Investigation of Two-Stage-to-Orbit Airbreathing Launch-Vehicle Configurations

Dissel, Adam F.; Kothari, Ajay P.; Lewis, Mark J.

doi:10.2514/1.17916

Cited by 28 publications

(10 citation statements)

References 5 publications

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“…Thus, launcher, payload, and mission must match each other within specified constraints. Since a certain variety of choices already exists and launchers behave differently in terms of cost, performance, or operational characteristics, methods for comparison are very important for mission optimization [373,374].…”

Section: Launchersmentioning

confidence: 99%

Aeronautics and astronautics: Recent progress and future trends

Martínez‐Val

Pérez

2009

Proceedings of the Institution of Mechanical Engineers, Part C:

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Aeronautics and astronautics are two closely related disciplines, sometimes found under the joint term aerospace, that have progressed at a formidable pace during the 20th century. Their impact on society is overwhelming. For example, the aeroplane, the core of aeronautics, has been identified as one of the three major inventions of that century. On its turn, satellites have paved the way for modern globalization. Major drivers leading this progress have changed from the classical motto ‘higher, further, faster’ to the current ‘more affordable, cleaner, quieter’, but safety has always been kept the undisputed number one. The underlying key factors for progress have been and still are excellence and co-operation. Both aeronautics and astronautics are multidisciplinary in nature and, accordingly, this review summarizes relevant advances and trends in pertinent fields: aerodynamics, structures, propulsion, and so on. All these fields are still very healthy and the 21st century will witness again a new era of astonishing aerospace developments.

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Section: Launchersmentioning

confidence: 99%

Aeronautics and astronautics: Recent progress and future trends

Martínez‐Val

Pérez

2009

Proceedings of the Institution of Mechanical Engineers, Part C:

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“…(1) airborne suspension, which can be external weapons [1] or embedded weapons [2], auxiliary fuel tank [3], aircraft seat [4], unmanned aerial vehicle, carrier rocket, etc. (2) multistage aircraft, such as series or parallel multistage carrier rocket [5], series [6] or parallel two-stage space vehicle into orbit [7], assisted torpedo [8], etc. (3) Aircraft with fairing [9].…”

Section: Introductionmentioning

confidence: 99%

Assessment of turbulence models and mesh types for the simulation of multi-body separation by coupling the CFD and rigid body dynamics

Wang

2023

J. Phys.: Conf. Ser.

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Turbulence models are considered one of the most important sources of numerical errors in the CFD studies on different aeronautical problems. The mesh type can also affect the numerical accuracy and computational efficiency. In this paper, various simulations on the store separation from an aircraft model in the transonic flow have been carried out by coupling the CFD and the rigid body dynamics on the overset mesh. The influence of S-A model, Standard k-epsilon model, SST k-omega model and inviscid model on the simulation results is examined. Different mesh types of both unstructured mesh and structured mesh as component part in overset are also considered. Grid-independence study are first carried out. The effects of different turbulence models and mesh types are then examined by comparing the trajectories, velocities and Eulerian angles. Recommendations are given to get better results for the simulation of multi-body separation problem.

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“…Compared with conventional type of inlets, these inlets have managed to overcome the bad effects leading from junction flow and increase compression efficiency to a certain extent, but most of them have an irregular entrance or exit shape, and are commonly assembled modularly on the missile bodies or applied straightforwardly as a part of the aircraft forebody. 7,8 For the objective of developing inlet-engine integration technique, the concept of cross-section transition was proposed subsequently. REST and RCST inlets preliminarily reached the intention of cross-section transition by applying regular entrance and exit shapes and generating the inlets configuration through geometric section transition.…”

Section: Introductionmentioning

confidence: 99%

An Improved Internal-Waverider-Inlet with High External-Compression for Ramjet Engine

Zhang¹,

Huang²,

Xia³

et al. 2015

20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference

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A new type of Internal-Waverider-Inlet(IWR inlet) for Ramjet Engine is presented in this paper. It is based on the new High External-Compression basic flowfield called InternalConical Flow C+ (ICFC+). Such new IWR inlet can improve the starting ability at lower Mach numbers than the previous design. The designing methodology of IWR inlet is presented. Analysis of such design shows that the basic flowfield is the key part in designing progress. A new method of generating characteristic lines is developed to evaluate the compressing efficiency of variable two dimensional flowfields. With the assistance of this method, the new High External-Compression basic flowfield ICFC+ is generated. One inlet was designed by using the ICFC and another inlet with same contraction ratio then was designed by using ICFC+. The numerical simulation results show that both inlets are capable of keeping their shock structures and other main flow characteristics exactly as their derived flowfield, thus resulting in capturing almost all upstream flow. But ICFC+ based inlet has better aerodynamic performance on low Mach number condition. Further, the higher compression ability led to shorter length of ICFC+ based inlet, which is helpful to inlet-engine integration design. Nomenclatureδ = deviation angle M 1 = entrance Mach number M 3 = exit Mach number β 1 = lip shock wave angle θ 3 = half of cone angle D eq1 = equivalent radius at inlet's throat θ e = expansion angle of diffuser L 1 = length of expansion section D eq2 = equivalent diameter at exit of diffuser L 2 = length of straight section M ∞ = Mach number of derived flowfield Cr = total contraction ratio W = Width of inlet's entrance L t = length of inlet L d = length of diffuser Φ = diameter of exit M t = Mach number at throat section M ex = Mach number at exit section 1 PhD student, College of energy and power engineering2 π = pressure ratio σ = pressure recovery ϕ = mass capturing coefficient η KE = kinetic energy efficiency

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Investigation of Two-Stage-to-Orbit Airbreathing Launch-Vehicle Configurations

Cited by 28 publications

References 5 publications

Aeronautics and astronautics: Recent progress and future trends

Aeronautics and astronautics: Recent progress and future trends

Assessment of turbulence models and mesh types for the simulation of multi-body separation by coupling the CFD and rigid body dynamics

An Improved Internal-Waverider-Inlet with High External-Compression for Ramjet Engine

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