Browse Topic: Launch vehicles

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Aerospace - Lightning Effects on Hydraulic Transport Elements on AircraftAIR6185A (Current)11/26/2025

This SAE Aerospace Information Report (AIR) describes hydraulic system design and installation to minimize the effects of lightning, especially when the aircraft structure is composite. Techniques for effective electrical bonding, hydraulic system lightning protection, and lightning protection verification techniques are discussed.

My new committee for commercial aircrafts
Inductive Power Transfer for Spaceflight SystemsTBMG-349138/1/2019
NASA Goddard Space Flight Center has developed technology that uses inductive power transfer (IPT) for wireless power interfaces between spaceflight elements (such as the payload, vehicle, and pad). Current spaceflight systems require traditional hardwire connections for power interfaces. This introduces risk of failure due to such factors as bent pins and contact contamination, as well as other disadvantages.
Celebrating the 50th Anniversary of Apollo 11: Getting There, To a New Era of Space ExplorationTBMG-347457/1/2019
For the first time in a generation, NASA is building a human spacecraft for deep-space missions that will usher in a new era of space exploration. A series of increasingly challenging missions awaits, and this new spacecraft will take astronauts farther than they’ve gone before, including to the Moon and Mars.
NASA’s John F. Kennedy Space CenterTBMG-347437/1/2019
On September 1, 1961, NASA requested appropriations for initial land purchases on Merritt Island on Florida’s east coast to support the Apollo Lunar Landing Program. Designers quickly began developing plans for Launch Complex 39 facilities, which include the Launch Control Center, Pads A & B, and the huge hangar now known as the Vehicle Assembly Building (VAB).
NASA Marshall Space Flight CenterTBMG-343945/1/2019
Founded on July 1, 1960, Marshall Space Flight Center in Huntsville, AL is one of NASA’s largest field centers. Marshall engineers designed, built, tested, and helped launch the Saturn V rocket that carried Apollo astronauts to the Moon. Marshall developed new rocket engines and tanks for the fleet of space shuttles, built sections of the International Space Station (ISS), and now manages all the science work of the astronauts aboard the ISS from a 24/7 Payload Operations Integration Center. Marshall also manages NASA’s Michoud Assembly Facility in New Orleans — the agency’s premier site for the manufacture and assembly of large-scale space structures and systems.
NASA at 60: Celebrating SuccessTBMG-3310910/1/2018
Over the past 60 years, NASA scientists and engineers have developed many advanced technologies and processes. But NASA has also partnered with industry, using commercially available products to complete its missions. Here, some of those companies join NASA in celebrating these collaborative successes.
Affordable Vehicle Avionics (AVA)TBMG-290386/1/2018
NASA Ames Research Center has developed a novel, low-cost, self-contained guidance system for small payload operators. Small satellites are becoming ever more capable of performing valuable missions for both government and commercial customers; however, currently these satellites can only be launched affordably as secondary payloads, which makes it difficult for the small satellite mission to launch when needed, to the desired orbit, and with acceptable risk.
Standard Handbook for Aerospace Engineers, 2nd EditionJP-MGH-0014/1/2018
This fully revised resource presents theories and practices from more than 50 specialists in the many sub-disciplines of aeronautical and astronautical engineering—all under one cover. The Standard Handbook for Aerospace Engineers, Second Edition, contains complete details on classic designs as well as the latest techniques, materials, and processes used in aviation, defense, and space systems. You will get insightful, practical coverage of the gamut of aerospace engineering technologies along with hundreds of informative diagrams, charts, and graphs. Standard Handbook for Aerospace Engineers, Second Edition covers: • Future of aerospace • Aircraft systems • Aerodynamics, aeroelasticity, and acoustics • Aircraft performance, stability and control • Avionics and air traffic management systems • Aeronautical design • Spacecraft design • Astrodynamics • Rockets and launch vehicles • Earth’s environment and space • Spacecraft subsystems • Spacecraft design
Robotic Gripper for Satellite Capture and ServicingTBMG-287264/1/2018
The robotic gripper was developed at NASA Goddard Space Flight Center as part of a robotic satellite servicing mission. The gripping device can be used to autonomously or remotely grasp and control an out-of-fuel or otherwise disabled satellite. Specifically, the gripper interfaces to the separation ring (marman ring) of the client spacecraft and when closed, is sufficient to constrain all six degrees of freedom of motion between the servicing spacecraft and the client. The jaws are designed with a conformable geometry that allows the same gripper to interface to all spacecraft separation rings commonly used with Atlas V and Delta IV launch vehicles.
Novel, Solid-State Hybrid Ultracapacitor BatteryTBMG-283232/1/2018
NASA's Marshall Space Flight Center has developed a solid-state ultracapacitor with a unique combination of high capacitance and battery-like discharge characteristics. The high capacitance in a solid-state form can enable a new type of ultracapacitor, and in combination with the ability to deliver sustained power like a battery, can perhaps enable an entirely new class of energy storage devices.
Modular Fixturing for Assembly and Welding ApplicationsTBMG-2797712/1/2017
Researchers at NASA’s Marshall Space Flight Center have developed new modular fixtures for holding metal in place during the assembly and welding of cylindrical and conical sections of rocket bodies. Previous methods required time-consuming design, fabrication, and assembly of expensive, project-specific fixtures, which often required up to six months of lead time and cost millions of dollars to complete. NASA’s modular fixtures are designed to be adjustable and to easily form different fixture body configurations for rocket sections with various diameters and heights. This improved setup efficiency allows for a more rapid shift from one project to the next, reducing the time a newly designed fixture body takes to complete, allowing welding to begin in a matter of weeks rather than months. NASA is currently seeking licensees that may benefit from modular fixtures in large-scale manufacturing.
Software Helps Optimize World’s Largest All-Composite AircraftTBMG-2800812/1/2017
Collier Research Corp. Newport News, VA
Vented Launch Vehicle Adapter for a Manned Spacecraft With “Pusher” Launch Abort SystemTBMG-2768610/1/2017
A Launch Vehicle Adapter (LVA) was developed that provides a structural interface between a Commercial Crew Vehicle (CCV) Crew Module/Service Module Spacecraft (CM/SM) and an expendable launch vehicle. It also provides a means to control the exhaust plume from a pusher type launch abort system integrated into the Service Module.
Radiation Tolerant “Smart Backplanes” for Spacecraft AvionicsTBMG-274869/1/2017
RADIATION TOLERANT “SMART BACKPLANES” FOR SPACECRAFT AVIONICS17AERP09_029/1/2017
In recent years there has been a trend towards the wider use of COTS (Commercial Off The Shelf) equipment in space missions. This trend has been mainly driven by the restrictions in R&D budgets and a growing demand for shorter design cycles. Funding Agencies are encouraging designers of spacecraft systems to identify and overcome the obstacles that previously prevented the use of COTS products for space missions. When it comes to space vehicle engineering, the tolerance of onboard electronics to radiation effects can be one of the most challenging aspects of the system design. The risk of failure for avionics equipment on-board spacecraft due to radiation exposure is determined by the vehicle's orbit trajectory and flight duration, during which the vehicle is exposed to trapped radiation as well as solar and cosmic radiation sources.
Towed-Glider Airborne Launch System Cuts Costs and Increases Efficiency and SafetyTBMG-275269/1/2017
Putting a satellite into low Earth orbit requires a lot of energy, with ground-launched rockets expending two-thirds of their propellant fighting to get through the atmosphere. Researchers at NASA’s Armstrong Flight Research Center have developed an innovative approach to launching satellites into space from an airborne platform. As with other air-launch approaches, it provides significant flexibility in the location and direction of the launch vehicle. Furthermore, unlike other air-based launch techniques, this system avoids the significant drawbacks related to expensive and complex design/development efforts, difficult maneuvering, risks to crew, and inefficient flight performance.
Noise Control Capability of Structurally Integrated Resonator Arrays in a Foam-Treated Cylinder2017-01-17656/5/2017
Corrugated-core sandwich structures with integrated acoustic resonator arrays have been of recent interest for launch vehicle noise control applications. Previous tests and analyses have demonstrated the ability of this concept to increase sound absorption and reduce sound transmission at low frequencies. However, commercial aircraft manufacturers often require fibrous or foam blanket treatments for broadband noise control and thermal insulation. Consequently, it is of interest to further explore the noise control benefit and trade-offs of structurally integrated resonators when combined with various degrees of blanket noise treatment in an aircraft-representative cylindrical fuselage system. In this study, numerical models were developed to predict the effect of broadband and multi-tone structurally integrated resonator arrays on the interior noise level of cylindrical vibroacoustic systems. Foam layers with a range of thicknesses were applied near the inside surface of the cylinder to represent different degrees of conventional blanket treatments. Excitations including point force as well as harmonic and random fluctuating pressure fields were considered. The results suggest that structurally integrated resonators can be tuned to address a variety of noise control requirements and effectively used in conjunction with foam blanket noise treatments, but their relative benefit is reduced when thicker foam treatments are used.
Allen, Albert, Schiller, Noah, Rouse, Jerry
Mechanically Strong, Thermally Stable, and Electrically Conductive Nanocomposite Structure and Method of Fabricating SameTBMG-270586/1/2017
NASA's Langley Research Center has developed a method for producing multifunctional, structural, thermally stable nanocomposites with aligned carbon nanotubes. The invention improves upon current state-of-the-art graphite fiber composites by providing the same lightweight and mechanically strong characteristics, but also adds thermal stability and electrical conductivity. Thus, the invention can be used to provide a new class of mechanically strong, thermally stable, and electrically conductive nanocomposites.
Tangential Wrap Rib Deployable ReflectorTBMG-268695/1/2017
There is a need for a large deployable reflector of 2-meter diameter or greater so smaller launch vehicles can be used. Common issues with going from a large solid reflector into deployable structures are the structural stiffness and deployable structure complexity.
Electric Rockets and the Future of Satellite Propulsion17AERP04_034/1/2017
Humans have been using rocket propulsion for almost a millennium, starting with Chinese rockets and “fire arrows” in the 13th century and continuing to the modern era's powerful Space Shuttle and Falcon rockets. For most of that history, rockets have been chemically fueled, but in the past century scientists and engineers have also experimented with electric rockets, also known as ion engines or ion propulsion systems. Rather than using chemical reactions to create heat and accelerate a propellant, electric rockets use electromagnetic or electrostatic fields acting on charged ions of propellant, speeding them up and shooting them out, away from the vehicle, producing thrust. The electrical energy to generate these fields comes from the sun, from batteries, or both.
Electric Rockets and the Future of Satellite PropulsionTBMG-266794/1/2017
Humans have been using rocket propulsion for almost a millennium, starting with Chinese rockets and “fire arrows” in the 13th century and continuing to the modern era's powerful Space Shuttle and Falcon rockets. For most of that history, rockets have been chemically fueled, but in the past century scientists and engineers have also experimented with electric rockets, also known as ion engines or ion propulsion systems.
Insulative Carbon Fiber Systems for Aerospace ApplicationsTBMG-2571211/1/2016
New insulative carbon-fiber composite systems have been developed for use in structural and thermal applications for the aerospace vehicle interface. The sandwich-type composite structure, including carbon fiber and aerogel blanket materials, is based on the previously disclosed family of hybrid laminate composites. Offering unique and tailorable combinations of structural and thermal properties, these insulative carbon fiber systems can be used in vehicle shroud and thermal protection system applications at the aerodynamic interface plane, panels between stages, or fairings for spacecraft equipment space of space launch vehicles. The novel, lightweight, fiber composite laminate system with reduced heat transfer also has increased impact resistance at low temperatures.
Actuation System Data Summary for Missiles and Launch VehiclesAIR1855A (Current)9/28/2016
This SAE Aerospace Information Report (AIR) includes all missile and launch vehicle actuation systems, including electrohydraulic, electropneumatic, and electromechanical types. The data for many systems are not complete. As more information becomes available, periodic updates will be issued to complete existing data sheets and to add new ones. An index by type of vehicle and by type of actuation system is included. The actual data sheets in the body of the report are organized in alphabetical order.
A-6B1 Hydraulic Servo Actuation Committee
Flexible Ablator for Thermal ProtectionTBMG-253509/1/2016
NASA has developed a class of low-density, flexible ablators that can be fabricated into heat-shields capable of being packaged, stowed, and deployed in space. The key characteristics of this new ablative thermal protection system (TPS) are its flexibility, conformability, and tailor-ability. Flexibility allows the material to be stowed in the shroud of a launch vehicle and deployed in space, without compromising functionality. Conformability allows the material to be attached to a curved surface without precise and expensive machining. Tailor-ability allows the density and composition to be optimized for the requirements. This flexible TPS can be used to cover and thermally protect a large, blunt shape that provides aerodynamic drag during hyper-velocity atmospheric flight. It can be used with minimal modification for large aeroshells whose deployment relies mainly on mechanical means and through inflation. Such devices are called Hypersonic Inflatable Aerodynamic Decelerators (HIADs). Large blunt body aeroshells may be used to deliver large payloads (40 metric tons) to the surface of Mars.
Human Spaceflight Takes a Giant LeapTBMG-252318/1/2016
NASA is developing the capabilities needed to send humans to an asteroid by 2025, and to Mars in the 2030s. While robotic explorers have studied Mars for more than 40 years, NASA’s path for the human exploration of Mars begins in low Earth orbit aboard the International Space Station (ISS). Astronauts on the ISS are proving many of the technologies and communications systems needed for human missions to deep space, including Mars. The ISS also advances understanding of how the body changes in space, and how to protect astronaut health.
Constraint Force Equation (CFE) Solver for Multi-Body Dynamics and its Implementation in POST2TBMG-242574/1/2016
Existing aerospace flight trajectory programs simulate the motion of aerospace vehicles by modeling external forces and moments acting on each body, but lack provisions for determining reaction forces and moments exerted by one body on another through a connecting joint. These reaction forces and moments are also known as constraint forces and moments because they permit specified motion of one body relative to another, and, at the same time, prohibit all other relative motions. In other words, a joint imposes certain constraints on relative motion.
Normally-Closed Zero-Leak Valve with a Magnetostrictive ActuatorTBMG-242604/1/2016
A hermetically sealed, normally closed (NC) zero-leak valve has been developed. Prior to actuation, the valve isolates the working fluid in the upstream volume from the downstream volume with a parent metal seal. The valve utilizes the magnetostrictive alloy Terfenol-D for actuation. This alloy experiences a phenomenon known as magnetostriction, i.e., a gross elongation, when exposed to a magnetic field. This elongation fractures the seal within the wetted volume of the valve, opening the valve permanently and establishing fluid flow. The required magnetic field is generated by redundant coils concentric to the Terfenol, but isolated from the working fluid. The response time for this phenomenon to occur and subsequently for actuation is on the order of milliseconds. The wetted volume consists of entirely parent-metal 6Al-4V titanium, compatible with all storable propellants, helium, nitrogen, argon, isopropyl alcohol, and argon. When coupled with the parent metal seal, this design gives the valve internal and external leak rates of zero.
Autonomous Flight Termination System Reference Design HardwareTBMG-240843/1/2016
The current range ground-based infrastructure is extremely costly to operate and maintain. NASA has developed an Autonomous Flight Termination System (AFTS) that is an independent, self-contained subsystem mounted onboard a launch vehicle. The AFTS reference system eliminates the need for a ground-based infrastructure by moving the flight termination function from the ground to the launch vehicle. It will allow multiple vehicles to be launched and tracked at the same time. AFTS is necessary to support vehicles that have multiple flyback boosters.
Adaptive Augmenting ControlTBMG-241053/1/2016
Adaptive augmenting control (AAC) is a forward gain, multiplicative adaptive algorithm for launch vehicle flight control that meets three summary-level design objectives: Do no harm — return to baseline control design when not needed; respond to errors in the ability of the vehicle to track commands to increase performance; and respond to undesirable parasitic dynamics (e.g., control-structure interaction) to maintain stability.
Eliminating the Need for Payload-Specific Coupled Loads Analyses Without Mission RiskTBMG-241173/1/2016
Amore efficient structural verification process for small satellites has been demonstrated. This new process eliminates the need for payload-specific coupled loads analysis (CLA) and simplifies structural testing while not increasing mission risk. The process entails the following:
Cryogenic Seal for Space Launch System Handles Extreme Pressure ConditionsTBMG-241603/1/2016
OmniSeal® RACO™ Spring-Energized Seals Saint-Gobain Seals Garden Grove, CA 800-544-0080
Launch Environment Water Flow Simulations Using Smoothed Particle HydrodynamicsTBMG-238972/1/2016
One of the crucial ground structures employed at the launch pad during the Space Shuttle program is the rainbird nozzle system, whose primary objective is to suppress acoustic energy generated by the launch vehicle during pad abort and nominal operations. It is important that the rainbird water flow does not impinge on the rocket nozzles and other sensitive ground support elements. For the new Space Launch System (SLS) vehicle, the operation is similar, regardless of the new mobile launcher and new engine configurations. The goal of the rainbird nozzle system remains sound suppression (SS), and the rocket engines still cannot get wet. However, the rearrangement of the rainbird water system for the SLS mobile launcher locates the rainbirds closer to the first-stage rocket engines, which are positioned above the exhaust hole. The close proximity of the rainbird nozzle system could potentially cause vehicle wetting during liftoff.
Computer-Aided Design Tools to Support Human Factors Design TeamsTBMG-2348312/1/2015
The purpose of this work was to develop a database of human model behavior primitives, which are basic scripts that can be chained together to create simulations of humans performing certain tasks. This is unique in that the human model behaviors were collected using motion capture technology and then incorporated into virtual simulation software. Typically, human model behaviors are created based on the subjective observations of the analyst rather than by using realistic motion data. Limitations of this approach include less reliable human models and a more time-consuming process for creating the human model in the virtual environment.
Use of Eccentric Bushings to Precision-Locate Multiple Parts on a Large Mating StructureTBMG-2346012/1/2015
Cups/cones are being used to provide a shear load transfer capability on a large separation interface that uses multiple discreet retention and release (R&R) devices (such as frangible nuts, separation nuts, separation bolts, etc.). To both provide good shear load-sharing among all R&Rs and to prevent relative motion between the mating structures, the cups/cones must be designed with minimal (and sometimes zero) radial clearance. This tight fit requires that the cup and the cone on the mating structures are precisely located to each other.
Computer and Displays Help Control and Maneuver Crew Transportation SystemTBMG-228959/1/2015
Space-qualified boards and subsystems Aitech Defense Systems Chatsworth, CA 888-248-3248
Mars Relay CubeSatTBMG-228739/1/2015
When NASA and other agencies send landers to Mars and other planets, they rely on existing orbiters to relay the data during the critical entry, descent, and landing (EDL) phase. The current orbiters are aging and there are no current NASA plans to replace them. Future landers have a critical challenge to communicate during a very risky mission phase. The InSight mission will land on Mars in September 2016 with no direct-to-Earth radio link. Instead, Insight expects the Mars Reconnaissance Orbiter (MRO) to be fully functional and placed in an orbit to be in view of the EDL time and place. MRO will take many hours to play back the data to Earth, leaving the project staff without knowledge if their valuable spacecraft has made it safely.
Nanosatellite Launch Adapter SystemTBMG-228599/1/2015
NASA has developed a Nanosatellite Launch Adapter System (NLAS) that maximizes the efficiency of satellite launch missions. NLAS increases access to space while simplifying the integration process of miniature satellites, called nanosats or CubeSats, onto launch vehicles. While a complete NLAS consists of an adapter integrated with four dispensers and a sequencer, its components can be used modularly with other adapter, deployer, and sequencer/actuator systems. The adapter is mounted to the upper surface of the launch vehicle at the separation plane and the lower deck of the primary spacecraft supporting its structural load. The dispensers are mounted inside the adapter and house a variety of CubeSats in fully enclosed bays. NLAS is stackable, allowing for the expansion of spacecraft deployments. An NLAS sequencer can initiate a secondary sequencer, allowing for the expansion of actuator and deployment capability.
Low-Density Flexible AblatorsTBMG-225538/1/2015
NASA has developed a class of low-density, flexible ablators that can be fabricated into heat shields capable of being packaged, stowed, and deployed in space. Several flexible versions have been developed by infiltrating a pyrolyzing silicone resin into flexible, low-density felts made of carbon, polymer, or ceramic materials. The material is produced by immersing a flexible fibrous substrate in a diluted polymer resin, curing the polymer resin using heat and/or catalyst, and removing the solvent.
Servo Motors Help Launch Vehicles Optimize FuelTBMG-226618/1/2015
Servo motors MICROMO (the FAULHABER Group) Clearwater, FL 800-807-9166
Modular Propulsion and Deployment Electronics SystemTBMG-224027/1/2015
The Lunar Reconnaissance Orbiter (LRO) required an innovative and modular approach to the design and development of the electronics needed to control the propulsion and deployment components, as well as the electronics necessary to support safety inhibits for personnel and range requirements. Since these electronics would be designed in parallel with the systems they would interface with, they would need to be flexible enough to quickly accommodate ongoing design changes.
Precision Measurement and Inspection Ensure Quality of SLS Rocket PanelsTBMG-217844/1/2015
Reverse engineering and inspection software Verisurf Software Anaheim, CA 714-970-1683
Method for Performing GPS L1 C/A Measurements in Wideband Jamming and InterferenceTBMG-215332/1/2015
For effective range safety, global positioning system (GPS) metric tracking must be robust to interference with, and jamming of, GPS signals. The conventional approach to mitigating interference and jamming is to use a Controlled Reception Pattern Antenna (CRPA). These few-element phased arrays are used to steer nulls in the directions of interference sources, and/or to point beams in the directions of GPS satellites. The use of CRPAs is limited by their cost and size, as well as the difficulties of integrating the array into a platform. The problems are compounded for a launch vehicle, which must acquire and track GPS signals at high speed and acceleration, and undergo vibration and temperature conditions not common to CRPA use.
Process-Hardened, Multi-Analyte Sensor for Characterizing Multiple Rocket Plume Constituents in a Test EnvironmentTBMG-212531/1/2015
Stennis Space Center (SSC) is one of three government-operated rocket engine test facilities in the United States and is the primary center for testing and flight-certifying rocket propulsion systems for future space vehicles. Safety is a top priority at NASA-SSC. To safely test and certify rocket engines, monitoring technologies for rocket test stands, which (1) verify compliance with federal, state, and local government guidelines; (2) ensure a safe work environment for its personnel at ground testing facilities; as well as (3) monitor environmental impacts, are all required. Additionally, NASA has a need to monitor engine combustion efficiencies and engine health of a variety of launch vehicle configurations utilizing liquid oxygen, liquid hydrogen, isopropanol, and kerosene. Multi-analyte measurement technology is essential for a safe and effective working environment. Therefore, for the advancement in multi-analyte technology in the rocket testing industry, a device was created that integrates multi-analyte measurements into a single sensor unit.
NASA Launch Pads Protected Against Lightning-Induced Power SurgesTBMG-2066810/1/2014
Circuit protection components Littelfuse Chicago, IL 773-628-1000
Analog Ceramic Isolated Voltage SensorTBMG-2067710/1/2014
Galvanic isolated monitoring of voltages for launch vehicle, missiles, and space-deployed systems can be very challenging. Radiation exposure makes use of optics-based sensors difficult, as they can latch-up and become corrupted by the radiation environment; such devices can moreover be thermally challenged. Magnetic transformer-based methods of isolated voltage measurement require shielding to prevent stray magnetic interference from degrading or corrupting the readings; moreover, magnetic-based solutions are unable to measure voltages down to DC levels.
Flexible, Lightweight Vacuum Shell for Load-Responsive Multilayer Insulation for High Thermal PerformanceTBMG-2069610/1/2014
Better thermal insulation is needed to insulate cryogenic propellants used by NASA for launch vehicles, spacecraft, and orbiting fuel depots. In particular, cryotank insulation during in-air pre-launch and launch ascent stages currently uses spray-on foam insulation (SOFI), which is extremely problematic.
Production of Satellite with First All-Electric Propulsion System AdvancesTBMG-2076710/1/2014
Boeing is “running on schedule” as it continues to achieve production milestones for the first of its all-electric-propulsion 702SP (small platform) satellites.
Non Linear Finite Element Verification Approach for Marman Fitting in Space AIT Operations2014-01-22689/16/2014
The marman interface is widely used in space applications to fit the spacecrafts to the launch vehicle and it is the same interface that allows the integration, test and transport of the satellites (AIT). It is usually designed for launch loads with related flight design safety factors and margins, but this is not always compatible with the handling and transport environment. In particular some criticalities are evidenced during the transport of satellites, where they are mounted in the container in horizontal position therefore subjected to bending loads due to gravity and transport dynamic loads. The study deals with a finite element analysis approach in the calculation and verification of marman clamp bands used for spacecraft AIT operations. The paper describes the details of modeling of the clamp band parts, the involved spacecraft launch vehicle interface ring and the MGSE interface. All these parts are in contact and this configuration has been modeled adopting the most recent non linear contact analysis techniques. It is highlighted that the elastic behavior of the parts in contact are determinant for the definition of the limit loads that can be sustained by the structural parts with enough safety margin, evidencing also the limitations of the simple geometric-analytic approach based only on trigonometric formulations with the hypothesis of high stiffness of the interface parts. Different configurations are investigated in order to determine the contribution to the load sustainability of each involved part structural performance.
Ladisa, Pietro, Santonico, Gabriele
Products of Tomorrow: September 2014TBMG-204979/1/2014
The technologies NASA develops don’t just blast off into space. They also improve our lives here on Earth. Life-saving search-and-rescue tools, implantable medical devices, advances in commercial aircraft safety, increased accuracy in weather forecasting, and the miniature cameras in our cellphones are just some of the examples of NASA-developed technology used in products today.
Durable Joining Technology for Uniformly-Curved Composite Sandwich StructuresTBMG-205149/1/2014
NASA’s next-generation launch vehicles will be enabled by high-performance composite materials and innovative manufacturing methods. As such, NASA uses adhesively bonded joints where possible instead of mechanically fastened (bolted) joints to design and manufacture structures. The adhesive joints typically are lighter and distribute loads more efficiently across an interface, while mechanically fastened joints are prone to stress concentrations around the bolts.
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