80 results about "Ground support equipment" patented technology

Ground support equipment for servicing an airplane includes a ground support equipment cart upon which are mounted at least two equipment modules and a control module. A first equipment module mounted upon the cart contains ground support equipment for servicing an airplane and also has a network connection, and at least one additional equipment module mounted upon the cart contains additional ground support equipment for servicing an airplane and also has a network connection. The control module has a user display and user controls that are connected to a control processor which has a network connection. The user display and the user controls serve as a shared control panel for the ground support equipment contained in the modules mounted upon the cart. A network interconnects the network connections of the modules mounted upon the cart. The control processor can cause the user display to present a menu listing various types or classes of airplanes for selection by a user. In response to user selection of a type or class of airplane, the control processor sends over the network to one or more of the other modules information defining what particular services the selected type or class of airplane requires of the modules.

A ground support equipment air conditioning system detachably connects to a port on an airplane. An air conduit connects an air intake and filter to a coupling that is adapted to be connected to one end of an air duct or hose the other end of which is adapted to be connected to an airplane's port. A variable speed blower in the air conduit has its speed varied by a controller to regulate the pressure supplied to an airplane. This controller receives as inputs the pressure sensed by a pressure sensor connected to the air conduit adjacent the coupling to sense the pressure of air passing into the airplane and also a setpoint pressure which can be varied to match the requirements of different types or classes of airplane. First and second air conditioners each include a circular refrigerant conduit channeling refrigerant through a compressor, a condenser, an expansion valve, and an evaporator. The evaporators are positioned in the air conduit with the first air conditioner's evaporator preceding the blower and the second air conditioner's evaporator following the blower in the air conduit. A condenser cooling fan drives air through the two condensers and is controlled by a controller responsive to one or more pressures or temperatures measured in one of the air or refrigerant conduits or in the surrounding air.

A ground support equipment cart contains one or more removable equipment modules. The cart contains a rectangular module containing airplane air conditioning components mounted upon the cart and extending the width of the cart but occupying substantially less than half of the cart's length. The cart also contains one or more rectangular equipment modules removably mounted upon the cart, one or two of the removable modules containing electrical power converting components. And the cart contains a rectangular module containing power generating components mounted upon the cart and occupying substantially the remainder of the cart. The cart separates into two parts, one part containing the module containing power generating components. The cart also contains a control module having a display and controls for, and that is networked to, the other modules. One or more of the removable modules slide out on a tray and may be locked in position.

Airplane ground service equipment includes an air conditioning system for an airplane and also a fluid cooling system for airplane electronics which detachably connects to a first port and a second port on the airplane. The fluid cooling system includes a first connector, a second connector, and a fluid conduit therebetween, the first and second connectors being adapted to be connected to the first and second ports, respectively, such that the connection of the ports to the connectors completes a fluid circuit. A fluid pump directs fluid through the fluid conduit, and a heat exchanger in the fluid conduit removes heat from the fluid circuit and transfers it into the air conditioning system of the ground support equipment. A temperature regulation mechanism stabilizes the temperature of the fluid in the fluid conduit to compensate for changes in the amount of heat that is drawn from the airplane electronics.

A method and ground support equipment (GSE) for attaching an engine core to an engine fan module on an aircraft pylon. The GSE may comprise GSE supports and lifting components attached to the pylon, two suspension rails attached to the lifting components, two translating rails translatably attached to the two suspensions rails and fixedly attached to opposite sides of the engine core, and two alignment fittings fixed to the engine fan module. The method of using the GSE may comprise lifting the engine core vertically using the lifting components and anchoring the suspension rails to the alignment fittings. The translating rails and engine core may then be translated in an aft-to-forward direction such that portions of the translating rails engage portions of the alignment fittings to cooperatively guide the translating rails into a final forward position in which the engine core is aligned relative to the engine fan module.

An actuated braking and distance sensing system for operational regulation of belt loader equipment and/or other applicable ground support equipment, wherein the present invention incorporates, among other embodiments, spring-responsive actuated emergency braking and distance sensing systems, emergency braking and distance sensing systems implemented via linear variable displacement transducers, and/or emergency braking and distance sensing systems actuated via sonar, lasers and/or infrared sensors. Structural incorporation of the afore-referenced emergency braking and distance sensing systems within airline ground support equipment, particularly belt loader equipment, seeks to effectively reduce accidental collision of such ground support equipment with parked aircraft.

An airplane ground support system includes a multi-voltage power supply. A control system within the power conversion module receives measurements to regulate the power module's output to a predetermined preset voltage level as mandated by the power output selection signal. In an alternate embodiment a multi-voltage or upgradable power supply has A.C. and D.C. capability, A.C. only capability with an upgrade kit available to add D.C. capability in addition to the A.C. capability, D.C. only capability with an upgrade kit available to add A.C. capability in addition to the D.C. capability.

Air filtration devices and systems are provided to filter conditioned air after air exits an air conditioner module located on a ground support equipment unit but prior to entering a grounded aircraft. Disclosed embodiments include a system with the air filtration unit located along a hose originating from an aircraft ground support unit and a system with the air filtration unit located along a hose originating from an aircraft. Certain embodiments of the air filtration unit include a diffuser, which is configured to couple to a filter and direct air through the filter during operation.

The invention discloses an air defense training target system, which includes: a ground control subsystem: used to plan the target system tasks for tasks including training, exercises, and weapon verification, and execute related tasks according to the plan; wherein, in the task During execution, the ground control subsystem performs real-time measurement and control of the controlled target drone and can change tasks in real time; a single ground control subsystem realizes measurement and control of multiple target drones, and multiple ground control subsystems are networked to realize Target drone cluster measurement and control; target drone flight platform subsystem; airborne mission equipment subsystem; ground support equipment subsystem; damage effect assessment and battlefield situation awareness subsystem: used to reflect real-time mission execution effect information. The invention adopts high technology, realizes high reliability, high versatility, and high applicability, is a serialized air defense training system with simple operation and maintenance, low requirements for control personnel, and strong scalability.

The invention relates to a generalization flight parameter recording system, which comprises a flight parameter gatherer 1, a flight parameter recorder 2, a cache recorder 3, a cockpit voice sensor 4, a download socket 5, an identification cable 6, a standard signal source 7, a new signal source 8, an internal conversation signal 9 and ground support equipment 10. According to the invention, maintenance efficiency and attendance guarantee rate are increased, the flight parameter ground equipment is uniform, and management is convenient. The operation of software is simple, interface is friendly and easy to grasp, and user usage is convenient. The generalization flight parameter recording system is adapted to requirement of future latent clients, and can avoid the cost of novel product development, and airplane refit cost can be reduced.

The invention discloses a multi-stage rocket transportation erecting vehicle, and belongs to the technical field of spaceflight ground support equipment. The support vehicle comprises a transport vehicle, a support adjusting system, an erecting arm assembly, a main erecting oil cylinder, a support seat and a lifting system, one end of the erecting arm assembly is hinged to the tail of the transport vehicle, and an auxiliary supporting arm is arranged at the bottom of the other end of the erecting arm. The main erecting oil cylinder is arranged on the inner side of the erecting arm assembly; the supporting and adjusting system is installed on the erecting arm assembly and has the functions of supporting, locking and four-degree-of-freedom adjusting of the multiple stages of rocket bodies, and butt joint between the multiple stages of rocket bodies and between the rocket bodies and the supporting base is achieved. The supporting seat is connected to the tail part of the erecting arm assembly, so that the perpendicularity of the erected rocket body can be adjusted, and support can be provided; the lifting system is installed on the erecting arm and can send an operator to the front binding point and the rear binding point of the rocket to achieve rocket connection. The erecting vehicle can achieve transportation and transfer of rockets, the rockets are erected as a whole after arriving at a launching area, and erecting work before launching is completed rapidly.

The present invention is a variable geometry aircraft that is capable of morphing its shape from a symmetric cross-section buoyant craft to an asymmetric lifting body and even to a symmetric zero lift configuration. The basic structure is a semi rigid airship with movable longerons. Movement of the longerons adjusts the camber of the upper and/or lower surfaces to achieve varying shapes of the lifting-body. This transformation changes both the lift and drag characteristics of the craft to alter the flight characteristics. The transformation may be accomplished while the craft is airborne and does not require any ground support equipment.

The present invention is a variable geometry lighter-than-air (LTA) aircraft that is adapted to morph its shape from a symmetric cross-section buoyant craft to an asymmetric lifting body and even to a symmetric zero lift configuration. The basic structure is a semi rigid airship with movable longerons. Movement of the longerons adjusts the camber of the upper and/or lower surfaces to achieve varying shapes of the lifting-body. This transformation changes both the lift and drag characteristics of the craft to alter the flight characteristics. The transformation may be accomplished while the craft is airborne and does not require any ground support equipment.

An air delivery hose assembly for use with aircraft ground support equipment provides conditioned air to an on-ground aircraft. The hose assembly includes an impermeable inner liner which forms an air conduit, a stress layer comprising a web of cord material which surrounds the inner liner, and an insulating layer which surrounds the inner liner and the stress layer to thermally insulate air passing through the air hose. The stress layer prevents air pressure in the conduit from expanding the inner liner and compressing the insulating layer, and thereby reducing the effectiveness of the insulating layer.