The Space Transportation System (STS) with Reusable Launch Ve- hicle (RLV) of the Next Generation (NG) Space Shuttle NG X-3033/ MagicStar is the further development of our revolutionary hyperson- ics concepts. Especially the integration of technologies developed with the projects and concepts:
National Aero-Space Plane (NASP) prototyp X-30,
Lockheed Martin Reusable Launch Vehicles (RLV) X-33 and VentureStar,
NASA Reusable Air-Breathing Launch Vehicle (RABLV) Space Express Concept,
SOS Hypersoar Catamaran concepts,
Defense Advanced Research Projects Agency (DARPA), United States Air Force (USAF) and Lockheed Martin
Force Application and Launch from CONtinental United States (FALCON) Hypersonic Cruise Vehicle (HCV),
Leninets Plasma Hypersonic Vehicle (PHV) Ayaks, and
yields into a new technological masterpiece.
The Space Shuttle NG X-3033/MagicStar features our Hybrid Double Bubble (HDB) lifting body shape that gives it an unprecedented aero- dynamic efficiency with a highly reduced drag in the atmosphere, and delivers the needed lift-off force and angel of attack.
Energy Generation, Transfer and Consumption System (EGTCS)
harvesting of highly destructive kinetic and thermal energy for transforming them into electricity, and
reduction of entropy rise on the surface of an aerospaceplane and in a scramjet engine by bypassing free kinetic energy of air,
The Energy Generation, Transfer and Consumption System (EGTCS) enables the:
and basically consists of the following components and their functionalities:
Energy Generation (EG) System (EGS),
Energy Regeneration (ER) System (ERS),
Directional Energy Transfer (DET) System (DETS),
Active Thermal Protection (ATP) System (ATPS), and
Energy Consumption (EC) System (ECS), that includes as subsystems the:
All subsystems are integarted with all other subsystems, like example given the navigation, guidance and control systems, into the Onto- logic System® for AeroSpacePlane Management (ASPM) with our AutoSemantic::Space module.
Integrated/Combined Propellant Thermal Protection System
Technology 1: MagnetoHydroDynamic (MHD) Shield
The Passive and Active Thermal Protection System consists of 4 different technologies that are integrated to one system. The TPS simply replaces all concepts that are based on ablative materials, particularly at the nose and leading edges, and makes the accommodation of the navigation, guidance and control system due to former shape change interferences to the aerodynamics and mass properties of an aerospacevehicle obsolete.
By applying the MagnetoHydroDynamic (MHD) generators of the Energy Regeneration System to harness destructive thermal energy for the generation of constructive electric energy they are also reducing the temperature at the aerospaceplane surface and in this way are functioning like a heat shield. The generated electricity is then partly used for the Technology 2 and 3.
Technology 2: Active Heat Shield
This technology consists of a superconducting coil that generates electron beams for the magnetic fields which extend out beyond the nose and leading edges of the vehicle and by this is able to deflect the hot atmospheric air away from the vehicle's surface. It forms also some kind of virtual aerospacecraft body.
The Active Heat Shield is also used inside the air-breathing hypersonic engines to replace the heat-absorbing material,
Technology 3: Active Anti-Friction system
Technology 4: Propellant Decomposition and Reformation
But even after applying the MHD generators (technology 1) and the Active Heat Shield (technology 2) there is still enough thermal energy/heat load on the surface of the aerospaceplane that can be harnessed. To use a Carnot cycle or Rankine cycle based steam operated heat engine in this subsequent harnessing step would be the first idea, but has some giant problems: First of all, there is to much heat, so that a condenser can't be applied. Quite the contrary holds, the condenser itself would have to be protected as well against the heat as it is done in air-breathing rocket engines, like the Liquid Air Cycle Engine (LACE) and the Deeply Cooled Engine. And also we have the huge weight penalty of such a system. A solution is to obmit the condenser and integrate a fuel reforming system based on steam into the double-hull and airframe of the body that uses water and the propellant of the engine as working fluid for optimizing the effici- ency (around 42+% after Leninets) compared to the original hydro- carbon fuel.
to enrich the propellant for the scramjet engine with energy by the energy of surface heating (and the power of the MHD generator in the nose of the engine) reforming process to enrich/increase the energy concentration/chemical energy/heating capacity (around 42%) of the propellant by breaking up H2O into O and H2. Due to the high heat and the resulting pressure works this part like the expander cycle of a rocket engine and pumps the O and H2 gases, and the now reformed propellant directly into the scramjet combustor.
Aerodynamic Characteristics Control System
The Aerodynamic Characteristics Control system of the spaceplane by controlling the generated magnetic field as plasma actuators are
The ACCS is also supported by the PAFS that is applied like plasma actuators.
The plasma funnels developed from the magnetohydrodynamics forces over the air inlet increase the ability of the engine to collect air, increasing the effective diameter of the air inlet up to 5 to 10 times or even more of the original inlet. Thus, the MagicStar's engines can use atmospheric oxygen, even at heights above 40 km (131,233 ft).
"TSTO is dead"
What makes our MagicStar literally Hyper Revolutionary is the fact, that the hybrid shape of the aerospaceplane, which is derived from the hypersonic catamaran configuration, together with the EGTCS are the missing stones that let reduce the propellant con- sumption of the whole aerospaceplane after several rough estimat- ions and comparisons with classic air- and spacecrafts by around incredible 60% to 70% or even more. More fascinating is that this reduction is achieved while the velocity as an air-breather is in- creased by around 100%, and that the maximal speed is around 800% higher than of an air-breather. And by this, the dream of Single-Stage-To-Orbit (SSTO) systems like example given the National Aero-Space Plane (NASP) become a reality.
Design exterior: Style of Speed, NASA, DARPA, Lockheed Martin and Leninets
Design interior: Style of Speed
Thrust: Not specified
Length: 52 m
Wingspan: Not specified
Height: Not specified
Mass: Not specified
Vmax: Mach 32 in atmosphere at 64,000 m/210,000 ft
Vmax: Mach 103+ (30 kilometers per second/108,000 km/h/ 67,111 MPH) in vacuum (see also our spaceship concept X-3³)
Service ceiling: 1,000 km/621.4 mi
Payload to LEO: 25,000 kg/55,115 lb
Payload to GTO: 4,536 kg/10,000 lb
Low Earth Orbit (LEO) AirLiner (LEOAL),
Fly-back Booster Launcher (FBL) in a Two-Stage-To-Orbit (TSTO) configuration based on our Hypersonic AirLiner (HAL) HCV-1/White Swift due to the same architecture,
Geosynchronous/-stationary Transfer Orbit (GTO) transporter of Space Taxis, like our X-3*/LittleStar, or smaller OSPs, like the X-37 by the NASA, Boeing and the United States Air Force, and
GeoSynchronous Orbit (GSO) AirLiner (GSOAL) and Geostationary Earth Orbit (GEO) AirLiner (GEOAL).
The X-3033/MagicStar is also deliverable as:
Custom specific configurations are available on special request.
This is an actual project. Interested persons can contact us day and night.
Yes, it works