Cost Comparison of Expendable, Hybrid, and Reusable Launch Vehicles

Gstattenbauer, Greg J.

doi:10.2514/6.2006-7211

“…where То is the UAV skin surface temperature, Т H is the temperature of the approach flow, which depends on the UAV/ILV separation altitude, r t is the boundary layer recovery coefficient, which is 0.89 for the turbulent boundary layer, k is the adiabatic coefficient, which is 1.4 for air, M is the Mach number of the approach flow. The cost calculations were based on the recommendations and methods given in [5,7,12]. The cost estimation plan is shown in Fig.…”

Section:  mentioning

confidence: 99%

Technical and Economic Substantiation of the Air Launch Aerospace System Parameters

Kalynychenko¹,

Manko²,

Pavlenko³

et al. 2023

Kosm. nauka tehnol.

0

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The substantiation of the technical and economic parameters of the air launch aerospace system, which consists of a reusable unmanned aerial vehicle and integrated launch vehicle, is given. A combination of a turbofan engine and a ramjet engine is used as the unmanned aerial vehicle propulsion system. The considered vehicle is capable of delivering a payload into low-Earth orbits without the use of a spaceport. We have developed the methodology of the technical and economic substantiation of the parameters of the air launch aerospace system. The results were obtained by searching for the minimum of the objective function, which established the relationship between the technical and economic parameters of the aerospace system. For the objective function solution, the design parameters of the integrated launch vehicle and unmanned aerial vehicle were determined, as well as the limitation of the total acceleration velocity of the aerospace system. The methods used allowed us to determine the velocity constraints provided by the operation of the turbofan engine, ramjet engine, and the three solid propellant motors of integrated launch vehicle stages, as well as maximum dynamic pressure and maximum permissible temperature on the unmanned aerial vehicle surface. We determined the scheme for estimating the cost of launching the spacecraft into Earth orbit by the air launch aerospace system. The result of the substantiation is the determination of the technical and economic parameters of the integrated launch vehicle, unmanned aerial vehicle, and the aerospace system as a whole. The influence of the maximum temperature on the surface of the unmanned aerial vehicle and the specific impulse of the ramjet engine on the parameters of the aerospace system was also evaluated. The substantiation is the first step towards the creation of the Ukrainian aerospace air launch system.

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“…where То is the UAV skin surface temperature, Т H is the temperature of the approach flow, which depends on the UAV/ILV separation altitude, r t is the boundary layer recovery coefficient, which is 0.89 for the turbulent boundary layer, k is the adiabatic coefficient, which is 1.4 for air, M is the Mach number of the approach flow. The cost calculations were based on the recommendations and methods given in [5,7,12]. The cost estimation plan is shown in Fig.…”

Section:  mentioning

confidence: 99%

Untitled

2023

Kosm. nauka tehnol.

0

View full text Add to dashboard Cite

The substantiation of the technical and economic parameters of the air launch aerospace system, which consists of a reusable unmanned aerial vehicle and integrated launch vehicle, is given. A combination of a turbofan engine and a ramjet engine is used as the unmanned aerial vehicle propulsion system. The considered vehicle is capable of delivering a payload into low-Earth orbits without the use of a spaceport. We have developed the methodology of the technical and economic substantiation of the parameters of the air launch aerospace system. The results were obtained by searching for the minimum of the objective function, which established the relationship between the technical and economic parameters of the aerospace system. For the objective function solution, the design parameters of the integrated launch vehicle and unmanned aerial vehicle were determined, as well as the limitation of the total acceleration velocity of the aerospace system. The methods used allowed us to determine the velocity constraints provided by the operation of the turbofan engine, ramjet engine, and the three solid propellant motors of integrated launch vehicle stages, as well as maximum dynamic pressure and maximum permissible temperature on the unmanned aerial vehicle surface. We determined the scheme for estimating the cost of launching the spacecraft into Earth orbit by the air launch aerospace system. The result of the substantiation is the determination of the technical and economic parameters of the integrated launch vehicle, unmanned aerial vehicle, and the aerospace system as a whole. The influence of the maximum temperature on the surface of the unmanned aerial vehicle and the specific impulse of the ramjet engine on the parameters of the aerospace system was also evaluated. The substantiation is the first step towards the creation of the Ukrainian aerospace air launch system.

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“…Aiming at the development of more affordable, convenient and reliable access to space, the reusable launch vehicles (RLVs) [1][2][3][4][5][6][7][8][9], such as space rider [10] and Skylon [11,12] have become a hot spot and received sustained attention during the last few decades. The RLVs will dramatically reduce the operational cost of space missions because they can be used repeatedly by quick recovering and reusing after each space mission.…”

Section: Introductionmentioning

confidence: 99%

Control Design for the Autonomous Horizontal Takeoff Phase of the Reusable Launch Vehicles

An

¹

,

Liu

²

,

Fan³

et al. 2020

IEEE Access

5

0

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The control system design for the reusable launch vehicles (RLVs), especially in the autonomous horizontal takeoff phase, is a highly challenging task. Significant issues arise due to the high nonlinearity, large uncertainties of aerodynamic coefficients as well as strong coupling among axes of the airframe. This paper studies autonomous takeoff control problem of the RLVs by the means of trajectory linearization control (TLC) and model predictive control (MPC) theory. The six degree of freedom dynamic model is firstly established, and the flight strategy of takeoff and climb stage is provided through the characteristic analysis of RLVs. Furthermore, the guidance law for the climbing phase is proposed via the TLC method against the high nonlinearity, and a speed based gain-schedule strategy is given under the consideration of both aerodynamic force and friction force. In order to eliminate the ground effect interference, an improved model predictive control approach is presented by introducing the online parameter estimation of the ground effect interaction coefficient, and a coupled model predictive controller is designed by introducing the feedback of sideslip angle into the roll control channel to eliminate the coupling effect. Finally, the performance of the design method for autonomous takeoff control of RLVs is demonstrated through the comparison simulation analysis.

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Cost Comparison of Expendable, Hybrid, and Reusable Launch Vehicles

Cited by 13 publications

References 3 publications

Technical and Economic Substantiation of the Air Launch Aerospace System Parameters

Technical and Economic Substantiation of the Air Launch Aerospace System Parameters

Untitled

Control Design for the Autonomous Horizontal Takeoff Phase of the Reusable Launch Vehicles

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