-point scale, residual pain according to a 0–10 visual analogue scale and instances of “stump neuroma”) were assessed via chart review and cross-sectional telephone survey after the 20th case.ResultsTwenty patients (15 female, 5 male; mean age 50.3 years) were included; 24 MN (mean size 12.7 mm) were treated. Technical success was 100 %. Mean procedural time was 40.9 ± 10.4 min (range 35–60). One minor complication (superficial cellulitis) was reported (4.2 %). Follow-up (mean 19.7 months) was available for 18/24 MN. Patient satisfaction on a per-lesion basis was as follows: “completely satisfied” in 77.7 %, “satisfied with minor reservations” in 16.6 % and “satisfied with major reservations” in 5.7 % of cases. Mean pain score at last follow-up post-CA was 3.0. No instances of “stump neuroma” were reported.ConclusionsMR-guided CA of MN is a novel therapy which appears technically feasible. Clinical advantages of the procedure are high patient satisfaction, reduced risk of “stump neuroma” syndrome and good patient tolerance on an outpatient basis. Further, prospective studies are needed to confirm these encouraging results.
The concept development, testing, evaluation, and the selection of a final wheel design concept for a dual-mode lunar surface vehicle (DLRV) is detailed. Four wheel configurations were fabricated (one open wheel and three closed wheel) (and subjected to a series of soft soil, mechanical, and endurance tests. Results show that the open wheel has lower draw-bar pull (slope climbing) capability in loose soil due to its higher ground pressure and tendency to dig in at high wheel slip. Endurance tests indicate that a double mesh, fully enclosed wheel can be developed to meet DLRV life requirements. There is, however, a 1.0 to 1.8 lb/wheel weight penalty associated with the wheel enclosure. Also the button cleats used as grousers for the closed-type wheels result in local stress concentration and early fatigue failure of the wire mesh. Load deflection tests indicate that the stiffness of the covered wheel increased by up to 50% after soil bin testing, due to increased friction between the fabric and the wire mesh caused by the sand. No change in stiffness was found for the open wheel. The single woven mesh open wheel design with a chevron tread is recommended for continued development
A key area of the Small Modular Reactor (SMR) Probabilistic Risk Assessment (PRA) strategy is the development of methodologies and tools that will be used to predict the safety, security, safeguards, performance, and deployment viability of SMR systems starting in the design process through the operation phase. The goal of the SMR PRA activity will be to develop quantitative methods and tools and the associated analysis framework for assessing a variety of risks. These risks will be focused on SMR designs and operational strategies as they relate to the technical basis behind safety and security characterization.
The primary focus of the BDBE pilot project was the review of BDBE analysis and mitigation features at four DOE nuclear facilities representing a range of DOE sites, nuclear facility types/activities, and responsible program offices. The pilots looked at (1) how beyond design basis accidents were evaluated and documented in the facility Documented Safety Analysis, (2) potential BDBE vulnerabilities and margins to failure of facility safety features as obtained from general area and specific system walkdowns and design documents reviews, and (3) preparations made in facility and site emergency management programs to respond to severe accidents. It also evaluated whether draft BDBE guidance on safety analysis and emergency management could be used to improve the analysis of and preparations for mitigating severe and beyond design basis accidents. The details of these activities are organized in this report as described below.
Lunar flight handbook - orbital departure windows, libration points, and lunar flight orbit estimation, theory, and operations
Data acquisition and automatic data processing system for normative electroencephalographic reference tape library
Instrumentation program and data acquisition details of normative electroencephalographic reference library
Mission analysis computer programs for evaluating nuclear engine, vehicle system, and mission parameters for nuclear propulsion system applications in 1975-1990
Passive instrumentation and stimuli generation for Saturn IB equipment checkout - nondestructive testing
Neutral buoyancy simulation of zero gravity conditions encountered in space maintenance and repair
Design and fabrication of conical wheels for lunar surface vehicle
For abstract, see N74-19888.
The Stanford Watershed Model, the Kentucky Watershed Model and OPSET program, and the NASA-IBM system for simulation and analysis of watersheds are described in terms of their applications to the study of remote sensing of water resources. Specific calibration processes and input and output parameters that are instrumental in the simulations are explained for the following kinds of data: (1) hourly precipitation data; (2) daily discharge data; (3) flood hydrographs; (4) temperature and evaporation data; and (5) snowmelt data arrays. The Sensitivity Analysis Task, which provides a method for evaluation of any of the separate simulation runs in the form of performance indices, is also reported. The method is defined and a summary of results is given which indicates the values obtained in the simulation runs performed for Town Creek, Alabama; Alamosa Creek, Colorado; and Pearl River, Louisiana. The results are shown in tabular and plot graph form. For Vol. 1, see N74-27813.
The Model is described along with data preparation, determining model parameters, initializing and optimizing parameters (calibration) selecting control options and interpreting results. Some background information is included, and appendices contain a dictionary of variables, a source program listing, and flow charts. The model was operated on an IBM System/360 Model 44, using a model 2250 keyboard/graphics terminal for interactive operation. The model can be set up and operated in a batch processing mode on any System/360 or 370 that has the memory capacity. The model requires 210K bytes of core storage, and the optimization program, OPSET (which was used previous to but not in this study), requires 240K bytes. The data band for one small watershed requires approximately 32 tracks of disk storage.
The objectives and accomplishments were to adapt and apply the newly created database of Shuttle/Centaur ground operations. Previously defined turnaround operations analyses were to be updated for ground-based OTVs (GBOTVs) and space-based OTVs (SBOTVs), design requirements identified for both OTV and Space Station accommodations hardware, turnaround operations costs estimated, and a technology development plan generated to develop the required capabilities. Technical and programmatic data were provided for NASA pertinent to OTV round and space operations requirements, turnaround operations, task descriptions, timelines and manpower requirements, OTV modular design and booster and Space Station interface requirements. SBOTV accommodations development schedule, cost and turnaround operations requirements, and a technology development plan for ground and space operations and space-based accommodations facilities and support equipment. Significant conclusion are discussed.
The recent trial flights and acceptance tests of the Rohrbach "Romar," the largest seaplane in the world, have yielded results fully confirming the principles followed in its development. Its take-off weight of 19,000 kg, its beating the world record for raising the greatest useful load to 2000 m by almost 2500 kg and its remarkable showing in the seaworthiness tests are the results of intelligent researches, the guiding principles of which are briefly set forth in this article.