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Structural Design and AnalysisENAE 483/788D - Principles of Space Systems Design
U N I V E R S I T Y O FMARYLAND
Structural Design and Analysis• Loads and Load Sources/Environments
– Designing for Critical Loads– Load Information / Estimation
• Piece Parts Analysis– Margin of Safety Definition– Factors of Safety – Summary Table
• Important Structural Concepts– Primary/Secondary Structure– Failsafe & Fracture Critical Structure– Aerospace Materials– Structural Failure
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Structural Design and AnalysisENAE 483/788D - Principles of Space Systems Design
U N I V E R S I T Y O FMARYLAND
Loads• "Designing Load" is the load that determines one or more structural
characteristic of the part:– shape, thickness, strength, stiffness, material...
• Critical Load (somewhat synonymous) is more exactly the load that gives the minimum margin of safety (MS) for a part– MS represents the amount of extra structural capability you have over the
applied load (elbow room)
• Examples of Critical Loads– pressurization loads for a solid rocket casing– launch loads for a spacecraft (𝑁𝑁𝑥𝑥 ,𝑁𝑁𝑦𝑦,𝑁𝑁𝑧𝑧,𝑀𝑀𝑥𝑥𝑦𝑦,𝑀𝑀𝑦𝑦𝑧𝑧 ,𝑀𝑀𝑧𝑧𝑥𝑥)– thermal loads for a propulsion subsystem– crash loads for a car
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Structural Design and AnalysisENAE 483/788D - Principles of Space Systems Design
U N I V E R S I T Y O FMARYLAND
Load Sources• Where do these loads come from?
• For every part (subsystem) in your design, you should review every phase of its life
and identify all loads that have the potential to be critical:
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• manufacturing & assembly• test (qualification, proof test)• transportation (truck or launch)
• operation• contingencies (crash landing)
• Obtain or estimate loads• look up loads in reference books
• ask other groups to determine loads
• guesstimate for the purposes of
starting analysis
• Calculate all margins of safety
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Structural Design and AnalysisENAE 483/788D - Principles of Space Systems Design
U N I V E R S I T Y O FMARYLAND
Launch Vehicle Loads• Max Q - Aerodynamic Loads
– maximum pressure and bending on vehicle• Max g's
– usually occurs at stage burnout– maximum axial load on vehicle and payload – depends on
mass distribution• Abrupt environmental & vehicle changes
– internal and external pressure drop – “Ascent Venting”– dramatic thermal changes
• Staging shock loads– high g's, high frequency shock response
• Random vibration and acoustics 𝐺𝐺𝑟𝑟𝑟𝑟𝑟𝑟 = 𝜋𝜋𝑓𝑓𝑛𝑛 𝑃𝑃𝑃𝑃𝐷𝐷𝑖𝑖𝑛𝑛𝑖𝑖𝑖𝑖𝑖𝑖4𝜁𝜁
–Some of these loads apply to payload as well
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𝑄𝑄 =12𝜌𝜌𝑉𝑉2
https://femci.gsfc.nasa.gov/random/
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Structural Design and AnalysisENAE 483/788D - Principles of Space Systems Design
U N I V E R S I T Y O FMARYLAND
Launch Vehicle Failures• LV failures are tied to the following subsystems
– Propulsion (70%)– Avionics (11%)– Separation (8%)– Electrical (7%)– Structural (2%)
• Propulsion or Control System Failure More Common
– Conestoga, LLV, Ariane V, and Antares –Structural Failure Relatively Rare– AmRoc, Shuttle, Pegasus, and Falcon 9
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Structural Design and AnalysisENAE 483/788D - Principles of Space Systems Design
U N I V E R S I T Y O FMARYLAND
Launch Vehicle Failures– SpaceX Structural… (>>2%)
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https://www.nasa.gov/sites/default/files/atoms/files/public_summary_nasa_irt_spacex_crs-7_final.pdf
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Structural Design and AnalysisENAE 483/788D - Principles of Space Systems Design
U N I V E R S I T Y O FMARYLAND
Spacecraft On-Orbit Loads • Accelerations
– orbital accelerations– gravity gradient– spinning– on-board disturbances– thrusting (attitude control, reboost)
• Thermal Loads– sun / shadow thermal gradients– eclipse effects (thermal snap)
• Other Special Cases– EVA loads (corners & edges)– rendezvous & docking
• Generally spacecraft are designed by launch loads!
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Structural Design and AnalysisENAE 483/788D - Principles of Space Systems Design
U N I V E R S I T Y O FMARYLAND
Planetary Vehicle Loads• Vibration loads from traversing rough terrain• Launch / landing loads• Maneuvering loads
– tight turn– driving on an incline– losing traction / support on one wheel
• Crash loads– driving into a big boulder– rolling vehicle in unstable soil– safety is primary consideration
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Structural Design and AnalysisENAE 483/788D - Principles of Space Systems Design
U N I V E R S I T Y O FMARYLAND
Piece Parts Analysis• Structural analysis of a system consists of at least
the following three tasks– Load Cycle Modeling (system-level) - iterative process– Piece-Part Analysis (static) - minimum margins of safety– Fracture and Fatigue Analysis (dynamic) - safe life
analysis• Piece Parts Analysis
– Identify all loads on each part / subsystem– Calculate margins of safety– Tabulate minimum margins of safety
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Structural Design and AnalysisENAE 483/788D - Principles of Space Systems Design
U N I V E R S I T Y O FMARYLAND
• Limit Loads: maximum loads expected (applied loads)
• Yield Load and Ultimate Load come from material properties
• Factors of Safety : numbers imposed by the Customer (or your own good sense) that reflect- how uncertain you are of the load or structure- how safe you want to be- examples: 10 for bridges, 5 for ground handling equip, ~2 for aircraft
• Margins of Safety are calculated as follows:
• Beware: There are other definitions of these terms in engineering, but the above approach is the most common in Aerospace
Factors & Margins of Safety
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Structural Design and AnalysisENAE 483/788D - Principles of Space Systems Design
U N I V E R S I T Y O FMARYLAND
NASA Standard Factors of Safety
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Source: NASA-STD-5001b https://standards.nasa.gov/structures-mechanical-systems
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Structural Design and AnalysisENAE 483/788D - Principles of Space Systems Design
U N I V E R S I T Y O FMARYLAND
NASA FoS Depend on the Material
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Source: NASA-STD-5001b
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Structural Design and AnalysisENAE 483/788D - Principles of Space Systems Design
U N I V E R S I T Y O FMARYLAND
NASA FoS Depend on the Material
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Source: NASA-STD-5001b
https://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20110023499.pdf
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Structural Design and AnalysisENAE 483/788D - Principles of Space Systems Design
U N I V E R S I T Y O FMARYLAND
Primary Structure• Primary, Secondary, & Tertiary Structure
– Primary structure is the system's backbone (carries all ofthe major loads imposed on vehicle)
– Secondary structure includes all essential appendages and support structures (such as solar arrays, antennas, & fuel tanks)
– Tertiary structures are less-essential mounting hardware (brackets, component housings, connector panels)
• Example of primary structure– Thin-walled cylindrical launch vehicle– Challenge is to figure out how to react shear & torsion
stresses– Buckling of skin is most common failure mode– Buckling of a cylindrical section:
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𝜎𝜎𝑐𝑐𝑟𝑟𝑐𝑐𝑐𝑐 =𝐸𝐸𝐸𝐸
𝑅𝑅 3 1 − 𝜈𝜈2
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Structural Design and AnalysisENAE 483/788D - Principles of Space Systems Design
U N I V E R S I T Y O FMARYLAND
Primary, Secondary, Tertiary
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Copyright Instar Engineering and Consulting, Inc.• instarengineering.com
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Structural Design and AnalysisENAE 483/788D - Principles of Space Systems Design
U N I V E R S I T Y O FMARYLAND
Critical Structure• Critical Items List (CIL) contains all parts that
– are deemed criticality 1 by Failure Modes and Effects Analysis (FMEA)ie, single point failures
– are fracture critical (ie, stressed to the point where a flaw will grow to critical size)
• Failsafe & Fracture Critical Structure– Catastrophic failure is generally defined by customer – Failsafe structure can take redistributed loads after failure (ie, not single
point failures); shall release no hazardous mass; shall not change dynamics significantly; shall have no fatigue problems
– Low-risk structure is not primary structure; has only a remote possibility of failure; will not propagate a crack in 4 lifetimesσmax < Ftu / [ 4 (1-0.5 R) Kt ]
– Fracture critical parts must be labeled and analyzed as such, then inspected, treated, and tracked more carefully than conventional parts
• Crack Growth Analysis (FLAGRO)– All FC parts must be shown good for four lifetimes of load cycles with
an initial flaw (determined by Non Destructive Investigation (NDI))
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Structural Design and AnalysisENAE 483/788D - Principles of Space Systems Design
U N I V E R S I T Y O FMARYLAND
Aerospace Materials• Comparison of specific stiffness, specific
strength, and buckling parameter for a variety of aerospace metals and composites
• Definition of Structural Failure– Detrimental Yield vs Textbook Yield
• deformation that detrimentally affects functionality of system
• 0.2% Tresca yield condition (assumes system linear in first place)
– Ultimate Failure• any material rupture or loss of functionality
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Structural Design and AnalysisENAE 483/788D - Principles of Space Systems Design
U N I V E R S I T Y O FMARYLAND
Material Strength & Stiffness• Typical Yield & Ultimate Strengths
– low strength steel yld: 36 ksi ult: 58 ksi– high strength steel yld:102 ksi ult:116 ksi– Titanium yld:134 ksi ult:145 ksi– aluminum yld: 37 ksi ult: 42 ksi
• Stiffness versus Strength Designs–aluminum ρ : 0.10 E/ ρ : 100 σ u/ ρ : 420–Low σu steel ρ : 0.28 E/ ρ : 102 σ u/ ρ : 204–high σ u steel ρ : 0.29 E/ ρ : 98 σ u/ ρ : 390–titanium ρ : 0.16 E/ ρ : 109 σ u/ ρ : 906
Conclusion: for aerospace structures - titanium and aluminum
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Structural Design and AnalysisENAE 483/788D - Principles of Space Systems Design
U N I V E R S I T Y O FMARYLAND
Structural Analysis• Some key structural formulas that are handy to have for early
(back-of-the-envelope) design analyses:
– Spring & Beam Stiffnesses
– Beam Natural Frequencies
– Euler Buckling Loads
– Stresses in Simple Pressurized Shell
σhoop = p R / t > σlong = p R / 2 t
– Random Vibe and Acoustic Equivalent g's
• Get a copy of Roark and Young, Formulas for Stress and Strain
– available in the library or as Excel spreadsheets from www.roarksformulas.com
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t
R
σlong
σhoop
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Structural Design and AnalysisENAE 483/788D - Principles of Space Systems Design
U N I V E R S I T Y O FMARYLAND
Structural Analysis• Definition of Example Problem• Definition of Load Cases• Combined Loads Analysis of Stresses• Tabulation of Margins of Safety• Identification of Critical Load Case
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Structural Design and AnalysisENAE 483/788D - Principles of Space Systems Design
U N I V E R S I T Y O FMARYLAND
International Space Station
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Structural Design and AnalysisENAE 483/788D - Principles of Space Systems Design
U N I V E R S I T Y O FMARYLAND
Close-up of Z1 Truss
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Structural Design and AnalysisENAE 483/788D - Principles of Space Systems Design
U N I V E R S I T Y O FMARYLAND
Structural Example
• Storage canister for ISS solar array deployment system
• 200 lb tip mass• Cantilever launch
configuration• Thin-wall aluminum shell
structure
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Structural Design and AnalysisENAE 483/788D - Principles of Space Systems Design
U N I V E R S I T Y O FMARYLAND
Loads Sources
• Launch– Accelerations– Pressurization– Acoustics– Random Vibration– Thermal
• Crash Landing• On-Orbit
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Structural Design and AnalysisENAE 483/788D - Principles of Space Systems Design
U N I V E R S I T Y O FMARYLAND
Structural Parameters
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Structural Design and AnalysisENAE 483/788D - Principles of Space Systems Design
U N I V E R S I T Y O FMARYLAND
Launch Accelerations±4.85 g
±5.8 g
±8.5 g
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Structural Design and AnalysisENAE 483/788D - Principles of Space Systems Design
U N I V E R S I T Y O FMARYLAND
Pressurization Loads
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Structural Design and AnalysisENAE 483/788D - Principles of Space Systems Design
U N I V E R S I T Y O FMARYLAND
Launch Vehicle Vibration EnvironmentFrequency (Hz)
Power Spectral Density(g2/Hz)
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Structural Design and AnalysisENAE 483/788D - Principles of Space Systems Design
U N I V E R S I T Y O FMARYLAND
Random Vibration Loads
(repeat for each axis)
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Miles’ Equation
Fundamental Bending Frequency for Cantilevered Beam w/ Tip Mass
Vibrationdata.com
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Structural Design and AnalysisENAE 483/788D - Principles of Space Systems Design
U N I V E R S I T Y O FMARYLAND
Thermal Loads
Assume support structure shrinks only half as much as canister
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Structural Design and AnalysisENAE 483/788D - Principles of Space Systems Design
U N I V E R S I T Y O FMARYLAND
Launch Loads Summary
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Structural Design and AnalysisENAE 483/788D - Principles of Space Systems Design
U N I V E R S I T Y O FMARYLAND
Observations about Launch Loads• Individual loads could be applied to same position
on canister at same times - conservative approach is to use superposition to define worst case
• 43% margin indicates that canister is substantially overbuilt - if launch loads turn out to be critical load case, redesign to lighten structure and reduce mass.
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