Landing Impact Load Analysis and Validation of a Civil Aircraft Nose Landing Gear
Abstract
:1. Introduction
2. Theoretical Model and Tool
2.1. Landing Gear Structure
2.2. Landing Dynamic Model
2.3. Landing Analysis Tool
3. Preliminary Analysis
3.1. Analysis Cases
3.2. Performance Verification
3.3. WA and GC Loads
4. Drop Test Validation
4.1. Test Facility and Preparation
4.2. Test Cases
4.3. Processing of Test Results
4.3.1. Parameter Tuning
4.3.2. Load Validation
4.3.3. Performance Validation
5. Conclusions
- The results of the drop test show that the landing simulation analysis model established by the assumption of the two masses (sprung and un-sprung), four degrees of freedom, and a rigid airframe can accurately analyze the landing impact loads.
- Through both the simulation and the test, the difference between the wheel-axle and the ground-contact loads was revealed to be non-negligible.
- If one takes reasonable consideration in the pre-test preparation of the structure’s stiffness and the during-test measurement of the wheel-axle loads, the drop test validation can be accurate and comprehensive, and both the vertical and the longitudinal loads, as well as the wheel-axle and ground-contact loads, can be fully validated.
- The importance of structural flexibility and tire friction modeling, as noted in this paper, should be considered in the current popular dynamic analysis methods based on ADAMS or other software, and the corresponding multi-body modeling methods can be further investigated to accurately analyze longitudinal loads.
- The lateral loads and the detailed attachment point loads may also need to be investigated further via both simulations and tests, including the motion equations for the lateral degrees of freedom, the lateral mechanics model of the tires, and the experimental validation of attachment point loads, especially for main landing gears with more complex asymmetric structures than the nose landing gear.
Author Contributions
Funding
Data Availability Statement
Conflicts of Interest
References
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Preliminary Analysis Case | A1 | A2 | A3 |
---|---|---|---|
Reduced mass (kg) | 13,400 | 13,400 | 13,400 |
Sinking speed (m/s) | 3.05 | 3.05 | 3.05 |
Longitudinal speed (m/s) | 0 | 58 | 96 |
Test Case | T1 | T2 | T3 |
---|---|---|---|
Reduced Mass (kg) | 13,472 | 13,472 | 13,472 |
Sinking Speed (m/s) | 3.10 | 3.08 | 3.08 |
Longitudinal Speed (m/s) | 0 | 58.6 | 96.5 |
Key Factor | Pre. | T1 | T2 | T3 | Tuned |
---|---|---|---|---|---|
Gas polytrophic (−) | 1.1 | 1.13 | 1.05 | 1.12 | 1.08 |
Oil discharging (−) | 0.8 | 0.82 | 0.84 | 0.79 | 0.8 |
Bearing friction (−) | 5% | 5% | 9% | 8% | 7% |
Tire dynamic (−) | 1.08 | 1.04 | 0.97 | 1.07 | 1.08 |
Performance Index | T1 | T2 | T3 |
---|---|---|---|
Load factor (−) | 1.69 | 1.62 | 1.63 |
Absorption efficiency (−) | 65.9% | 67.8% | 67.4% |
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Liu, W.; Wang, Y.; Ji, Y. Landing Impact Load Analysis and Validation of a Civil Aircraft Nose Landing Gear. Aerospace 2023, 10, 953. https://doi.org/10.3390/aerospace10110953
Liu W, Wang Y, Ji Y. Landing Impact Load Analysis and Validation of a Civil Aircraft Nose Landing Gear. Aerospace. 2023; 10(11):953. https://doi.org/10.3390/aerospace10110953
Chicago/Turabian StyleLiu, Wenbin, Youshan Wang, and Yuchen Ji. 2023. "Landing Impact Load Analysis and Validation of a Civil Aircraft Nose Landing Gear" Aerospace 10, no. 11: 953. https://doi.org/10.3390/aerospace10110953