A launch apparatus comprising a second stage and a first stage wherein said second stage comprises a second stage space frame; wherein said first stage comprises a first stage space frame; wherein said second stage space frame is approximately pyramid shaped; and wherein said first stage space frame is shaped like a truncated pyramid; and wherein the overall shape of the combined second stage space frame and first stage space frame is pyramidal.

Implementations of the disclosed subject matter may provide an adaptive thrust structure for a space launch vehicle that may include an interface block that is fluidically coupled to a fuel supply, a fuel manifold, an oxidizer supply, and an oxidizer manifold. A first adapter plate may be coupled to a first engine assembly. First adapter lines may be fluidically coupled to the first engine assembly and the interface block, via the first adapter plate. A second engine assembly, second adapter lines, and a second adapter plate are capable of replacing the first engine assembly, first adapter lines, and first adapter plate. Implementations of the disclosed subject matter may provide a reusable and reconfigurable launch vehicle that may include a reusable second stage, and a reusable and reconfigurable transporter having a plurality of zones that are configurable to transport cargo, one or more passengers, and/or one or more satellites.

A propulsion stage, in particular a reusable propulsion stage, comprising: a rocket body having a longitudinal axis; at least one recoil propulsion unit acting substantially parallel to the longitudinal axis; a plurality of rotor assemblies, each drivable by an electric rotor drive including at least one electric motor electrically connected to at least one current storage device configured to supply electrical energy to the at least one electric motor, wherein the at least one current storage device is displaceable within the propulsion stage in a direction located in a plane oriented at a right angle relative to the longitudinal axis or which has a dominant directional component which extends in the radial direction at a right angle relative to the longitudinal axis.

A recovery system for receiving rockets upon landing comprising a deceleration pool filled with liquid. The system may have a volume filled with the liquid having a desired density profile. An injection manifold injects gas into the liquid to create the density profile. The liquid may have a first density at a landing region of the pool and a second density greater than the first density away from the landing region, such as increasing in density radially outward from a center of the landing region. The pool may be located under a primary landing system intended to secure the landing rocket, such as a hook catch. The pool may be a contingency system for mitigating damage to a landing rocket that unsuccessfully attempts securing with the primary landing system.

Systems and methods for a fully reusable upper stage for a multi-stage launch vehicle are provided. The reusable upper stage uses an aerospike engine for main propulsion and for vertical landing. A heat shield can include a plurality of scarfed nozzles embedded radially around a semi-spherical surface of the heat shield, wherein inboard surfaces of the plurality of scarfed nozzles collectively define an aerospike contour. The heat shield can be actively cooled to dissipate heat encountered during reentry of the upper stage.

Systems and methods for a fully reusable upper stage for a multi-stage launch vehicle are provided. The reusable upper stage uses an aerospike engine for main propulsion and for vertical landing. A heat shield can include a plurality of scarfed nozzles embedded radially around a semi-spherical surface of the heat shield, wherein inboard surfaces of the plurality of scarfed nozzles collectively define an aerospike contour. The heat shield can be actively cooled to dissipate heat encountered during reentry of the upper stage.

An atmospheric re-entry vehicle includes a main body defining a forward end of the vehicle, a base defining an aft end of the vehicle, and a heat shield at the base. The heat shield includes a heat shield outer surface. The main body and the heat shield are configured such that a centerline of the heat shield is offset relative to a centerline of the main body. At least a portion of the heat shield outer surface is at least substantially axisymmetric relative to the centerline of the heat shield.

A recovery system for receiving rockets upon landing comprising a deceleration pool filled with liquid. The system may have a volume filled with the liquid having a desired density profile. An injection manifold injects gas into the liquid to create the density profile. The liquid may have a first density at a landing region of the pool and a second density greater than the first density away from the landing region, such as increasing in density radially outward from a center of the landing region. The pool may be located under a primary landing system intended to secure the landing rocket, such as a hook catch. The pool may be a contingency system for mitigating damage to a landing rocket that unsuccessfully attempts securing with the primary landing system.

An atmospheric re-entry vehicle includes a body defining a first end of the vehicle and a heat shield at a second end of the vehicle opposite the first end. The heat shield includes a heat shield outer surface that is configured to be exposed to a high enthalpy flow during atmospheric re-entry. A centerline of the heat shield is offset relative to a centerline of the body. At least a portion of the heat shield outer surface is at least substantially axisymmetric relative to the centerline of the heat shield.

A stage of a rocket is disclosed. The rocket stage may include: a body, and a plurality of foldable propulsion units spaced around a circumference of the body, where each propulsion unit comprises: a folding beam; at least one motor mounted to the folding beam, and at least one propeller mounted to the at least one motor, configured to generate a thrust to propel the rocket.