Add to ORKGA flightworthy active control landing gear system for a supersonic aircraft was designed to minimize aircraft loads during takeoff, impact, rollout, and taxi. The design consists of hydromechanical modifications to the existing gear and the development of a fail-safe electronic controller. analytical RESULTS INDICATE that for an aircraft sink rate of 0.914 m/sec (3 ft/sec) the system achieves a peak load reduction of 36% during landing impact
Forces generated by the Space Shuttle orbiter tire under varying vertical load, slip angle, speed, a...
Selected research and technology activities at Ames Research Center, including the Moffett Field sit...
This report presents some of the challenging research and technology accomplished at NASA Ames Resea...
Advanced high performance vehicles, including Single-Stage-To-Orbit (SSTO) hypersonic flight vehicle...
A controller for an electrohydraulic active control landing gear was developed for the F-4 aircraft....
An integrated flight/propulsion control for an advanced vector thrust supersonic STOVL aircraft, was...
A study was conducted to identify, rank, and define development plans for the critical guidance and ...
An integrated autopilot/autothrottle was designed for flight test on the NASA TSRV B-737 aircraft. T...
A structural design study was made, to assess the relative merits of various metallic structural con...
This is the second volume in the 1994 annual report for the NASA Propulsion Engineering Research Cen...
The separated flow method is evaluated. This method was developed for moderately swept wings with mu...
Partial failures of aircraft primary flight control systems and structural damages to aircraft durin...
An automatic landing system was developed for the Augmentor Wing Jet STOL Research Airplane to estab...
Ultrahigh frequency air traffic control satellite simulation experiment using high altitude balloon
Today's carrier based deck launched intercept (DLI) mission is a vital one that is aimed at protecti...
Forces generated by the Space Shuttle orbiter tire under varying vertical load, slip angle, speed, a...
Selected research and technology activities at Ames Research Center, including the Moffett Field sit...
This report presents some of the challenging research and technology accomplished at NASA Ames Resea...
Advanced high performance vehicles, including Single-Stage-To-Orbit (SSTO) hypersonic flight vehicle...
A controller for an electrohydraulic active control landing gear was developed for the F-4 aircraft....
An integrated flight/propulsion control for an advanced vector thrust supersonic STOVL aircraft, was...
A study was conducted to identify, rank, and define development plans for the critical guidance and ...
An integrated autopilot/autothrottle was designed for flight test on the NASA TSRV B-737 aircraft. T...
A structural design study was made, to assess the relative merits of various metallic structural con...
This is the second volume in the 1994 annual report for the NASA Propulsion Engineering Research Cen...
The separated flow method is evaluated. This method was developed for moderately swept wings with mu...
Partial failures of aircraft primary flight control systems and structural damages to aircraft durin...
An automatic landing system was developed for the Augmentor Wing Jet STOL Research Airplane to estab...
Ultrahigh frequency air traffic control satellite simulation experiment using high altitude balloon
Today's carrier based deck launched intercept (DLI) mission is a vital one that is aimed at protecti...
Forces generated by the Space Shuttle orbiter tire under varying vertical load, slip angle, speed, a...
Selected research and technology activities at Ames Research Center, including the Moffett Field sit...
This report presents some of the challenging research and technology accomplished at NASA Ames Resea...