Disclosed is a micrometeoroid and debris protection system (MDPS) for a thermal control system on a spacecraft. The MDPS comprises a radiator face-sheet, a truss attached to the radiator face-sheet, and a thermally transparent bumper disposed on the truss. The thermally transparent bumper shields the radiator face-sheet from micrometeoroids and debris and enables thermal transfer from the radiator face-sheet through the thermally transparent bumper.

A near space aircraft pod, including a pod body and a covering piece, where a heat dissipation part is disposed on the pod body for dissipating heat inside the pod body; and the covering piece is connected to the outside of the pod body in a movable manner, for covering the heat dissipation part or keeping a pre-designed distance from the heat dissipation part. According to the near space aircraft pod provided in the embodiments, the covering piece can adjust a distance from the heat dissipation part in time or cover the heat dissipation part based on a temperature change. Therefore, a heat dissipation speed of the pod can be effectively controlled, so that temperature inside the pod is kept in a proper range, and it is ensured that electronic devices in the pod operate under a good temperature environment.

The present invention is directed to a phosphated epoxy resin comprising at least one terminal group comprising a phosphorous atom covalently bonded to the re sin by a carbon-phosphorous bond or by a phosphoester linkage; and at least one carbamate functional group. The present invention is also directed towards aqueous resinous dispersions comprising the phosphated epoxy resin, methods of coating a substrate, coated substrates, and methods of making a phosphated epoxy resin.

A solid-state thermochromic device and method for producing the device, the device including: a stack successively including, from a rear face to a front face exposed to solar radiation: a) a solid substrate of an inorganic material resistant up to a temperature of 550° C.; b) an infrared-reflective layer of an electronically conductive material; c) electronically insulating interface layers; d) an electronically insulating inorganic dielectric layer transparent to infrared radiation, of cerium oxide CeO2, with a thickness between 400 and 900 nm; e) electronically insulating interface layers; f) a layer of an infrared-active thermochromic material, an n-doped VO.sub.2 vanadium oxide, and crystallized in a monoclinic or rutile phase, with a thickness between 30 and 50 nm; and g) a solar-protective coating, transparent to infrared radiation.

A payload module (1) of a stratospheric drone including: a casing (10), and a piece of optical equipment (20) comprising an optical axis, mounted in the casing, wherein the module being includes a mirror (40) positioned on the optical axis facing the optical equipment, the mirror being swivelable about at least one axis, within an angular range, wherein the casing has a through-opening (11) shaped so that any light ray received or emitted by the optical equipment parallel to the optical axis and reflected by the mirror passes through the through-opening, over the entire angular range of the mirror.

A protective assembly comprises a first region formulated and configured to provide protection from alpha, beta, and electromagnetic radiation and comprising a composite of particles and polymer; a second region formulated and configured to provide protection from ballistic impact and comprising a composite of fibers and polymer; and a third region formulated and configured to provide protection from thermal radiation and comprising a composite of particles, fiber, and polymer. The protective assembly may be provided on an aerospace structure. The protective assembly may be formed on the aerospace structure body using a co-curing process.

Various systems and methods of a layered tile insulation system of a space vehicle, configured to withstand vibration, high temperatures, and extreme thermal gradients, are disclosed. The layered tile insulation system can include at least one layered tile, each of the at least one layered tile including an outer layer having a first interlocking surface with a first set of interlocking features and an inner layer having a second interlocking surface with a second set of interlocking features, such that the outer layer is configured to be couple to the inner layer thereby forming a mechanical joint via the interlocking of the first interlocking surface with the second interlocking surface.

Chemically resistant sealant compositions include high equivalent weight sulfur-containing prepolymers. Upon exposure to chemicals the properties of sealants prepared using the prepolymers exhibit excellent fuel and phosphate ester resistance.

The present invention is directed to a phosphated epoxy resin comprising at least one terminal group comprising a phosphorous atom covalently bonded to the resin by a carbon-phosphorous bond or by a phosphoester linkage; and at least one carbamate functional group. The present invention is also directed towards aqueous resinous dispersions comprising the phosphated epoxy resin, methods of coating a substrate, coated substrates, and methods of making a phosphated epoxy resin.

A spacecraft, for example a satellite, or a part thereof having a coating comprising a 2D material on an outer surface thereof is described. The 2D material comprises one or more elements, excluding C, N and S, in an amount of at least 50 at. %; and respective oxides of the one or more elements of the 2D material have a vapour pressure of at most 10 Pa at a temperature of 323 K.