Overview and reconstruction of the ASPIRE project's SR01 supersonic parachute test

O’Farrell, Clara; Karlgaard, Chris; Tynis, Jake A.; Clark, Ian G.

doi:10.1109/aero.2018.8396502

Cited by 24 publications

(3 citation statements)

References 7 publications

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“…The textile was woven into broadcloth with a crosshatch pattern with regular intervals that reinforces against ripping and tearing [ 8 ] at the peak load experienced by parachutes during supersonic inflation (Δ P > 144.56 kN). [ 53 ] To imbue these nylon parachute textiles with strain sensing ability, it was chosen to stitch on the OL composed of a clear, soft, thermoplastic elastomer ( D = 1 mm, E t = 9.3 MPa, n = 1.54; Crystal Tec, Inc.; Figure S14, Supporting Information) core that was clad with silicone ( n = 1.5, E t = 0.4 MPa; RTV silicone) and then coated with an opaque black silicone ( E t = 0.4 MPa, RTV silicone) as depicted in Figure 1b.…”

Section: Methodsmentioning

confidence: 99%

Measurement of Parachute Canopy Textile Deformation Using Mechanically Invisible Stretchable Lightguides

Mishra

et al. 2022

Adv Materials Technologies

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Conventional strain gauges are not designed for accurate measurement over the large range of deformations possible in compliant textiles. The thin, lightweight, and flexible nature of textiles also makes it challenging to attach strain gauges in a way that does not affect the mechanical properties. In this manuscript, soft, highly extensible fibers that propagate light (i.e., stretchable lightguides) are stitched as a strain gauge to map the deformation of a nylon parachute textile under tension. When under load, these fiber optic strain gauges propagate less light, and this strain‐induced light modulation is used to accurately (absolute error≈2.93%; Std. Dev.: 3.02%) measure strain in the <30% range before these textiles fail. This system has directionality; strain in parallel to the sensor results in little light attenuation while perpendicular loading shows high sensitivity (Gauge factor⊥≈24.8 and Gauge factor||≈0.05 at the first 1% strain). Structural and optical simulations are coupled to demonstrate that load transfer on the fiber optic by the stitchwork is the dominating cause of signal modulation. To further validate the hypotheses, digital image correlation was used under dynamic loading conditions to show that these sensors do not significantly affect the mechanical properties.

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Section: Methodsmentioning

confidence: 99%

Measurement of Parachute Canopy Textile Deformation Using Mechanically Invisible Stretchable Lightguides

Mishra

et al. 2022

Adv Materials Technologies

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“…The first flight test (SR01) occurred on 4 th October 2017 13 . The two-stage sounding rocket delivered the payload (containing the parachute and the instrumentation) to an altitude of roughly 50 km.…”

Section: Figure 4 Trajectory During the First Flight Test (Sr01) Figures Show The Variation Of Mach Number Altitude Attitude And Dynamicmentioning

confidence: 99%

ASPIRE Aerodynamic Models and Flight Performance

Muppidi

O’Farrell

Norman

et al. 2019

AIAA Aviation 2019 Forum

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Experiments (ASPIRE) project was established to test full-scale supersonic parachutes at Mars-relevant conditions, as a risk-reduction activity for NASA's upcoming Mars2020 mission. Deployment and inflation of Disk-Gap-Band (DGB) parachutes were examined at Mach number and dynamic pressure conditions relevant to Mars2020, using a sounding rocket platform. The flight tests examined two parachutes: a build-to-print version of the parachute used by the Mars Science Laboratory and a strengthened version of this parachute that has the same geometry but differs in materials and construction. The first flight test (SR01) of the built-to-print parachute took place on October 4, 2017, followed by the first test of the strengthened parachute during flight SR02 on March 31, 2018. A second test of the strengthened parachute with a higher target load, SR03, took place on September 7, 2018. Over the sequence of the three tests, the parachute was exposed to increasing aerodynamic loads with the peak load during SR03 being significantly larger than is expected during a Martian descent. All three tests were successful: the parachute deployment and inflation occurred at the intended conditions, the measurement systems performed as designed and provided the data, and the parachutes survived the aerodynamic loads they were exposed to. The flight tests yielded valuable data on parachute forces and high-speed imagery of the deployment and inflation process.The final paper will provide details of the aerodynamic behavior and performance of the parachute over the three tests, along with comparisons to pre-flight predictions.

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“…Therefore, based on the predicted trajectory of atmospheric reentry, on-site measurement of atmospheric conditions above the landing site is essential for conducting post-flight analysis. 4,6,7) However, from the perspective of pre-flight prediction, it is impossible to obtain information on the flight day in advance. Even if the information is obtained at the same time of the day, it cannot be effective if the weather is unstable.…”

Section: Introductionmentioning

confidence: 99%

Landing Point Analysis and Forecast Wind Data Validation for Low-Ballistic-Coefficient Flight Vehicles with a Deployable Aeroshell

Nagata

Yamada

Nakao

2022

Trans. Japan Soc. Aero. S Sci.

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In this study, the landing point ellipse predicted using the Earth GRAM atmosphere model and the pinpointed landing point predicted using NCEP GFS forecast data are validated using flight data for a low-ballistic-coefficient flight vehicle with a deployable aeroshell. The equations of motion in the Earth-centered Earth-fixed (ECEF) coordinate system are used for the atmospheric re-entry trajectory calculation, combined with the atmospheric model or the forecast data. The flight data of the RATS, which was launched by the S-520-31 sounding rocket, is used for validation. It was confirmed that the actual landing point is located within the 1• landing error ellipse calculated using Monte Carlo simulation with Earth GRAM. It was found that the closer the forecast data was to the flight data, the more accurate the forecast became, and the smaller the change in the landing point for each forecast update. The maximum likelihood trajectory using the NCEP GFS forecast data available immediately before the flight is similar in shape to the actual flight trajectory, and the difference in the landing point is approximately 1 km.

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Overview and reconstruction of the ASPIRE project's SR01 supersonic parachute test

Cited by 24 publications

References 7 publications

Measurement of Parachute Canopy Textile Deformation Using Mechanically Invisible Stretchable Lightguides

Measurement of Parachute Canopy Textile Deformation Using Mechanically Invisible Stretchable Lightguides

ASPIRE Aerodynamic Models and Flight Performance

Landing Point Analysis and Forecast Wind Data Validation for Low-Ballistic-Coefficient Flight Vehicles with a Deployable Aeroshell

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