Search NASA⌕ Search

SEARCH · Search NASA

Results for “DRAGONFLY”

Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.

Quote a phrase for an exact phrase match. Source license links do not imply unrestricted reuse.

At least 37 records · Page 2
All sourcesNASA NTRSDOE OSTI
DOE OSTI2021

Radiological Consequence Evaluation for Dragonfly Mission

The scoping calculations presented in this report were developed to provide a conservative estimate of radiological dose consequences associated with launch accidents involving one multi-mission radioisotope thermoelectric generator (MMRTG) and possibly up to 43 light-weight radioisotope heater units (LWRHUs) for the upcoming National Aeronautics and Space Administration (NASA) Dragonfly mission. This report summarizes dose consequence analysis from SAND2019-11148, “Nuclear Risk Assessment 2019 Update for the Mars 2020 Mission Environmental Impact Statement,” referred to in this document as the Mars 2020 nuclear risk analysis (NRA) and compares those results to a parametric analysis used to analyze potential dose consequences for the Dragonfly mission.

07 ISOTOPE AND RADIATION SOURCES↗
NASA NTRSDate not supplied

Dragonfly Entry and Descent Flight Mechanics Modeling and Analysis

Dragonfly is a New Frontiers Program mission that will deliver a rotorcraft lander to Saturn’s moon, Titan [1]. The focus of this work is to analyze the trajectory from cruise stage separation until lander separation. This analysis is done by the NASA Langley (LaRC) EDL team using Program to Optimize Trajectories II (POST2)[2]. This poster provides an overview of the current design and the robustness of the overall entry sequence as assessed using a Monte Carlo uncertainty analysis. This mission is led by Johns Hopkins Applied Physics Laboratory (APL), presented here is the design and analysis as of the Dragonfly EDL Assembly Preliminary Design Review (PDR).

Modeling↗
NASA NTRSDate not supplied

Aerothermal Analysis of the Dragonfly Titan Entry

Dragonfly is an upcoming NASA New Frontiers mission that will send a rotorcraft lander to Saturn’s moon Titan [1]. This will be the first spacecraft to land on Titan since the Huygens probe’s descent in 2005 and only the second spacecraft overall to enter Titan’s atmosphere. With its dense N 2 atmosphere containing trace amounts of CH 4 , Titan provides a unique entry environment with an unusually long entry sequence and significant radiant heating at relatively low velocities. To address these challenges, the Dragonfly entry capsule design is informed by state-of-the-art aerothermodynamic analysis tools and methodologies that will be laid out in this poster.

EDL↗
NASA NTRSDate not supplied

Dragonfly Mission Entry and Descent Modeling and Simulation Overview

Dragonfly is a New Frontiers Program mission, led by The Johns Hopkins Applied Physics Laboratory, that will deliver a rotorcraft lander to Saturn’s moon, Titan. The focus of this work is to analyze the trajectory of the entry vehicle from cruise stage separation until lander separation. This analysis is done by the NASA Langley Research Center Entry, Descent, and Landing team using the Program to Optimize Trajectories II. This paper provides an overview of the current design and the robustness of the overall entry sequence using a Monte Carlo uncertainty analysis. The work presented in this study includes the updated design, models, and analysis completed since the Dragonfly Entry, Descent, and Landing Mission Preliminary Design Review.

Simulation↗
NASA NTRSDate not supplied

Dragonfly Mission Entry and Descent Modeling and Simulation Overview

Dragonfly is a New Frontiers Program mission, led by The Johns Hopkins Applied Physics Laboratory, that will deliver a rotorcraft lander to Saturn’s moon, Titan. The focus of this work is to analyze the trajectory of the entry vehicle from cruise stage separation until lander separation. This analysis is done by the NASA Langley Research Center Entry, Descent, and Landing team using the Program to Optimize Trajectories II. This paper provides an overview of the current design and the robustness of the overall entry sequence using a Monte Carlo uncertainty analysis. The work presented in this study includes the updated design, models, and analysis completed since the Dragonfly Entry, Descent, and Landing Mission Preliminary Design Review.

Simulation↗
NASA NTRS1972

Azimuth orientation of the dragonfly (Sympetrum)

Evidence is presented of directional orientation by an alighting dragonfly relative to the azimuth of the sun. The effects of wind direction on this orientation are analyzed. It was concluded that wind does not play a major role in orientation but may have some secondary function in helping greater numbers of dragonflies face windward more often than leeward. A search was made to find the principle sensory receptor for orientation. Two possibilities, the large compound eye and the frontal ocelli, were noted; however, no conclusive evidence could be found.

Hisada, M.↗
NASA NTRS2021

Overview of Dragonfly Entry Aerosciences Measurements (DrEAM)

Dragonfly Entry Aerosciences Measurements (DrEAM) is an instrumentation suite for the Dragonfly mission’s entry vehicle heat shield and backshell that satisfies NASA’s Engineering Science Investigation requirement for a New Frontiers mission. Key in-situ measurements will be made in Titan’s atmosphere for the first time. High level DrEAM project goals include the following: measure heat shield near surface and in-depth temperatures; measure backshell near surface and in-depth temperatures; measure pressure at the heat shield and backshell surface; and measure backshell radiative and total heat flux.

EDL↗
NASA NTRSDate not supplied

Technology Development of a Solid State 266 nm Laser for NASA’s Dragonfly Mission

NASA’s Dragonfly mission is a rotorcraft lander which will explore several geologic locations on Saturn’s moon, Titan and investigate evidence of surface-level prebiotic chemistry as well as search for chemical signatures of water-based and/or hydrocarbon-based life. To perform molecular composition investigations in-situ, the payload includes the Dragonfly Mass Spectrometer (DraMS), being developed at NASA’s Goddard Space Flight Center (GSFC). DraMS will utilize laser desorption mass spectrometry (LDMS) to interrogate surface samples and measure the organic composition. Enabling this science capability is the Throttled Hydrocarbon Analysis by Nanosecond Optical Source (THANOS) laser being developed at NASA-GSFC. The THANOS laser is comprised of a solid state, passively Q-Switched Nd:YAG oscillator which is frequency converted to 266 nm and utilizes a RTP high voltage electro-optic for pulse energy control. The laser outputs <2.0 ns pulses with a maximum energy of approximately 200 uJ which can be emitted in 1 - 50 shot bursts at 100 Hz while performing LDMS science operations. While operating, the laser has the capability to throttle its UV pulse energy output from full attenuation to maximum energy to provide varying levels of fluence on samples in the DraMS instrument. This paper reports the technology development and space qualification effort of the THANOS laser including vibration, thermal vacuum cycling, radiation as well as Titan atmospheric composition optical damage testing performed at NASA-GSFC from 2019 through 2022.

Matthew W Mullin↗
NASA NTRSDate not supplied

Dragonfly TPS Sizing and Analysis

Material response analysis methods and results for the design of the Dragonfly thermal protection system (TPS) are presented. The presentation is divided into two parts. In the first part, the primary components of the Dragonfly aeroshell TPS are described, and the methodology used for sizing the TPS materials are documented. In the second part, some modeling challenges unique to the Dragonfly/Titan entry problem are discussed.

Eric Stern↗
NASA NTRSDate not supplied

Development of the Thermal Interface Between the Dragonfly Mass Spectrometer and the DrACO Sample Delivery Carousel

Icy celestial bodies are an exciting new frontier for surface exploration and in-situ sampling and analysis. These destinations are inherently cryogenic in nature, and each body presents unique challenges related to thermal design. The Dragonfly mission to Titan is one such example. One of the most important requirements of a sampling system is to preserve the integrity of the surface material. The interface between the Dragonfly Mass Spectrometer (DraMS) and the Drill for Acquisition of Complex Organics (DrACO) is complicated by several competing requirements. Development of this interface has required the use of new enabling technologies such as 3D printing to achieve a successful design. This overview of the DraMS Cryogenic subsystem will show how the design meets all the requirements of the interface and preserves integrity of Titan surface samples.

Peter W. Barfknecht↗
NASA NTRSDate not supplied

Performance of the Dragonfly Mass Spectrometer (DraMS) Programmable UV Laser Source Engineering Test Unit (ETU)

NASA’s Dragonfly mission will sample surface materials from multiple sites on Saturn’s largest moon, Titan, in exploration of its potential for prebiotic chemistry. We report on the performance of our short-pulsed UV laser transmitter, developed for the Dragonfly’s on-board Mass Spectrometer (DraMS). Our engineering test unit (ETU) has completed flight qualification and demonstrated its operational science requirements, such that the final flight unit build can begin. The Titan Hydrocarbon Analysis Nanosecond Optical Source (THANOS) ETU laser produces 266 nm laser pulses at programmable energy levels in order to create high resolution laser desorption mass spectrometry (LDMS) measurements. The laser operates in short bursts of 1-50 pulses, each at < 2 ns pulse width, at a 100 Hz repetition rate. Creating a sealed Titanium unit, capable of operation on the extreme environment of Titan’s surface was a major engineering challenge. The laser successfully demonstrated its ability to meet all operational requirements in terms of pulse energy, beam pointing on target and repeatability even after extensive environmental testing.

Matthew W Mullin↗
NASA NTRSDate not supplied

Performance of the Dragonfly Mass Spectrometer (DraMS) Programmable UV Laser Source Engineering Test Unit (ETU)

NASA’s Dragonfly mission will sample surface materials from multiple sites on Saturn’s largest moon, Titan, in exploration of its potential for prebiotic chemistry. We report on the performance of our short-pulsed UV laser transmitter, developed for the Dragonfly’s on-board Mass Spectrometer (DraMS). Our engineering test unit (ETU) has completed flight qualification and demonstrated its operational science requirements, such that the final flight unit build can begin. The Titan Hydrocarbon Analysis Nanosecond Optical Source (THANOS) ETU laser produces 266 nm laser pulses at programmable energy levels in order to create high resolution laser desorption mass spectrometry (LDMS) measurements. The laser operates in short bursts of 1-50 pulses, each at < 2 ns pulse width, at a 100 Hz repetition rate. Creating a sealed Titanium unit, capable of operation on the extreme environment of Titan’s surface was a major engineering challenge. The laser successfully demonstrated its ability to meet all operational requirements in terms of pulse energy, beam pointing on target and repeatability even after extensive environmental testing.

Matthew Mullin↗
NASA NTRSDate not supplied

An Investigation of the Dragonfly Mission Aeroshell/Parachute Dynamics through Subscale Drop Tests

The Dragonfly mission will place a rotorcraft/lander on Titan by 2034. The entry, descent, and landing system of the Dragonfly mission includes two parachutes: a drogue and a main. To provide needed data, subscale drop tests were used to conduct an experimental investigation of the aeroshell/parachute dynamics. The drop tests used a Disk-Gap-Band drogue parachute and two types of Ringslot main parachutes. All tests used a representative aeroshell which included the heatshield. All models were geometrically scaled to 16.7 percent. The model aeroshell had a diameter of 0.75 m. The model parachute nominal diameters were 0.9 m for the drogue and 2.78 m for the main. The aeroshell’s mass properties were dynamically scaled to simulate flight at an altitude of 4 km at Titan. This dynamic scaling allowed the conversion of model test results to full-scale Titan conditions. Onboard instrumentation on the aeroshell provided data on the rotation rates, from which the Euler angles were determined. Tests were conducted by lifting the models with a drone to an altitude of 350 m and dropping them inverted. Key results from these tests were: 1) the models were able to recover from the extreme inverted initial condition and settle to low-amplitude oscillations; 2) ninety nine percent of the time the oscillation amplitudes observed with the drogue parachute were 11.4 degrees or less; 3) ninety nine percent of the time the oscillation amplitudes observed with the 20 percent porosity main parachute were 15.4 degrees or less.

Parachutes↗
NASA NTRSDate not supplied

An Investigation of the Dragonfly Mission Aeroshell/Parachute Dynamics through Subscale Drop Tests

The Dragonfly mission will place a rotorcraft/lander on Titan by 2034. The entry, descent, and landing system of the Dragonfly mission includes two parachutes: a drogue and a main. To provide needed data, subscale drop tests were used to conduct an experimental investigation of the aeroshell/parachute dynamics. The drop tests used a Disk-Gap-Band drogue parachute and two types of Ringslot main parachutes. All tests used a representative aeroshell which included the heatshield. All models were geometrically scaled to 16.7 percent. The model aeroshell had a diameter of 0.75 m. The model parachute nominal diameters were 0.9 m for the drogue and 2.78 m for the main. The aeroshell’s mass properties were dynamically scaled to simulate flight at an altitude of 4 km at Titan. This dynamic scaling allowed the conversion of model test results to full-scale Titan conditions. Onboard instrumentation on the aeroshell provided data on the rotation rates, from which the Euler angles were determined. Tests were conducted by lifting the models with a drone to an altitude of 350 m and dropping them inverted. Key results from these tests were: 1) the models were able to recover from the extreme inverted initial condition and settle to low-amplitude oscillations; 2) ninety nine percent of the time the oscillation amplitudes observed with the drogue parachute were 11.4 degrees or less; 3) ninety nine percent of the time the oscillation amplitudes observed with the 20 percent porosity main parachute were 15.4 degrees or less.

Parachutes↗
NASA NTRS2023

Dragonfly Entry and Descent Overview

Dragonfly is a New Frontiers class mission led by Johns Hopkins Applied Physics Laboratory (APL) which will deliver a rotorcraft lander to Saturn’s moon Titan [1] for an extended science mission. The spacecraft will launch in 2027 and arrive at Titan in 2033. This presentation will provide an overview of the Entry and Descent system that is under development to ensure the safe delivery of this unique “relocatable lander” to Titan, with an emphasis on some of the key technical challenges that the team is addressing.

Dragonfly↗
NASA NTRSDate not supplied

Dragonfly Preparation for Powered Flight: Lander Separation State Control to Ensure Successful Landing

NASA’s Dragonfly mission, led by The Johns Hopkins University Applied Physics Laboratory, is a relocatable octocopter lander to study Saturn’s largest moon Titan. The scientific goals of the mission include studying Titan’s prebiotic chemistry, geology, and atmosphere. Upon Titan arrival, the lander will enter the atmosphere, descend on a parachute to a ground-relative altitude of about 1000 m before being released, and then fly on internal power down to the surface. To guarantee desirable initial conditions for the lander release, the lander must meet certain angular rate conditions. These conditions include reducing the spin rate about the vertical axis to 4.9 deg/sec, using the rotors as actuators; and releasing with a negative pitch rate (rotating nose down) to ensure a successful transition to powered flight. This is achieved using a release trigger. Achieving these desired rates for lander release is part of the mission phase known as ‘preparation for powered flight’ (PPF). This paper proposes controls and logic to achieve the desired conditions for releasing the lander from the parachute.

Flight Mechanics↗
NASA NTRSDate not supplied

Dragonfly Preparation for Powered Flight: Lander Separation State Control to Ensure Successful Landing

NASA’s Dragonfly mission, led by The Johns Hopkins University Applied Physics Laboratory, is a relocatable octocopter lander to study Saturn’s largest moon Titan. The scientific goals of the mission include studying Titan’s prebiotic chemistry, geology, and atmosphere. Upon Titan arrival, the lander will enter the atmosphere, descend on a parachute to a ground-relative altitude of about 1000 m before being released, and then fly on internal power down to the surface. To guarantee desirable initial conditions for the lander release, the lander must meet certain angular rate conditions. These conditions include reducing the spin rate about the vertical axis to 4.9 deg/sec, using the rotors as actuators; and releasing with a negative pitch rate (rotating nose down) to ensure a successful transition to powered flight. This is achieved using a release trigger. Achieving these desired rates for lander release is part of the mission phase known as ‘preparation for powered flight’ (PPF). This paper proposes controls and logic to achieve the desired conditions for releasing the lander from the parachute.

Flight Mechanics↗