Aerothermal and flight mechanic considerations by development of small launchers for low orbit payloads started from lorentz rail accelerator

Bozic, Ognjan; Eggers, Thino; Wiggen, Stefan

doi:10.1051/eucass/201102765

Cited by 10 publications

(5 citation statements)

References 11 publications

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“…T HERE exist a number of studies related to the topic of using electromagnetic acceleration to launch payload into a low earth orbit. Several feasibility studies were carried out by the German Aerospace Center (DLR) within the last years [1], [2]. These studies propose to use an LRA (railgun) to accelerate a small vehicle with a total mass of roughly 500 kg to a starting velocity of 3.3 km/s with an acceleration of about 3300 g. A rough description of the vehicle is given, and the key parameters of the required railgun are presented in [3].…”

Section: Daniel Lancelle and Ognjan Božićmentioning

confidence: 99%

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Thermal Protection, Aerodynamics, and Control Simulation of an Electromagnetically Launched Projectile

Lancelle

Bozic

2015

IEEE Trans. Plasma Sci.

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In recent years, several ideas to apply electromagnetic launch technology to spaceflight applications have come up. The use of electric energy to propel a payload carrier promises savings of propellant and, therefore, cost reduction for the transfer to orbit. Previous studies mostly comprised a rough estimation of the launcher and the vehicle size. Sometimes, a v-budget is given to illustrate the energy expenditure. Some studies neglect the necessity of a rocket engine. Only by means of an electromagnetic launch, without the capability to maneuver reaching an orbit is not achievable. In addition to a propulsion system, an attitude control system and a flight controller are needed to bring the vehicle into a circular orbit. The high acceleration and high velocities at low altitudes have set high demands on the payload-carrying vehicle. Its structure has to withstand the high acceleration forces during launch and the tremendous aerodynamic heat fluxes during ascent through the dense atmosphere. This paper presents a vehicle concept that addresses all these demands. The vehicle consists of a two-stage hybrid rocket engine system, a thermal protection system (TPS), and high-test peroxide monopropellant thrusters for an attitude control system and a guidance, navigation, and control system. A simulation model is created, which consists of a 6-DOF flight mechanics module, an aerodynamic module, propulsion module, TPS simulation, as well as a guidance and flight control simulation. Therefore, the complete ascent with all its aspects can be simulated. The simulation results show that a 710-kg vehicle launched with 2586 g and an initial velocity of 3642 m/s can carry 31.5 kg of payload into a 300-km circular orbit. The configuration of the vehicle can be defined by a set of input parameters. This allows the use of the model within an optimization tool.

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Section: Daniel Lancelle and Ognjan Božićmentioning

confidence: 99%

“…Fig. 6 shows the thrust vector direction according to (1). PEG starts at a specific time prior to the ignition of the first stage.…”

Section: Guidance Navigation and Controlmentioning

confidence: 99%

Thermal Protection, Aerodynamics, and Control Simulation of an Electromagnetically Launched Projectile

Lancelle

Bozic

2015

IEEE Trans. Plasma Sci.

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“…The time t  is chosen such that the total change in velocity generated by thrust is along  v [8]. 6 illustrates the thrust vector direction according to equation (1). PEG starts at a specific time prior to first stage ignition.…”

Section: Guidance Navigation and Controlmentioning

confidence: 99%

“…Several feasibility studies are carried out by the German Aerospace Center (DLR) within the last years [1], [2]. In these studies it is proposed to use a Lorentz accelerator (LRA, railgun) to accelerate a small vehicle with a total mass of roughly 500 kg to a start velocity of 3.3 km/s with an acceleration of about 3300 g. A rough description of the vehicle is given and the key parameters of the required railgun are derived in [3].…”

Section: Introductionmentioning

confidence: 99%

Thermal protection-, aerodynamics- and control simulation of an electromagnetically launched projectile

Lancelle

Bozic

2014

2014 17th International Symposium on Electromagnetic Launch Technology

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In recent years several ideas came up to apply electromagnetic launch technology for spaceflight applications. Using electric energy to propel a payload carrier promises the saving of propellant and therefore cost reduction for the transfer to orbit.The conducted studies mostly comprise of a rough estimation of the launcher and the vehicle size. Sometimes a Δv-budget is given to illustrate the energy expenditure. Some of the studies neglect the necessity of a rocket engine. Only by means of an electromagnetic launch without the capability to maneuver, an orbit is not achievable.The high acceleration and the high velocities at low altitude evoke high demands on the payload carrying vehicle. Its structure has to withstand the high acceleration forces during launch and the tremendous aerodynamic heat fluxes during the ascent flight in the dense atmosphere. Moreover a propulsion system, an attitude control system, and a flight controller are needed to bring the vehicle into a circular orbit. This paper presents a vehicle concept that addresses all these demands. The vehicle comprises of a two stage hybrid rocket engine system, a thermal protection system, high test peroxide monopropellant thrusters for attitude control, and a guidance, navigation and control system. A simulation model is created, that consists of a 6-DOF flight mechanics module, aerodynamics model, propulsion module, thermal protection system simulation, as well as of guidance and flight control simulation. Therefore, the complete ascent with all its aspects can be simulated.The simulation results show that a 710 kg vehicle launched with 2586 g and an initial velocity of 3642 m/s can carry 31.5 kg of payload into a 300 km circular orbit. The configuration of the vehicle can be defined by a set of input parameters. This allows using the model within an optimization tool.

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“…In this paper, continuum-based Navier-Stokes solvers are used to calculate Mach number (Ma) contours and temperature distributions around the EML projectile. To avoid the extreme initial velocities and thermal loads, rocket assisted EML projectiles are also proposed in two separate papers [4], [5]. In these papers, the projectile is initialized with four different Mach numbers and flight characteristics are analyzed.…”

Section: Introductionmentioning

confidence: 99%

Aerothermal Load and Drag Force Analysis of the Electromagnetically Launched Projectiles Under Rarefied Gas Conditions

Şengil

Sengil

2015

IEEE Trans. Plasma Sci.

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Electromagnetically launched projectiles fly with hypersonic speeds in different regions of the Earth's atmosphere. Because of their hypersonic speeds, these projectiles are designed to withstand extreme thermal loads. Drag forces should also be considered to maximize the operational range. To reduce the thermal loads and drag forces, the geometric shape of these projectiles should be carefully designed. We can utilize either experimental or numerical methods to calculate these heating effects and drag forces. Numerical methods are more economic in terms of monetary cost and time. However, we cannot use the same numerical method in different regions of the Earth's atmosphere. In this paper, we used direct simulation Monte Carlo method to calculate thermal loads and drag forces of four different projectile geometries in the rarefied part of the atmosphere. Simulation results show that thermal loads and drag forces vary considerably depending on the projectile geometry.Index Terms-Aerothermal load, drag, electromagnetically launched (EML) projectiles, hypersonic flight.

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Aerothermal and flight mechanic considerations by development of small launchers for low orbit payloads started from lorentz rail accelerator

Cited by 10 publications

References 11 publications

Thermal Protection, Aerodynamics, and Control Simulation of an Electromagnetically Launched Projectile

Thermal Protection, Aerodynamics, and Control Simulation of an Electromagnetically Launched Projectile

Thermal protection-, aerodynamics- and control simulation of an electromagnetically launched projectile

Aerothermal Load and Drag Force Analysis of the Electromagnetically Launched Projectiles Under Rarefied Gas Conditions

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