An earth to space transport method, system and apparatus. The earth to space transport system can include a main body; a plurality of storage tanks disposed in an inside of the main body, the storage tanks configured to store helium; one or more electric jet propulsion turbines coupled to the main body; a first inflatable cushion disposed at a top of the main body and a second inflatable cushion disposed at a bottom of the main body; a space capsule disposed above the first inflatable cushion; a power generator; and a rotor propeller. Such an earth to space transport system may be utilized to efficiently move humans, satellites and cargo from earth to space.

A mass acceleration system for launching objects, such as a projectile or launch vehicle, via rotational acceleration is disclosed. The system may comprise a chamber maintained at near vacuum pressure, a motor that rotates a hub attached to a tethered projectile in a circular motion inside the vacuum chamber, accelerating the projectile until the projectile reaches a desired launch speed. The projectile may be released from the tether upon reaching the desired launch speed and may exit the chamber through an exit port that is opened briefly to allow the projectile to exit. In various embodiments, the circular mass acceleration system can be used to launch a projectile into space orbit. By employing rotational acceleration via a mechanical approach, the acceleration system provides a cost-effective reusable system for launching objects.

Disclosed is a high altitude space launcher system for transferring payloads from surface to orbit at a significantly lower cost than conventional rockets. It comprises a aerostat lifted one stage light gas gun operating in stratosphere that shoots rocket assisted projectiles containing payload at near orbital velocities to a low angle trajectory. Alternatively, to launch acceleration sensitive payloads such as astronauts the light gas gun is replaced with a muzzle loaded conventional gun that shoots a single stage rocket at a much lower velocity. The system is mostly static structure, attached to a tether-elevator that moors it to land or a ship and provided it with electricity and lifts the projectiles to the gun.

A vehicle and method enabling propulsive flight from the Earth's surface to and from the Moon's surface returning to horizontal Earth landing along an airstrip. This reusable geolunar shuttle vehicle can employ external drop tanks, and function as the final propulsive stage of a multi-stage vehicle which can be: 1) expendable, reusable or party reusable; 2) ground-launched, sea-launched, or air-launched; 3) single-launched or multiple-launched with assembly/refueling en route. The geolunar shuttle can employ axial or ventral propulsion using current operational single-fuel engines or dual-fuel engines providing enhanced system performance. The geolunar shuttle can be crewed or not, and can be internally configured to carry personnel, cargo, or a mix of both. The geolunar shuttle can optionally be used for low earth orbit and far space, including Earth escape missions.

The invention is a system and method of air launching a powered launch vehicle into space or high altitude. More specifically, the invention is a tow aircraft which tows an unpowered glider, with the powered launch vehicle attached thereto, to launch altitude. The powered launch vehicle is released from the unpowered glider and powered on for launch.

Methods of accelerating a target vehicle to a higher orbit via a Kinetic Energy Storage and Transfer (KEST) vehicle are provided. The KEST vehicle is configured to transfer kinetic energy to the target vehicle by way of a catching mechanism using one or more brakes on one or more associated tethers along which the braking mechanism traverses, accelerating the target vehicle into a higher orbit, potentially even beyond the Earth.

A system for launching aerospace payloads includes a wingless, unmanned modified lifting body spacecraft (100), with a payload compartment in the forward section of the spacecraft. The spacecraft is propelled by hybrid rockets clustered in the aft section of the spacecraft. Reaction control system (RCS) modules control the flight path and its associated avionics hardware and software. This system also includes a carrier aircraft (200) configured to air-launch the spacecraft. The carrier aircraft includes a flight operations control system, which monitors the spacecraft's payload and monitors and controls launch and flight operations of the spacecraft. A ground-based mission control system monitors and controls the spacecraft's payload and monitors and controls the launch and flight operations of the spacecraft.

A system and method for carrying an aeronautical or launch vehicle to altitude for release to flight may involve a multiplicity of mounting elements affixed to a carrier aircraft in distributed fashion along a mounting axis. Each mounting element may include a cradle and a retention strap. Each retention strap may be suspendedly attached to a respective cradle, and actuatable from a retention configuration to a release configuration. The retention configuration allows the retention straps to clampingly secure the vehicle to the respective cradles. The actuation of the retention straps from the retention configuration to the release configuration may disable the clamping securement and thereby release the vehicle to drop away from the cradles. For one or more of the retention straps, the actuation may be by way of detonating at least one corresponding pyrotechnic fastener.

An airship includes a capsule and an external structure attached to the capsule and extending vertically above an upper portion of the capsule. A plurality of gas balloons are secured to the external structure and hold a lighter-than-air lifting gas. The volume of lifting gas in the plurality of balloons is at least a sufficient volume to lift the airship into the stratosphere. The airship may also include a first boom and second boom that extend horizontally outward from a lower portion of the capsule. The booms each include a weight or cargo container at a far end to assist in balancing and stabilizing the airship. The number and/or the sizes of the gas balloons may be adjusted and configured to obtain the volume of lifting gas needed to lift the airship to a desired altitude above the Earth.

A dimpled spherical storage unit is described in the form of a cargo ball. The cargo ball includes a spherical exterior surface and a plurality of dimples in a pattern on the exterior surface. At least a first cover is configured to extend outward from the center of the cargo ball and at least a first thruster is configured to be deployed from the cargo ball.