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  • 1
    Electronic Resource
    Electronic Resource
    Comparison of N-acetylcysteine and mesna as uroprotectors with ifosfamide combination chemotherapy in refractory germ cell tumors (1992)
    Springer
    Investigational new drugs 10 (1992), S. 159-163 
    Details
    ISSN: 1573-0646
    Keywords: uroprotectants ; mesna ; N-acetyl-cysteine ; germ cell tumor ; ifosfamide
    Source: Springer Online Journal Archives 1860-2000
    Topics: Chemistry and Pharmacology , Medicine
    Notes: Abstract From January 1983 through August 1988, 318 consecutive patients with refractory germ cell neoplasms were treated with ifosfamide-containing combination chemotherapy. The patients received ifosfamide at 1.2 gm/m2 day with cis-platin 20 mg/m2 day for 5 days and etoposide 75 mg/m2 day for 5 days or vinblastine 0.11 mg/kg on days 1 and 2 for each cycle. Of 277 evaluable patients, NAC was used as an uroprotector in the initial 86 patients while the latter 191 consecutive patients received mesna to reduce urothelial toxicity. Dosages of NAC was 2.0 gm po q 6 hr and for mesna 120 mg/m2 IV push prior to ifosfamide and then 1200 mg/m2/day as continuous infusion of 5 consecutive days. All patients received 3.0 liters of normal saline per day. The number of courses of chemotherapy given in the two groups were similar. Twenty-four of the 86 patients (27.9%) receiving NAC developed hematuria (13 patients — grade 1, 4 patients — grade 2, and 7 patients — grade 3 toxicity). While 8 out of 191 (4.2%) mesna patients developed hematuria (6 — grade 1 and 2 — grade 3) (p〈0.0001). The incidence of severity of renal toxicity was similar in the two groups. Ifosfamide dosage was reduced solely for urothelial toxicity in 11 patients receiving NAC compared with none of the patients receiving mesna (p〈0.0001). Chemotherapy response was similar in the two groups. In conclusion, mesna provides better urothelial protection from ifosfamide-induced toxicity than NAC and allows better maintenance of the drug dosage.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1007/BF00877240
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    Paper (German National Licenses)
    Fulltext
  • 2
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    Comparison of N-acetylcysteine and mesna as uroprotectors with ifosfamide combination chemotherapy in refractory germ cell tumors (1992)
    Springer
    Details
    Publication Date: 1992-08-01
    Print ISSN: 0167-6997
    Electronic ISSN: 1573-0646
    Topics: Chemistry and Pharmacology , Medicine
    Published by Springer
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    PAPER CURRENT
  • 3
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    GPS measured rates of deformation in the northern San Francisco Bay Region, California, 1990-1993 (1994)
    American Geophysical Union
    Details
    Publication Date: 1994-07-01
    Print ISSN: 0094-8276
    Electronic ISSN: 1944-8007
    Topics: Geosciences , Physics
    Published by American Geophysical Union
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    PAPER CURRENT
  • 4
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    TPS design for aerobraking at Earth and Mars (1991)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An investigation was made to determine the feasibility of using an aerobrake system for manned and unmanned missions to Mars, and to Earth from Mars and lunar orbits. A preliminary thermal protection system (TPS) was examined for five unmanned small nose radius, straight bi-conic vehicles and a scaled up Aeroassist Flight Experiment (AFE) vehicle aerocapturing at Mars. Analyses were also conducted for the scaled up AFE and an unmanned Sample Return Cannister (SRC) returning from Mars and aerocapturing into Earth orbit. Also analyzed were three different classes of lunar transfer vehicles (LTV's): an expendable scaled up modified Apollo Command Module (CM), a raked cone (modified AFT), and three large nose radius domed cylinders. The LTV's would be used to transport personnel and supplies between Earth and the moon in order to establish a manned base on the lunar surface. The TPS for all vehicles analyzed is shown to have an advantage over an all-propulsive velocity reduction for orbit insertion. Results indicate that TPS weight penalties of less than 28 percent can be achieved using current material technology, and slightly less than the most favorable LTV using advanced material technology.
    Keywords: THERMODYNAMICS AND STATISTICAL PHYSICS
    Type: NASA-TM-104739 , S-645 , NAS 1.15:104739
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    A preliminary TPS design for MRSR - Aerobraking at Mars and at earth (1990)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: An investigation was made to determine the feasibility of using an aerobrake system for an unmanned mission to Mars and for a return vehicle to earth. A preliminary thermal protection system (TPS) is examined for two small nose radius, straight biconic vehicles aerocapturing at Mars. The TPS for these vehicles, entering at 6 km/s and 8 km/s, are shown to have an advantage over a propulsive burn velocity reduction for orbit insertion. The TPS for each vehicle consisted of an ablator in the region of high heating, and reusable insulation over the rest of the structure. It was determined that a reusable TPS could be used over 98 percent of the aeroshell structure. Also presented is the preliminary TPS design for an Apollo-shaped vehicle aerocapturing at earth. As with the biconics, this vehicle had an ablator in the region of high heating, and reusable insulation on the aft conic section. In contrast to the vehicles aerocapturing at Mars, the ablator is used on 63 percent of the vehicle's aeroshell structure.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: AIAA PAPER 90-0052
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Thermal protection materials: Thermophysical property data (1992)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This publication presents a thermophysical property survey on materials that could potentially be used for future spacecraft thermal protection systems (TPS). This includes data that was reported in the 1960's as well as more current information reported through the 1980's. An attempt was made to cite the manufacturers as well as the data source in the bibliography. This volume represents an attempt to provide in a single source a complete set of thermophysical data on a large variety of materials used in spacecraft TPS analysis. The property data is divided into two categories: ablative and reusable. The ablative materials have been compiled into twelve categories that are descriptive of the material composition. An attempt was made to define the Arrhenius equation for each material although this data may not be available for some materials. In a similar manner, char data may not be available for some of the ablative materials. The reusable materials have been divided into three basic categories: thermal protection materials (such as insulators), adhesives, and structural materials.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-RP-1289 , S-693 , NAS 1.61:1289
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Analysis of the Shuttle Orbiter reinforced carbon-carbon oxidation protection system (1994)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Reusable, oxidation-protected reinforced carbon-carbon (RCC) has been successfully flown on all Shuttle Orbiter flights. Thermal testing of the silicon carbide-coated RCC to determine its oxidation characteristics has been performed in convective (plasma Arc-Jet) heating facilities. Surface sealant mass loss was characterized as a function of temperature and pressure. High-temperature testing was performed to develop coating recession correlations for predicting performance at the over-temperature flight conditions associated with abort trajectories. Methods for using these test data to establish multi-mission re-use (i.e., mission life) and single mission limits are presented.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TM-104792 , S-763 , NAS 1.15:104792
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Thermal Protection System design studies for lunar crew module (1993)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The results of a study to predict aeroheating and Thermal Protection System (TPS) requirements for manned entry vehicles returning to Earth from the moon are presented. The effects of vehicle size and lunar-return strategies on the aerothermodynamic environment and TPS design were assessed. Study guidelines were based on an Apollo Command Module (CM) configuration and lunar return strategies included direct entry and aerocapture followed by Low Earth Orbit entry (LEO). Convective heating was obtained by the boundary layer integral matrix procedure (BLIMP) code, and radiative heating was computed with the QRAD program. The AESOP-STAB code and the AESOP-THERM code were used for TPS analysis for ablating materials and nonablating materials respectively. Results indicated that there was an optimum size for minimum heating and that direct entry had higher heating rates than aerocapture. Aerocapture resulted in higher heat loads and TPS weight. The TPS weight factor was 6-8 percent for all lunar return strategies, with the TPS weight being about 50 percent less than that of the original Apollo CM vehicle.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 93-2843 , ; 9 p.|AIAA, Thermophysics Conference; Jul 06, 1993 - Jul 09, 1993; Orlando, FL; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    TSS-1 - Orbiter current and voltage experiments (1993)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Although the deployment distance of the TSS-1 tethered satellite was only about 1 percent of nominal, experiments to study the current collection and vehicle charging effects at low voltages were performed. We present measurements of Orbiter charging resulting from electron beam emission from the Orbiter, currents in the TSS system with and without electron beam emissions, and the effects of Orbiter thrusters on charging and currents. Generally, charging induced by beam emission was limited to a few volts, though during times with low ambient plasma density the Orbiter was charged up to 80 V. Thrusters are seen to enhance Orbiter charging during beam emission, and reduce ion current collection at other times.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 93-0702 , AIAA, Aerospace Sciences Meeting and Exhibit; Jan 11, 1993 - Jan 14, 1993; Reno, NV; United States|; 10 p.
    Format: text
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    NASA TECHNICAL REPORTS
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