Mcdonnell Douglas Corporation

The Uab Research Foundation (the University of Alabama at Birmingham)

The Boeing Company

United States of America as Represented by the Secretary of the Air Force

James Bertram Blackmon

Nelson Edwin Jones

Frederick Scott Gant

Robert E Drubka

David Lee Dean

R Andrew Gerrick

Kenneth W Stone

John Stephen Kirby

David Brian Landrum

Edwin C Cady

Sean Entrekin

Don Edwards

Gary Glover

Brian Seaworth

Thomas Ingersoll

Dave Johnson

A coupling system can include an energy transfer device and a load mitigation system. The energy transfer device can include a shaft, gear, chain or piston-cylinder arrangement to transfer the energy from a power supply to an object to be moved. The load mitigation system can be used to limit or prevent the transfer of forces from the object to the drive unit as a result of external loads being applied to the object. The load mitigation system can be pre-loaded such that external loads on the object having an excessive impulsive or resonant cyclic force greater than the pre-load force on the load mitigation system are reduced and only partially transferred to the energy transfer device and power supply. The load mitigation system can dampen both resonant loads and impulsive impact loads occurring at the object thereby preventing damage and extending life.

Coupling system for reducing fatigue and dynamic amplification of loads in objects

The present disclosure generally pertains to devices and methods for determining propellant mass based on average measurements irrespective of the fluid orientation in a fuel tank. The device is useful in detecting fuel levels in tanks where the fuel is in motion, for instance in aircraft (i.e., undergoing varying acceleration maneuvers) or spacecraft (i.e., a microgravity environment). The devices and methods can also be used for determining the liquid in a surface tension screen liquid acquisition device (LAD), and particularly, the incipient breakdown as gas bubbles enter or are formed inside the LAD as the screen dries or heat transfer induces vaporization. The same basic electrode configuration can be used to stir the liquid to reduce thermal stratification and condense vapor bubbles.

Apparatus and method for determination of liquid mass

The present disclosure generally pertains to rocket based combined cycle (RBCC) propulsion units. In one exemplary embodiment, at least one rocket thruster is integrated with a jet engine but is external to the flow path of the jet engine, forming an altitude compensating plug nozzle. Since the rocket thruster is external to such flow path, the rocket flow from the rocket thruster interacts with the jet flow from the jet engine aft of the nozzle of the jet engine. Such interaction occurs without a significant performance penalty in the operation of the jet engine. In fact, it is possible that the interaction of the rocket flow with the jet flow may actually improve the efficiency of the jet engine under some conditions. Moreover, having the rocket thrusters positioned external to the flow path of the jet engine helps to avoid many of the problems plaguing conventional RBCC propulsion units.

Rocket based combined cycle propulsion unit having external rocket thrusters

A glass structure, such as a mirror facet, having a glass member, a composite structure and a support structure. The composite structure includes a rigid interlayer which is bonded to the glass member and exerts a compressive force thereon to place the glass member in compression. The support structure is used to mount the glass structure and prevents the glass member from collapsing due to the compressive force exerted by the rigid interlayer. The glass structure is particularly well adapted for use in forming heliostats, parabolic dishes, trough concentrators, or other like elements for use in solar power systems, and does not suffer from the limitations or prior forms of such devices.

Composite backed prestressed mirror for solar facet

A geodome tower reflector for a beam down optics solar power system has three equidistantly spaced tower assemblies. A geodome reflector assembly is movably mounted to the plurality of tower assemblies for vertical movement along the plurality of tower assemblies. The geodome reflector assembly has a facet support structure. The facet support has a plurality of rigid frames to which facets are mounted. Each facet has a downwardly facing mirror for reflecting light from a heliostat to a receiver of the beam down optics solar power system.

Geometric dome stowable tower reflector

An azimuth drive unit for a solar power system has a multistage sprocket configuration. The drive unit includes an input shaft for receiving an input torque, where the multistage sprocket configuration is coupled to the input shaft. The sprocket configuration converts the input torque into an output torque, and an output shaft is coupled to the sprocket configuration for applying the output torque to a solar reflector. In a highly preferred embodiment, the sprocket configuration includes a tensioning system contacting one or more of the chains and a housing of the drive unit. The tensioning system applies a tension force to the contacted chains such that backlash in the sprocket configuration is reduced. The present invention also provides for a plurality of bearing members coupled to the output shaft for adding stiffness to the output shaft. The use of a multistage sprocket configuration eliminates destructive backlash forces, dampens shock, prevents reflector oscillations, and provides redundancy while reducing the overall cost of the drive unit.

Solar power system drive unit

Radiant energy sensor is protected from severe environments with a radiant energy sensor assembly that off-sets the sensor from the environment. The sensor assembly includes a radiant energy sensor, a pair of reflective walls facing one another, one of the walls having a transmissive aperture for receiving radiant energy over a wide angle of incidence, an entry, the other wall having a transmissive aperture for passing energy from behind the wall to the sensor, an exit, with the walls having the reflection characteristics such that the radiant energy entering the entry aperture at any angle is always reflected to the exit aperture. The reflective walls may be paraboloids or Fresnel surfaces in geometry.

Sensor assembly with dual reflectors to offset sensor

A fluid ejection nozzle is disclosed which facilitates a wide distribution of fluid therefrom and which permits the fluid flow rate to be easily adjustable. The nozzle is particularly adapted to a heat rejection system useful in a space environment. The nozzle includes a flow distributor positioned within an orifice of the nozzle housing which is comprised of a tongue member and an attached flow control block. Adjustment screws mounted through the nozzle housing permit axial movement of the flow distributor within the housing, thus controlling the flow rate of the fluid even to the extent of total shut-off. The tongue member is shaped to widely disperse the fluid, and includes turbulence generators such as roughening or ridges for facilitating its dispersion.

Turbulent droplet generator with boom mounted pitot pump collector

A photovoltaic electric power system for use in space. A self contained sun powered electric power generating system comprising a fresnel mirror array made up of a plurality of quadrilateral mirrors individually mounted on a generally flat supporting structure with the mirrors aimed at a common point above the structure, a photovoltaic array positioned at the common point by a movable strut mechanism, heat exchanger means at the PV array to draw excess heat therefrom, coolant lines from the heat exchanger means running through the struts to transfer heat to heat pipes configured as flat panels at the edges of and perpendicular to the supporting structure, and positioning means attached to a separate structure to enable the system to track the sun. The system is designed to fold into itself in the form of an elongate box for launch, maneuvering and protection.

Advanced survivable space solar power system

A heat pipe radiator coating of a fibrous material provides protection for the radiator, such as a heat pipe, pumped loop, etc., while allowing good emissivity and heat rejection. Fibers are constructed from fiberglass, glass, quartz, saphire, diamond, carbon carbon, tantalum, stainless steel, aluminum, beryllium, and copper, and may be coated with a variety of metallic materials.

Growing community of inventors

Brownsboro, AL, United States of America

James Bertram Blackmon