Design&Engineering

OMPM Staff is composed by Engineers and technicians with experience that varies from 2 up to 25 years. Most significant skills are:

• Design of Main structural components for aerospace;
• Design of structural provision for equipment installation;
• Design of Jugs and Rigs;
• Strength and Stability Analysis;
• Linear and not linear Static Analysis;
• Dynamic and Frequency response Analysis;
• Fatigue Analysis;
• Damage Tolerance;
• Crash Analysis;
• Topology Optimization.

The main software used in the Engineering Departments are: CAtia V4 and V5; Vericut, Enovia, MSC Nastran, MSC Marc, MSC Adams, MSC Patran, Teamcenter. Others for the engineering development are: CAD Unigraphics, ProE; FEM Processor Hypermesh; FEM Software Hyperworks; Radioss, LS-Dyna.

OMPM is responsible of the following activities on Boeing B787 Program Boeing B787-8

• Stress & Design of Body splice (CFRP-Metal) between section 43/44 & sections 44/46.
• Stress & Design of Pax floor (CFRP-Metal) at section 46 including system installation.
• Stress & Design of Electrical installation for sections 44 & 46
• Design of strain gage installation for Horizontal Stabilizer for static and fatigue test.
• Static and fatigue test strain gages prediction/correlation.

Boeing B787-9

• Stress & Design of Side of body at main landing gear and pressure deck interface.
• Stress & Design activities for the Horizontal stabilizer.
• Stress & Design of Pax floor (CFRP-Metal) at section 46 including system installation.
• Stress & Design of Cargo barrier (flame resistant and smoke containment) at section 46
• Stress & Design of EEBAY floor at section 46

Engine pylon study designed according the certification EASA CS25 and FAR Part 25. The layout proposed takes also in account the “Fire Protection” requirements prescribed by CS25 subparagraphs with the following considerations:

• The CS 25.1181 defines as “Designated Fire Zones” the Engine Accessory Sections;
• The CS 25.1182 states that any item of the Engine Pod attaching to the structure, behind the firewall and that contains flammable liquids must respects the requirements related to the fire zones;
• The CS 25.865 states that the engine mounts must be of fire proof material or fire shielded in the designated fire zones;
• The CS 25.1191 states that the Engine must be isolated by the rest of the structure trough firewalls that are at least fire proof;
• The CS 25.1193 comma c, states that in the airplanes in which the Engine Section is isolated by the Engine;
• Accessory Section by a firewall the cowling of the last one section must be fireproof both if subjected to flames or to exhaust gases (as in thrust reverse conditions).

Integral design of a monolithic frame emergency door and impact analysis according the certification normative JAR 25.562 that require an Hybrid III 50% dummy with a weight of 77.11 Kg. The study allowed to calculate the acceleration on the Dummy and the HIC on the head

Study of a crashworthy seat the certification normative JAR 25.562 that require an Hybrid III 50% dummy with a weight of 77.11 Kg.

Bird strike analysis on a crashworthy leading edge made of sandwich panel, according to PART 25 Sect 25.631 AMDT 25-23 Eff. 5/8/70.

• Bird mass 3.6 Kg
• Speed 180 m/s – Design cruising speed at sea level (Vc)
• Panel mass/surface ratio 5.6 Kg/m2

OMPM is studying a new Forward Onboard Airstairs for Business Jets with a cabin floor higher than 3.5 m from the ground. The Airstairs are installed under the cabin floor to avoid impacting the Door Design. OMPM’ s goal is to reduce as much as possible the weight and to respect the systems already in use which represents the biggest problem for these items. Additionally, OMPM have had under consideration simplify the design of the Airstairs as much as possible to improve safety and reduce malfunctions.

OMPM has the capability design components made in plastic and advance techno polymers which usage is growing in the aerospace sector, because they presents good mechanic and thermal resistance characteristics associated with low cost and excellent esthetic view. The picture shows a study of an handle for the cap of the oil tank of a PART25 aircraft. The material selected was, ordered from the one to higher to lower performance and cost:

• PEEK, spec MIL-P-46183 TYPE I
• PEI, MIL-P-46184 TYPE I
• POLYSULFONE, MIL-P–46120 TYPE