Application of CFE/POST II for Simulation of Launch Vehicle Stage Separation

Abstract Stage separation is a critical technical issue for developing two-stage-to-orbit (TSTO) launch systems with widebody carrier aircraft that use air-breathing propulsion and launch vehicle stages that use rocket propulsion. During conceptual design phases, this issue can be addressed with a combination of engineering methods, computational fluid dynamics simulations, and trajectory analysis of the mated system and the launch vehicle after staging. The outcome of such analyses helps to establish the credibility of the proposed TSTO system and formulate a ground-based test programme for the preliminary design phase. This approach is demonstrated with an assessment of stage separation from the shuttle carrier aircraft. Flight conditions are determined for safe mated flight, safe stage separation, and for the launch vehicle as it commences ascending flight. Accurate assessment of aerodynamic forces and moments is critical during staging to account for interference effects from the proximities of the two large vehicles. Interference aerodynamics have a modest impact on the separation conditions and separated flight trajectories, but have a significant impact on the interaction forces.

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Rigid body separation dynamics for space launch vehicles

The Aeronautical Journal ◽

10.1017/s0001924000013166 ◽

2006 ◽

Vol 110 (1107) ◽

pp. 289-302 ◽

Cited By ~ 6

Author(s):

B. N. Rao ◽

D. Jeyakumar ◽

K. K. Biswas ◽

S. Swaminathan ◽

E. Janardhana

Keyword(s):

Rigid Body ◽

Launch Vehicle ◽

Rigid Body Dynamics ◽

Separation Process ◽

Object Oriented Programming ◽

Levels Of Abstraction ◽

Programming Technique ◽

Pull Out ◽

Stage Separation ◽

Short Period

Abstract This paper presents a systematic formulation for the simulation of rigid body dynamics, including the short period dynamics, inherent to stage separation and jettisoning parts of a satellite launcher. This also gives a review of various types of separations involved in a launch vehicle. The problem is sufficiently large and complex; the methodology involves iterations at successively lower levels of abstraction. The best choice to tackle such problems is to use state-of-the-art programming technique known as object oriented programming. The necessary classes have been identified to represent various entities in the launch vehicle separation process (e.g., gravity, aerodynamics, propulsion and separation mechanisms etc.). Simple linkages are modelled with suitable objects. This approach helps the designer to simulate a launch vehicle separation dynamics and also to analyse separation system performance. To examine the influence of the design variables on the separating bodies, statistical analyses have been performed on the upper stage separation process and pull out of ongoing stage nozzle from the spent stage of a multistage rocket carrier using retro rockets.

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Modelica Stage Separation Dynamics Modeling for End-to-End Launch Vehicle Trajectory Simulations

Proceedings of the 10th International Modelica Conference, March 10-12, 2014, Lund, Sweden ◽

10.3384/ecp14096589 ◽

2014 ◽

Cited By ~ 1

Author(s):

Paul Acquatella ◽

Matthias J. Reiner

Keyword(s):

Launch Vehicle ◽

Dynamics Modeling ◽

Stage Separation ◽

End To End ◽

Vehicle Trajectory ◽

Trajectory Simulations

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Application of Constraint Force Equation Methodology for Launch Vehicle Stage Separation

Journal of Spacecraft and Rockets ◽

10.2514/1.a32048 ◽

2013 ◽

Vol 50 (1) ◽

pp. 191-205 ◽

Cited By ~ 1

Author(s):

Bandu N. Pamadi ◽

Paul V. Tartabini ◽

Mathew D. Toniolo ◽

Carlos M. Roithmayr ◽

Christopher D. Karlgaard ◽

...

Keyword(s):

Launch Vehicle ◽

Constraint Force ◽

Force Equation ◽

Stage Separation

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Optimization of the stage separation and the flight path of a future launch vehicle

System Modelling and Optimization - Lecture Notes in Control and Information Sciences ◽

10.1007/bfb0035498 ◽

1994 ◽

pp. 491-500

Author(s):

Kurt Chudej

Keyword(s):

Launch Vehicle ◽

Flight Path ◽

Stage Separation

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Ecological aspect of launch vehicles development by criterion of minimal cost

Ecology and Noospherology ◽

10.15421/031427 ◽

2014 ◽

Vol 25 (3-4) ◽

pp. 114-119

Author(s):

A. A. Baldin

Keyword(s):

Space Debris ◽

Low Cost ◽

Launch Vehicle ◽

Rocket Engines ◽

Launch Vehicles ◽

Rocket Propulsion ◽

Second Stage ◽

Maximal Performance ◽

Stage Separation ◽

The Future

One of the topical problems in modern aerospace engineering is accordance between ecological requirements and performance of the vehicle. On the other hand, problem of economical efficiency leads to change of the main criterion of designing to the minimization of costs (instead of maximal performance). According to modern trends of “low-cost” vehicles, different concepts of the future cost-effective launch vehicles are considered. It is necessary to validate these concepts according to requirements of ecological safety for the purpose of detection of the dominant launch vehicle configuration. Typical configurations of the future 'low-cost' launch vehicle are presented by 6 conceptual groups (Koelle, 2001). Conceptual group 1 (CG1) is presented by the Ballistic “Single stage to orbit” (SSTO) reusable vehicle. All vehicles which use classical rocketry scheme of the propulsion trajectory are called “Ballistic” i.e. the ballistic vehicle is lifted to orbit under the impact of rocket engines thrust. CG1-vehicle is able to reach the low earth orbit (LEO) without stage separation reducing the number of required rocket engines. Technological feasibility of SSTO concepts is proven by numerous studies (Koelle, 2001). CG2 representatives are ballistic “Two stages to orbit” (TSTO) reusable vehicles. The difference between CG1 and CG2 consists in application of vacuum rocket engines in the second stage and, consequently, stage separation. CG2 are the most mass-effective vehicles. CG3 is presented by the winged SSTO vehicles with rocket propulsion by “Lifting body” aerodynamic scheme. Ascensional force is provided by the aerodynamic shape of the vehicle’s structure at high speeds. Winged TSTO vehicles with rocket propulsion and parallel or tandem staging form the CG4. The winged configuration provides wide landing capability for both stages. CG5 is presented by winged TSTO vehicles with airbreathing propulsion in the first stage and rocket-propelled second stage. Airbreathing jet engines provide high reusability ratio comparing with other concepts as well as the widest landing capability. Aerospace Plane with scramjet-rocket propulsion forms CG6. The vehicle is able to reach near-cosmic speed in rarefied layers of the atmosphere and then accelerate with rocket engines. The most ecologically important resemblance of represented concepts is reusability. This reduces space debris formation (due to lack of waste hardware). Reusable launch vehicles can also be used to return the spent satellites. Structural differences between the concepts form 3 criterions of comparison by ecological impact: 1) propellant toxicity; 2) safety of surface facilities (vehicle damage inside the atmosphere); 3) probability of space debris formation (vehicle damage outside the atmosphere). Comparison of the concepts by these criterions allows substantiating the most ecologically acceptable direction of research. Results of the comparison demonstrate that the most ecologically acceptable low-cost launch vehicle configuration is: Ballistic SSTO or TSTO reusable launch vehicle with “LOX+LH2” propellant. The results can be explained by following way: combustion products of the propellant “liquid oxygen + liquid hydrogen” are absolutely safe for environment. It also provides maximal performance of rocket engine (due to the highest specific impulse). Ballistic ascent scheme allows using relatively simple technologies and provides high reliability level. In combination with minimal time of atmospheric flight this provides high level of safety for surface facilities. These results may be used for substantiation of dominant research direction.

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