Disclosed herein are articles comprising: (a) a glass micro sheet having top and bottom surfaces and a thickness of about 0.001 to about 0.040 inches; and (b) a layer comprising a plurality of composite layers, the layer having top and bottom surfaces, wherein the bottom layer of the glass micro sheet is bonded to the top surface of the layer comprising a plurality of composite layers; and wherein the (Ra) of the top surface of the glass micro sheet is 1 nm<Ra<1 μm, and methods of making same.

Disclosed herein are articles comprising: (a) a glass micro sheet having top and bottom surfaces and a thickness of about 0.001 to about 0.040 inches; and (b) a layer comprising a plurality of composite layers, the layer having top and bottom surfaces, wherein the bottom layer of the glass micro sheet is bonded to the top surface of the layer comprising a plurality of composite layers; and wherein the (Ra) of the top surface of the glass micro sheet is 1 nm<Ra<1 μm, and methods of making same.

A radiator system uses an innovative passive control scheme in combination with dependable mechanical design features to meet or exceed the requirements for orbital applications. The disclosed radiator system is unique because we target an extremely high turndown ratio of 200:1 with an entirely passive two-phase pumped loop using ammonia as the working fluid. Sections of the radiator will selectively freeze to assist the turndown, and the mechanical design of the radiator can handle the high pressures experienced during such freezing and thawing events.

A radiator system uses an innovative passive control scheme in combination with dependable mechanical design features to meet or exceed the requirements for orbital applications. The disclosed radiator system is unique because we target an extremely high turndown ratio of 200:1 with an entirely passive two-phase pumped loop using ammonia as the working fluid. Sections of the radiator will selectively freeze to assist the turndown, and the mechanical design of the radiator can handle the high pressures experienced during such freezing and thawing events.

A spacecraft is disclosed having at least three flat side walls, at least one main communication antenna, including a radiating element having a central axis of radiation (AC-AC), a movable arm configured to move between a deployed position and a folded position, a reflector suitable for reflecting or receiving radiofrequency waves in a direction of emission (DE). The radiating element is fixed to a side wall so that the central axis of radiation (AC-AC) is arranged perpendicularly to the side wall, and the movable arm is shaped so that an offset angle (β) of between 25° and 65° is formed between the side wall and the direction of emission (DE), when the movable arm is in a deployed position.

A solar sail includes a bus and a plurality of separate movable vanes coupled to the bus. Each movable vane includes a reflective surface for generating solar radiation pressure and propel the solar sail in space. Each vane may be movable relative to the bus in a fully deployed configuration such that an amount of thrust generated by solar radiation pressure on each vane is controllable.

A solar sail includes a bus and a plurality of separate movable vanes coupled to the bus. Each movable vane includes a reflective surface for generating solar radiation pressure and propel the solar sail in space. Each vane may be movable relative to the bus in a fully deployed configuration such that an amount of thrust generated by solar radiation pressure on each vane is controllable.

Protective blankets comprise a flexible blanket body and a voltage supply. The flexible blanket body comprises a plurality of sheets of material operatively coupled together to define the flexible blanket body. The plurality of sheets comprises one or more sheets composed at least in part of a carbon nanotube material and at least one sheet composed of a different material. The voltage supply is electrically coupled at least to a first sheet of the one or more sheets composed at least in part of the carbon nanotube material, such that the first sheet defines a resistive heater.

An insert for a condensing heat exchanger, having: a body extending aft from a forward end to an aft end, and defining: a body exterior surface; a forward segment that extends aft from the forward end of the insert to a first axial location between the forward and aft ends of the insert, along the forward segment the body exterior surface is without openings; a middle segment that extends aft from the first axial location to a second axial location, along the middle segment the body exterior surface is cylindrical; and an aft segment that extends aft from the second axial location to the aft end of the insert, along the aft segment the body exterior surface of the body is cylindrical and defines axially extending grooves, and the grooves are spaced apart from each other and extend forward from the aft end of the insert to the middle segment.

A device for protecting a body from damage The protective device comprises an outer protective cover, the outer protective cover comprising a thermal energy conduction element for transferring thermal energy through at least part of the outer protective cover and an inner assembly located adjacent the outer protective cover, the inner assembly comprising a thermal energy transfer device adapted to transfer thermal energy to and/or from the thermal energy conduction element. The thermal conduction element comprises a graphite-like or pyrolytic graphite-like material and the thermal energy transfer device comprises a thermal energy transfer fluid.