Hyper-X stage separation--simulation development and results

Reubush, D. E.; Martín, José Manuel Sánchez; Robinson, J. C.; Bose, David M.; Strovers, Brian K.

doi:10.2514/6.2001-1802

Cited by 10 publications

(4 citation statements)

References 4 publications

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“…The procedure was validated by comparing the analysis results with full-scale payload fairing separation test data of the Titan IV launch vehicle. Reubush et al [24] simulated hyper-X stage separation with the Monte Carlo method. Jeyakumar and Biswas [25−27] provided the stage separation system design and dynamic analysis of launch vehicles.…”

Section: Introductionmentioning

confidence: 99%

Monte Carlo simulation of stage separation dynamics of a multistage launch vehicle

Roshanian

Talebi

2008

Appl. Math. Mech.-Engl. Ed.

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This paper provides the formulation used for studing the cold and hot separating stages of a multistage launch vehicle. Monte Carlo simulation is employed to account for the off nominal design parameters of the bodies undergoing separation to evaluate the risk of failure for the separation event. All disturbances, effect of dynamic unbalance, residual thrust, separation disturbance caused by the separation mechanism and misalignment in cold and hot separation are analyzed to find out nonoccurrence of collision between the separation bodies. The results indicate that the current design satisfies the separation requirements.

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Section: Introductionmentioning

confidence: 99%

Monte Carlo simulation of stage separation dynamics of a multistage launch vehicle

Roshanian

Talebi

2008

Appl. Math. Mech.-Engl. Ed.

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“…Major objectives of the program are to acquire data on the operation of the scramjet propulsion system and to demonstrate controlled hypersonic flight technologies. 1,2 A secondary goal is to evaluate the experimental [3][4][5][6] and computational [7][8][9][10] techniques used in the design and analysis of the Hyper-X vehicle in order to facilitate future hypersonic and launch vehicle programs. 1,11,12 The flight experiment mission profile is shown in Fig.…”

Section: Introductionmentioning

confidence: 99%

Hyper-X Post-Flight Trajectory Reconstruction

Karlgaard

Tartabini

Blanchard

et al. 2004

AIAA Atmospheric Flight Mechanics Conference and Exhibit

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This paper discusses the formulation and development of a trajectory reconstruction tool for the NASA X-43A/Hyper-X high speed research vehicle, and its implementation for the reconstruction and analysis of flight test data. Extended Kalman filtering techniques are employed to reconstruct the trajectory of the vehicle, based upon numerical integration of inertial measurement data along with redundant measurements of the vehicle state. The equations of motion are formulated in order to include the effects of several systematic error sources, whose values may also be estimated by the filtering routines. Additionally, smoothing algorithms have been implemented in which the final value of the state (or an augmented state that includes other systematic error parameters to be estimated) and covariance are propagated back to the initial time to generate the best-estimated trajectory, based upon all available data. The methods are applied to the problem of reconstructing the trajectory of the Hyper-X vehicle from flight data.

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“…The simulation has been run in a Monte-Carlo fashion to estimate the probability of re-contact between the two vehicles and to evaluate the capability of the X-43A control system to limit attitude excursions during separation as well as ensure a proper post-separation vehicle attitude. 10,11 Prior to the 2001 flight, validation of the SepSim tool consisted of modular level checks performed by comparing simulation results with independent standalone models, and one integrated level check that compared results with those from an independent sixdegree-of-freedom RV simulation. This independent simulation modeled the dynamical motion of only the RV during separation by including additional force and moment increments due to the pistons and the aerodynamic interference effects on top of the baseline aerodynamic forces predicted for free flight.…”

Section: Introductionmentioning

confidence: 99%

Hyper-X Stage Separation Trajectory Validation Studies

Tartabini

Bose

Mcminn

et al. 2003

AIAA Modeling and Simulation Technologies Conference and Exhibit

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An independent twelve degree-of-freedom simulation of the X-43A separation trajectory was created with the Program to Optimize Simulated trajectories (POST II). This simulation modeled the multi-body dynamics of the X-43A and its booster and included the effect of two pyrotechnically actuated pistons used to push the vehicles apart as well as aerodynamic interaction forces and moments between the two vehicles. The simulation was developed to validate trajectory studies conducted with a 14 degree-offreedom simulation created early in the program using the Automatic Dynamic Analysis of Mechanics Systems (ADAMS) simulation software. The POST simulation was less detailed than the official ADAMS-based simulation used by the Project, but was simpler, more concise and ran faster, while providing similar results. The increase in speed provided by the POST simulation provided the Project with an alternate analysis tool. This tool was ideal for performing separation control logic trade studies that required the running of numerous Monte Carlo trajectories.

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Hyper-X stage separation--simulation development and results

Abstract: This

Cited by 10 publications

References 4 publications

Monte Carlo simulation of stage separation dynamics of a multistage launch vehicle

Monte Carlo simulation of stage separation dynamics of a multistage launch vehicle

Hyper-X Post-Flight Trajectory Reconstruction

Hyper-X Stage Separation Trajectory Validation Studies

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