Showing papers on "Landing gear published in 1983"

The design of the aeroplane

Abstract: Section 1 - Introduction: Airworthiness the object Vocabulary of Design Section 2 - Aerodynamics: The nature of air Arrangement of surfaces Drag, flaps and wakes Section 3 - Performance: Power for flight Reciprocating engines Turbine engines - and a range equation Section 4 - Operational Characteristics: Fuselages, hulls and floats Choice of landing gear Longitudinal stability Control surfaces Lateral and directional stability and spinning How big and how heavy Section 5 - Project Examples: Layout Appendices Index

The Design of the Airplane

Abstract: Section 1 - Introduction: Airworthiness the object Vocabulary of Design. Section 2 - Aerodynamics: The nature of air Arrangement of surfaces Drag, flaps and wakes. Section 3 - Performance: Power for flight Reciprocating engines Turbine engines - and a range equation. Section 4 - Operational Characteristics: Fuselages, hulls and floats Choice of landing gear Longitudinal stability Control surfaces Lateral and directional stability and spinning How big and how heavy. Section 5 - Project Examples: Layout, including 'Using the back of an envelope' Appendices Index

Door operated linkage for support of retracted airplane landing gear

Abstract: A shaped support beam is joined to and extends laterally across a landing gear door to provide support and to hold a retracted airplane landing gear in position when the landing gear door is closed. Pivotable linkage, extending between airplane structure and the shaped support beam, press against the landing gear to hold the gear in the retracted position with the door latched, and to be pressed against to move an unlatched door aside to permit extension of the landing gear into operating position.

Helicopter weight measuring system

Abstract: A helicopter weight measuring system for detecting the loaded weight of a helicopter operating under partial or full hover conditions while the wheels of the helicopter are contacting the ground includes means for sensing loading on the landing gear of the helicopter and means for determining the lift produced by a rotating wing of the helicopter. The sensed loading on the landing gear is added to the calculated lift to produce an indication of total helicopter loading.

Shock absorbing struts for aircraft landing gear

Abstract: Shock absorbing struts for use on aircraft landing gear which include a pair of fluid containing chambers defined by a pair of telescoping cylinders. Fluid flows from one of the chambers to another through a metering orifice proportional to the differential in pressure generated by impact loads created upon landing or taxiing of the aircraft. Upon the differential pressure exceeding a predetermined threshold level an additional flow path positioned in parallel to the metering orifice is opened by an amount proportional to the amount of differential pressure in excess of the threshold to thereby maintain a substantially constant load on the landing gear irrespective of impact loads imparted thereto.

Warning system for aircraft landing with landing gear up

Abstract: A system for providing a voice warning to the pilot of a fighter/attack aircraft when the aircraft is landing with the landing gear up monitors the radio altitude, airspeed and engine power of the aircraft and provides a predetermined voice warning if the landing gear is not down when the airspeed is less than a predetermined speed, for example, approximately 200 knots, the radio altitude is less than a predetermined altitude, for example, approximately 100 feet, and the engine is not developing take-off power.

Application of tire dynamics to aircraft landing gear design analysis

Abstract: The tire plays a key part in many analyses used for design of aircraft landing gear. Examples include structural design of wheels, landing gear shimmy, brake whirl, chatter and squeal, complex combination of chatter and shimmy on main landing gear (MLG) systems, anti-skid performance, gear walk, and rough terrain loads and performance. Tire parameters needed in the various analyses are discussed. Two tire models are discussed for shimmy analysis, the modified Moreland approach and the von Schlippe-Dietrich approach. It is shown that the Moreland model can be derived from the Von Schlippe-Dietrich model by certain approximations. The remaining analysis areas are discussed in general terms and the tire parameters needed for each are identified. Accurate tire data allows more accurate design analysis and the correct prediction of dynamic performance of aircraft landing gear.

Apparatus for landing loads from transport aircraft, especially low flying aircraft

Abstract: A landing gear for loads including cargoes and/or personnel is removably secured to the load. At least one tiltable jet engine forms part of the landing gear and automatically controls the descent movement. A stabilizing mechanism forms part of the landing gear and provides a positioned control for the landing gear and load during descent. Preferably two solid fuel rockets are provided for supporting the load during descent. The rockets are tiltable about an axis extending across the longitudinal axis of the landing gear. The tilting is controlled by a computer on board in accordance with a program present in the computer whereby the landing is substantially independent of local wind conditions and other external factors.

The design of the aeroplane : which describes common-sense mechanics of design as they affect the flying qualities of aeroplanes needing only one pilot

Abstract: Section 1 - Introduction: Airworthiness the object Vocabulary of Design Section 2 - Aerodynamics: The nature of air Arrangement of surfaces Drag, flaps and wakes Section 3 - Performance: Power for flight Reciprocating engines Turbine engines - and a range equation Section 4 - Operational Characteristics: Fuselages, hulls and floats Choice of landing gear Longitudinal stability Control surfaces Lateral and directional stability and spinning How big and how heavy Section 5 - Project Examples: Layout Appendices Index

STOL Fighter Technology Program

Abstract: In recent years, the Air Force has provided additional funds to investigate the technologies and problems associated with providing fighters a Short Take Off and Landing (STOL) capability without seriously degrading today’s maneuver, load, and cruise performance. Within the Flight Dynamics Laboratory, this technology thrust has been planned and organized under the title of “Runway Independence.”The thrust is multi-disciplined in that the following technologies are being investigated both singularly and in integrated combinations to quantify their contribution to providing options in solving the STOL design task. These technologies are: aerodynamics, integrated controls, thrust vectoring/reversing exhaust nozzles, landing gear, and cockpit aids and controllers necessary to operate under weather and/or at night.To help focus these technology efforts and to mature existing technology, the STOL Technology Fighter program was formulated. The objective of the program is to flight validate and mature near-term advanced technologies applicable to providing a STOL capability without sacrificing today’s maneuver, cruise or dash performance. Specific technologies to be addressed in this program are: two-dimensional thrust vectoring/reversing exhaust nozzle; integrated flight/propulsion control; advanced high lift systems; rough/soft field landing gear; and cockpit aids and controllers necessary to locate and land a fighter on the usable portion of the runway at night and in weather.The program will either modify an existing fighter like the F-15, F-16 or F-18 or build a hybrid vehicle like the X-29 with these technologies integrated into the vehicle. The contract will be awarded in 1983 with first flight in late 1987. The end objective of the program is to demonstrate take offs and landings under wet runway conditions of under 1500 feet including dispersion. This paper discusses the integration of these technologies into a total flight program.Copyright © 1983 by ASME

Experimental and analytical investigation of active loads control for aircraft landing gear

Abstract: A series hydraulic, active loads control main landing gear from a light, twin-engine civil aircraft was investigated. Tests included landing impact and traversal of simulated runway roughness. It is shown that the active gear is feasible and very effective in reducing the force transmitted to the airframe. Preliminary validation of a multidegree of freedom active gear flexible airframe takeoff and landing analysis computer program, which may be used as a design tool for active gear systems, is accomplished by comparing experimental and computed data for the passive and active gears.

Improvements to the FATOLA computer program including added actively controlled landing gear subroutines

Abstract: Modifications to a multi-degree-of-freedom flexible aircraft take-off and landing analysis (FATOLA) computer program, including a provision for actively controlled landing gears to expand the programs simulation capabilities, are presented. Supplemental instructions for preparation of data and for use of the modified program are included.