Mars Exploration Rover Parachute Decelerator System Program Overview

Witkowski, Allen; Bruno, R.

doi:10.2514/6.2003-2100

Cited by 31 publications

(13 citation statements)

References 4 publications

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“…In this paper, we utilize a D 0 = 19.7m nominal diameter DiskGap-Band parachute [11] to establish a 6DOF mathematical model of the parachute and vehicle system. The parachute performance in Mars deployment conditions is very well, which is verified through supersonic and subsonic wind tunnel test program [12].…”

Section: Dof Mathematical Modelmentioning

confidence: 65%

A 6DOF mathematical model of parachute in Mars EDL

Shen

Xia

Sun

2015

Advances in Space Research

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Section: Dof Mathematical Modelmentioning

confidence: 65%

A 6DOF mathematical model of parachute in Mars EDL

Shen

Xia

Sun

2015

Advances in Space Research

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“…The MER parachute system consisted of a single-stage mortar-deployed DGB parachute of 14.1 m in diameter. 79,80 As with the MPF DGB parachute, the MER DGB parachute had an elongated band (as compared to the Viking DGB parachute geometry) to enhance the parachute's stability -a key requirement of MPF's and MER's EDL architecture. Deployment of the parachute was initiated at a dynamic pressure of approximately 729 Pa for American Institute of Aeronautics and Astronautics MER A and 765 Pa for MER B, with corresponding Mach numbers of approximately 1.8 and 1.9, respectively.…”

Section: 78mentioning

confidence: 99%

Aerodynamic Decelerators for Planetary Exploration: Past, Present, and Future

Cruz

Lingard²

2006

AIAA Guidance, Navigation, and Control Conference and Exhibit

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In this paper, aerodynamic decelerators are defined as textile devices intended to be deployed at Mach numbers below five. Such aerodynamic decelerators include parachutes and inflatable aerodynamic decelerators (often known as ballutes). Aerodynamic decelerators play a key role in the Entry, Descent, and Landing (EDL) of planetary exploration vehicles. Among the functions performed by aerodynamic decelerators for such vehicles are deceleration (often from supersonic to subsonic speeds), minimization of descent rate, providing specific descent rates (so that scientific measurements can be obtained), providing stability (drogue function -either to prevent aeroshell tumbling or to meet instrumentation requirements), effecting further aerodynamic decelerator system deployment (pilot function), providing differences in ballistic coefficients of components to enable separation events, and providing height and timeline to allow for completion of the EDL sequence. Challenging aspects in the development of aerodynamic decelerators for planetary exploration missions include: deployment in the unusual combination of high Mach numbers and low dynamic pressures, deployment in the wake behind a blunt-body entry vehicle, stringent mass and volume constraints, and the requirement for high drag and stability. Furthermore, these aerodynamic decelerators must be qualified for flight without access to the exotic operating environment where they are expected to operate. This paper is an introduction to the development and application of aerodynamic decelerators for robotic planetary exploration missions (including Earth sample return missions) from the earliest work in the 1960s to new ideas and technologies with possible application to future missions. An extensive list of references is provided for additional study.

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“…Their history dates back to 19 th Century. A vital part of the sounding rockets is a deceleration system for which any failure leads to entire failure of the rocket mission [1]. It is very helpful to design quick and easy-to-use universal deceleration system.…”

Section: Introductionmentioning

confidence: 99%

Designing a Universal Deceleration System for Sounding Rockets Lighter than 100kg by System Engineering Approach

Samani¹

2017

AAOAJ

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For many years deceleration systems are developed in evolutionary fashion. This evolution needed flight test, and experimental data. This research deals with designing a deceleration system for a sounding rocket. It is mainly aimed at designing a universal deceleration system so that the payload touches the land with a safe velocity. To do so, first a deceleration system is designed for a 25kg payload in altitudes of less than 2km.Having considered flight equations for the sounding rocket and parachute, a number of parameters including recovery weight, landing time and velocity and maximum post-deployment acceleration have been computed for sounding rockets lighter than 250kg. Sensitivity analysis of the payload weight and recovery initiation velocity led to designing a universal deceleration system capable of recovering sounding rockets weighing between 25kg and 75kg with a landing velocity between l0 m/sec and 12m/ sec. Base on system engineering approach, universal deceleration subsystem is design for sounding rocket with various mass.

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Mars Exploration Rover Parachute Decelerator System Program Overview

Cited by 31 publications

References 4 publications

A 6DOF mathematical model of parachute in Mars EDL

A 6DOF mathematical model of parachute in Mars EDL

Aerodynamic Decelerators for Planetary Exploration: Past, Present, and Future

Designing a Universal Deceleration System for Sounding Rockets Lighter than 100kg by System Engineering Approach

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