Mid-L/D Ballistic Range Aerodynamics Test

This effort proposes to test a subscale version of Mars Mid-L/D vehicle at an (Earth) ballistic test range to gather information about the aerodynamic stability of the design and to calibrate Mid-L/D models. Data regarding the vehicle dynamic response will be collected during the test. This will be used to extract the dynamic aero terms via parameter estimation and simulation matching. Testing is required since the techniques for modeling dynamic aero terms in CFD are experimental and not well validated. Ballistic testing will provide critical test data for future Mid-L/D test flights and also provide valuable data for improving the potential of CFD capabilities in this area. Well-validated vehicle models are needed for correctly predicting the in-flight behavior of the vehicle, which is critical for achieving adequate landing accuracy for human Mars campaigns. A follow-on effort will be needed to refine the model to the level quality needed for achieving accuracy goals. This is a unique proposal which is not otherwise being performed without NASA investments. Current state-of-the-art Entry, Descent, and Landing (EDL) systems for Mars are capable of safely landing ~1 metric ton (mt) on the surface. Human mission studies show that a 20 mt mass capability is required in a single landing. Robotic Mars EDL technologies do not scale up to this mass. A rigid, Mid-L/D approach appears to be a promising solution and draws from recent human spaceflight experience (Shuttle Orbiter). The subscale Mid-L/D ballistic range test is used to validate vehicle aerodynamic models, which are critical for predicting the in-flight behavior of the vehicle and achieving adequate landing accuracy for human Mars campaigns. The subscale model is shot out of a large-caliber gun (120 mm) at a speed of greater than Mach 3. Data regarding the vehicle dynamic response is collected during the test. The data is used to extract the dynamic aero terms via parameter estimation and simulation matching. The testing provides an incremental improvement in understanding the performance of the Mid-L/D shape while serving as a needed development test for performing future Mid-L/D flight tests.

The data from this testing will be used to improve aerodynamic models to be used in EDL simulation studies (TA 9). These studies, tools, and models will be used to design the Mid-L/D vehicle and refine the EDL architecture. This proposal is aligned with the JSC technology priority investment area of Entry, Descent, and Landing (EDL). Current state-of-the-art EDL payload mass capability to the surface of Mars is about 1 metric ton, but human mission studies show the need for 20 - 40 metric tons. The technologies currently used for Mars EDL will not scale up to these masses. NASA is investigating multiple technologies for delivering large mass to the surface. Of these, Mid-L/D is the most scalable and most similar to current human spaceflight experience (Shuttle Orbiter). The proposed ballistic range test provides an incremental improvement in understanding the performance of the Mid-L/D shape while serving as a needed development test for performing future Mid-L/D flight tests (at larger scale and higher velocities). This enables advances in EMC technology needs for EDL technologies and will help close the gaps for Mid-L/D vehicles in the areas of active guidance and accurate landings.

This is early/mid-stage (TRL 4) — the most realistic path in is NASA SBIR/STTR, which funds small businesses and research institutions to develop technology aligned with NASA's needs (equity-free, phased funding). Check whether a current SBIR/STTR solicitation topic overlaps with this project's technology area, or contact the project directly (above) to ask.

None of these are guaranteed paths for this specific project — TechPort itself doesn't have an "apply" button. Reaching out to the contact(s) above with a specific question is usually the fastest way to find out what's actually open.