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Ditonno Pasquale - One of the best experts on this subject based on the ideXlab platform.

  • Penile prostheses
    'SAGE Publications', 2010
    Co-Authors: Bettocchi Carlo, Battaglia Michele, Palumbo F, Spilotros M, Palazzo S, Ga Saracino, Martino P, Selvaggi, Francesco Paolo, Ditonno Pasquale
    Abstract:

    Penile prosthesis implantation is recognized as a valid option to obtain an artificial erection satisfactory for sexual intercourse in those patients in which a pharmacological approach is contraindicated or ineffective. Penile prostheses are subbject to continuous development and they are achieving ever better mechanical reliability and safety. The devices are divided into two general types: semirigid (malleable and mechanical) and Inflatables. The AMS® (American Medical Systems) and Coloplast Ltd® produce the majority of inflatable and semirigid devices.Malleable and mechanical prostheses have the disadvantage that the penis is always erect although it can be orientated in different ways, while the advantages are ease of use and the need for a simpler surgical procedure compared with inflatable prostheses. Three-component prostheses are more sophisticated than semirigid devices. The advantages of these devices are that the prosthesis feels softer than semirigid or two-piece devices when deflated, with a better cosmetic result, and it ensures a more natural erection than others kinds of prosthesis. The disadvantages are the possibility of malfunction and the need for a more complicated surgical technique. Implantation of a penile prosthesis can be performed in a short surgical time under locoregional anaesthesia, and for this reason hospitalization is usually brief and the patient can be discharged 2 days after the operation if complications are not evident. Patient and partner satisfaction reflect the quality and the effectiveness of this treatment. Even though the results are positive in the vast majority of patients, the possibility of several complications makes penile prosthesis implantation a delicate kind of surgery. Complications can happen when the operation is carried out, in the peri-operative and in the postoperative period, and include infections, erosions of the prosthesis and mechanical failure in case of inflatable prosthesis. Penile prostheses available on the market have improved the success of this kind of surgery, thanks to the introduction of new materials and designs

  • Penile prostheses
    SAGE Publications, 1
    Co-Authors: Bettocchi Carlo, Palumbo Fabrizio, Spilotros Marco, Palazzo Silvano, Saracino, Gabriele A., Martino Pasquale, Battaglia Michele, Selvaggi, Francesco P., Ditonno Pasquale
    Abstract:

    Penile prosthesis implantation is recognized as a valid option to obtain an artificial erection satisfactory for sexual intercourse in those patients in which a pharmacological approach is contraindicated or ineffective. Penile prostheses are subbject to continuous development and they are achieving ever better mechanical reliability and safety. The devices are divided into two general types: semirigid (malleable and mechanical) and Inflatables. The AMS® (American Medical Systems) and Coloplast Ltd® produce the majority of inflatable and semirigid devices

David P. Cadogan - One of the best experts on this subject based on the ideXlab platform.

  • Recent Development and Test of Inflatable Wings
    47th AIAA ASME ASCE AHS ASC Structures Structural Dynamics and Materials Conference<BR> 14th AIAA ASME AHS Adaptive Structures Conference<BR&, 2006
    Co-Authors: David P. Cadogan, Jamey Jacob, Stephen E. Scarborough, Dan Gleeson, Anshu Dixit, Andrew Simpson
    Abstract:

    In recent years the Departments of Defense and Homeland Security have had a desire to tightly pack small Unmanned Aerial Vehicles (UAVs) in order to allow them to be launched via gun, by hand, or air dropped for reconnaissance or munitions delivery. Inflatable components enable compact packaging and rapid deployment on the ground or in flight, while minimizing system mass and complexity. Inflatable structures also provide UAVs with a significant amount of robustness as they can sustain hard landings without damage due to their inherent inflatable nature, in essence functioning as airbags. The combination of these two factors, compact packaging and damage tolerance, can be combined to provide UAVs that are easily transportable and cost effective. Numerous laboratory and flight tests have been performed to demonstrate the damage tolerance of inflatable wings. The survivability rate has remained at 100% beyond one hundred flight test impacts, and has been verified by similar laboratory testing. The resilience of the inflatable components manufactured from engineered materials is outstanding and tracks well with related inflatable structures such as the Pathfinder and MER airbags, which landed on the rocky surface of Mars. Inflatable wings have also demonstrated two aspects of morphing for UAVs or other flight platforms (such as airships). These are high aspect ratio changes via the deployment of inflatable tip extensions, and camber morphing for aerodynamic control. Inflatable wings with embedded actuation systems have been developed that are deployable and can easily be shape morphed to provide the required aerodynamic control for small UAVs. The flexible composite materials used in inflatable wings also allow for the inclusion of multi-functional elements to augment performance. Multi-functional elements for deployable wings include those that perform structural or aerodynamic functions, but are also used for functions such as aerodynamic control, power generation, power storage, and communication. Key tests conducted during this research and discussed herein include: rapid simultaneous wing deployment, gust and impact loading survivability tests, and wing shape vs. inflation pressure as characterized through wind tunnel testing. This paper discusses the various morphing concepts in detail and the subsequent development and testing of various components for UAVs. The design and fabrication of a small UAV with embedded actuation technology on the inflatable components is also detailed along with flight-test data.

  • Inflatable Solar Arrays: Revolutionary Technology?
    SAE Technical Paper Series, 1999
    Co-Authors: Mark S. Grahne, David P. Cadogan
    Abstract:

    Recent technological advancements in space inflatable structures, in the areas of material rigidization and controlled deployment, have presented a new possibility to the space community with a low cost, lightweight alternative to mechanically deployed space structures. Space inflatable structures have many benefits and advantages over current mechanical systems. They are low in mass and can be packaged into small volumes, which can potentially reduce the overall program cost by reducing the launch vehicle size. Reduction in total system mass and deployment complexity can also increase system reliability. This new technology is fast becoming a reality, especially in the field of inflatable solar arrays and other applications for spacecraft components. Many solar array applications such as the Mars rover inflatable solar array, the JPL Deep Space Four (ST4) inflatable blanket solar array, and the Teledesic blanket solar array have been developed and prototypes have been built and tested. Several flight experiments are underway and will be flown in the very near future.

  • Inflatable composite habitat structures for lunar and mars exploration
    Acta Astronautica, 1999
    Co-Authors: David P. Cadogan, J. Stein, Mark S. Grahne
    Abstract:

    Abstract Recent advances in materials technology have improved the performance capabilities of inflatable, flexible composite structures, which have increased their potential for use in numerous space applications. Space suits, which are comprised of flexible composite components, are a good example of the successful use of inflatable composite structures in space. Space suits employ Inflatables technology to provide a stand alone spacecraft for astronauts during extra-vehicular activity. A natural extension of this application of Inflatables technology is in orbital or planetary habitat structures. NASA Johnson Space Center (JSC) is currently investigating flexible composite structures deployed via inflation for use as habitats, transfer vehicles and depots for continued exploration of the Moon and Mars. Inflatable composite structures are being investigated because they offer significant benefits over conventional structures for aerospace applications. Inflatable structures are flexible and can be packaged in smaller and more complex shaped volumes, which result in the selection of smaller launch vehicles which dramatically reduce launch costs. Inflatable composite structures are typically manufactured from materials that have higher strength to weight ratios than conventional systems and are therefore lower in mass. Mass reductions are further realized because of the tailorability of inflatable composite structures, which allow the strength of the system to be concentrated where needed. Flexible composite structures also tend to be more damage tolerant due to their “forgiveness” as compared to rigid mechanical systems. In addition, Inflatables have consistently proven to be lower in both development and manufacturing costs. Several inflatable habitat development programs are discussed with their increasing maturation toward use on a flight mission. Selected development programs being discussed include several NASA Langley Research Center habitat programs that were conducted in the 1960s, the Lawrence Livermore National Laboratory inflatable space station study, the NASA JSC deployable inflatable Lunar habitat study, and the inflatable Mars TransHab study and test program currently ongoing at NASA JSC. Relevant technology developments made by ILC Dover are also presented.

Komar D. R. - One of the best experts on this subject based on the ideXlab platform.

  • Entry, Descent and Landing Systems Analysis Study: Phase 2 Report on Exploration Feed-Forward Systems
    2011
    Co-Authors: Mcguire M. Kathleen, Engelund, Walter C., Zumwalt, Carlie H., Arnold, James O., Zang, Thomas A., Dwyer Ciancolo, Alicia M., Kinney, Daivd J., Queen, Eric M., Olds, Aaron D., Komar D. R.
    Abstract:

    NASA senior management commissioned the Entry, Descent and Landing Systems Analysis (EDL-SA) Study in 2008 to identify and roadmap the Entry, Descent and Landing (EDL) technology investments that the agency needed to successfully land large payloads at Mars for both robotic and human-scale missions. Year 1 of the study focused on technologies required for Exploration-class missions to land payloads of 10 to 50 t. Inflatable decelerators, rigid aeroshell and supersonic retro-propulsion emerged as the top candidate technologies. In Year 2 of the study, low TRL technologies identified in Year 1, Inflatables aeroshells and supersonic retropropulsion, were combined to create a demonstration precursor robotic mission. This part of the EDL-SA Year 2 effort, called Exploration Feed Forward (EFF), took much of the systems analysis simulation and component model development from Year 1 to the next level of detail

Dwyer Cianciolo, Alicia M. - One of the best experts on this subject based on the ideXlab platform.

  • Entry, Descent and Landing Systems Analysis: Exploration Feed Forward Internal Peer Review Slide Package
    2011
    Co-Authors: Dwyer Cianciolo, Alicia M.
    Abstract:

    NASA senior management commissioned the Entry, Descent and Landing Systems Analysis (EDL-SA) Study in 2008 to identify and roadmap the Entry, Descent and Landing (EDL) technology investments that the agency needed to successfully land large payloads at Mars for both robotic and human-scale missions. Year 1 of the study focused on technologies required for Exploration-class missions to land payloads of 10 to 50 mt. Inflatable decelerators, rigid aeroshell and supersonic retro-propulsion emerged as the top candidate technologies. In Year 2 of the study, low TRL technologies identified in Year 1, Inflatables aeroshells and supersonic retropropulsion, were combined to create a demonstration precursor robotic mission. This part of the EDL-SA Year 2 effort, called Exploration Feed Forward (EFF), took much of the systems analysis simulation and component model development from Year 1 to the next level of detail

Jianzheng Wei - One of the best experts on this subject based on the ideXlab platform.

  • Design and testing of inflatable gravity-gradient booms in space
    CEAS Space Journal, 2019
    Co-Authors: Jianzheng Wei, Huifeng Tan, Weizhi Wang, Anders Eriksson
    Abstract:

    Inflatable space structures have many advantages such as small size, high reliability, and low cost. Aiming at a gravity-gradient boom for an XY-1 satellite, New Technology Verifying Satellite-1, a slender inflatable boom with low magnetic is presented. First of all, an inflatable boom with six self-supporting thin shells made of carbon and Vectran fiber composite materials on the inner wall was designed for eliminating a magnetic dipole moment and increasing structural stiffness. A precise stowage was designed for a tip mass surrounded by a pair of lightweight honeycomb blocks added on the top of the boom. The stowed boom was tested by sine sweep vibrations with three directions on the ground to verify the reasonable design. The XY-1 satellite which carried the inflatable boom was launched into low orbit. After being stowed state in space for at least 6 months, the inflatable boom orderly unfolded a 2.0 kg tip mass to 3.0 m away in May, 2013. The inflatable boom was successfully deployed from a series of photographs received on the satellite. The results show that this kind of lightweight inflatable boom with self-supporting thin shells can orderly unfold and fulfil the function of gravity-gradient in space for a long time.

  • Deployable dynamic analysis and on-orbit experiment for inflatable gravity-gradient boom
    Advances in Space Research, 2015
    Co-Authors: Jianzheng Wei, Huifeng Tan, Weizhi Wang, Xu Cao
    Abstract:

    Abstract Inflatable structures have numerous advantages, such as small folding size, high deployable reliability, and low cost. This paper accomplishes several tasks with a focus on the gravity-gradient boom of microsatellite. An inflatable boom model balanced by inflatable deployment and delaminating resistance is presented. A system is established to simulate agravic deployment. The inflatable deployment of a tip mass has been tested with the aid of a 3.0 m rolled deployable boom. The perturbation moment during the inflatable deployment is analyzed. Three inflatable booms are tested in a thermal vacuum chamber further. Based on the tests and analyses, the microsatellite which carried an inflatable gravity-gradient boom was launched into orbit successfully in November 2012. After being stored on-orbit for 6 months, the inflatable method was applied to the inflatable boom to unfold the 2.0 kg tip mass steadily at a distance 3.0 m away from the microsatellite in May 2013. This work completes the test of inflatable on-orbit deployment on the base of microsatellite for the first time internationally.