A first panel member constituting the outer wall facing the outside of the vehicle, a vehicle body structure having a second panel member. Here, the second panel member, as the space portion is formed between the first panel member, located on the vehicle inside than the first panel member, when the hole in the first panel member is opened, the first panel member by pressure in the vehicle in contact with the member, it is configured to close the hole.

A first panel member constituting the outer wall facing the outside of the vehicle, a vehicle body structure having a second panel member. Here, the second panel member, as the space portion is formed between the first panel member, located on the vehicle inside than the first panel member, when the hole in the first panel member is opened, the first panel member by pressure in the vehicle in contact with the member, it is configured to close the hole.

Space vehicles configured with a micrometeoroid and orbital debris (MMOD) protection system are described herein. The MMOD protection system can include (a) a front face sheet and a rear face sheet spaced apart from the front face sheet directed outwardly, and the rear face sheet being positioned to attach to the space launch vehicle; (b) at least one absorption core layer and at least one impact resistant fabric layer positioned between the front face sheet and the rear face sheet; and (c) an expandable adhesive layer carried by the rear face sheet to attach the MMOD protection system to the space launch vehicle. The front face sheet and the rear face sheet can comprise a metal matrix composite. The MMOD protection system can protect the space vehicle from damage in space, while withstanding launch loads, and can accordingly eliminate the need for a protective launch fairing.

Space vehicles configured with a micrometeoroid and orbital debris (MMOD) protection system are described herein. The MMOD protection system can include (a) a front face sheet and a rear face sheet spaced apart from the front face sheet directed outwardly, and the rear face sheet being positioned to attach to the space launch vehicle; (b) at least one absorption core layer and at least one impact resistant fabric layer positioned between the front face sheet and the rear face sheet; and (c) an expandable adhesive layer carried by the rear face sheet to attach the MMOD protection system to the space launch vehicle. The front face sheet and the rear face sheet can comprise a metal matrix composite. The MMOD protection system can protect the space vehicle from damage in space, while withstanding launch loads, and can accordingly eliminate the need for a protective launch fairing.

An electrode performance evaluation system and an electrode performance evaluation method is disclosed. The method includes acquiring impedance measurement data for different frequencies by applying an alternating current signal to an electrode assembly including an electrode which is immersed in an electrolyte solution, calculating impedance calculation data for different frequencies while changing the frequency of an impedance equation corresponding to a circuit model of the electrode assembly, calculating the resistance value of ion bulk resistance in the electrolyte solution using the ion conductivity of the electrolyte solution, the area of the electrode and the thickness and porosity of an active material layer of the electrode, and determining effective tortuosity as a factor of the electrode performance based on the impedance measurement data for different frequencies, the impedance calculation data for different frequencies and the resistance value of the ion bulk resistance.

An electrode performance evaluation system and an electrode performance evaluation method is disclosed. The method includes acquiring impedance measurement data for different frequencies by applying an alternating current signal to an electrode assembly including an electrode which is immersed in an electrolyte solution, calculating impedance calculation data for different frequencies while changing the frequency of an impedance equation corresponding to a circuit model of the electrode assembly, calculating the resistance value of ion bulk resistance in the electrolyte solution using the ion conductivity of the electrolyte solution, the area of the electrode and the thickness and porosity of an active material layer of the electrode, and determining effective tortuosity as a factor of the electrode performance based on the impedance measurement data for different frequencies, the impedance calculation data for different frequencies and the resistance value of the ion bulk resistance.

A moon/planet complex, an orbiting docking spaceport, and transportation vehicles therebetween that includes i) moon/planet base station having a landing platform with a plurality of charged plates; ii) a moon/planet orbiting craft, docking spacecraft having landing platform with a plurality of charged plates; iii) a personnel transport spacecraft to shuttle personnel between an orbiting craft and planetary/moon base station having rotating electromagnetic rings 320 and/or rotating electromagnetic plates to interact with charged plates; iv) a large personnel/cargo transport spacecraft to shuttle personnel between an orbiting craft and planetary base station having rotating electromagnetic plates to interact with charged plates.

Various embodiments provide multi-layered self-healing materials, capable of repairing puncture damage. The multi-layered self-healing materials, capable of repairing puncture damage of the various embodiments may be constructed by sandwiching a reactive (e.g., oxygen sensitive) liquid monomer formulation between two solid polymer panels, such as a polymer panel of Barex 210 IN (PBG) serving as the front layer panel and a polymer panel of Surlyn® 8940 serving as the back layer panel. The various embodiments may provide methods to produce multi-layered healing polymer systems. The various embodiments may provide a two-tier, self-healing material system that provides a non-intrusive capability to mitigate mid to high velocity impact damage in structures.

Various embodiments provide multi-layered self-healing materials, capable of repairing puncture damage. The multi-layered self-healing materials, capable of repairing puncture damage of the various embodiments may be constructed by sandwiching a reactive (e.g., oxygen sensitive) liquid monomer formulation between two solid polymer panels, such as a polymer panel of Barex 210 IN (PBG) serving as the front layer panel and a polymer panel of Surlyn® 8940 serving as the back layer panel. The various embodiments may provide methods to produce multi-layered healing polymer systems. The various embodiments may provide a two-tier, self-healing material system that provides a non-intrusive capability to mitigate mid to high velocity impact damage in structures.

A multilayer particle shield for a spacecraft includes an inboard exterior layer configured to be disposed proximal to the spacecraft, an outboard exterior layer configured to be disposed distal from the spacecraft and at least one interior layer disposed between the inboard exterior layer and the outboard exterior layer, wherein the interior layer includes a semi-rigid, porous, compressible spacer.