An interlocking paver system including a polygon paver and a spacer paver is provided. The polygon paver may have a top level having a top level polygon paver perimeter and a bottom level secured to and protruding from the top level and having a bottom level polygon paver perimeter contained within the top level polygon paver perimeter. The spacer paver may have a top level having a top level spacer paver perimeter and a bottom level secured to and protruding from the top level and having a bottom level spacer paver perimeter extending beyond an entirety of the top level spacer paver perimeter. The spacer paver may be configured to selectively interlock with the polygon paver. The top level spacer paver perimeter, top level polygon paver perimeter, and bottom level spacer paver perimeter are different from one another.

A vertiport for an aircraft. The vertiport includes a landing platform that includes a landing surface and a plurality of primary through-openings, wherein the landing platform at least partially defines a primary chamber subjacent to the landing platform, the primary chambering having a primary chamber volume, and wherein the plurality of primary through-openings are in fluid communication with the primary chamber. The disclosed vertiport further includes an air moving unit positioned to withdraw air from the primary chamber.

A modular roadway structure that includes a body portion including a bottom surface and a top surface. The bottom surface is configured to be positioned on a surface, and the top surface is formed with a predetermined textured pattern for defining a predetermined coefficient of friction across the top surface.

A modular landing port for use on a top of a building structure. The modular landing port includes a base portion. One or more landing module extend from the base portion. The one or more landing modules have a first end provide proximate the base portion and a second end spaced from the base portion. Each of the one or more landing modules have a landing/take-off zone proximate the second end and at least one loading/unloading zone proximate the first end. The landing/take-off zone and the at least one loading/unloading zone are configured to receive a vertical take-off and landing aircraft.

A first construction module for a modular landing platform is for vertical landing aircraft. The module includes a module body with a resting wall placed on a supporting surface. A landing wall opposite to the resting wall is adapted be contacted by the aircraft during the landing step. First and second interconnecting walls are opposite to each other and interposed between the resting wall and the landing wall. First and second coupling portions protrude laterally outwards from the first interconnecting wall, the first and second coupling portions being of a different type and mutually spaced apart. Third and fourth coupling portions protrude laterally outwards from the second interconnecting wall, and are of a different type and spaced apart. The third and fourth coupling portions of the first module are adapted to couple respectively with the first and second coupling portions of a second module identical to the first module.

Described herein is a method of constructing a landing pad using a rocket engine while in-flight. Among other benefits, this method can reduce ejecta that otherwise would occur during landing on an unimproved surface. While a spacecraft is hovering over an unimproved surface, the spacecraft can inject particles into its rocket engine, after which the particles absorb heat from the engine and are projected at ballistic speeds toward the unimproved surface to create a landing pad. After constructing the landing pad and waiting for the landing pad to cool, the spacecraft can land on the landing pad. Also described herein are landing pads created from such particles as they impact the surface in a disc splat mode into the unimproved surface.

Described herein is a method of constructing a landing pad using a rocket engine while in-flight. Among other benefits, this method can reduce ejecta that otherwise would occur during landing on an unimproved surface. While a spacecraft is hovering over an unimproved surface, the spacecraft can inject particles into its rocket engine, after which the particles absorb heat from the engine and are projected at ballistic speeds toward the unimproved surface to create a landing pad. After constructing the landing pad and waiting for the landing pad to cool, the spacecraft can land on the landing pad. Also described herein are landing pads created from such particles as they impact the surface in a disc splat mode into the unimproved surface.

Described herein is a method of constructing a landing pad using a rocket engine while in-flight. Among other benefits, this method can reduce ejecta that otherwise would occur during landing on an unimproved surface. While a spacecraft is hovering over an unimproved surface, the spacecraft can inject particles into its rocket engine, after which the particles absorb heat from the engine and are projected at ballistic speeds toward the unimproved surface to create a landing pad. After constructing the landing pad and waiting for the landing pad to cool, the spacecraft can land on the landing pad. Also described herein are landing pads created from such particles as they impact the surface in a disc splat mode into the unimproved surface.

A system and associated method constructs a building material from lunar soil. A magnetic sorter magnetically sorts the lunar soil and the system creates a layered surface comprising a microwave susceptible, thermal conductive top layer of lunar soil and a poorly microwave-susceptible and poorly thermally conductive sublayer of lunar soil. A microwave generator generates microwave energy into an antenna and directs the microwave energy onto the top layer of lunar soil to sinter the microwave susceptible, thermal conductive top layer of lunar soil.

A surface assembly and related method of constructing a surface assembly are used as part of a landing platform. The surface assembly includes a modular structure having an upper surface with a plurality of discrete elements. Each discrete element has a body of metal material defining at least one anchor aperture for receiving a hook or like anchor device for anchoring a helicopter or other powered light aircraft to the surface assembly. The surface assembly is configured to define an array of the plurality of discrete elements in which at least two of the anchor apertures are provided side-by-side. The body of each discrete element has a periphery, and each anchor aperture of the array is inboard of the periphery of a respective body of a discrete element in the array.