Commissioning of upgrades to T6 to study giant planet entry

The scientific potential of a mission to the ice giants is well recognized and has been identified by NASA and ESA as a high priority on several occasions, most recently in the 2023–2032 Decadal Survey. The payload capacity of such a spacecraft is limited by the heat shield thickness, which must be sized conservatively due to a lack of reliable data for convective and radiative heat flux along the proposed entry trajectories. Major upgrades to the Oxford T6 Stalker Tunnel have been commissioned that allow study of giant planet entry trajectories, including a flammable gas handling system, a Mach 10 expansion nozzle, and a steel shock tube with optical access. Initial testing has been completed in shock tube and expansion tunnel modes, with peak shock speeds of 18.9 km/s achieved. Convective heat flux and surface pressure were measured at several locations on a 45° sphere cone model in expansion tunnel mode. Measurements of the radiating shock layer were made in shock tube mode to assess the effect of CH4 concentration. This work establishes the first high-enthalpy giant planet entry test bed in Europe

Microsatellite Constellation for Mars Communication and Navigation

Exploration of Mars and establishment of human settlement have been of sharp interest for several decades. Since the turn of the century, efforts have been ramped up to make these a reality. With the execution of multiple robotic exploration missions and several more planned missions in the next two decades, as well as serious plans for human landing missions, a key need is the establishment of accurate, reliable, expansive, and cost-effective positioning and communication service for several users in the Mars environment. The Mars Communication and Navigation (MCN) mission is a multi-satellite constellation at Mars that shall provide data relay and positioning services for the identified possible users, that are orbiters, landers, ascenders, autonomous rovers, and human landing missions. The aim of MCN is to investigate and prototype key technologies for a Mars positioning and communication system using small satellites, in order to enable the development and operations of a wide range of Mars missions, providing a backbone Earth–Mars communication and navigation infrastructure. This work focuses on the critical architectural aspects of the MCN. The end-to-end (E2E) system architecture is presented, in order to provide an overview of the space and ground segments along with the operations concepts. Concerning the orbital configuration, the constellation and its deployment strategy are discussed. The MCN constellation baseline comprises 24 microsatellites operating in a Walker-like orbital configuration at Mars to provide service for more than 70 users potentially. Moreover, a Relay/Gateway link is utilized to serve as a communication bridge between Earth ground segment and the MCN constellation. Concerning the communication and navigation aspects, their architectures and possible solutions are highlighted, together with an overview of the related critical technologies required to achieve the mission objectives

Numerical Investigation of Charring Material Demisability in Atmospheric Entry Conditions

peer reviewedHigh-fidelity models have been developed in the recent years to predict the response of light-weight ablative thermal protection materials used to build heat shields of re-entry capsules. Because the main components of these ablators are typically also present in some spacecraft/satellite components, there is a growing interest in exploring the possible extension of the high-fidelity models to predict demisability of these components. A unified approach simulating the degrading composite material and the high enthalpy flow is extended to treat this type of charring dense material interesting for demise applications. The comparison in between highly porous and dense material shows the numerical challenges to simulate the thermal response of composite carbon fibers materials using this methodology.GSTP #400012271

Base Flow Investigation of the Apollo AS-202 Command Module

In recent years, both Europe and the US are developing hypersonic research and operational vehicles. These include (re)entry capsules (both ballistic and lifting) and lifting bodies such as ExoMars, EXPERT, ARV, CEV and IXV. The research programs are meant to enable technology and engineering capabilities to support during the next decade the development of affordable (possibly reusable) space transportation systems as well as hypersonic weapons systems for time critical targets. These programs have a broad range of goals, ranging from the qualification of thermal protection systems, the assessment of RCS performances, the development of GNC algorithms, to the full demonstration of the performance and operability of the integrated vehicles. Since the aerothermodynamic characteristics influence nearly all elements of the vehicle design, the accurate prediction of the aerothermal environment is a prerequisite for the design of efficient hypersonic systems. Significant uncertainties in the prediction of the hypersonic aerodynamic and the aerothermal loads can lead to conservative margins in the design of the vehicle including its Outer Mould Line (OML), thermal protection system, structure, and required control system robustness. The current level of aerothermal prediction uncertainties results therefore in reduced vehicle performances (e.g., sub-optimal payload to mass ratio, increased operational constraints). On the other hand, present computational capabilities enable the simulation of three dimensional flow fields with complex thermo-chemical models over complete trajectories and ease the validation of these tools by, e.g., reconstruction of detailed wind tunnel tests performed under identified and controlled conditions (flow properties and vehicle attitude in particular). These controlled conditions are typically difficult to achieve when performing in flight measurements which in turn results in large associated measurement uncertainties. Similar problems arise when attempting to rebuild measurements performed in "hot" ground facilities, where the difficulty level is increased by the addition of the free-flow characterization itself. The implementation of ever more sophisticated thermochemical models is no obvious cure to the aforementioned problems since their effect is often overwhelmed by the large measurement uncertainties incurred in both flight and ground high enthalpy facilities. Concurrent to the previous considerations, a major contributor to the overall vehicle mass of re-entry vehicles is the afterbody thermal protection system. This is due to the large acreage (equal or bigger than that of the forebody) to be protected. The present predictive capabilities for base flows are comparatively lower than those for windward flowfields and offer therefore a substantial potential for improving the design of future re-entry vehicles. To that end, it is essential to address the accuracy of high fidelity CFD tools exercised in the US and EU, which motivates a thorough investigation of the present status of hypersonic flight afterbody heating. This paper addresses the predictive capabilities of after body flow fields of re-entry vehicles investigated in the frame of the NATO/RTO - RTG-043 Task Group and is structured as follows: First, the verification of base flow topologies on the basis of available wind-tunnel results performed under controlled supersonic conditions (i.e., cold flows devoid of reactive effects) is performed. Such tests address the detailed characterization of the base flow with particular emphasis on separation/reattachment and their relation to Mach number effects. The tests have been performed on an Apollo-like re-entry capsule configuration. Second, the tools validated in the frame of the previous effort are exercised and appraised against flight-test data collected during the Apollo AS-202 re-entry

Experimental Simulation of a Galileo Sub-Scale Model at Ice Giant Entry Conditions in the T6 Free-Piston Driven Wind Tunnel

Uranus and Neptune, known collectively as the Ice Giants, are the only two planets in the solar system that are yet to be explored with a dedicated mission. Planetary entry probe missions to the Ice Giants were proposed in 2010 by NASA and ESA which prompted a resurgence of interest in experimental simulation of the aero-heating environment that would be encountered by such a spacecraft. More recently, the 2023 - 2032 Decadal Survey recommended that NASA’s highest priority new flagship mission should be a Uranus orbiter and probe with a launch date in the early 2030s. The Oxford T6 Stalker tunnel is the only facility in Europe capable of replicating the high speeds required for Ice Giant entry and is therefore a key stepping stone on the path to realising the goal of an Ice Giant mission. In the present work, a 1:10 scaled model of the Galileo probe has been tested at Ice Giant entry conditions. Conditions for nominal composition (85%H215%He), Stalker substituted, and nominal composition with methane (0.5% and 5% CH4) gas mixtures have been developed and validated for use with a new expansion nozzle via a pitot rake survey. Test flows with flight equivalent velocities greater than 18 km/s have been produced with test times on the order of 30 µs. Heat flux into the model for the developed conditions has been inferred from temperature measurements with a series of coaxial thermocouples. High speed video has been captured to aid in characterisation of the test conditions