NDLI: Mortar deployment extensibility for the Low Density Supersonic Decelerator parachute

Content Provider	IEEE Xplore Digital Library
Author	Adams, D.S.
Copyright Year	2014
Description	Author affiliation: Johns Hopkins Univ. Appl. Phys. Lab., Laurel, MD, USA (Adams, D.S.)
Abstract	A pilot ballute deployment planned for use with the Low Density Supersonic Decelerator parachute is shown to be capable of producing canopy initial presentation and inflation conditions functionally equivalent to those encountered in a traditional mortar deployment. This equivalence is critically important as it allows the pilot deployed test results to be extended to a mortar deployment without necessitating the use of a large mortar. In this manner the as-tested parachute can be brought to TRL 6 making it suitable for use in future Mars landed missions. This equivalence is achieved through the use of a full-scale decelerator system with matching flow characteristics and vehicle relative velocities. Most notably, a solution was found that maintains at least some tension in the parachute rigging throughout the deployment process and releases the ballute prior to line stretch such that the parachute extraction from the deployment bag is unaided and proceeds in a manner nearly identical to that expected for a Mars mortar deployment. The pilot ballute is also shown to automatically compensate for the uncertainty in dynamic pressure inherent to the uncontrolled flight of the test vehicle. Hence, the test deployment problem reduces to designing for a minimum ballistic coefficient ratio between the vehicle and the ballute/pack system. The ensuing design is demonstrated to be robust to the expected LDSD deployment environment.
Sponsorship	IEEE Aerosp. Electron. Syst. Soc.
Starting Page	1
Ending Page	9
File Size	1990902
Page Count	9
File Format	PDF
e-ISBN	9781479916221
DOI	10.1109/AERO.2014.6836489
Language	English
Publisher	Institute of Electrical and Electronics Engineers, Inc. (IEEE)
Publisher Date	2014-03-01
Publisher Place	USA
Access Restriction	Subscribed
Rights Holder	Institute of Electrical and Electronics Engineers, Inc. (IEEE)
Subject Keyword	Cameras
Content Type	Text
Resource Type	Article

Sl.	Authority	Responsibilities	Communication Details
1	Ministry of Education (GoI), Department of Higher Education	Sanctioning Authority	https://www.education.gov.in/ict-initiatives
2	Indian Institute of Technology Kharagpur	Host Institute of the Project: The host institute of the project is responsible for providing infrastructure support and hosting the project	https://www.iitkgp.ac.in
3	National Digital Library of India Office, Indian Institute of Technology Kharagpur	The administrative and infrastructural headquarters of the project	Dr. B. Sutradhar bsutra@ndl.gov.in
4	Project PI / Joint PI	Principal Investigator and Joint Principal Investigators of the project	Dr. B. Sutradhar bsutra@ndl.gov.in Prof. Saswat Chakrabarti will be added soon
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Low Density Supersonic Decelerator Parachute Decelerator System

Parachute Decelerator System Performance During the Low Density Supersonic Decelerator Program's First Supersonic Flight Dynamics Test

Thermal Design and Analysis of the Supersonic Flight Dynamics Test Vehicle for the Low Density Supersonic Decelerator Project

Plume Induced Aerodynamic and Heating Models for the Low Density Supersonic Decelerator Test Vehicle

Low Density Supersonic Decelerator (LDSD) Supersonic Flight Dynamics Test (SFDT) Plume Induced Environments Modelling

Post-Flight Assessment of Low Density Supersonic Decelerator Flight Dynamics Test 2 Simulation

An Overview of the Mars Science Laboratory Parachute Decelerator System

The first balloon flight of the Low Density Supersonic Decelerator technology demonstration mission

Results from the Mars Science Laboratory Parachute Decelerator System Supersonic Qualification Program

Mortar deployment extensibility for the Low Density Supersonic Decelerator parachute

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