Development and Flight Results of Solid Propulsion System for Enhanced Epsilon Launch Vehicle
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The development of enhanced propulsion system for the next Epsilon rocket was progressed. The development of Enhanced Epsilon is mainly the renewal of the second stage, and also includes each subsystem's improvement. The second stage motor M-35 was newly designed and manufactured. In order to verify the design, the static firing test of the second motor M-35 under the condition of vacuum ambient was conducted in 2015. The JAXA successfully launched the first Enhanced Epsilon launch vehicle. All solid propulsion systems for the Enhanced Epsilon launch vehicle showed a very good behavior during the flightKeywords:
Solid-fuel rocket
Launched
Rocket (weapon)
Solid-fuel rocket
Rocket (weapon)
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Abstract Rocket engines that use solid propellants are widely used in the commercial space flight industry for powering orbital-class launch vehicles and small research rockets. Thrust and the specific impulse developed by a rocket engine are essential properties of a rocket propulsion system, and it specifies the overall performance of a rocket. These properties heavily influenced by the burn-rate properties of the solid propellants. One of the many methods to improve the burn rate of the solid propellant is the addition of metallic powders into the fuel-oxidizer matrix. This technique has been observed to enhance the burn rate of the solid propellants; several studies have concluded the same. On the other hand, these additives result in the release of metal oxides into the atmosphere and lead to a higher amount of environmental pollution. This paper summarizes the effects of adding metals and their concentrations on the burning properties of the solid propellants.
Solid-fuel rocket
Specific impulse
Burn rate (chemistry)
Solid fuel
Booster (rocketry)
Rocket (weapon)
Ammonium perchlorate
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A simple method, which had been proposed by the authors to compute grain burnback during the operation of a solid-propellant rocket motor, is revisited. The method uses a fixed grid, which is imposed on the propellant grain. The intersection of the moving solid-gas interface with the grid is tracked and the burning surface is described using straight lines to compute the burning surface area and the port area. The revised version allows a more accurate tracking of the propellant regression than in the original method. The precision of the procedure is greatly increased by recording both the position and inclination of the solid-gas interface with respect to the grid lines, and the grain geometry is described using straight lines and circular arcs. Coarser grids can be used for the same expected error and the corresponding computing time is reduced. Improvements include the capability of handling surface merging and spatially dependent burning rates.
Solid-fuel rocket
Position (finance)
Solid fuel
Tracking (education)
Interface (matter)
Rocket (weapon)
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There are two major groups in solid propellants, the composite propellant and the double base propellant, used for rockets. The famous “Pencil Rocket” developed by Prof. Itokawa of Tokyo Univ. used double base propellant, that is made from nitrocellulose and nitroglycerine. Recently, composite propellants are widely used for large-sized solid rocket motors, since that have good burning property, good mechanical property, processibility, higher stability and long shelf-life. In this paper, some characteristics of composite propellants are briefly introduced.
Solid-fuel rocket
Rocket (weapon)
Rocket propellant
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This paper is concerned with the development of ultrasonic non-destructive testing (UT) method for a solid propellant. Solid propellants are fuels for motive force of a rocket motor. In general, the radiographic testing (RT) has been used to detect a defect in solid propellants. Since the use of RT needs much cost and time, it is strongly desirable to develop an alternative non-destructive testing method for solid propellants. Therefore, in this study, the use of UT, which is simple and widely used for various inspection for structures, is considered for detection of a defect in solid propellants. The voxel-based finite element method (FEM) is used to understand the ultrasonic wave propagation and scattering behavior in solid propellants. The fundamental elastodynamic theory and the FEM formulation used in this study are introduced. Some numerical results for UT simulation in which the complicated solid propellant geometry is considered are demonstrated to show the potential of the application of UT to on-site UT experiments.
Solid-fuel rocket
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Solid-fuel rocket
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Report describes proposed solid-propellant rocket motor. Case of motor integrated with propellant and burns and produces thrust as propellant combustion proceeds outward. Propellant and case manufactured together. Proposed motor increases payload-weight capacity.
Solid-fuel rocket
Payload (computing)
Rocket (weapon)
Liquid-propellant rocket
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Storage of rocket motors loaded with composite solid propellant for long periods may change the propellant properties, thus causing failure and affecting the safety during launch. In this study, an accelerated aging assay was carried out, in order to predict the useful lifetime and to evaluate variations on the propellant properties with time by means of thermal analysis (TG/DSC). The aging temperatures used were 65°C, and samples were withdrawn after 3 months. Aging was also carried out at room temperature. There was significant variation in the activation energy of the solid propellant samples thermal decomposition in the two kinetic methods used – Ozawa or model-free isoconversional method and Kissinger method – during the aging period. There was significant decrease of enthalpy of aged propellant enthalpy causing changes in ballistics parameters of the solid propellant grain affecting the rocket's performance.
Solid-fuel rocket
Rocket propellant
Internal ballistics
Energetic material
Rocket (weapon)
Ballistics
Accelerated aging
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1. Abstract This paper deals with performance test results of a new solid composite propellant based on GAP and Hydrazinium Nitroformate (HNF). This propellant delivers about 3,5% 9,3% higher performance (c*) than the best existing composite solid rocket propellant. Characteristics of ingredients and propellant formulations are presented together with the test results which demonstrate the increased performance compared to conventional high-performance propellants based on Ammonium Perchlorate (AP). The test equipment is being described as well as estimates of losses which occur in the test motor. This allows to estimate the expected performance in full-size rocket motors.
Ammonium perchlorate
Solid-fuel rocket
Rocket propellant
Rocket (weapon)
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The aim of this research is to examine the effects of propellant properties such as: combustion temperature, propellant density, characteristic velocity, reference burning rate and burning rate pressure exponent on internal ballistic performance of solid rocket motors. A zero dimensional internal ballistic solver is developed and internal ballistic performance analyses of solid rocket motors having slotted cross section are performed. Thus, different internal ballistic results such as maximum combustion pressure, burning time, specific impulse and total impulse are determined. Finally, variation of these response variables according to solid propellant properties are determined constructing different response surfaces. Graphical results represented in this work makes easier to select solid propellants for a certain kind of geometrical configuration.
Specific impulse
Solid-fuel rocket
Internal ballistics
Burn rate (chemistry)
Internal pressure
Rocket (weapon)
Ballistics
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