An atmosphere reentry and landing device for a safe reentry of a rocket stage into the atmosphere and for a safe splashdown thereof. The device includes a ballute which is folded in a first state and unfolded in a second state, a shrouding mechanism which carries out a shrouding of the rocket stage with the ballute, a filling mechanism, and a control unit which controls the shrouding mechanism and the filling mechanism. The ballute is disposed on the rocket stage so that an aerodynamics thereof is not compromised in the first state. The ballute substantially shrouds the rocket stage in the second state. During reentry into the atmosphere, the filling mechanism fills the ballute in the second state with air or a gas from a boundary layer which is created between a plasma formed in front of a surface of the device and the surface of the device.

A rocket landing stabilization system can include one or more upright support structures such as posts, columns, or walls, from which one or more stabilizing elements can be supported. The stabilizing elements can be used to stabilize a rocket as it lands at a landing site. The rocket landing stabilization system can also include a cradle, funnel, or cone to catch or otherwise support a rocket as it lands at the landing site. The rocket landing stabilization system can be located on land or at sea.

A rocket landing stabilization system can include one or more upright support structures such as posts, columns, or walls, from which one or more stabilizing elements can be supported. The stabilizing elements can be used to stabilize a rocket as it lands at a landing site. The rocket landing stabilization system can also include a cradle, funnel, or cone to catch or otherwise support a rocket as it lands at the landing site. The rocket landing stabilization system can be located on land or at sea.

A reusable floating device suitable for launching a space rocket has a support structure which includes a toroidal balloon housing and a rigid platform attached thereto; an elongated rigid structure surrounded by said support structure, releasably connected thereto, and adapted for attachment to a space rocket; at least one buoyant gas balloon within said balloon housing; and a compressor module and at least one rigid-walled tank carried by said platform. The compressor module is in confined flow communication with the at least one buoyant gas balloon and the at least one rigid-walled tank.

A rocket landing stabilization system can include one or more upright support structures such as posts, columns, or walls, from which one or more stabilizing elements can be supported. The stabilizing elements can be used to stabilize a rocket as it lands at a landing site. The rocket landing stabilization system can also include a cradle, funnel, or cone to catch or otherwise support a rocket as it lands at the landing site. The rocket landing stabilization system can be located on land or at sea.

This disclosure describes various techniques and systems for rapid low-cost access to suborbital and orbital space and accommodation of acceleration of sensitive payloads to space. For example, a distributed gas injection system may be used in a ram accelerator to launch multiple payloads through the atmosphere. Additionally or alternatively, multiple projectiles may assemble during flight through the atmosphere to transfer and/or resources to another projectile.

The satellite launcher comprises a plurality of stages detachable from each other, at least one stage including at least one engine, and at least one of said stages carrying a payload, and said stages are placed one beside or around the other, so that the width of the vehicle is at least one third of its length.

The method comprises the following phases: a) ascent of the vehicle with a balloon from a ship; and b) ignition of engines of the vehicle to put a satellite placed in the vehicle into orbit.

A rocket landing stabilization system can include one or more upright support structures such as posts, columns, or walls, from which one or more stabilizing elements can be supported. The stabilizing elements can be used to stabilize a rocket as it lands at a landing site. The rocket landing stabilization system can also include a cradle, funnel, or cone to catch or otherwise support a rocket as it lands at the landing site. The rocket landing stabilization system can be located on land or at sea.

Systems and methods for securing an upright rocket. The rocket may be on a moveable platform, such as a landing area of a ship. The rocket may land on the deck, and the system may include cables that surround the landing area. The cables may be tightened about the rocket after the rocket has landed in an upright position. The system may include poles that telescope upward, such that the cables may tighten about the upright rocket at various heights along the body of the rocket.

A generally vertical rocket (2) flies generally horizontally into recovery line, cable or chain (3) suspended between towers (5, 7) of a catamaran landing ship (9). High speed winches (11, 13), preferably located near or at the tops of the towers (5, 7) can rapidly reel in or out the recovery line (3) to effectively raise or lower the recovery line (3). The fixture engages a capture device on the rocket located usually above the rocket center of gravity. This invention provides a more reliable means of landing a rocket and also eliminates rocket weight, cost and complexity associated with previous means of landing a rocket.