Abstract: In a brake for detachable arrangement on projectiles, the brake is configured with a surface which is situated in the direction of travel of the projectile, where the surface is larger than a surface given by ?R2-?r2, where R is the outer radius of the brake and r is the inner radius of the brake. A method for braking projectiles is also provided.

Abstract: The system can include: a vehicle 100 and a stabilizer 200. However, the system can additionally or alternatively include any other suitable set of components. The system functions to facilitate vehicular transport (e.g., via a cabin). Additionally, the system can provide impact attenuation and/or mitigate rebound of the vehicle during a water landing. Additionally or alternatively, the system can function to provide aquatic stabilization of the vehicle and/or cabin thereof. However, the system 100 can provide any other suitable functionalities.

Abstract: A soil probing device includes a probing rod with a measuring probe, a driving for penetrating the probing rod into the ground, generators for generating acoustic compression and shear waves into the ground, detectors for detecting the generated acoustic compression and shear waves. The detectors are built into the measuring probe. Also the generators are built into the measuring probe at positions that are interspaced at fixed distances in a z-direction from the detectors in the measuring probe. A processing unit CPU is provided for calculating velocities of the generated acoustic compression and shear waves that get to travel from the generators towards the detectors through local ground layers that lie adjacent the measuring probe in between the generators and detectors.

Abstract: An aircraft operable to transition between thrust-borne lift in a VTOL orientation and wing-borne lift in a biplane orientation. The aircraft has an airframe including first and second wings with a fuselage extending therebetween. A propulsion assembly is coupled to the fuselage and includes a counter-rotating coaxial rotor system that is tiltable relative to the fuselage to generate a thrust vector. A flight control system is configured to direct the thrust vector. In the VTOL orientation, the first wing is forward of the fuselage, the second wing is aft of the fuselage and the coaxial rotor system is configured to provide thrust in line with a yaw axis of the aircraft. In the biplane orientation, the first wing is below the fuselage, the second wing is above the fuselage and the coaxial rotor system is configured to provide thrust in line with a roll axis of the aircraft.

Abstract: A system for neutralizing target aerial vehicles comprises a projectile launching mechanism that launches a projectile that supports a counter-attack unmanned aerial vehicle (UAV) having an aerial vehicle countermeasure. The counter-attack UAV can be folded in the projectile, and operable to unfold when separated from the projectile. The system comprises an aerial vehicle detection system comprising a detection sensor that detects a target aerial vehicle. Upon detection, the projectile launching mechanisms launches the projectile, and the counter-attack UAV is thereafter separated from the projectile to operate in flight to neutralize the detected target aerial vehicle with the aerial vehicle countermeasure. The projectile launching mechanism can comprise a movable platform comprising a plurality of projectiles and counter-attack UAVs, and can comprise a detection sensor to detect target aerial vehicles.

Abstract: Disclosed is a method for gauging the liquid propellant tank of a spacecraft during a phase of high-thrust along an axis, the tank being thermally conductive and having a known geometry. The method includes steps of: attaching, on a wall of the tank, a heating member and at least one temperature sensor in proximity to the heating member and in a plane of interest perpendicular to the thrust axis; during the high-thrust phase, heating the wall of the tank and acquiring temperature measurements of the wall of the tank at rapid frequency; determining the instant I when the temperature measured by the sensor changes, such change indicating the presence of the liquid-gas interface in the tank in the plane of interest; and determining the volume of liquid propellant present in the tank at instant I.

Abstract: Embodiments of the present invention relate to a launch vehicle fairing recovery system and method using inflatable bags and fairing repositioning mechanisms. Embodiments of the present invention also relate to providing a system or mechanism to flip the fairing into the proper floating position. In some embodiments, the fairing has an inner surface and an outer surface, where the outer surface is exposed to the atmosphere when the fairing is interconnected to a spacecraft, and one or more inflatable bags interconnected to the outer surface of the fairing, where when the fairing is interconnected to the spacecraft the one or more inflatable bags is empty, and after the fairing separates from the spacecraft the one or more airbags are filled with pressurized gas and/or hydraulic liquids.

Abstract: A first spacecraft and a second spacecraft are configured to be disposed together, in a launch configuration, for launch by a single launch vehicle. In the launch configuration, the first spacecraft is mechanically coupled with a primary payload adapter of the launch vehicle, and the second spacecraft is mechanically coupled with the first spacecraft by way of an inter-spacecraft coupling arrangement. The spacecraft are configured to be deployed, following injection into a first orbit by the launch vehicle, by separating the first spacecraft from the primary payload adapter while the second spacecraft is mechanically coupled with the first spacecraft. A first onboard propulsion subsystem of the first spacecraft includes one or more thrusters configured to execute an orbit transfer maneuver from the first orbit to a second orbit. A propellant line arrangement detachably couples the first onboard propulsion subsystem with a second propellant storage arrangement on the second spacecraft.

Abstract: Launch vehicles with ring-shaped external elements, and associated systems and methods. An aerospace system in accordance with a particular embodiment includes a launch vehicle having a first end and a second end generally opposite the first end, with the launch vehicle being elongated along a vehicle axis extending between the first and second ends, and having an external, outwardly facing surface. The system can further include an annular element carried by the launch vehicle, the annular element having an external, inwardly-facing surface radially spaced apart from, and extending at least partially circumferentially around, the vehicle axis. The annular element can have a first edge surface facing a first direction along the vehicle axis, and a second edge surface facing a second direction along the vehicle axis, the second direction being opposite the first direction.

Abstract: A projectile for firing from a launcher includes a propulsion stage having non-axisymmetric boosters arranged about a longitudinal axis of the propulsion stage. The propulsion stage may further include a central booster about which the non-axisymmetric boosters are arranged.

Abstract: An aerial vehicle includes an outer surface, an arithmetic unit and a control unit. The arithmetic unit calculates a control command using a control parameter. The control unit controls an attitude of the aerial vehicle or a thrust of the aerial vehicle based on the control command. At least a part of the outer surface of the aerial vehicle is composed of ablation material. The arithmetic unit changes the control parameter in response to an amount of shape change of the aerial vehicle caused by disappearance of the ablation material.

Abstract: An aircraft having propulsion units for both conventional aircraft flight in the atmosphere and for high-altitude operation as a rocket. The aircraft is divided into a payload compartment and a compartment containing rocket propulsion unit propellant or fuel, and includes a long transverse wing with a small back-sweep to favor lift in the dense layers of the atmosphere and to thus make it possible to climb to high altitudes at a subsonic speed before using the rocket propulsion units. The return flight portion is performed by gliding or controlled as for a conventional aircraft.

Abstract: Vehicles with bidirectional control surfaces and associated systems and methods are disclosed. In a particular embodiment, a rocket can include a plurality of bidirectional control surfaces positioned toward an aft portion of the rocket. In this embodiment, the bidirectional control surfaces can be operable to control the orientation and/or flight path of the rocket during both ascent, in a nose-first orientation, and descent, in a tail-first orientation for, e.g., a tail-down landing.

Abstract: A space probe including a descent module with a mobile exploration vehicle, wherein the descent module is a landing module inside which the mobile exploration vehicle is fastened, the landing module being provided with landing legs which can be deployed under the lower level of the mobile exploration vehicle.

Abstract: A vehicle comprises a first stage supersonic aircraft, and a second stage hypersonic aircraft. The second stage aircraft is in tandem with the first stage aircraft.

Abstract: Aircraft systems that are optimized for multiple phases of flight are disclosed. In an aspect, an in-line staged aircraft is disclosed comprising a launch vehicle and a flight vehicle which are configured to join together along a common center line and form a single air foil in the joined configuration. The flight vehicle and the launch vehicle are separable in flight. In an aspect, the flight vehicle is an unmanned aerial vehicle configured for high-altitude, long-endurance operations.

Abstract: Vehicles with bidirectional control surfaces and associated systems and methods are disclosed. In a particular embodiment, a rocket can include a plurality of bidirectional control surfaces positioned toward an aft portion of the rocket. In this embodiment, the bidirectional control surfaces can be operable to control the orientation and/or flight path of the rocket during both ascent, in a nose-first orientation, and descent, in a tail-first orientation for, e.g., a tail-down landing.

Abstract: Vehicles with bidirectional control surfaces and associated systems and methods are disclosed. In a particular embodiment, a rocket can include a plurality of bidirectional control surfaces positioned toward an aft portion of the rocket. In this embodiment, the bidirectional control surfaces can be operable to control the orientation and/or flight path of the rocket during both ascent, in a nose-first orientation, and descent, in a tail-first orientation for, e.g., a tail-down landing.

Abstract: Vehicles with bidirectional control surfaces and associated systems and methods are disclosed. In a particular embodiment, a rocket can include a plurality of bidirectional control surfaces positioned toward an aft portion of the rocket. In this embodiment, the bidirectional control surfaces can be operable to control the orientation and/or flight path of the rocket during both ascent, in a nose-first orientation, and descent, in a tail-first orientation for, e.g., a tail-down landing.

Abstract: A launch system comprises a nose section comprising a nose coupling surface, a tail section comprising a tail coupling surface facing the nose coupling surface and a mast coupling the nose and tail sections. The mast is configured to expand and retract to displace the nose and tail sections within a range of distances from one another. In a retracted state, the nose and tail sections are either structurally coupled to one another at the nose and tail coupling surfaces or structurally coupled to at least one integrated module located between the nose and the tail sections.

Abstract: A recoverable module for a propulsion module configured to launch a craft into space, the recoverable module including a central body, a propulsion system configured to launch the craft, systems for commanding and controlling the propulsion system, at least one propulsion engine in subsonic flight, lift surfaces for the subsonic flight and landing gear, the lift surface including two substantially flat wings fixed with respect to the central body, arranged on either side of the central body of the module, and a stabilizer mounted articulated for rotation on a downstream end of each wing, each stabilizer including at least one pair of lower wing surface and upper wing surface flaps mounted articulated on the stabilizer or any other flap fulfilling a dynamic function.

Abstract: Launch vehicles with ring-shaped external elements, and associated systems and methods are disclosed. An aerospace system in accordance with a particular embodiment includes a launch vehicle having a first end and a second end generally opposite the first end, with the launch vehicle being elongated along a vehicle axis extending between the first and second ends, and having an external, outwardly facing surface. The system can further include an annular element carried by the launch vehicle, the annular element having an external, inwardly-facing surface radially spaced apart from, and extending at least partially circumferentially around, the vehicle axis. The annular element can have a first edge surface facing a first direction along the vehicle axis, and a second edge surface facing a second direction along the vehicle axis, the second direction being opposite the first direction.

Abstract: A reusable unmanned single-stage boost-glide suborbital Earth launcher, able to propel large or smaller payloads from Earth surface or from air launch, to a nearly Earth-orbital condition, then glide circum-globally to horizontal airstrip landing at its launch site or similar circum-global recovery site. The payload, using its own propulsion, is thus enabled to complete insertion into low-Earth-orbit (LEO) or destinations beyond LEO. This technically feasible capability, beyond conferring economic benefits of reusability and maneuverability, can be adapted to increase payload by adding drop tanks, or solid or liquid “strap on” boosters, and might eventually be modified and evolved to perform manned aerospace missions, as well as single stage to orbit (SSTO) missions.

Abstract: A modular spacecraft comprising: a capsule module comprising a common bulkhead, and an additional spacecraft module comprising a common bulkhead, wherein said capsule modules common bulkhead is attached to said additional spacecraft module's common bulkhead.

Abstract: Technology for predicting and correcting a trajectory is described. The technology can create a model to predict a position of the reusable launch vehicle at a time in the future; observe a wind condition during ascent of the reusable launch vehicle; store the observed wind condition in a wind map; predict during ascent a position and a terminal lateral velocity of the reusable launch vehicle at a terminal altitude; and correct a flight trajectory of the reusable launch vehicle based on the wind map.

Abstract: An aircraft having propulsion units for both conventional aircraft flight in the atmosphere and for high-altitude operation as a rocket. The aircraft is divided into a payload compartment and a compartment containing rocket propulsion unit propellant or fuel, and includes a long transverse wing with a small back-sweep to favor lift in the dense layers of the atmosphere and to thus make it possible to climb to high altitudes at a subsonic speed before using the rocket propulsion units. The return flight portion is performed by gliding or controlled as for a conventional aircraft.

Abstract: Launch vehicle systems and methods for landing and recovering a booster stage and/or other portions thereof on a platform at sea or on another body of water are disclosed. In one embodiment, a reusable space launch vehicle is launched from a coastal launch site in a trajectory over water. After booster engine cutoff and upper stage separation, the booster stage reenters the earth's atmosphere in a tail-first orientation. The booster engines are then restarted and the booster stage performs a vertical powered landing on the deck of a pre-positioned sea-going platform. In one embodiment, bidirectional aerodynamic control surfaces control the trajectory of the booster stage as it glides through the earth's atmosphere toward the sea-going platform. The sea-going platform can broadcast its real-time position to the booster stage so that the booster stage can compensate for errors in the position of the sea-going platform due to current drift and/or other factors.

Abstract: Vehicles with bidirectional control surfaces and associated systems and methods are disclosed. In a particular embodiment, a rocket can include a plurality of bidirectional control surfaces positioned toward an aft portion of the rocket. In this embodiment, the bidirectional control surfaces can be operable to control the orientation and/or flight path of the rocket during both ascent, in a nose-first orientation, and descent, in a tail-first orientation for, e.g., a tail-down landing.

Abstract: A vehicle includes a first sub-vehicle, and a second sub-vehicle which is repeatably moveable between coupled and uncoupled conditions with the first sub-vehicle. The first and second sub-vehicles each include a landing system and propulsion system. The first and second sub-vehicles are in the coupled condition during take-off. The first and second sub-vehicles are separately flyable in the uncoupled condition. Both vehicles are launched horizontally, by a ramp, or vertically, using atmospheric lift to achieve atmospheric flight, orbital, or sub-orbital launch.

Abstract: A reversible aerospace plane includes an air intake at a first end of the aerospace plane, at least one heat exchanger disposed in the aerospace plane, and an engine at a second end of the aerospace plane, wherein the aerospace plane is configured to accelerate in a first direction and configured to glide and land in a second direction, wherein the second direction is substantially in a reverse direction from the first direction.

Abstract: The present invention relates to a spacecraft structure that comprises a flat-wide body center fuselage, right and left side arch-wings and rocket propulsion power plant compartments, wherein the arch-wing is anchored to the fuselage via a foldable hinge mechanism. The fuselage structure is constructed as a single solid structure body of the spacecraft. A top portion at the rear of fuselage comprises a jet propulsion power plant to provide thrust during take-off from the airport. Both the left and right side arch-wings are anchored to a front and a rear portion of the center fuselage structure. Both the front and rear wing portions enable spacecraft lift and superior maneuverability during flight. The spacecraft is air tight and water tight and includes floatation devices.

Abstract: A sky/space elevator vehicle for going from the surface of a planet or moon up into space and back again. The vehicle has a single fuselage comprising multiple floor sections including a top and bottom cone. The movement of the vehicle is controlled by helium filled envelops as well as a combined jet and rocket propulsion system.

Abstract: Technology is described for enabling a reusable launch vehicle to compensate for wind prior to engaging propulsion during approach to landing. The technology can cause the reusable launch vehicle to begin un-powered descent; determine a first rotation angle of the reusable launch vehicle about a specified vertical descent path, the first rotation angle corresponding to a first attitude of the reusable launch vehicle selected to stabilize the reusable launch vehicle on the vertical descent path based on a wind speed and angle; and prior to engaging a propulsion device, command a second rotation angle for the reusable launch vehicle, the second rotation angle corresponding to a second attitude that, when the propulsion device is engaged, will cause the reusable launch vehicle to remain at least approximately at the vertical descent path.

Abstract: A recoverable module for a propulsion module configured to launch a craft into space, the recoverable module including a central body, a propulsion system configured to launch the craft, systems for commanding and controlling the propulsion system, at least one propulsion engine in subsonic flight, lift surfaces for the subsonic flight and landing gear, the lift surface including two substantially flat wings fixed with respect to the central body, arranged on either side of the central body of the module, and a stabilizer mounted articulated for rotation on a downstream end of each wing, each stabilizer including at least one pair of lower wing surface and upper wing surface flaps mounted articulated on the stabilizer or any other flap fulfilling a dynamic function.

Abstract: Launch vehicles with fixed and deployable deceleration surfaces and associated systems and methods are disclosed. A system in accordance with a particular embodiment includes a launch vehicle that has a first end and a second end generally opposite the first end, and is elongated along a vehicle axis extending between the first and second ends. The vehicle carries an exposed outwardly facing surface having a first region positioned or positionable to have a first cross-sectional area generally normal to the vehicle axis toward the first end of the vehicle, and a second region positioned or positionable to have a second cross-sectional area generally normal to the vehicle axis toward the second end of the vehicle. The first cross-sectional area is less than the second cross-sectional area. The system can further include a propulsion system carried by the launch vehicle and having at least one nozzle positioned toward the first end of the vehicle to launch the launch vehicle.

Abstract: An aero-assisted pre-stage (10) with a commensurably large wing area having a short-burn rocket propulsion system providing sufficient thrust is used to launch a variety of single-stage and multiple-stage space vehicles (20), such as conventional ballistic rockets and prospective spaceplanes, from conventional runways. This method of launch eliminates the need for dedicated ground launch structures and/or dedicated long runways. The vehicle to be launched (20) is mated to this aero-assisted pre-stage (AP) (10), with their flight directions aligned, using a lock-and-release mechanism (30). The resulting stack takes off like a conventional airplane using the propulsion and aerodynamic lift of the AP. After the desired trajectory of the vehicle is achieved and propulsion system of the AP is shut down, the vehicle is separated from the AP, the propulsion system of the vehicle is ignited, and the vehicle continues its ascent. The AP returns back to the surface for reuse or disposal.

Abstract: An orbital debris removal assembly is provided. The orbital debris removal and asset protection assembly includes a plurality of spaced layers of netting. Each netting layer includes a plurality of sub-layers of meshed composite fibers that are configured and arranged to break up debris that comes in contact with the assembly.

Abstract: A reversible aerospace plane includes an air intake at a first end of the aerospace plane, at least one heat exchanger disposed in the aerospace plane, and an engine at a second end of the aerospace plane, wherein the aerospace plane is configured to accelerate in a first direction and configured to glide and land in a second direction, wherein the second direction is substantially in a reverse direction from the first direction.

Abstract: A pod (100) for flights to and/or from space or near-space, comprising a pressurized body (10) for hosting passengers, said pressurized body having a substantially ring-like shape provided around a central axis (7) and having a central opening, wherein said pressurized body comprises one or more windows.

Abstract: A reversible aerospace plane includes an air intake at a first end of the aerospace plane, at least one heat exchanger disposed in the aerospace plane and an engine at a second end of the aerospace plane, wherein the aerospace plane is configured to accelerate in a first direction and configured to glide and land in a second direction, wherein the second direction is substantially in a reverse direction from the first direction.

Abstract: The invention relates to an airship which can be unfolded and folded up automatically on the ground and during flight and which can be operated as an aircraft or as a reusable space shuttle, having a combined collapsible gas cell (400), a grid network (600) which provides the shape, an aircraft body (200) comprising a cockpit (210), a cargo bay (220), a machine bay (230) and collapsible wheels (240), components for aircraft navigation control (300), two rocket motors (500L, 500R) which can be rotated, a collapsible control surface (700) and a mechanism for operation of the collapsible control surface (100). The combined collapsible gas cell (400) comprises an envelope (402) which can be folded and a housing (401) which cannot be folded. The housing (401) which cannot be folded is mounted on the inner walls and the bottom of the cargo bay (220). The gas cell (400) is filled with helium or hydrogen in the unfolded state, and is completely empty in the collapsed state.

Abstract: A fairing includes three sections: an aft section, a middle section, and a nose section. The aft section includes a first surface having a generally constant conic angle (i.e., a “boat-tail angle”) with respect to the longitudinal axis such that the aft section tapers to a first end configured to attach to a generally cylindrical body. The middle section, which intersects and is axially aligned with the aft section, has a second surface characterized by a constant elliptical cross-section along a plane orthogonal to the longitudinal axis. The nose section intersects and is axially aligned with the middle section. The nose section is further defined by four generally concave trianguloid surfaces, each extending from the middle section to a common apex intersecting the longitudinal axis, wherein each adjacent pair of trianguloid surfaces intersects at an edge (e.g., an incurvate edge).

Abstract: A propulsion module configured to launch a craft into space including a recoverable module and a non-recovered part, which is secured to the recoverable module at launch. The recoverable module includes a propulsive system to launch the craft, systems for command and control of the propulsive system, a subsonic flight propulsion motor, airfoils for the subsonic flight, a landing gear, and a braking parachute. The recoverable module is installed in a lower position of the craft when the craft is in the launch position. The non-recovered part includes at least one tank to feed the propulsive system. The recoverable module and the non-recovered part are configured to be separated when the propulsion module reaches a given altitude, and the recoverable module is capable of landing in a controlled fashion after a coasting flight, for example for a return to the launch site.

Abstract: The present invention is a space launch system and method to propel a payload bearing craft into earth orbit. The invention has two, or preferably, three stages. The upper stage has rocket engines capable of carrying a payload to orbit and provides the capability of releasably attaching to the lower, or preferably, middle stage. Similar to the lower stage, the middle stage is a reusable booster stage that employs all air breathing engines, is recoverable, and can be turned-around in a short time between missions.

Abstract: An In Orbit Transportation & Recovery System (IOSTAR™) (10) is disclosed. One preferred embodiment of the present invention comprises a space tug powered by a nuclear reactor (19). The IOSTAR™ includes a collapsible boom (11) connected at one end to a propellant tank (13) which stores fuel for an electric propulsion system (12). This end of the boom (11) is equipped with docking hardware (14) that is able to grasp and hold a satellite (15) and as a means to refill the tank (13). Radiator panels (16) mounted on the boom (11) dissipate heat from the reactor (19). A radiation shield (20) is situated next to the reactor (19) to protect the satellite payload (15) at the far end of the boom (11). The IOSTAR™ (10) will be capable of accomplishing rendezvous and docking maneuvers which will enable it to move spacecraft between a low Earth parking orbit and positions in higher orbits or to other locations in our Solar System.

Abstract: Launch vehicle systems and methods for landing and recovering a booster stage and/or other portions thereof on a platform at sea or on another body of water are disclosed. In one embodiment, a reusable space launch vehicle is launched from a coastal launch site in a trajectory over water. After booster engine cutoff and upper stage separation, the booster stage reenters the earth's atmosphere in a tail-first orientation. The booster engines are then restarted and the booster stage performs a vertical powered landing on the deck of a pre-positioned sea-going platform. In one embodiment, bidirectional aerodynamic control surfaces control the trajectory of the booster stage as it glides through the earth's atmosphere toward the sea-going platform. The sea-going platform can broadcast its real-time position to the booster stage so that the booster stage can compensate for errors in the position of the sea-going platform due to current drift and/or other factors.

Abstract: Vehicles with bidirectional control surfaces and associated systems and methods are disclosed. In a particular embodiment, a rocket can include a plurality of bidirectional control surfaces positioned toward an aft portion of the rocket. In this embodiment, the bidirectional control surfaces can be operable to control the orientation and/or flight path of the rocket during both ascent, in a nose-first orientation, and descent, in a tail-first orientation for, e.g., a tail-down landing.

Abstract: Launch vehicles with fixed and deployable deceleration surfaces and associated systems and methods are disclosed. A system in accordance with a particular embodiment includes a launch vehicle that has a first end and a second end generally opposite the first end, and is elongated along a vehicle axis extending between the first and second ends. The vehicle carries an exposed outwardly facing surface having a first region positioned or positionable to have a first cross-sectional area generally normal to the vehicle axis toward the first end of the vehicle, and a second region positioned or positionable to have a second cross-sectional area generally normal to the vehicle axis toward the second end of the vehicle. The first cross-sectional area is less than the second cross-sectional area. The system can further include a propulsion system carried by the launch vehicle and having at least one nozzle positioned toward the first end of the vehicle to launch the launch vehicle.

Abstract: Technology is described for enabling a reusable launch vehicle to compensate for wind prior to engaging propulsion during approach to landing. The technology can cause the reusable launch vehicle to begin un-powered descent; determine a first rotation angle of the reusable launch vehicle about a specified vertical descent path, the first rotation angle corresponding to a first attitude of the reusable launch vehicle selected to stabilize the reusable launch vehicle on the vertical descent path based on a wind speed and angle; and prior to engaging a propulsion device, command a second rotation angle for the reusable launch vehicle, the second rotation angle corresponding to a second attitude that, when the propulsion device is engaged, will cause the reusable launch vehicle to remain at least approximately at the vertical descent path.

Abstract: The process comprises the steps of: 1) launching the vehicle from the launch site using the first stage booster rocket engine system; 2) separating the at least one upper stage from the first stage booster; 3) terminating operation of the first booster stage rocket engine system; 4) turning the first stage booster back toward the launch site using the aerodynamic flight control system; 5) operating the first stage booster rocket engine system to boost the first stage booster to an altitude sufficient to allow non-powered flight back to the launch side; and 6) landing the first stage booster at the launch site.