Guinaldo Fernandez
Enrique Guinaldo Fernandez, Salamanca ES
Patent application number | Description | Published |
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20120166037 | AIRCRAFT BLACK BOX - Commercial aircraft ( | 06-28-2012 |
20120248247 | AIRCRAFT FUSELAGE WITH HIGH STRENGTH FRAMES - Fuselage section of an aircraft whose structure comprises a skin ( | 10-04-2012 |
20130099057 | IMPACT RESISTANT AND DAMAGE TOLERANT AIRCRAFT FUSELAGE - Aircraft fuselage section ( | 04-25-2013 |
Enrique Guinaldo Fernandez, Geafe Madrid ES
Patent application number | Description | Published |
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20140011006 | MULTIFUNCTIONAL COMPOSITE MATERIAL INCLUDING A VISCOELASTIC INTERLAYER - Provided is a structure of composite material, comprising a continuous first layer of composite material, a second layer of viscoelastic material, and a continuous impact-protection third layer. The first layer is formed by structural components in the form of a matrix and fibers. The second layer of viscoelastic material is added on top of the first layer and said second layer can be continuous or non-continuous. If a non-continuous second layer is used, elongate, circular or square cavities are arranged inside the layer. Optionally, reinforcements comprising carbon nanofibers or nanotubes are provided in either of the first and second layers. The third layer of impact-protection material is added in a continuous manner on top of the second layer, the third layer forming the outermost layer of the composite material. In addition, this third layer is electrically conductive. The composite material has noise attenuation, | 01-09-2014 |
Enrique Guinaldo Fernandez, Getafe (madrid) ES
Patent application number | Description | Published |
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20140133987 | HIGHLY INTEGRATED LEADING EDGE OF AN AIRCRAFT LIFTING SURFACE - A method for manufacturing a leading edge profile section of an aircraft lifting surface is provided. The method comprises the following steps: a) providing a set of laminated preforms of a composite material configured with a suitable shape for constituting the leading edge profile section; b) arranging said laminated preforms in a curing tooling and subjecting the assembly to an autoclave cycle to co-cure said laminated preforms; c) demoulding the curing tooling in a spanwise direction towards the aircraft symmetry plane. The invention also comprises a leading edge profile section manufactured by said method comprising in addition to the skin of the leading edge profile section, one or more of the following structural elements: an auxiliary spar, a longitudinal stiffener reinforcing an auxiliary spar, a longitudinal stringer reinforcing the skin of the leading edge profile. | 05-15-2014 |
20140151505 | MAIN SUPPORTING STRUCTURE OF AN AIRCRAFT LIFTING SURFACE - An aircraft lifting surface with a main supporting structure comprising upper and lower faces defining its aerodynamic profile, front and rear faces oriented towards, respectively, the leading and trailing edges, a first set of transverse ribs extended from the front face to the rear face and a second set of transverse ribs crossing the front face and/or the rear face. The integration of leading and trailing edge ribs in the main supporting structure allows a weight and cost reduction of aircraft lifting surfaces. A manufacturing method of said main supporting structure is also disclosed. | 06-05-2014 |
Enrique Guinaldo Fernandez, Getafe ES
Patent application number | Description | Published |
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20140151506 | HIGHLY INTEGRATED STRUCTURE INCLUDING LEADING AND TRAILING EDGE RIBS FOR AN AIRCRAFT LIFTING SURFACE - The invention provides an aircraft lifting surface with a monolithic main supporting structure ( | 06-05-2014 |