Parachutes Supersonic portion – Hemisflo Ribbon Most practical for velocities up to Mach 3 Subsonic portion – Ringsail Parachutes Historically proven success.

Slides:

Advertisements

Similar presentations

Mig-29 A Flight Model data

Advertisements

PANTHR Hybrid Rocket Final Design Review December 6 th 2006.

MAE 4261: AIR-BREATHING ENGINES

International Planetary Probe Workshop 10

DOC-TAS-EN-002 ExoMars-2018 DM Entry Decent Landing LSSWS# December 2014 Turin.

M. R. Tetlow and C.J. Doolan School on Mechanical Engineering

Mission To Mars In Kerbal Space Program, Where distances are 1/9 real world values.

Babakin Space Center, Space Research Insitute, Makeev Rocket Design Bureau COSMOS ONE: THE FIRST SOLAR SAIL a project of The Planetary Society with Cosmos.

MAE 4262: ROCKETS AND MISSION ANALYSIS Single and Multi-Stage Rockets September 9, 2014 Mechanical and Aerospace Engineering Department Florida Institute.

Copyright 2011 | Company Proprietary Parachute Development for Venus Missions Christopher Kelley – Airborne Systems Robert Sinclair – Airborne Systems.

Minimalist Human Mars Mission Surface infrastructure discussion July 26 th, 2008.

AAE450 Spring 2009 Propellant Choice and Mass Estimates for the Translunar OTV Week 2 Presentation Thursday, Jan 22, 2009 Brad Appel Propulsion Group.

AAE450 Spring 2009 Hopper Trajectory February 26, 2009 [Alex Whiteman] [Mission Ops] [Lunar Descent] Page 1.

AAE 450 Spring 2008 Dana Lattibeaudiere February 7, 2008 New Code Developments.

AAE450 Spring 2009 Analysis of Trans-Lunar Spiral Trajectory [Levi Brown] [Mission Ops] February 12,

AAE450 Spring 2009 Descent Trajectory Hover Trajectory LD Code Integration John Aitchison March 5 th, 2009 [John Aitchison] [Mission Ops]

AAE450 Spring 2009 Translunar OTV (Orbital Transfer Vehicle) : Chemical Propulsion System Refined estimates: OTV WET Mass, Propellant Volume & Propellant.

Class 4: Fundamentals of Rocket Propulsion

Spacecraft Propulsion Dr Andrew Ketsdever Lesson 13 MAE 5595.

AAE450 Senior Spacecraft Design Goppert, 1 James Goppert Week 6: February 22 th, 2007 Aerodynamics: Reentry Optimization Dynamics and Control: Communication.

AAE450 Senior Spacecraft Design Ben Jamison Week 5: February 15th, 2007 Aeronautics Group Taxi Capsule Vehicle Group ET/MT Group Integration Group.

Preliminary Rocket Design Objectives: 1. Comprehend a preliminary sizing example for a rocket 2. Explain basic trade-offs in rocket design.

Mass Estimations for Tami RCS: 4kg each * 24 engines = 96 kg Parachutes: Supersonic = 136 kg Subsonic = 595 kg Retro Engine: 135 kg (OMS) Propellants:

AAE450 Senior Spacecraft Design Atul Kumar Presentation Week 3: February 1 st, 2007 Aerodynamics Team Re-Entry vehicle analysis - Lifting body 1.

Rocket Propulsion Contents: Review Types of Rockets New concept 1 Example 1 Whiteboards 1,2,3Whiteboards123 Concept 2, Example 2Concept 2Example 2 Whiteboards:

Launch System Launch Vehicle Launch Complex Orbit Insertion Orbit Maneuvers.

AE 1350 Lecture Notes #13.

MER PDS PDR - Document No. EA Mars Exploration Rover 3 April 2001ACW - 1 Welcome MER Parachute DeceleratorSystem Preliminary Design Review.

A Simple Entry, Descent, and Floating System for Planetary Ballooning Daisuke Akita Tokyo Institute of Technology.

Rockets Tuesday: Rocketry Wednesday: Meet in my room 601: hydrogen demo and Quiz over rocketry. Thursday: Satellites and Orbital Mechanics Friday: Satellites,

EXTROVERTSpace Propulsion 02 1 Thrust, Rocket Equation, Specific Impulse, Mass Ratio.

Ryan Mayes Duarte Ho Jason Laing Bryan Giglio. Requirements  Overall: Launch 10,000 mt of cargo (including crew vehicle) per year Work with a $5M fixed.

Critical Design Review Presentation Jan. 20, 2011.

Team PM8 Eventus Slide 1. Commercial spaceflight has seen increased activity as more privately owned companies invest in the venture. To avoid a catastrophic.

REVISION What force keeps the satellite orbiting the Earth.? (1)

1 Weekly Summary Asteroid Sample Return Spring Semester March 5, 2008 Ashley Chipman.

AAE 450- Propulsion LV Stephen Hanna Critical Design Review 02/27/01.

STRATEGIES FOR MARS NETWORK MISSIONS VIA AN ALTERNATIVE ENTRY, DESCENT, AND LANDING ARCHITECTURE 10 TH INTERNATIONAL PLANETARY PROBE WORKSHOP June,

Mars Today 1 An immediate and inexpensive program for manned Mars visitation.

MAE 4262: ROCKETS AND MISSION ANALYSIS

AAE450 Spring 2009 Lunar Lander Main Engine Thaddaeus Halsmer Thursday, February 12, 2009 Thaddaeus Halsmer, Propulsion.

Multi-Mission Earth Entry Vehicle: Aerodynamic and Aerothermal Analysis of Trajectory Environments Kerry Trumble, NASA Ames Research Center Artem Dyakonov,

NOON UNO HIGH-MOBILITY MARS EXPLORATION SYSTEM DANIEL MCCAFFERY JEFF ROBINSON KYLE SMITH JASON TANG BRAD THOMPSON.

Rocket Propulsion Contents: Review Types of Rockets New concept 1 Example 1 Whiteboards 1,2,3Whiteboards123 Concept 2, Example 2Concept 2Example 2 Whiteboards:

MAE 5360: Hypersonic Airbreathing Engines Ramjet Overview Mechanical and Aerospace Engineering Department Florida Institute of Technology D. R. Kirk.

AAE 450 Spring 2008 Ricky Hinton February 6 th, 2008 Propulsion Group Solid Propellant Research and Optimum Expansion Ratio Code Additional help from:

High Altitude Free Fall: Theoretical Analysis of Physical Hazards Impacting Human Subjects V. Rygalov, Ph.D., J. Jurist, Ph.D., Space Studies Students.

A&AE 450 – Senior Design Jeremy Davis Group A – Aerodynamics Preliminary Design Analysis January 23, 2001.

Review of Past and Proposed Mars EDL Systems. Past and Proposed Mars EDL Systems MinMars Mars entry body design is derived from JPL Austere Mars entry.

Space Shuttle  Presentation by:  Adjunct Professor Walter Barry  Space Shuttle launch  Orbit  Re-entry  Private Enterprise.

Critical Design Review Presentation Project Nova.

1AAE 450 Spring 2008 Scott Breitengross Mar 27, 2008 Trajectory group, Delta V, Saturn V, Feasability Determination, 1 kg Final Design Final Presentation.

AAE450 Senior Spacecraft Design Goppert, 1 James Goppert Week 8: March 8 th, 2007 Aerodynamics: Reentry Optimization Dynamics and Control: Communication.

AAE 450 Spring 2008 Trajectory Code Validation Slides 04/12/08.

Rocket Propulsion Contents: Review Types of Rockets New concept 1

The mariner mark-III Dragon series

MAE 5360: Hypersonic Airbreathing Engines

Analysis of Rocket Propulsion

Find the velocity of a particle with the given position function

FLUID MECHANICS: DERIVATION OF THRUST EQUATION

Junichi (Jun) Kanehara 03/06/2008 Trajectory The Winner of the Balloon, 5[kg] case (LB-HA-DA-DA_v125) & New Version of Trajectory 3-D Plots AAE 450 Spring.

Ricky Hinton February 21st, 2008 Propulsion Group CAD group Updated Altitude vs. Pressure Code and Nozzle CAD AAE 450 Spring 2008.

John Beasley 3/20/2008 Propulsion Group Contact: Black Boxes and Code Flowchart AAE 450 Spring 2008.

Propulsion – Attitude Control Casey Kirchner

Section 5: Lecture 3 The Optimum Rocket Nozzle

Rocket Physics The Rocket Nozzle

Team A Propulsion 1/16/01.

University of Iowa USLI

Stephan Shurn 20 March 2008 Propulsion Final Slides Rail Guns and LITVC AAE 450 Spring 2008.

Parachutes Changed Supersonic portion of descent

Presentation transcript:

Parachutes Supersonic portion – Hemisflo Ribbon Most practical for velocities up to Mach 3 Subsonic portion – Ringsail Parachutes Historically proven success rate Reefed for a short time to decrease max g- load during deployment and increase parachute stability

Parachutes Continued Landing parachute – Volplane Developed for the Pioneer spacecraft, tested with the Gemini capsule (L/D)max = 3.0 Provide softer landing and maneuverability

Parachute Code Written by Jeremy Davis for Spring 2001, modified by Jon Edwards Consists of 6 Matlab files subreefeom.m / supereom.m subreefdiam.m / superdiam.m supersubhm.m acceldiff.m

Parachute Sample Case Initial Conditions Altitude at Mach 3 = 17.5 km Flight Path Angle = 45 deg Mass = kg

Parachute Sample Case Con’t Supersonic Stage 7 hemisflo ribbon parachutes D = 25 m Total Mass = 278 kg Deployment time = 42 s

Parachute Sample Case Con’t Subsonic Reefed Stage 3 reefed ringsail parachutes Reefing factor = 0.3 Inflated area = 0.3 * max inflation area Reefing time = 10 s

Parachute Sample Case Con’t Subsonic Un-reefed Stage 3 ringsail parachutes let open to full inflation by cutting the reefing line Total mass = 222 kg D = 38.5 m Deployment time = 39 s Landing Speed = 55.7 m/s

Altitude History

Velocity History

Acceleration History (G-load)

Propulsion Systems Shuttle OMS Engine - Retro/Boost F = 6000 lbf Isp = 313 s NTO and MMH propellants (non-cryo) Mass = kg

Propulsion Systems Cont’d Marquardt R-40A – RCS System F = 500 lbf Isp = 306 s NTO and MMH propellants (non-cryo) Mass = 10 kg 24 R-40A’s – 8 in each plane Also used on Shuttle Orbiter

Engine Tank Sizing Code tanksize.m Written by Casey Kirchner for Spring 2001, modified by Jon Edwards Changes No descent or hovering delta v’s No heat shield OMS Isp, expansion ratio and RCS Isp Landing mass Vehicle Dimensions

Tank Sizing Sample Case Initial Conditions Mass = kg Periapsis lowering/raising delta v = 20 m/s Hab length = 16.5 m Hab diameter = 13 m

Tank Sizing Sample Case Oxidizer tank (cylindrical w/ hemi ends) Length = 0.90 m Diameter = 1.00 m Fuel tank (cylindrical w/ hemi ends) Length = 0.94 m Diameter = 1.00 m Pressurant Tank (spherical) Diameter = 1.36 m

Tank Sizing Sample Case Oxidizer Tank mass = kg Propellant mass = kg Fuel Tank mass = kg Propellant mass = kg Pressurant Tank mass = 4.70 kg Pressurant mass = 6.07 kg

Tank Sizing Sample Case Structural support According to Humble we add 10% of total inert mass for structural support Structural support mass = 4.19 kg Total Mass = kg