A review of contemporary solid rocket motor performance prediction techniques

Barrington, D. K.; Miller, W.

doi:10.2514/3.29911

Cited by 23 publications

(8 citation statements)

References 29 publications

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“…This raised concern on the stable burning of the propellant at low pressures. Hence detailed measurements were done in a newly developed burning rate measurement set-up working on ultrasonic technique 7 . Figure 8 provides the test results and pressure index estimated by this technique.…”

Section: Burning Rate Measurement and Burning Rate Indexmentioning

confidence: 99%

Development of Slow-Burning Solid Rocket Booster for RLV-TD Hypersonic Experiment

et al. 2018

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This article discusses the developmental challenges of the low-thrust, long-duration solid rocket motor for the launch of the experimental Reusable Launch Vehicle-Technological Demonstrator (RLV-TD). The main challenges were: (1) developing a motor case and subsystems with low inert mass; (2) design of an optimum nozzle such that the motor can have maximum specific impulse at atmospheric conditions, but with no flow separation at low operation pressures; (3) developing a slow-burning propellant (3 mm/s) to meet the mission requirements; (4) design of propellant grain for the motor so that it has long burning time, the vehicle experiences low dynamic pressure at the transonic regime, and the motor is without combustion instability; (5) developing necessary thermal protection system to take care of long-duration operations, and (6) developing the igniter to ensure the ignition of the motor, especially when easy ignition is difficult with slow-burning propellants and that there should be sufficient overlap of igniter functioning with motor initiation. Performance of the motor in flight indicated that the design met all the required criteria within the expected tolerance.

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Section: Burning Rate Measurement and Burning Rate Indexmentioning

confidence: 99%

Development of Slow-Burning Solid Rocket Booster for RLV-TD Hypersonic Experiment

et al. 2018

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“…Figure 2 shows that the chamber pressure cannot maintain constant during combustion of the propellants, which is common in the case of small rocket motors with very short working times, and a proper grain selection can help in getting neutral burning only in the case of full-scale rocket motors [25]. In order to investigate the effect of pressure on the combustion products, the time-averaged pressure P c,av was used to characterize operation one.…”

Section: Methodsmentioning

confidence: 99%

Transformation of Combustion Nanocatalysts inside Solid Rocket Motor under Various Pressures

Li¹,

Liu

Fu³

et al. 2019

Nanomaterials

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In this paper, the dependences of the morphology, particle sizes, and compositions of the condensed combustion products (CCP) of modified double-base propellants (1,3,5-trimethylenetrinitramine (RDX) as oxidizer) on the chamber pressure (<35 MPa) and nickel inclusion have been evaluated under a practical rocket motor operation. It has been shown that higher pressure results in smaller average particle sizes of the CCPs. The CCPs of Ni-containing propellants have more diverse morphologies, including spherical particles, large layered structures, and small flakes coated on large particles depending on the pressure. The specific surface area (SSA) of CCPs is in the range of 2.49 to 3.24 m2 g−1 for propellants without nickel are less dependent on the pressure, whereas it is 1.22 to 3.81 Ni-based propellants. The C, N, O, Al, Cu, Pb, and Si are the major elements presented on the surfaces of the CCP particles of both propellants. The compositions of CCPs from Ni-propellant are much more diverse than another one, but only three or four major phases have been found for both propellants under any pressure. The metallic copper is presented in CCPs for both propellants when the chamber pressure is low. The lead salt as the catalyst has been transformed in to Pb(OH)Cl as the most common products of lead-based catalysts with pressure lower than 15 MPa. When pressure is higher than 5 MPa, the nickel-based CCPs has been found to contain one of the following crystalline phases: Pb2Ni(NO2)6, (NH4)2Ni(SO4)2·6H2O, C2H2NiO4·2H2O, and NiO, depending on the pressure.

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“…This equation predicts satisfactorily the motor performance with erosive burning under subsonic cross-flow conditions [14]. However, despite the absence of any correlation beyond this condition, it is assumed that the equation is valid also in the transonic and supersonic flow regimes.…”

Section: Numerical Schemementioning

confidence: 94%

“…For the port envelope, the iterative gas dynamic procedure is as follows. At time t, the head-end trial pressure p head is taken as the previously converged p head (however, at time t 0, p head is suitably estimated) [14]. The incremental integration of subsonic flow down the port up to the throat is performed by applying the mass, momentum and energy conservation equations [16].…”

Section: Methods Of Solutionmentioning

confidence: 99%

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Effect of motor length and propellant formulation on nozzleless solid rocket performance

Krishnan

Ramakrishnan

1999

Proceedings of the Institution of Mechanical Engineers, Part G:

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Experimental results are presented for four nozzleless motors of different length-diameter ( L/D) ratios using two different composite propellants. The experimental observations discussed are: the premature unchoking in motors of insufficient L/D ratios and the tendency for the propellant to extinguish under highly negative pressure gradient environment, both peculiar to nozzleless operation. A simple one- dimensional numerical scheme is presented to predict the performance of a nozzleless solid motor. Erosive burning, elastic grain deformation and L/D ratio-dependent combustion efficiency are considered in the scheme. A relatively simple procedure is followed to account for the coupling effect between port gas dynamics and elastic grain deformation. The experimental results are compared with those predicted by the numerical scheme. The predictions are in reasonable agreement with the experimental values. For a composite propellant the burning rate index n can significantly vary with respect to pressure. The application of this fact plays a very important role in accurately predicting the thrust-time trace of nozzleless motors.

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A review of contemporary solid rocket motor performance prediction techniques

Cited by 23 publications

References 29 publications

Development of Slow-Burning Solid Rocket Booster for RLV-TD Hypersonic Experiment

Development of Slow-Burning Solid Rocket Booster for RLV-TD Hypersonic Experiment

Transformation of Combustion Nanocatalysts inside Solid Rocket Motor under Various Pressures

Effect of motor length and propellant formulation on nozzleless solid rocket performance

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