SuperSmart Parachute Deployment Algorithm for Mars Pinpoint Landing

Wolf, Aron A.; Ivanov, Mark C.

doi:10.2514/6.2008-6942

Cited by 5 publications

(5 citation statements)

References 5 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…A golden-section search method is used to determine the initiation Mach number that corresponds to the minimum PMF trajectory. This initiation strategy is similar to range triggers that have been proposed for Mars missions using supersonic parachutes [15].…”

Section: Srp Initiation Mach Number: Range Triggermentioning

confidence: 94%

Supersonic Retropropulsion Thrust Vectoring for Mars Precision Landing

Mandalia

Braun

2015

Journal of Spacecraft and Rockets

View full text Add to dashboard Cite

Landing heavier payloads with pinpoint precision on the surface of Mars is a known challenge for future missions to Mars. Supersonic retropropulsion has been proposed as a means to deliver higher-mass payloads to the surface, traditionally with the sole intent of deceleration. By adding range control capability during the supersonic retropropulsion maneuver by means of thrust vectoring, it has been found that a substantial amount of propellant can be saved in a precision landing scenario when compared with traditional architectures. Decreasing the propellant mass necessary for the mission increases the amount of payload mass that can be brought to the surface. Propellant mass savings greater than 30% are possible if thrust vectoring is unconstrained during the supersonic phase of flight. Propellant mass fraction is found to be sensitive to the divert direction and also the altitude and flight-path angle at ignition, favoring low altitudes and shallow flight-path angles. Decreased nozzle cant angles and aerodynamic drag preservation have also been found to reduce propellant usage.= reference area, m 2 s = range, m T∕W = thrust-to-weight ratio, referenced to Mars surface gravity V = velocity, m∕s β = ballistic coefficient, kg∕m 2 ΔV = change in velocity, m∕s = flight-path angle, defined as positive above the horizon,°θ = off-velocity thrust angle,°∞ = freestream conditions

show abstract

Section: Srp Initiation Mach Number: Range Triggermentioning

confidence: 94%

Supersonic Retropropulsion Thrust Vectoring for Mars Precision Landing

Mandalia

Braun

2015

Journal of Spacecraft and Rockets

View full text Add to dashboard Cite

show abstract

“…In general, Mars entry lasts several minutes, in this paper about 300 s, which means that the target landing site at the equator moves about km. For future Mars landing accuracy to be within 100 m of the target (Wolf et al, 2004), if Mars rotation is not considered, it will not and cannot reach this goal. Mars rotation has to be taken into account.…”

Section: Numerical Simulation and Analysismentioning

confidence: 99%

“…In general, Mars entry lasts several minutes, in this paper 300 s, which means that the target landing site at the equator moves about km. For future Mars landing accuracy to be within 100 m of the target (Wolf et al, 2004), Mars rotation must be taken into account. Mars rotation was considered in Kluever (2008), which evaluated the performance and advantages of Mars entry guidance for Mars precision landing.…”

Section: Introductionmentioning

confidence: 99%

Comparison of Several Nonlinear Filters for Mars Entry Navigation Using Radiometric Measurements

2017

View full text Add to dashboard Cite

This paper studies the application of several nonlinear filters for the problem of Mars entry navigation by using radiometric measurements from Mars orbiters and Mars Surface Beacons (MSBs). A suitable dynamic model of Mars entry is developed. The movement of MSBs due to Mars rotation is also considered in the measurement model. The performance of an Extended Kalman Filter (EKF), First-order Divided Difference Filter (DDF1), Unscented Kalman Filter (UKF), and Particle Filter (PF) is compared in terms of estimation capability and computation costs. The theoretical Cramer-Rao Lower Bound (CRLB) of estimation errors are derived for Mars entry to evaluate the performance of the filters. A consistency test is also carried out to verify the filters. In simulations, by the comparison of estimation errors, position and velocity Root Mean Square Error (RMSE), error standard deviation versus Square Root of CRLB (SR CRLB), credibility and computation time, it is concluded that DDF1 is preferred for Mars entry navigation.

show abstract

“…However, the errors of the traditional autonomous navigation method, inertial navigation, are of the order of a few kilometres as the navigation errors are always accumulating and the initial errors are hard to correct (Braun and Manning, 2007). It is hard for inertial navigation systems to meet the National Aeronautics and Space Administration (NASA) precise landing requirement that the landing errors are less than 100 m (Qin et al, 2014; Wolf et al, 2004). In 2014, NASA tested the Lander Vision System on the new Mars Lander (Johnson and Golombek, 2012), Mars 2020 Lander Vision System Tested (2016) showed that visual navigation based on feature matching is feasible.…”

Section: Introductionmentioning

confidence: 99%

A Novel Approach to Visual Navigation based on Feature Line Correspondences for Precision Landing

Shao

et al. 2018

J. Navigation

View full text Add to dashboard Cite

To satisfy the needs of precise pin-point landing missions in deep space exploration, this paper proposes a method based on feature line extraction and matching to estimate the attitude and position of a lander during the descent phase. Linear equations for a lander's motion parameters are given by using at least three feature lines on the planetary surface and their two-dimensional projections. Then, by taking advantage of Singular Value Decomposition (SVD), candidate solutions are obtained. Lastly, the unique lander's attitude and position relative to the landing site are selected from the candidate solutions. Simulation results show that the proposed algorithm is able to estimate a lander's attitude and position robustly and quickly. Without an extended Kalman filter, the average errors of attitude are less than 1°and the average errors of position are less than 10 m at an altitude of 2,000 m. With an extended Kalman filter, attitude errors are within 0·5°and position errors are within 1 m at an altitude of 247·9 m.

show abstract

SuperSmart Parachute Deployment Algorithm for Mars Pinpoint Landing

Cited by 5 publications

References 5 publications

Supersonic Retropropulsion Thrust Vectoring for Mars Precision Landing

Supersonic Retropropulsion Thrust Vectoring for Mars Precision Landing

Comparison of Several Nonlinear Filters for Mars Entry Navigation Using Radiometric Measurements

A Novel Approach to Visual Navigation based on Feature Line Correspondences for Precision Landing

Contact Info

Product

Resources

About