Dec    2001                  Catia-Ver 5 R8 Basic Solids/Surfaces                                          Incat Ltd

Apr     2001                  Catia-Ver 4.2.2 Advanced Surface/Solid Modelling                         Fastec Ltd.

Aug    1992                  Auto-Cad Ver 11.                                                                         SSI Ltd.

1988 to 1992                BEng (Hons) Degree Aerospace Engineering. Class 2:1.           University Of Hertfordshire.

Sponsored by Hunting Engineering R&D Ltd.

Computer Packages Used:

Catia-Ver. 5

Catia Ver. 4.2.2

MathCAD 12

Airbus LAP 3.0F

Excel / Word / PowerPoint

Solid Edge Ver.16

AutoCAD.

Fortran 77

Unix.

Nastran/Patran

Summary

I am a aerospace structural engineer with +15 years experience, +7 yrs of which has been with a small team at Chichester Miles Consultants (CMC Ltd) tasked with the design, structural test, development & flight testing of a prototype composite jet aircraft (CMC Leopard). At GKN Cowes I gained experience in primary composite structural test & certification of composite design allowables. At Astrium, I was part of a team involved in the design of two major satellite structures and coordination of the associated systems installations. On the centaur amphibian aircraft I was solely responsible for the mechanical concept, design & analysis of the nose u/c, doors and related sub systems. My 2^nd visit to Astrium allowed me to become involved with my 3^rd satellite structure with responsibility for the overall structural design of the systems module (SM) along with the conceptual structural design and supporting analysis of non-generic components. At QinetiQ I was solely responsible for the stress analysis of a large metallic under wing pylon mounted test pod. As a Principle Engineer for GKN-Melbourne I lead a stress team in Malaysia working on the A400M FTE package. I am currently working on the prototype future lynx helicopter. Experience has allowed me to gain a practical/theoretical approach to engineering enabling low cost and reliable systems solutions, all of which have been proven in flight.

Work Experience

Sept 2006 to present                  GED Sitec. (Hurn – Stress Office)

Analysis of the prototype future lynx helicopter, notably the fuselage side skins (Batch 7), the main u/c sponson structure and structure outboard of V560 (Batch 6 & 8) using S214, MathCAD, Patran & Microsoft tools.

Jan 2006 to Sept 2006                GKN Ltd. (Melbourne – Stress Office)

Lead a team of 8 stress engineers at CTRM in Malaysia working on the C-Scheme A400M FTE package, namely the 24 composite shroud panels for the spoiler and flap and their associated metallic components. This involved,

a)                   Compilation of all the MathCad templates used in the composite static, F&DT analysis in accordance with Airbus CSM Iss.2 & 3 where applicable.

b)                   Responsibility for delivery of all C-Scheme static stress reports, ASD’s from CTRM in Malaysia.

c)                   Managerial decisions relating to transfer of work to GKN Melbourne in order to make C-Scheme dates.

d)                   Technical liaison between design and stress in GKN (Cowes), Malaysia & GKN (Melbourne).

e)                   Assessment of stress program timescales & dates.

Aug 2004 to Jan 2006                 QinetiQ Ltd. (Boscombe Down – Stress Office)

Senior stress engineer using MathCAD stressing skills in the analysis of a large wing pylon mounted test pod. I was the sole stress engineer on project with responsibility for the compilation of all reports. A static, dynamic & fatigue analysis was completed on all components (Metallic). Stress & Design input from concept into development and manufacture stages.

Nov 2003 to Aug 2004                Astrium Ltd. (Stevenage – Structural Design Dept)

Senior structural design engineer working on the systems module of a military communications satellite. I was expected to come up with any new concepts that were outside the generic design and ensure structural & functional compliance.  The tasks required the use of sprint, conceptual design, manual stressing skills & overseeing the modelling and drawing on Catia V4 leading a number of Catia operators and transferring my stress work and assumptions to the stress office for detail analysis work.

Dec 2002 to Oct 2003                Aim Aviation Ltd.(Hurn Stress Office)

Stress engineer using manual stressing skills in the analysis of aerospace quality composite structures. Compilation of numerous interface load and stress office reports for Boeing and the certifying authorities.

Nov 2001 to Nov 2002                Chichester-Miles Consultants Ltd.

Structural design engineer using Catia Ver 5 R9+ and manual stressing skills in the design of aerospace quality structures & systems for use on an all-composite amphibian aircraft - Centaur, and feasibility studies on a six seater small business jet. The role required creation of a Catia V5 based concept backed up with classical stress calculations and to complete the design and analysis package.

May 2001 to Nov 2001                Astrium Ltd. (Stevenage – Structural Design Dept)

Structural design engineer using Catia Ver 4.2.2 and manual stressing skills in the design of aerospace quality structures for use on Communications satellites Intelsat X-01 & Inmarsat IV-F1

Nov 1998 to Mar 2001                 Chichester-Miles Consultants Ltd.

The task being to enable the expansion of Leopard 002 aircraft flight-test program through:

a.       Enabling the recording/Analysis of flight test data.

b.       Design, stress and manufacture of systems modifications as required.

Typical design projects completed are as follows. Installation of various instrumentation systems, main u/c doors, oxygen system, seat-back release, Re-profile of existing wing section, extended wing tip, flap/wing gap aerodynamic sealing, environmental seals. All design work was carried out on AutoCAD 14/2000, the wing surface model being completed using AutoCAD Mechanical Desktop. The analysis/documentation of data was completed using excel.

Dec 1997 to Oct 1998                GKN Westland (Cowes Stress Office)

Composite certification work on the nacelle of the de-Havilland Q400 aircraft. Involved in the compilation of a complete set of primary and secondary design allowables for the laminate used on the lower cowl of the nacelle (primary carbon structure). This work was based on initial work carried out by Hexcel. Certification & testing was conducted in accordance with MIL-HDBK-17, AMA 500 C/8 (TCA), AC 20-107A (FAA) and involved DERA/GKN Westland/Shorts/Transport Canada Aviation. Other tasks undertaken were as follows…

1.              Certification substantiation and analysis of a composite repair to the monolithic and honeycomb structure of the lower cowl on the Q400. Involved liaison with DERA Farnborough SMC regarding coupon level testing in support of the design allowables and repair certification programs.

2.              Involvement in component level static & fatigue flowcharts for nacelle level tests.

3.              Submittal of composite repair sections for commercial bids on A340 Flap/AS900 Nacelle/C27J Nacelle.

4.              Began certification stress report of the composite lower cowl using MathCAD.

July 1992 to Dec 1997                Chichester-Miles Consultants Ltd.

Leopard 002 aircraft project. Employed primarily as a junior design/stress engineer but also became engaged in all aspects of manufacture, structural testing, assembly and flight-testing. Tasks completed were as follows….

Mock-up, Design, stress analysis, manufacturing drawing package (BS308) for….

1.       Canopy structure. The Leopard 002 is a pressurised, composite business jet and the canopy represents a ¼ of the fuselage.

2.       Main U/C Doors structures, mechanisms, systems and wheel box profiles.

3.       Translating instrument panel/Engine Instrument console and its actuation system.

4.       Canopy Jacking/Retraction Systems (Systems 3 & 4 are mechanically connected)

5.       Wing/Wheel bay systems - Harness Conduits,

6.       Throttle detent mechanism.

Rig design, testing and compilation of test reports for the CAA on the following:

Nose U/C, Fin, Fin Tab, Engine Pylon, Tail-plane, Tail-plane Tab, Tail-plane Spigots, Rear Fuselage Torsion & Bending Test & Controls Test, 7 month final assembly & systems testing at Old Sarum & Cranfield. First flight 9-4-97.

Flight Test Phase design mod tasks…

7.    Directional stability mod to all flying fin.

8.    Yaw stops on pitch/roll resolver.

9.    Instrumented flight-test probe.

10.   Increase in area to ventral fin.

11.   Nav/Strobe light Installation.

12.   De-gearing of the all-flying fin to rudder pedal movement.

13.   Fairing in main U/C Doors to profile of lower wing surface.

14.   Leading edge profiling.