Abstract: An aerodynamic brake includes a rigid panel having a panel leading edge portion and a panel trailing edge portion. The aerodynamic brake also includes a flexible sheet having a sheet lower edge portion coupled to the vehicle body, and a sheet upper edge portion coupled to the panel leading edge portion. The aerodynamic brake further includes a panel actuator configured to move the rigid panel between a stowed position and a deployed position. In the stowed position, the rigid panel is located proximate the vehicle body and covers the flexible sheet in a folded state. In the deployed position, the panel leading edge portion is moved away from the vehicle body and the flexible sheet is in an open state exposable to an oncoming airflow for generating aerodynamic drag for slowing the vehicle.

Abstract: An aerodynamic brake includes a rigid panel having a panel leading edge portion and a panel trailing edge portion. The aerodynamic brake also includes a flexible sheet having a sheet lower edge portion coupled to the vehicle body, and a sheet upper edge portion coupled to the panel leading edge portion. The aerodynamic brake further includes a panel actuator configured to move the rigid panel between a stowed position and a deployed position. In the stowed position, the rigid panel is located proximate the vehicle body and covers the flexible sheet in a folded state. In the deployed position, the panel leading edge portion is moved away from the vehicle body and the flexible sheet is in an open state exposable to an oncoming airflow for generating aerodynamic drag for slowing the vehicle.

Abstract: An aerodynamic brake includes a rigid panel having a panel leading edge portion and a panel trailing edge portion. The panel trailing edge portion is pivotably coupled to a vehicle body. The aerodynamic brake also includes a flexible sheet having a sheet lower edge portion coupled to the vehicle body, and a sheet upper edge portion coupled to the panel leading edge portion. The aerodynamic brake further includes a panel actuator configured to pivot the rigid panel between a stowed position and a deployed position. In the stowed position, the rigid panel is located proximate the vehicle body and covers the flexible sheet in a folded state. In the deployed position, the panel leading edge portion is pivoted away from the vehicle body and the flexible sheet is in an open state exposable to an oncoming airflow for generating aerodynamic drag for slowing the vehicle.

Abstract: Various techniques provide a heat shield assembly and mounting thereof on an aircraft. In one example, a heat shield assembly may include flexible member. The heat shield assembly may further include a plurality of frame members disposed on the flexible member. The heat shield assembly may further include a plurality of mounting structures configured to directly mount the heat shield assembly to a strut of an airplane. Each of the plurality of mounting structures may be disposed on one of the plurality of frame members. Related methods are also provided.

Abstract: An aerodynamic brake includes a rigid panel having a panel leading edge portion and a panel trailing edge portion. The panel trailing edge portion is pivotably coupled to a vehicle body. The aerodynamic brake also includes a flexible sheet having a sheet lower edge portion coupled to the vehicle body, and a sheet upper edge portion coupled to the panel leading edge portion. The aerodynamic brake further includes a panel actuator configured to pivot the rigid panel between a stowed position and a deployed position. In the stowed position, the rigid panel is located proximate the vehicle body and covers the flexible sheet in a folded state. In the deployed position, the panel leading edge portion is pivoted away from the vehicle body and the flexible sheet is in an open state exposable to an oncoming airflow for generating aerodynamic drag for slowing the vehicle.

Abstract: A system includes a signal generator that is configured to generate a first electrical signal. The system also includes a light source configured to generate a light beam based on the first electrical signal. The light source is also configured to direct the light beam towards a structural member of an aircraft. The system also includes a photoelectric sensor configured to receive a reflected light beam and convert the reflected light beam to a second electrical signal. The reflected light beam corresponds to a portion of the light beam that is reflected from one or more optical reflectors coupled to the structural member. The system also includes circuitry configured to estimate a location of a center-of-gravity of the aircraft based on a timing difference between the first electrical signal and the second electrical signal.

Abstract: Various techniques provide a heat shield assembly and mounting thereof on an aircraft. In one example, a heat shield assembly may include flexible member. The heat shield assembly may further include a plurality of frame members disposed on the flexible member. The heat shield assembly may further include a plurality of mounting structures configured to directly mount the heat shield assembly to a strut of an airplane. Each of the plurality of mounting structures may be disposed on one of the plurality of frame members. Related methods are also provided.

Abstract: A system includes a signal generator that is configured to generate a first electrical signal. The system also includes a light source configured to generate a light beam based on the first electrical signal. The light source is also configured to direct the light beam towards a structural member of an aircraft. The system also includes a photoelectric sensor configured to receive a reflected light beam and convert the reflected light beam to a second electrical signal. The reflected light beam corresponds to a portion of the light beam that is reflected from one or more optical reflectors coupled to the structural member. The system also includes circuitry configured to estimate a location of a center-of-gravity of the aircraft based on a timing difference between the first electrical signal and the second electrical signal.

Abstract: Provided are aircraft for transporting intermodal containers and methods of operating such aircraft including methods of loading and unloading the containers. An aircraft includes a fuselage having a cargo space for receiving and supporting intermodal containers. The containers are oriented in the transverse direction in the cargo space or, more specifically, in a direction normal to the longitude direction that extends from the nose to the tail of the aircraft. The aircraft may transport standard 20-foot or 40-foot containers or lighter version of such containers that otherwise have the same form and features as the standard intermodal containers. The intermodal containers may be loaded through an opening in the bottom of the fuselage. Specifically, intermodal containers may be arranged into a row. The aircraft may be then rolled over this row of the containers and lowered onto the containers followed by engaging container corners.

Abstract: Provided are aircraft for transporting intermodal containers and methods of operating such aircraft including methods of loading and unloading the containers. An aircraft includes a fuselage having a cargo space for receiving and supporting intermodal containers. The containers are oriented in the transverse direction in the cargo space or, more specifically, in a direction normal to the longitude direction that extends from the nose to the tail of the aircraft. The aircraft may transport standard 20-foot or 40-foot containers or lighter version of such containers that otherwise have the same form and features as the standard intermodal containers. The intermodal containers may be loaded through an opening in the bottom of the fuselage. Specifically, intermodal containers may be arranged into a row. The aircraft may be then rolled over this row of the containers and lowered onto the containers followed by engaging container corners.

Abstract: An aircraft cabin has been reconfigured with a rear fuselage galley and a modified aft pressure bulkhead that enables the galley to be moved rearwardly to provide additional floor space in the aircraft cabin.

Abstract: An aircraft cabin has been reconfigured with a rear fuselage galley and a modified aft pressure bulkhead that enables the galley to be moved rearwardly to provide additional floor space in the aircraft cabin.

Abstract: Provided are aircraft for transporting intermodal containers and methods of operating such aircraft including methods of loading and unloading the containers. An aircraft includes a fuselage having a cargo space for receiving and supporting intermodal containers. The containers are oriented in the transverse direction in the cargo space or, more specifically, in a direction normal to the longitude direction that extends from the nose to the tail of the aircraft. The aircraft may transport standard 20-foot or 40-foot containers or lighter version of such containers that otherwise have the same form and features as the standard intermodal containers. The intermodal containers may be loaded through an opening in the bottom of the fuselage. Specifically, intermodal containers may be arranged into a row. The aircraft may be then rolled over this row of the containers and lowered onto the containers followed by engaging container corners.

Abstract: An aircraft cabin has been reconfigured with a rear fuselage galley and a modified aft pressure bulkhead that enables the galley to be moved rearwardly to provide additional floor space in the aircraft cabin.

Abstract: An aircraft passenger cabin in an aircraft fuselage wherein an upper portion of the cabin volume is a substantially elliptical cross section and a lower portion of the cabin volume is a cross section extending laterally into a blended area of the wing and fuselage typically referred to as a wing to body fairing.

Abstract: An aircraft passenger cabin in an aircraft fuselage wherein an upper portion of the cabin volume is a substantially elliptical cross section and a lower portion of the cabin volume is a cross section extending laterally into a blended area of the wing and fuselage typically referred to as a wing to body fairing.

Abstract: A first mixer trailer forms the plant frame foundation around a twelve-yard compulsory mixer. The compulsory mixer is mounted for elevation relative to plant frame foundation by hydraulic lifting columns. In system erection, a cement silo trailer is first mounted to the top of the compulsory mixer when the compulsory mixer is at ground level. Thereafter, both the mounted silo and the compulsory mixer are raised and pinned in place by the hydraulic lifting columns so that gravitational discharge of mixed concrete can occur directly from the compulsory mixer to an underlying transporting apparatus, usually a truck.

Abstract: A first mixer trailer forms the plant frame foundation around a twelve-yard compulsory mixer. The compulsory mixer is mounted for elevation relative to plant frame foundation by hydraulic lifting columns. In system erection, a cement silo trailer is first mounted to the top of the compulsory mixer when the compulsory mixer is at ground level. Thereafter, both the mounted silo and the compulsory mixer are raised and pinned in place by the hydraulic lifting columns so that gravitational discharge of mixed concrete can occur directly from the compulsory mixer to an underlying transporting apparatus, usually a truck.

Abstract: A four trailer portable concrete batching and mixing plant has production volumes of up to 600 cubic yards of concrete per hour of paving concrete meeting exacting modem paving standards. A first mixer trailer with a mounted water tank forms the plant frame foundation at a twelve-yard compulsory mixer. A second silo trailer having 900 barrel capacity has cantilever support from a steered towing wheel set at the bottom of the silo. The silo trailer is backed at the steered towing wheel set to the side of the compulsory mixer trailer and pinned at its cantilevered connection for pivotal erection. Once pinned to the side of the compulsory mixer trailer, a silo trailer contained jacking system self erects the silo utilizing the compulsory mixer and trailer as a foundation. With the silo erected, a third aggregate trailer occupies the footprint vacated by the erected silo.

Abstract: A portable concrete plant capable of producing up to 240 to 300 cubic yards or more of concrete per hour is disclosed in which two hauling trailers, a mixer trailer and an aggregate trailer, both serve as the transport vehicles and as foundation for the completely erected plant. The aggregate trailer includes three bins used respectively for sand, fine aggregate and course aggregate. Weigh belts convey weighed and humidity measured amounts of sand and aggregate from discrete open top bins to a batch aggregate loading belt for batch loading of a compulsory mixer on the mixer trailer. The side of the aggregate trailer is provided with a bulkhead for an earthen or gravel ramp with large width bins enabling a single loader to supply the high volume of sand and aggregate required. The mixer trailer supports a twin shaft compulsory mixer on a foundation pad which is top loading for concrete constituents and bottom emptying to an elevating and concrete discharge point to awaiting trucks.