Feasibility and Performance Analysis of Neptune Aerocapture Using Heritage Blunt-Body Aeroshells

Girija, Athul Pradeepkumar; Saikia, Sarag J.; Longuski, James M.; Bhaskaran, Shyam; Smith, Matthew; Cutts, J. A.

doi:10.2514/1.a34719

Cited by 10 publications

(8 citation statements)

References 34 publications

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“…The vehicle state is propagated using a variable-step Runge-Kutta numerical integration method of order 5(4) [30]. The vehicle is initialized at the atmospheric interface altitude h atm , and the values used are listed in Table 1 [34][35][36]38]. For each target destination, a representative planet-relative entry velocity V R;0 is defined based on entry velocities of previous planetary entry missions or aerocapture mission studies [31][32][33].…”

Section: A Methodologymentioning

confidence: 99%

Flight Mechanics Feasibility Assessment for Co-Delivery of Direct-Entry Probe and Aerocapture Orbiter

Albert

Schaub

Braun

2022

Journal of Spacecraft and Rockets

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The co-delivery of a direct-entry probe and an aerocapture orbiter from a single atmospheric entry state is a novel way to include ride-along probes or orbiters on interplanetary missions. This is made possible through combining two technologies: low-cost small satellites and aerocapture. This study investigates the feasibility of this co-delivery method from a flight-mechanics perspective. The availability of direct-entry and aerocapture trajectories from a single entry flight-path angle is assessed for a large range of feasible ballistic coefficients at Earth, Mars, Venus, Titan, and Neptune. Apoapsis altitude, peak heat flux, total heat load, and peak g-load are also quantified across this trade space. A representative scenario implementing closed-loop guidance is presented for a proof of concept, and the trajectory dispersions due to relevant uncertainties are quantified in a Monte Carlo analysis. Passive ballistic impactor or penetrator probes as a secondary mission with a primary lift-modulated aerocapture orbiter is identified as the most promising configuration.

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Section: A Methodologymentioning

confidence: 99%

Flight Mechanics Feasibility Assessment for Co-Delivery of Direct-Entry Probe and Aerocapture Orbiter

Albert

Schaub

Braun

2022

Journal of Spacecraft and Rockets

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“…Figure 2 shows an example feasibility chart for lift modulation aerocapture at Neptune created by using AMAT. (Girija et al, 2020;Saikia et al, 2021).…”

Section: Rapid Design Capabilitymentioning

confidence: 99%

“…AMAT can be used to perform Monte Carlo simulations to assess user-defined guidance schemes and system performance with a vehicle design and interplanetary trajectory considering navigation, atmospheric, and aerodynamic uncertainties as shown in Figure 4. (Girija et al, 2020).…”

Section: Rapid Design Capabilitymentioning

confidence: 99%

“…Interplanetary trajectory trade space (left, generated using STOUR code) and aerocapture feasibility chart for Neptune (right, generated using AMAT). Figure based on the mission design presented in(Girija et al, 2020;Saikia et al, 2021).…”

mentioning

confidence: 99%

“…Examples of Monte Carlo simulation resultsshowing post-aerocapture orbit parameters for a drag modulation system at Venus (left) and a lift modulation system at Neptune (right) computed by using AMAT. Based on(Girija et al, 2020).…”

mentioning

confidence: 99%

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