Lifting entry vehicle mass reduction through integrated thermostructural/trajectory design

Wurster, Kathryn E.

doi:10.2514/3.8591

Cited by 6 publications

(4 citation statements)

References 6 publications

Supporting

Mentioning

Contrasting

Unclassified

Order By: Relevance

“…The advent of winged space transportation systems with relatively good aerodynamic performance characteristics provided the flexibility to develop trajectories over a broad range of altitude-velocity conditions. Several investigations [48][49][50] were conducted that demonstrated the effect of turbulence on different TPS concepts; the requirements for ceramic versus metallic systems; and the interrelationship of several key parameters including heating rates, heat load and vehicle geometry, attitude, weight and aerodynamics. Trade studies were presented highlighting the importance of developing a trajectory for a particular TPS concept 48,49 as well as the importance of mitigating early boundary-layer transition 50 .…”

Section: Fig 13 Effect Of Bump On Windward Centerline Surface Datamentioning

confidence: 99%

“…The altitude needs to be maintained at or above this limit until velocities are sufficiently low such that the temperatures associated with transition at that trajectory condition are within the capability of the selected TPS and do not exceed the peak laminar values that generally occur early in the entry. Figure 26 demonstrates the impact of applying a metallic hot structure to a trajectory tailored for a ceramic TPS compared to a trajectory actually optimized for a metallic hot structure 49 . The metallic materials that can tolerate the high heating rates/temperatures of a ceramic TPS trajectory are high-density materials and thus a significant weight penalty would be encountered.…”

Section: Fig 13 Effect Of Bump On Windward Centerline Surface Datamentioning

confidence: 99%

See 1 more Smart Citation

Aeroheating Design Issues for Reusable Launch Vehicles -- A Perspective

Zoby

Thompson

Wurster

2004

34th AIAA Fluid Dynamics Conference and Exhibit

View full text Add to dashboard Cite

An overview of basic aeroheating design issues for Reusable Launch Vehicles (RLV), which addresses the application of hypersonic ground-based testing, and computational fluid dynamic (CFD) and engineering codes, is presented. Challenges inherent to the prediction of aeroheating environments required for the successful design of the RLV Thermal Protection System (TPS) are discussed in conjunction with the importance of employing appropriate experimental/computational tools. The impact of the information garnered by using these tools in the resulting analyses, ultimately enhancing the RLV TPS design is illustrated. A wide range of topics is presented in this overview; e.g. the impact of flow physics issues such as boundary-layer transition, including effects of distributed and discrete roughness, shockshock interactions, and flow separation/reattachment. Also, the benefit of integrating experimental and computational studies to gain an improved understanding of flow phenomena is illustrated. From computational studies, the effect of low-density conditions and of uncertainties in material surface properties on the computed heating rates are highlighted as well as the significant role of CFD in improving the Outer Mold Line (OML) definition to reduce aeroheating while maintaining aerodynamic performance. Appropriate selection of the TPS design trajectories and trajectory shaping to mitigate aeroheating levels and loads are discussed. Lastly, an illustration of an aeroheating design process is presented whereby data from hypersonic wind-tunnel tests are integrated with predictions from CFD codes and engineering methods to provide heating environments along an entry trajectory as required for TPS design. I.

show abstract

Section: Fig 13 Effect Of Bump On Windward Centerline Surface Datamentioning

confidence: 99%

Section: Fig 13 Effect Of Bump On Windward Centerline Surface Datamentioning

confidence: 99%

Aeroheating Design Issues for Reusable Launch Vehicles -- A Perspective

Zoby

Thompson

Wurster

2004

34th AIAA Fluid Dynamics Conference and Exhibit

View full text Add to dashboard Cite

show abstract

“…For cases in which the vehicle mission allows a vehicle of sufficient aerodynamic performance, the three disciplines -aerothermodynamics, TPS design, and trajectory control -can be integrated to provide an optimal TPS/entry strategy thus reducing TPS weight requirements. 6 More recent efforts 7,8 to integrate aerothermodynamics and TPS sizing for multidisciplinary design and analysis optimization (MDAO) purposes also emphasized the importance of the system-of-systems analysis environment for conceptual design. The approach to obtaining surface heating environments as discussed in this paper is intended for implementation in a multidisciplinary analysis tool to support conceptual vehicle design, specifically TPS and trajectory design strategies.…”

Section: Introductionmentioning

confidence: 99%

Inviscid/Boundary-Layer Aeroheating Approach for Integrated Vehicle Design

Lee

Wurster

2017

55th AIAA Aerospace Sciences Meeting

Self Cite

View full text Add to dashboard Cite

A typical entry vehicle design depends on the synthesis of many essential subsystems, including thermal protection system (TPS), structures, payload, avionics, and propulsion, among others. The ability to incorporate aerothermodynamic considerations and TPS design into the early design phase is crucial, as both are closely coupled to the vehicle's aerodynamics, shape and mass. In the preliminary design stage, reasonably accurate results with rapid turn-around times for parametric studies and quickly evolving configurations are necessary to steer design decisions. This investigation considers the use of an unstructured 3D inviscid code in conjunction with an integral boundary-layer method; the former providing the flowfield solution and the latter the surface heating. Sensitivity studies for Mach number, angle of attack, and altitude, examine the feasibility of using this approach to populate a representative entry flight envelope based on a limited set of inviscid solutions. Each inviscid solution is used to generate surface heating over the nearby trajectory space. A subset of a representative entry envelope was explored. Initial results suggest that for Mach numbers ranging from 9-20, a few inviscid solutions could reasonably support surface heating predictions at Mach numbers variation of +/-2, altitudes variation of +/-10 to 20 kft, and angle-of-attack variation of +/-5 • . Agreement with Navier-Stokes solutions was generally found to be within 10-15% for Mach number and altitude, and 20% for angle of attack. A smaller angle-of-attack increment than the 5 • considered in this study is recommended. Results of the angle-of-attack sensitivity studies show that smaller increments may be needed for better heating predictions. The approach is well suited for application to conceptual multidisciplinary design and analysis studies where transient aeroheating environments are critical for vehicle TPS and thermal design. Concurrent prediction of aeroheating environments, coupled with the use of unstructured methods, is considered enabling for TPS material selection and design in conceptual studies where vehicle mission, shape, and entry strategies evolve rapidly.

show abstract

“…(3) Υψηλές ολικές ενθαλπίες h t (ενθαλπίες ανακοπής, J/kg) και κατά συνέπεια υψηλές θερµοκρασίες T t και υψηλοί ρυθµοί µεταφοράς θερµότητας από την υπέρθερµη ροή προς τα τοιχώµατα του Υ/Ο q o (J/(m 2 s) = W/m 2 ), σύµφωνα µε τις σχ. (1.1.3 και 4): Ως αποτέλεσµα της υψηλής θερµοκρασίας ανακοπής, οι υψηλές τιµές της µεταφοράς θερµότητας προς το Υ/Ο υποχρεώνουν να χρησιµοποιούνται για τη θερµοθωράκισή του ειδικά πυράντοχα και θερµοµονωτικά υλικά, τα οποία όµως περιορίζονται πάντοτε ένεκα της µεγάλης τους µάζας [70,159] . Γι' αυτό παράλληλα ακολουθείται κατάλληλο ίχνος καθόδου του Υ/Ο µε βαθµιαία µείωση της ταχύτητάς του, ώστε να µην υπερβαίνει το "φράγµα υπερθέρµανσης", που θέτει η αντοχή των τοιχωµάτων στις υψηλές θερµοκρασίες, και γενικότερα η υπερθέρµανση ολόκληρου του Υ/Ο.…”

Section: 17unclassified

Ροές Υψηλών Ταχυτήτων Και Θερμοδυναμική Αερίων Σε Υψηλές Θερμοκρασίες

Panagiotopoulos¹

View full text Add to dashboard Cite

show abstract

Lifting entry vehicle mass reduction through integrated thermostructural/trajectory design

Cited by 6 publications

References 6 publications

Aeroheating Design Issues for Reusable Launch Vehicles -- A Perspective

Aeroheating Design Issues for Reusable Launch Vehicles -- A Perspective

Inviscid/Boundary-Layer Aeroheating Approach for Integrated Vehicle Design

Ροές Υψηλών Ταχυτήτων Και Θερμοδυναμική Αερίων Σε Υψηλές Θερμοκρασίες

Contact Info

Product

Resources

About