Detailed studies of aviation fuel flowability

Six Jet A fuels, with varying compositions, were tested for low temperature flowability in a 190-liter simulator tank that modeled a section of a wing tank of a wide-body commercial airplane. The insulated tank was chilled by circulating coolant through the upper and lower surfaces. Flow-ability was determined as a function of fuel temperature by holdup, the fraction of unflowable fuel remaining in the tank after otherwise complete withdrawal. In static tests with subfreezing tank conditions, hold up varied with temperature and fuel composition. However, a general correlation of two or three classes of fuel type was obtained by plotting holdup as a function of the difference between freezing point and boundary-layer temperature, measured 0.6 cm above the bottom tank surface. Dynamic conditions of vibrations and slosh or rate of fuel withdrawal had very minor effects on holdup. Tests with cooling schedules to represent extreme, cold-day flights showed, at most, slight holdup for any combination of fuel type or dynamic conditions. Tests that superimposed external fuel heating and recirculation during the cooldown period indicates reduced hold up by modification of the low-temperature boundary layer. Fuel heating was just as effective when initiated during the later times of the tests as when applied continuously

Bearing optimization for SSME HPOTP application

The space shuttle main engine (SSME) high-pressure oxygen turbopumps (HPOTP) have not experienced the service life required of them. To improve the life of the existing turbopump bearings, modifications to the bearings that could be retrofitted into the present bearing cavity are being investigated. Several bearing parameters were optimized using the computer program SHABERTH, which performs a thermomechanical simulation of a load support system. The computer analysis showed that improved bearing performance is feasible if low friction coefficients can be attained. Bearing geometries were optimized considering heat generation, equilibrium temperatures, and relative life. Two sets of curvatures were selected from the optimization: an inner-raceway curvature of 0.54, an outer-raceway curvature of 0.52, and an inner-raceway curvature of 0.55, an outer-raceway curvature of 0.53. A contact angle of 16 deg was also selected. Thermal gradients through the bearings were found to be lower with liquid lubrication than with solid film lubrication. As the coolant flowrate through the bearing increased, the ball temperature decreased but at a continuously decreasing rate. The optimum flowrate was approximately 4 kg/s. The analytical modeling used to determine these feasible modifications to improve bearing performance is described

Calculation of the radiation hazard at supersonic aircraft altitudes produced by an energetic solar flare, 2

Radiation hazard calculations for supersonic aircraft altitudes produced by energetic solar flare of 23 Feb. 196

Three dimensional thermal analysis of rocket thrust chambers

A numerical model for the three dimensional thermal analysis of rocket thrust chambers and nozzles has been developed. The input to the model consists of the composition of the fuel/oxidant mixture and flow rates, chamber pressure, coolant entrance temperature and pressure, dimensions of the engine, materials and the number of nodes in different parts of the engine. The model allows for temperature variation in three dimensions: axial, radial and circumferential directions and by implementing an iterative scheme, it provides nodal temperature distribution, rates of heat transfer, hot gas and coolant thermal and transport properties

Combined State and Parameter Estimation for a Static Model of the Maypole (Hoop-Column) Antenna Suface

Parameter and state estimation techniques are discussed for an elliptic system arising in a developmental model for the antenna surface of the Maypole Hoop/Column antenna. A computational algorithm based on spline approximations for the state and elastic parameters is given and numerical results obtained using this algorithm are summarized

Parkes-CDSCC telemetry array: Equipment design

A unique combination of Deep Space Network (DSN) and non-DSN facilities in Australia provided enhanced data return from the Voyager spacecraft as it encountered the planet Uranus. Many of the key elements are duplicated from Voyager's encounters with Jupiter and Saturn. Some are unique extensions of that technology

FUTURE INTERESTS-WORTHIER TITLE DOCTRINE

Plaintiff created an irrevocable trust of $75,000, reserving the income to himself for life and directing distribution of the corpus upon his death to his heirs according to the California laws of succession in existence at his death. Later he sued to terminate the trust on the theory that since the worthier title doctrine prevented creation of a remainder in his heirs, he was sole beneficiary. The intermediate California appellate court held that the worthier title doctrine was inapplicable because of a California statute changing the word heirs from one of limitation to one of purchase. Therefore, the outstanding remainder in the heirs prevented termination of the trust. On appeal to the California Supreme Court, held, reversed. As a matter of construction, when the settlor created a life estate in himself with a limitation to his heirs he did not intend to create an interest in his heirs. Bixby v. California Trust Co., (Cal. 1949) 202 P. (2d) 1018

TAXATION-INCOME TAX-REALIZATION OF INCOME BY CORPORATION IN DISTRIBUTION OF NOTES TO SHAREHOLDERS

A corporation charged off notes as worthless prior to 1942. Anticipating future collections on the notes, the corporation distributed them as a dividend in kind. The commissioner determined that the amount collected subsequent to distribution was taxable to the corporation. The Tax Court held that no income was realized by the corporation. On appeal, held, reversed. This was not a distribution of capital assets but rather an assignment of anticipated income. Commissioner v. First State Bank of Stratford, (C.C.A. 5th, 1948) 168 F. (2d) 1004, certiorari denied, 335 U.S. 867, 69 S.Ct. 137 (1948)

DESCENT AND DISTRIBUTION - WIDOW\u27S STATUTORY SHARE - WIDOW ALLOWED TO ELECT AGAINST HUSBAND\u27S INTER VIVOS TRUST OF PROMISE UNDER SEAL

Eleven years before his death, H executed his bond under seal for $20,000 payable one year after his death. He delivered the bond to a trustee to hold upon an irrevocable trust to collect and pay the proceeds to named beneficiaries. Upon H\u27s death with a personal estate approximately equal to the amount of the bond, his widow elected to claim her statutory share in the estate, alleging that the bond was invalid. The trustee filed a bill alleging that the trust was sufficient to bar the widow, and the widow demurred. The demurrer was overruled by the trial court and the bond was held a valid claim. On appeal, held, reversed. The bond should be set aside as a fraud on the rights of the widow. Norris v. Barbour, (Va. 1949) 51 S.E. (2d) 334