WorldCat Identities


Works: 30 works in 44 publications in 1 language and 44 library holdings
Classifications: QD516,
Publication Timeline
Dynamics of two-phase flow in rocket nozzles by Sunnyvale, Calif United Technology Center( Book )

5 editions published between 1961 and 1964 in English and held by 5 WorldCat member libraries worldwide

An experimental and theoretical investigation is being conducted of the axial and radial velocity lag of a dispersed solid phase in accelerating gases. The program objective is to generate basic information and nozzle design criteria for the flow dynamics of the two-phase flow resulting from the combustion of metalized solid propellants. The correction of the particle size of molecularsieve powder used in calculation of the cold-flow differential nozzle flow has resulted in improved agreement of theory and experiment. Experimental studies of two-dimensional particle trajectories in nozzles (0.250 inch throat diameter), covering a large variety of conditions, have been performed. A theory to predict particle trajectories in the subsonic portion of nozzles has been developed and compared to experimental results. A preliminary study of the effect of particle radial velocity lag on characteristic velocity has been performed. (Author)
Development of propellants containing an energetic oxidizer( Book )

4 editions published between 1966 and 1967 in English and held by 4 WorldCat member libraries worldwide

United Technology Center (UTC) is conducting a 24-month program to produce the first practical propellants exploiting the high energy and favorable density of nitronium perchlorate (NP). In a previous program a curable binder system was developed and demonstrated using both uncoated and coated particulate NP. Propellants containing uncoated NP had a useful life of only a few days at room temperature, and those using Reta-coated NP were stable for a few months. Original plans for scaled-up motor firings and incorporation of energetic fuel appeared less desirable than emphasis on improvement of stability. During the period of contract redirection only limited effort was undertaken. Because of the unavailability of Reta-coated NP, emphasis has been placed on increasing the useful life of propellants containing uncoated or UTECOATED NP. Means to this end include development of more compatible ingredients and use of reduced temperatures for processing and storage. The latter approach requires methods of decreasing binder viscosity and increasing cure reactivity. Potentially useful hydrocarbon and nitroparaffin plasticizers have been found, and cure catalysis has been effected. Stability studies show that Reta-coated NP has a useful life of less than 1 year under mild storage conditions. Propellants containing UTECOATED NP exhibit unacceptable thermal stability and explosive combustion characteristics after about 1 week at ambient temperature
Hybrid propulsion system for an advanced rocket-powered target missile( Book )

3 editions published between 1966 and 1968 in English and held by 3 WorldCat member libraries worldwide

The objectives of this program are: (1) to demonstrate that low-cost hybrid propulsion units are capable of providing step thrust operation over an approximately 8 to 1 range, burning for durations of up to 7 min, and operating reliably under extreme environmental conditions of temperature and vibration; and (2) to provide hybrid propulsion units to be used in a flight demonstration program to prove the feasibility of a hybrid-powered target missile. The program will be conducted in four phases: phase I, design; phase II, development; phase III, system fabrication, assembly, and delivery; and phase IV, technical liaison. During this report period, a total of seven heavyweight motor firings were conducted, of which four were nozzle evaluation tests at boost thrust conditions and three were fuel grain insulation tests at sustain thrust conditions. The results of the initial nozzle evaluation tests have shown that the nozzle material and configuration can produce nozzle material erosion rates of from 0 to 5 mils/sec. Initial fuel grain insulation tests results have shown that silicon materials ablate at a rate of 2 mils/sec when exposed to the combustion chamber gases. In addition, a pyrogen igniter system was successfully developed, and performance has been verified at ambient temperature conditions
Thermochemistry of oxygen-fluorine bonding( Book )

3 editions published between 1961 and 1962 in English and held by 3 WorldCat member libraries worldwide

Study continued on the thermochemical data required to derive O-F bond energies for NO3F and ClO4F and establish the thermochemical properties of NO2F. Various oxygen fluorides, sulfur fluoride compounds, and fluorocarbon derivatives with O-F bond groupings were studied. The bond energies which were derived for O-F compounds show wide variati n depending on the relatively arbitrary assignment of energies to the other bonds of the molecules. (Author)

2 editions published in 1966 in English and held by 2 WorldCat member libraries worldwide

Work was continued on studying the cure problem of PBEP propellants. It now appears that a rapid reaction between the isocyanate curative and triol crosslinkers is the source of difficulty. It appears possible that this problem became enhanced by a change in PBEP during synthesis scaleup that resulted in a lower reactivity of the hydroxyl groups. Further investigations of the impact sensitivity of PBEP and PBEP propellants were made. No change in previously reported data was found, and it was concluded that neither PBEP nor propellant was unduly impact sensitive. Good cures were obtained on LMH-1/PBEP propellant. Stress of 121 psi and strain of 52% were obtained on an ambient cured system. Preparation of HAP-containing propellant requires a dry atmosphere throughout the complete operation. The cured propellant also must be protected from moisture. Surveillance studies of 2-in. cubes have indicated that DBTDA cure catalyst has better aging characteristics. (Author)
Characterization of wire-wound tungsten composite( Book )

2 editions published in 1970 in English and held by 2 WorldCat member libraries worldwide

The program was conducted to determine and extend the potential of wirewound tungsten composites for analysis, design, and fabrication of rocket hardware through characterization of its mechanical, thermal, chemical, and physical properties. Specimens, designed specifically for desired structural and thermal analytical properties, were fabricated by previously developed rocket nozzle techniques of plasma-spraying and filament reinforcement. Thermal and mechanical properties were determined for the temperature range of 70 to 4, 000F (21 to 2,210C). Residual test specimen material was evaluated to characterize physical and chemical properties of both as-composited and elevated temperature exposed wire-wound tungsten. Suitable test methods for nondestructive examinations were determined, and a material specification was prepared based on the program results
Vapor-phase combustion of beryllium and aluminum by Robert W Hermsen( Book )

2 editions published between 1964 and 1968 in English and held by 2 WorldCat member libraries worldwide

Experimental studies of the vapor-phase combustion of beryllium and aluminum were conducted using electrically vaporized wire as a source of high-temperature, high-pressure metal vapor. The effect of oxidizing atmospheres such as oxygen, water, and carbon dioxide in various mixtures and with inert diluents was investigated as well as the effect of total pressure from subatmospheric to 15 atm. Under all conditions, the beryllium oxide particles were produced in the form of regular hexagonal prisms, rather than spheres as in the case of aluminum oxide. The intensity of continuum and band radiation from aluminum and beryllium flames was investigated spectroscopically. The results showed that scattering of radiation by metal oxide particles had a strong effect on the spectral distribution of continuum radiation. A set of equations describing the condensation of beryllium or aluminum oxide droplets from an atmosphere containing metal vapor and oxygen was formulated and programmed for solution on a high-speed digital computer. Starting with a given mass fraction of metal vapor, condensation takes place both by nucleation of new particles and growth of all the particles in the system, until the partial pressure of metal vapor decreases to the equilibrium value. The time required for condensation and the resulting particle size distribution were calculated for different initial metal vapor concentrations and temperatures. (Author)
Oxide Scale Adherence Mechanisms( Book )

1 edition published in 1972 in English and held by 1 WorldCat member library worldwide

Combustion Instability Study of Solid Propellants( Book )

1 edition published in 1973 in English and held by 1 WorldCat member library worldwide

The rotating valve method of measuring the combustion response of solid propellants to small amplitude pressure oscillations were evaluated. The method is based on producing pressure oscillations in a small rocket motor by varying the area of a secondary exhaust nozzle in a periodic manner. This is accomplished by using a rotating value as the secondary orifice. The valve apparatus operates concurrently with a primary nozzle which controls the steady-state pressure. The frequency of the oscillations is determined by the rotational speed of the valve. A theoretical analysis was conducted to relate the combustion response function to measurable ballistic properties of the combustion chamber. (Modified author abstract)
Development of nondestructive testing techniques for large solid-propellant rocket motors( Book )

1 edition published in 1962 in English and held by 1 WorldCat member library worldwide

Contents: Relationship of chamber pressure to excess burning area Stress analysis of the propellant grain Defect analysis Determination of the pressure distribution in a propellant grain crack Temperature increase of the metal case resulting from premature exposure of the case insulation Method for determining the burning propellant surface area as a function of time based on an experimental combustion chamber pressure
Annual contractor's meeting on chemical kinetics of propulsion (7th), 11-12 august 1966( Book )

1 edition published in 1968 in English and held by 1 WorldCat member library worldwide

Abstracts are given for the reports on chemical kinetics of propulsions presented at the 7th annual AFOSR Contractor's meeting
An electron microscopy study of carbide precipitation in vanadium by Dwight Richard Diercks( Book )

in English and held by 1 WorldCat member library worldwide

Exploratory Development for the TECHROLL (Trade Name) Seal Movable Nozzle System. Volume I( Book )

1 edition published in 1973 in English and held by 1 WorldCat member library worldwide

The seal is a constant-volume, fluid-filled bearing configured with a pair of rolling convolutes that permits omniaxis deflection of a rocket motor nozzle. The fluid-filled bearing is pressurized by nozzle ejection loads and serves as both the movable nozzle seal. The TECHROLL seal is made of a fabric-reinforced elastomeric composite material and does not require complex manufacturing processes or tight tolerances. United Technology Center, under contract to the Air Force Rocket Propulsion Laboratory, has conducted a three-phase exploratory development program for the seal. This report covers only phase I and phase II activities. During these two phases, seal material evaluation was completed, and demonstration motor tests of a high-pressure tactical system movable nozzle and a movable nozzle for a second-stage Minuteman motor were conducted at the Air Force Rocket Propulsion Laboratory. Each movable nozzle system was characterized by bench testing prior to firing. Torques, spring rates, and dynamic response characteristics were identified and later verified during static motor tests. in addition, an analytical model describing seal characteristics was developed. All static motor firings were completely successful and verified the performance predictability and low torque characteristics of the seal. (Author)
Development of nondestructive testing techniques large solid-propellant rocket motors. feasibility of low-frequency ultrasonics for detection of propellant-liner unbonds( Book )

1 edition published in 1963 in English and held by 1 WorldCat member library worldwide

Ultrasonic techniques for detecting propellant liner unbonds are reported. A detailed de scription of the ultrasonic equipment is given. The work was carried out using the 120-inch diameter segment containing known defects which was manufactured under this contract. (Author)
Demonstration of an advanced solid propellant. addendum( Book )

1 edition published in 1967 in English and held by 1 WorldCat member library worldwide

At the end of the primary technical effort on this program, a number of specimens were in storage for evaluation after an extended storage period. The specimens to be evaluated included a segment of a TM-3 test motor (6-in. web), analog physical property motors, tensile specimens, and 2-in. propellant cubes. The TM-3 motor grain developed fissures in less than 6 months. The analog motors swelled sufficiently to preclude internal bore measurements, thus eliminating the analog motor thermal test. Tests of tensile specimens stored up to 1 year at 25 and 35 C including propellant batches containing magnesium-treated LMH-1 and standard LMH-1 revealed no effects on physical property stability that might be attributed to LMH-1, nor was there any noticeable difference in behavior between the two types of LMH-1. A comparison of propellant formulations (UTP-6814 and UTP-8812) based on the evaluation of 2-in. cubes stored for periods up to 2 years clearly established the superiority of the polyester binder system over the UTEFLEX binder system at the current state of development. Dubes of propellant formulation UTP-6814 stored for 2 years at 95 F and 0 percent relative humidity remained in excellent condition

1 edition published in 1967 in English and held by 1 WorldCat member library worldwide

The AFRPL, RTD, Edwards, California, is sponsoring a program which is directed toward the demonstration of the capabilities of UTC's wire-wound plasma-spray bonded tungsten nozzle inserts. For this program, Advanced Wire-Wound Tungsten Nozzles, three nozzle inserts are to be designed, fabricated, and tested. During the third quarter of this program, the first two nozzle assemblies were completed, viz, the thick-block and thin-shell configurations, in that order. The thick-block assembly as test fired at Atlantic Research Corporation's facilities on 4 October 1955. Test results are included in this report
Combustion termination system for 120-inch-diameter solid rocket motor (titan iii-c)( Book )

1 edition published in 1965 in English and held by 1 WorldCat member library worldwide

An investigation was made of combustion termination of solid propellant motors by liquid injection. The program consists of four tasks, which include laboratory and small-motor testing, subscale testing, and system demonstration in a 120-in.-diameter solid-propellant motor. A total of 4 laboratory motor and 19 small-motor (TM-1) tests were performed to evaluate several injection systems and to provide data for the study of the fundamental phenomena of combustion termination by liquid injection. In addition, 22 laboratory cold flow tests were conducted to evaluate injector flow patterns. As a result of these tests, a pintle-type injector was selected for further evaluation in the subscale (TM-3A) motor firings. Data obtained during the test program have been analyzed, and a correlation between the requirements of water flow rate and total water quantity and the motor ballistic properties was established. (Author)
Compilation of abstracts, 2nd afosr combined contractors meeting on combustion dynamics research, august 8-10, 1966( Book )

1 edition published in 1966 in English and held by 1 WorldCat member library worldwide

The report consists of a collection of abstracts of the numerous research progress reports given by AFOSR contractors. These papers presented over a two-day period composed the 2nd Annual Meeting on Combustion Dynamics Research. Each paper was grouped under one of three major subject headings: Advanced Air Breathing Combustion, Liquid Propellant Rocket Combustion, or Solid Propellant Rocket Combustion. (Author)

1 edition published in 1966 in English and held by 1 WorldCat member library worldwide

A PBEP/TVOPA/AP/AL propellant has been successfully scaled up to 1- and 4-lb motors. This formulation delivered 256.4 sec and 260.0 sec (0 half-angle, 1000 - 14.7 psi) in 1 - and 4-lb motors, respectively. This represented a specific impulse efficiency of 96.5% and 97.8% for the two motors. Extrapolation of the mass discharge curve predicts an efficiency of 98.2% at about 40 lb/sec mass discharge rate. Using the most pessimistic calculation method reduces these efficiencies by only 0.9%. Physical property evaluation gave a crosshead tensile of 110 psi and an elongation of 36.4%. Tensile properties were demonstrated to be easily variable by modifications of curative and catalyst. Hazard evaluation studies on the PBEP/TVOPA/AP/Al propellant gave impact values ranging from 9.0 to 14.2 kg-cm. Spark sensitivity of the propellant was greater than 10 joules. Autoignition values were 540 and 470 F for the 10-sec and 30-sec times. The card-gap sensitivity was greater than 119.6 cards in the micro card-gap test. (Author)
Combustion study of light metal based fuels( Book )

1 edition published in 1966 in English and held by 1 WorldCat member library worldwide

United Technology Center is conducting a research program to investigate the effect of formulation variables on the combustion behavior of light metal hydrides. The present investigation is intended to provide a fundamental understanding of the mechanism of combustion under conditions as nearly free of formulation limitations as possible. Design work and procurement of hardware have been completed and a four-phase program is in progress, as follows: Phase I. Construction of apparatus. Hardware procurement is complete and final assembly is in progress; Phases II and III. Investigation of combustion mechanisms of two light metal hydrides to be conducted concurrently upon completion of Phase I. Phase IV. Development of a mathematical model. This phase is being conducted concurrently with the other phases. (Author)
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English (34)