Showing papers on "Solid-fuel rocket published in 1974"
147 citations
TL;DR: In this article, it was shown that the acceleration of the shear wave is strongly influenced by the mean flow due to propellant combustion; for larger values of burning surface Mach number, the speed of propagation approaches that of the combustion gases.
70 citations
01 Aug 1974
TL;DR: In this paper, a finite difference procedure has been substituted for the method of characteristics solution of the governing equations of motion, and the range of allowable motor and grain geometries has been greatly extended.
Abstract: : The primary objective of the current effort was to improve the utility, efficiency and accuracy of the previously developed nonlinear longitudinal combustion instability program. A finite difference procedure has been substituted for the method of characteristics solution of the governing equations of motion. The range of allowable motor and grain geometries has been greatly extended. In addition, the two-phase analysis has been extended to multiple particle sizes. A comparison with data from a small laboratory pulse motor has demonstrated that the present nonlinear model is capable of quantitatively predicting limiting amplitude when the combustion response of the propellant is adequately characterized. The program has also been modified to make it applicable to T-burners. A vent model which accounts for acoustic radiation losses has been developed. Separate nonlinear particle damping and uncoupled nonlinear combustion response studies have been carried out. (Modified author abstract)
33 citations
01 Mar 1974
TL;DR: In this article, the authors investigate the complex coupling between the chamber flow conditions and the solid propellant combustion process, which may lead to large amplitude longitudinal instabilities, leading to increased mean chamber pressure and burning rate, excessive heat transfer rates, and a severe vibration level.
Abstract: : Nonlinear axial-mode combustion instability remains a serious problem in the development of solid propellant rocket motors. Although the use of metal- loaded solid propellants which produce solid particles in the flow has reduced the occurrence of high frequency instabilities, it has not eliminated the axial-mode intermediate frequency (100 - 1000 Hz.) problem. If such an instability reaches a large amplitude limit cycle, it may lead to an increase in mean chamber pressure and burning rate, excessive heat transfer rates, and a severe vibration level. The objective of this report is to investigate the complex coupling between the chamber flow conditions and the solid propellant combustion process which may lead to large amplitude longitudinal instabilities.
7 citations
01 Jul 1974
TL;DR: In this article, a NASTRAN analysis of the solid rocket booster (SRB) substructure of the space shuttle 1/8-scale structural dynamics model is presented, where three layers of three-dimensional CHEXAI elements are used to model the propellant.
Abstract: A NASTRAN analysis of the solid rocket booster (SRB) substructure of the space shuttle 1/8-scale structural dynamics model. The NASTRAN finite element modeling capability was first used to formulate a model of a cylinder 10 in. radius by a 200 in. length to investigate the accuracy and adequacy of the proposed grid point spacing. Results were compared with a shell analysis and demonstrated relatively accurate results for NASTRAN for the lower modes, which were of primary interest. A finite element model of the full SRB was then formed using CQUAD2 plate elements containing membrane and bending stiffness and CBAR offset bar elements to represent the longerons and frames. Three layers of three-dimensional CHEXAI elements were used to model the propellant. This model, consisting of 4000 degrees of freedom (DOF) initially, was reduced to 176 DOF using Guyan reduction. The model was then submitted for complex Eigenvalue analysis. After experiencing considerable difficulty with attempts to run the complete model, it was split into two substructres. These were run separately and combined into a single 116 degree of freedom A set which was successfully run. Results are reported.
7 citations
01 Feb 1974
TL;DR: The nonlinear differential equations of motion for a general parachute-riser-payload system are developed and the resulting math model is applied for analyzing the descent dynamics and stability characteristics of both the drogue stabilization phase and the main descent phase of the space shuttle solid rocket booster (SRB) recovery system.
Abstract: The nonlinear differential equations of motion for a general parachute-riser-payload system are developed. The resulting math model is then applied for analyzing the descent dynamics and stability characteristics of both the drogue stabilization phase and the main descent phase of the space shuttle solid rocket booster (SRB) recovery system. The formulation of the problem is characterized by a minimum number of simplifying assumptions and full application of state-of-the-art parachute technology. The parachute suspension lines and the parachute risers can be modeled as elastic elements, and the whole system may be subjected to specified wind and gust profiles in order to assess their effects on the stability of the recovery system.
6 citations
25 Nov 1974
TL;DR: In this article, a two phase program was conducted to define requirements and to prepare a preliminary design of a test motor system that will accurately and economically simulate the chamber environments of present and future large solid propellant rocket motors.
Abstract: : A two phase program was conducted to define requirements and to prepare a preliminary design of a test motor system that will accurately and economically simulate the chamber environments of present and future large solid propellant rocket motors. A segmented motor configuration with 28-in. outside diameter case bonded propellant grains was selected. The nominal grain configuration is an internal burning cylinder with both ends burning.
5 citations
Patent•
25 Jun 1974TL;DR: In this paper, a valve arrangement for a high speed rocket powered vehicle involving the use of a valve configuration in which hot gases are received from the motor, and selectively ported overboard or into the rocket nozzle in order to provide maneuvering or vectoring control for the vehicle is presented.
Abstract: A control system for a high speed rocket powered vehicle involving the use of a valve arrangement in which hot gases are received from the motor, and selectively ported overboard or into the rocket nozzle in order to provide maneuvering or vectoring control for the vehicle. In a preferred embodiment, at least one pair of oppositely disposed valves is utilized, with the movable portions of the valves arranged to be relatedly movable such that the vectoring forces provided by the valves are additive. My valves have a neutral position in which no maneuvering forces are generated, with an inherent fail-safe design being involved such that catastrophic maneuvers are prevented in the event control power is lost. Also, inasmuch as my valves do not shut off the hot gas flow, the rocket motor chamber pressure desirably does not fluctuate. Advantageously, the valve construction taught herein can withstand the hot erosive gases emanating from a solid fuel rocket.
5 citations
01 Aug 1974
TL;DR: In this article, the authors used the Davidon-Fletcher-Powell penalty function to optimize a control variable parametrically by using third-degree spline function interpolation, which allows the control to be shaped so that inequality constraints are strictly adhered to and all corners are eliminated.
Abstract: Optimal solid-rocket thrust profiles for the parallel-burn, solid-rocket-assisted space shuttle are investigated. Solid-rocket thrust profiles are simulated by using third-degree spline functions, with the values of the thrust ordinates defined as parameters. The profiles are optimized parametrically, using the Davidon-Fletcher-Powell penalty function method, by minimizing propellant weight subject to state and control inequality constraints and to terminal boundary conditions. This study shows that optimizing a control variable parametrically by using third-degree spline function interpolation allows the control to be shaped so that inequality constraints are strictly adhered to and all corners are eliminated. The absence of corners, which is realistic in nature, makes this method attractive from the viewpoint of solid rocket grain design.
4 citations
22 Mar 1974
TL;DR: A bibliography of reports pertaining to the hard start phenomenon in attitude control rocket engines on Apollo spacecraft is presented in this paper, where some of the subjects discussed are; combustion of hydrazine, one dimensional theory of liquid fuel rocket combustion, preignition phenomena in small pulsed rocket engines, experimental and theoretical investigation of the fluid dynamics of rocket combustion and nonequilibrium combustion and nozzle flow in propellant performance.
Abstract: A bibliography of reports pertaining to the hard start phenomenon in attitude control rocket engines on Apollo spacecraft is presented. Some of the subjects discussed are; (1) combustion of hydrazine, (2) one dimensional theory of liquid fuel rocket combustion, (3) preignition phenomena in small pulsed rocket engines, (4) experimental and theoretical investigation of the fluid dynamics of rocket combustion, and (5) nonequilibrium combustion and nozzle flow in propellant performance.
21 Oct 1974
Patent•
01 Aug 1974
TL;DR: In this paper, a core sampling tube is driven into the ground by a rocket propulsion system, which can be adapted to the depth of water by varying the cross section and/or widening ratio of the rocket nozzle.
Abstract: Appts. which can be lowered on ropes, for the removal of soil samples from underwater geological formations, by means of a recoverable core sampling tube driven into the ground by a rocket propellant system, which can be adapted to the depth of water by varying the cross section and/or widening ratio of the rocket nozzle. More especially, the rocket propulsion system is a solid fuel rocket with a removable nozzle holder in which the nozzle is exchangeably mounted.
01 Nov 1974
TL;DR: In this article, a 0.004-scale representation of the space shuttle launch vehicle was used to determine transonic and supersonic model support interference effects for use in a future exhaust plume effects study.
Abstract: Strut support interference investigations were conducted on an 0.004-(-) scale representation of the space shuttle launch vehicle in order to determine transonic and supersonic model support interference effects for use in a future exhaust plume effects study. Strut configurations were also tested. Orbiter, external tank, and solid rocket booster pressures were recorded at Mach numbers 0.9, 1.2, 1.5, and 2.0. Angle of attack and angle of sideslip were varied between plus or minus 4 degrees in 2 degree increments. Parametric variations consisted only of the strut configurations.
Patent•
29 Oct 1974
TL;DR: In this paper, a block of propellant fuel is located within the engine body and has a portion of reduced cross-sectional dimensions corresponding to the internally thickened portion at the end of an engine body.
Abstract: One or both ends of the body of a solid fuel rocket engine is provided with an internally thickened portion, which serves for the mechanical attachment of additional parts, that is the rocket head or the rocket base, to the end of the engine body, without any increase in the external cross-sectional dimension of the body. A block of propellant fuel is located within the engine body and has a portion of reduced cross-sectional dimensions corresponding to the internally thickened portion at the end of the engine body. The block is introduced into the body by cooling the former until its dimensions have shrunk sufficiently for it to be introduced.
01 Apr 1974
TL;DR: In this paper, the effect of plume-induced flow separation and aspiration effects due to operation of both orbiter and the solid rocket motors on a 0.019-scale model of the Space Shuttle Vehicle is determined.
Abstract: The effect of plume-induced flow separation and aspiration effects due to operation of both orbiter and the solid rocket motors on a 0.019-scale model of the launch configuration of the Space Shuttle Vehicle is determined. Longitudinal and lateral-directional stability data were obtained at Mach numbers of 1.6, 2.0, and 2.2 with and without the engines operating. The plumes exiting from the engines were simulated by a cold-gas jet supplied by an auxiliary 200-atm air supply system and solid-body plume simulators. The aerodynamic effects produced by these two simulation procedures are compared. The parameters most significantly affected by the jet plumes are pitching moment, elevon control effectiveness, axial force, and orbiter wing loads. The solid rocket motor (SRM) plumes have the largest effect on the aerodynamic characteristics. The effect of the orbiter plumes in combination with the SRM plumes is also significant. Variations in the nozzle design parameters and configuration changes can reduce the jet plume-induced aerodynamic effects.
01 Jun 1974
TL;DR: In this article, a 2.112 percent scale model of the space shuttle solid rocket booster model was tested in a transonic pressure tunnel at Mach numbers ranging from 0.4 to 1.2 and angles of attack from minus one degree to plus 181 degrees.
Abstract: Tests of a 2.112 percent scale model of the space shuttle solid rocket booster model were conducted in a transonic pressure tunnel. Tests were conducted at Mach numbers ranging from 0.4 to 1.2, angles of attack from minus one degree to plus 181 degrees, and Reynolds numbers from 0.6 million to 6.1 million per foot. The model configurations investigated were as follows: (1) solid rocket booster without external protuberances, (2) solid rocket booster with an electrical tunnel and a solid rocket booster/external tank thrust attachment structure, and (3) solid rocket booster with two body strakes.
21 Oct 1974
01 Apr 1974
TL;DR: In this paper, a miniature solid propellant rocket motor has been developed to determine those parameters which must be duplicated in a cold gas flow to produce aerodynamic effects on an experimental model similar to those produced by hot, particle-laden exhaust plumes.
Abstract: A miniature solid propellant rocket motor has been developed to be used in a program to determine those parameters which must be duplicated in a cold gas flow to produce aerodynamic effects on an experimental model similar to those produced by hot, particle-laden exhaust plumes. Phenomena encountered during the testing of the miniature solid propellant motors included erosive propellant burning caused by high flow velocities parallel to the propellant surface, regressive propellant burning as a result of exposed propellant edges, the deposition of aluminum oxide on the nozzle surfaces sufficient to cause aerodynamic nozzle throat geometry changes, and thermal erosion of the nozzle throat at high chamber pressures. A series of tests was conducted to establish the stability of the rocket chamber pressure and the repeatibility of test conditions. Data are presented which define the tests selected to represent the final test matrix. Qualitative observations are also presented concerning the phenomena experienced based on the results of a large number or rocket tests not directly applicable to the final test matrix.
01 Oct 1974
TL;DR: In this paper, a technique is developed to optimize the shuttle solid rocket booster (SRB) design for water impact loads, where the SRB is dropped by parachute and recovered at sea for reuse.
Abstract: A technique is developed to optimize the shuttle solid rocket booster (SRB) design for water impact loads. The SRB is dropped by parachute and recovered at sea for reuse. Loads experienced at water impact are design critical. The probability of each water impact load is determined using a Monte Carlo technique and an aerodynamic analysis of the SRB parachute system. Meteorological effects are included and four configurations are evaluated.
21 Oct 1974
TL;DR: The development of the Astrobee F sounding rocket vehicle through the first flight test at NASA-Wallops Station is described in this paper, where the development of a 15 in. diameter, dual thrust, solid propellant motor demonstrating several new technology features provided the basis for the flight vehicle.
Abstract: The development of the Astrobee F sounding rocket vehicle through the first flight test at NASA-Wallops Station is described. Design and development of a 15 in. diameter, dual thrust, solid propellant motor demonstrating several new technology features provided the basis for the flight vehicle. The 'F' motor test program described demonstrated the following advanced propulsion technology: tandem dual grain configuration, low burning rate HTPB case-bonded propellant, and molded plastic nozzle. The resultant motor integrated into a flight vehicle was successfully flown with extensive diagnostic instrumentation.-