High-elevation equatorial catapult-launched RBCC SSTO spaceplane for economic manned access to LEO

Daidzic, Nihad E.

doi:10.15394/ijaaa.2016.1116

Cited by 3 publications

(2 citation statements)

References 32 publications

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“…The illustration of the flight trajectory and critical mission altitudes is depicted in Fig. 3 (17) . The thrust and aerodynamic forces are as follows:…”

Section: Model Of the First Stage Of The Spacecraftmentioning

confidence: 99%

Integral performance optimization for the two-stage-to-orbit RBCC-RKT launch vehicle based on GPM

Zhang¹,

Sun²,

Cheng³

et al. 2019

Aeronaut. j.

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The takeoff-mass of a two-stage-to-orbit Rocket-Based Combined Cycle Engine-Rocket (RBCC-RKT) launch vehicle is a crucial factor in its comprehensive performance. This paper optimizes the takeoff-mass together with the trajectory by reformulating it to a nonlinear optimal control problem. The range of the second stage rocket mass is considered as a process constraint. When the scopes of initial and terminal states are specified, the problem can be solved by using the Gauss pseudo-spectral method (GPM). In order to reduce the convergent difficulty caused by using table data, the data in different stages are utilized by employing an integrated interpolation strategy through the optimization. Simulation results show that the mass can be effectively optimized to meet the inertia mass ratio constraint of the first-stage, and the separation of Mach number and altitude can be optimized at the same time.

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“…The illustration of the flight trajectory and critical mission altitudes is depicted in Fig. 3 (17) . The thrust and aerodynamic forces are as follows:…”

Section: Model Of the First Stage Of The Spacecraftmentioning

confidence: 99%

Integral performance optimization for the two-stage-to-orbit RBCC-RKT launch vehicle based on GPM

Zhang¹,

Sun²,

Cheng³

et al. 2019

Aeronaut. j.

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“…The basic methodology presented here could perhaps be extended to emerging hypersonic suborbital and even orbital reentry transports. For example, Daidzic [32] discusses the conceptual design and analysis of hypersonic RBCC SSTO spaceplane with gliding reentry for cost-effective LEO access. The article by Fusaro at al.…”

mentioning

confidence: 99%

Estimation of Transport-Category Jet Airplane Maximum Range and Airspeed in the Presence of Transonic Wave Drag

Wislicenus

Daidzic

2022

Aerospace

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One of the most difficult steps in estimating the cruise performance characteristics of high-subsonic transport-category turbofan-powered airplanes is the estimation of the transonic wave drag. Modern jet airplanes cruise most efficiently in the vicinity of the drag-divergence or drag-rise Mach numbers. In the initial design phase and later when the preliminary wind-tunnel and/or CFD computations and drag polars are known with increased accuracy, a method of estimating cruise performance is needed. In this study, a new semi-empirical transonic wave drag model using modified Lock’s equation was developed. For maximum range cruise estimations, an optimization criterion based on maximizing specific air range was used. The resulting nonlinear equations are of 12th- and 13th-order. Numerical Newton–Raphson nonlinear solvers were used to find real positive roots of such polynomials. The NR method was first tested for accuracy and convergence using known analytical solutions. A methodology for an initial guess was developed starting with the maximum-range cruise Mach without the wave-drag included. This guess resulted in fast quadratic convergence in all computations. Other novel features of this article include a new semi-empirical fuel-flow law, which was also extensively tested. Additionally, a semi-empirical turbofan thrust model usable for a wide range of bypass ratios and the entire flight envelope was developed. Such physics-based semi-empirical model can be used for a wide range of turbofans. The algorithm can be utilized to identify most beneficial input parameter values and combinations for the cruise flight phase. The model represents a powerful tool to estimate important cruise performance airspeeds located in the transonic regime. An intended application is in the conceptual development stages for early design optimizations of future airplanes. It is possible with additional effort to extend existing model capabilities to deal with supersonic transports optimal cruise parameters.

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Thermodynamic analysis for a novel steam Rankine cycle based indirect chemical precooled engine used for supersonic flight

Wang

Dang

et al. 2022

Fuel

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High-elevation equatorial catapult-launched RBCC SSTO spaceplane for economic manned access to LEO

Cited by 3 publications

References 32 publications

Integral performance optimization for the two-stage-to-orbit RBCC-RKT launch vehicle based on GPM

Integral performance optimization for the two-stage-to-orbit RBCC-RKT launch vehicle based on GPM

Estimation of Transport-Category Jet Airplane Maximum Range and Airspeed in the Presence of Transonic Wave Drag

Thermodynamic analysis for a novel steam Rankine cycle based indirect chemical precooled engine used for supersonic flight

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