Difference between revisions of "Landing Gear"
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==== Safran Landing Systems ==== | ==== Safran Landing Systems ==== | ||
− | Safran Landing Systems (SLS) manufactures landing gear for a wide range of aerospace vehicles including the Airbus A380 and Boeing 787 Dreamliner aircrafts. SLS offers innovative solutions to the Airbus A380's landing gear such as a 350-bar hydraulic system in the retractable nose landing gear, which previously had never been used before on large commercial aircraft. Similarly, SLS has made significant technological advances in the materials used for the Boeing 787 landing gear. Specifically, SLS reduced landing gear weight, reduced corrosion, and | + | Safran Landing Systems (SLS) manufactures landing gear for a wide range of aerospace vehicles including the Airbus A380 and Boeing 787 Dreamliner aircrafts. SLS offers innovative solutions to the Airbus A380's landing gear such as a 350-bar hydraulic system in the retractable nose landing gear, which previously had never been used before on large commercial aircraft. Similarly, SLS has made significant technological advances in the materials used for the Boeing 787 landing gear. Specifically, SLS reduced landing gear weight, reduced corrosion, and provided higher resistance to fatigue versus steel components. Several components in the Boeing 787 landing gear are made from titanium including the inner cylinder of the main gear, which is an industry first. |
==== Performance Testing ==== | ==== Performance Testing ==== | ||
Safran Landing Systems (SLS) performs a variety of quality assurance tests for each landing gear. The landing gears are first subject to 150% of the maximum loading conditions that they would be subjected to in commercial service. This provides confidence in the capabilities of a loaded landing gear with a safety factor. SLS also drops the landing gear from a height which generates up to a 3.6576 m/s impact speed on the landing gear. The tested impact speed is above the FAA maximum required impact speed without failure of 3.048 m/s for commercial aircraft. Additionally, SLS conducts rigorous environmental testing for the landing gear to ensure that they will function successfully under extreme conditions. The landing gear in subjected to temperatures ranging from -55℃ to 75 ℃. While conducting low temperature testing, the landing gear must demonstrate that it is able to break through up to 6 mm thick ice while extending and retracting. Other tests are conducted to ensure that the landing gears are resilient to vibrations, corrosion, sand, dust, high intensity frequency pulses, and that they can dissipate the charge from a lightning strike without being damaged or losing functionality. | Safran Landing Systems (SLS) performs a variety of quality assurance tests for each landing gear. The landing gears are first subject to 150% of the maximum loading conditions that they would be subjected to in commercial service. This provides confidence in the capabilities of a loaded landing gear with a safety factor. SLS also drops the landing gear from a height which generates up to a 3.6576 m/s impact speed on the landing gear. The tested impact speed is above the FAA maximum required impact speed without failure of 3.048 m/s for commercial aircraft. Additionally, SLS conducts rigorous environmental testing for the landing gear to ensure that they will function successfully under extreme conditions. The landing gear in subjected to temperatures ranging from -55℃ to 75 ℃. While conducting low temperature testing, the landing gear must demonstrate that it is able to break through up to 6 mm thick ice while extending and retracting. Other tests are conducted to ensure that the landing gears are resilient to vibrations, corrosion, sand, dust, high intensity frequency pulses, and that they can dissipate the charge from a lightning strike without being damaged or losing functionality. |
Revision as of 23:58, 16 April 2019
Contents
Manufacturing Requirements
The following four sections provide information critical to the manufacturing requirements of the landing gear for each of the aircraft. The maximum allowed load is important to know in order to design a landing gear strut with a suitable cross-sectional area built from a material with optimal mechanical properties for the given max loads.
Boeing 787 Dreamliner
Below is a table for the maximum allowed loads per strut on the landing gear for specific conditions.
Airplane Model | Unit | Max Design Taxi Weight | Vertical Nose Gear Load Static at Most Forward CG | Vertical Nose Gear Load Static + Braking 10 ft/s2 Deceleration | Vertical Main Gear Load per Strut at Max Load at Static AFT CG | Horizontal Main Gear Load Static + Braking 10 ft/s2 Deceleration | Horizontal Main Gear Load per Strut CG at Instantaneous Braking |
---|---|---|---|---|---|---|---|
787-8 | kg | 228,383 | 24,819 | 38,594 | 104,234 | 35,468 | 83,388 |
787-9 | kg | 254,692 | 21,322 | 34,546 | 117,736 | 39,554 | 94,189 |
787-10 | kg | 254,692 | 19,138 | 30,939 | 118,745 | 39,554 | 94,996 |
Boeing 747
Below is a table for the maximum allowed loads per strut on the landing gear for specific conditions.
Airplane Model | Unit | Max Design Taxi Weight | Vertical Nose Gear Load Static at Most Forward CG | Vertical Nose Gear Load Static + Braking 10 ft/s2 Deceleration | Vertical Main Gear Load per Strut at Max Load at Static AFT CG | Horizontal Main Gear Load Static + Braking 10 ft/s2 Deceleration | Horizontal Main Gear Load per Strut CG at Instantaneous Braking |
---|---|---|---|---|---|---|---|
747-8 | kg | 449,056 | 31,802 | 54,252 | 106,299 | 34,870 | 85,039 |
747-8F | kg | 443,613 | 29,549 | 52,789 | 105,010 | 34,447 | 84,008 |
Airbus A330-700 Beluga XL
Below is a table for the maximum allowed loads per strut on the landing gear for specific conditions.
CG Height | Unit | Max Design Taxi Weight | Vertical Nose Gear Load Static at Most Forward CG | Vertical Nose Gear Load Static + Braking 10 ft/s2 Deceleration | Vertical Main Gear Load per Strut at Max Load at Static AFT CG | Horizontal Main Gear Load Static + Braking 10 ft/s2 Deceleration | Horizontal Main Gear Load per Strut CG at Instantaneous Braking |
---|---|---|---|---|---|---|---|
ZCG -0.5 m | kg | 227,900 | 23,280 | 38,150 | 104,440 | 35,420 | 83,550 |
ZCG -0.4 m | kg | 227,900 | 24,700 | 39,890 | 104,440 | 35,420 | 83,550 |
ZCG 0 m | kg | 227,900 | 24,700 | 41,170 | 104,440 | 35,420 | 83,550 |
ZCG 0.4 m | kg | 227,900 | 24,700 | 42,440 | 103,620 | 35,420 | 82,890 |
ZCG 0.6 m | kg | 202,300 | 23,650 | 39,970 | 92,710 | 31,440 | 74,160 |
Airbus A380
Below is a table for the maximum allowed loads per strut on the landing gear for specific conditions.
Weight Variant | Unit | Max Design Taxi Weight | Vertical Nose Gear Load Static at Most Forward CG | Vertical Nose Gear Load Static + Braking 10 ft/s2 Deceleration | Vertical Wing Gear Load per Strut at Max Load at Static AFT CG | Vertical Body Gear Load per Strut at Max Load at Static AFT CG | Horizontal Body Gear Load Static + Braking 10 ft/s2 Deceleration | Horizontal Body Gear Load per Strut CG at Instantaneous Braking | Horizontal Wing Gear Load Static + Braking 10 ft/s2 Deceleration | Horizontal Wing Gear Load per Strut CG at Instantaneous Braking |
---|---|---|---|---|---|---|---|---|---|---|
WV008 | kg | 577,000 | 40,190 | 70,590 | 108,850 | 163,270 | 53,800 | 130,620 | 35,870 | 87,080 |
There are several other weight variants listed for the Airbus A380. WV008 has the largest loads per strut for each landing gear. A complete list of the 15 different weight variants can be founds below.
Manufacturing and Testing
Safran Landing Systems
Safran Landing Systems (SLS) manufactures landing gear for a wide range of aerospace vehicles including the Airbus A380 and Boeing 787 Dreamliner aircrafts. SLS offers innovative solutions to the Airbus A380's landing gear such as a 350-bar hydraulic system in the retractable nose landing gear, which previously had never been used before on large commercial aircraft. Similarly, SLS has made significant technological advances in the materials used for the Boeing 787 landing gear. Specifically, SLS reduced landing gear weight, reduced corrosion, and provided higher resistance to fatigue versus steel components. Several components in the Boeing 787 landing gear are made from titanium including the inner cylinder of the main gear, which is an industry first.
Performance Testing
Safran Landing Systems (SLS) performs a variety of quality assurance tests for each landing gear. The landing gears are first subject to 150% of the maximum loading conditions that they would be subjected to in commercial service. This provides confidence in the capabilities of a loaded landing gear with a safety factor. SLS also drops the landing gear from a height which generates up to a 3.6576 m/s impact speed on the landing gear. The tested impact speed is above the FAA maximum required impact speed without failure of 3.048 m/s for commercial aircraft. Additionally, SLS conducts rigorous environmental testing for the landing gear to ensure that they will function successfully under extreme conditions. The landing gear in subjected to temperatures ranging from -55℃ to 75 ℃. While conducting low temperature testing, the landing gear must demonstrate that it is able to break through up to 6 mm thick ice while extending and retracting. Other tests are conducted to ensure that the landing gears are resilient to vibrations, corrosion, sand, dust, high intensity frequency pulses, and that they can dissipate the charge from a lightning strike without being damaged or losing functionality.