Feb 1-2
All structural analysis depends on the development of a sufficient set of applied design load conditions to cover the significant load events during the life of a structure. On aircraft and other weight-critical structures, these loads must not only be sufficient but also no higher than necessary. This second requirement makes the development of good aircraft design loads a real challenge. Furthermore, the design loads need to meet the applicable civil or military regulations. These regulations have, over time, evolved to provide a good framework for the expected loads events; however, on occasion, it may be prudent to go beyond the minimum requirement.
Aircraft Structural Considerations.Internal Loads.Load Paths.Analysis Sizing Criteria Requirements Objectives. FAR’s. MIL Specs. SOW/PDS Configuration. Aircraft Loads, Conditions & Requirements. Every Requirement and Condition is There for a Reason! 747/767/777 Daily Highlight Report.
Course Details
This course provides you with an overview of the theory, as well as practical knowledge, of the methodologies for performing aircraft loads analysis and the presentation and validation of those loads for civil or military certification. Participation in in-depth discussion with those who are experts in the field is welcomed and encouraged.
The course benefits:
- Loads engineers who seek to interact with others in their field
- Design and stress engineers who would like to become more familiar with aircraft loads analysis to help them understand how the design parameters interact with the applied loads
Upon completing this course, students can:
- Evaluate a loads analysis for completeness
- Discuss certification aspects of chosen loads methods, including validation
- Understand more of the theory behind the loads analysis
- See how design modifications might impact design loads
- Participate in in-depth discussions of a few aspects of loads analysis
Course Materials
The text, Structural Loads Analysis for Commercial Transport Aircraft: Theory and Practice, Ted L. Lomax, AIAA, 1996; and lecture notes are distributed on the first day of the course. The notes are for participants only and are not for sale.
Coordinator and Lecturer
Willem J. Kernkamp, MS, Loads and Flutter Certification Consultant, Kernkamp Industries Corporation, Chatsworth, California. Mr. Kernkamp is a consultant for aerodynamic loads, flutter, structural substantiation, and FAA certification of transport and commuter category aircraft (FAR 25 and 23). He is involved in all areas of structural analysis, including finite element and detail stress analysis, dynamics, and aerodynamic loads. He has managed the documentation and analysis of many projects conforming with civil aircraft requirements, and is currently an FAA Designated Engineering Representative in structures, loads, and flutter.
Mr. Kernkamp’s loads-related areas of experience include consultant to Airbus in the litigation about the Bell Harbor A300 crash resulting from separation of the vertical tail; management of a FAA certification team for an unmanned vehicle; structural design of all-composite seven-foot propeller blades for a Raptor (high-altitude unmanned aircraft); aerodynamic loads analysis for radomes on the Lockheed C-130; loads analysis and certification of cargo doors and surround structure for Douglas DC-8 and Boeing 757 passenger-to-freighter conversions; structural and aerodynamic loads analysis for certification of weight increases on Douglas DC-8 and Boeing 727 aircraft; aeroelastic loads and flutter analysis of the bulb keel for Dennis Conner’s Stars & Stripes America’s Cup 1992 racing yacht; simulation of the capsizing of the tug TEMI IV due to tow rope forces (with loss of life) during litigation before the High Court of the Netherlands; and developed computer code for aerodynamic loads analysis (static and dynamic), non-linear dynamic analysis (landing and taxi), and structural analysis.
Mr. Kernkamp has been an independent structural certification consultant in close association with Structural Integrity Engineering since 1994. Prior to that, he worked at Rasmussen and Associates on certification loads and at National Aerospace Laboratory (NLR), Amsterdam, The Netherlands, in computation fluid dynamics. He has taught courses in aerodynamic loads analysis to Lockheed Martin employees and general computer science courses to PE engineering students.
Daily Schedule
Day 1
Structural Design Parameters
- Structural Design Weights and Center of Gravity Limits
- V-n Diagrams; Structural Design Airspeeds
- Balanced Maneuvers
- Discrete Gust
- Symmetrical Flight Maneuvers
- Rolling Flight Maneuvers
- Yawing Flight Maneuvers
— Bell Harbor A300 Crash (Loss of Fin) - Asymmetric Flight Maneuvers
- Effects of Fuel Distribution
- Comparison of Military and Commercial Flight Maneuvers
Key Concepts
![Loads Loads](/uploads/1/2/4/9/124948538/428083885.jpg)
- Dynamic Analysis vs. Static Analysis
- Aeroelastic Analysis vs. Rigid Analysis
Day 2
Aerodynamic Air Loads
- Flight in Turbulence
- Aircraft Load Spectrum
- Acoustic Fatigue Loads
- Buffeting
Ground, Landing, and Miscellaneous Conditions
- Landing Conditions
— MD80 Prototype Hard Landing with Empennage Falling Off - Ground-Handling Conditions
- Emergency Landing Conditions
- Pressurization
- Bird Strike
- Conditions Specific for Military Aircraft Types
- Comparison of Military and Commercial Requirements
Day 3
Validation and Certification
- The Type Certification Process
- Instrumentation and Calibration
- Ground and Flight Testing
— Actual Strain Data: The Good, the Bad, and the Ugly - Horizontal Tail Loads
- Vertical Tail Loads
- Wing Loads
— CFD Example Compared to Other Methods - Body Monocoque Loads
- Control Surface Loads and High-Lift Devices
- Radomes
— CFD Example: Handling Unsteady Flow
For more information contact the Short Course Program Office:
[email protected] (310) 825-3344 | fax (310) 206-2815
[email protected] (310) 825-3344 | fax (310) 206-2815
There are different testing activities that are done on aircrafts in order to maintain strength and make sure that the manufacturing integrity is still preserved. These processes are done differently but there is a single goal and that is to determine if fixing is needed for the plane.
Before the discussion of major Aircraft testing that is done for this type of Aerospace vehicle, you need to have an idea about what a structural load is. Structural loads are considered to be the forces or the accelerations that are applied to the structure or to the components of such. This can be a cause of problems in the structure such as deformation and stress. When checking structural loads, there is a standard that Aircraft owners should always be considering. There are different types of loads; dead loads, live loads and cyslic loads.
Here is a list of some of the major Aircraft testing:
- Structural Testing. This is used in order to test the component according to its fatigue strength and also to verify another aspect that is called static strength. Using the measured loads that will then be applied to the item to be tested is one of the most important parts of Structural Testing. This can be done on different items with different sizes and it can also be done on the whole aircraft.
- Fatigue Testing.This is another important process of Aircraft testing activity wherein the stress range is being measured. The goal of Fatigue Testing is to measure the one aspect of structural load called stress range. This is done in order to know how much stress range can be applied before it can cause failure.
Those are just two of the basic examples of testing that are done on aircrafts. One of the most important things that will be discussed in this section is the role of structural loads in the wings of an aircraft.
According to the experts, the construction of the aircraft wing is actually the same no matter what type of plane is created. During the point of manufacturing, the aircraft wing should be created in a way that it can stand pressure and high levels of stress. This is the reason why many of the newly created aircrafts are made with metal wings. Now, the next part of the discussion is the calculation of load for the aircraft wing. According to experts, the wing’s weight distribution should be considered as a major component if you are going to calculate for the bending force. When there are damages incurred in aircrafts because of the stress and loads that are not properly taken care of, metal bonding is one of the repairing options. This has been available not only for those that are created with new materials but also with those that are old-fashioned aircrafts.
Structural loads in wings are also very important. It is as important as knowing about aero structure and aircraft spares. Calculating the load structure is something that can be done when you are going to calculate first for the bending force. All in all, all tests that are done on aircraft have a common goal and that is to ensure the safety of the aircraft when it travels. The wing is only one of the major parts of the aircraft but its structural loads can affect the whole aircraft if it is not given enough attention. So, to ensure a safe flight, you have to consider structural loads in wings as an important aspect of aircraft testing.