Abstract: A heat shield for mounting on a heat-radiating object, particularly on a rocket engine comprises a first planar element having a front side and a back side. In its mounted state, the first planar element extending from the heat-radiating object toward the outside, with its front side being exposed to the heat radiation at least of a section of the heat-radiating object. A second insulating element having a front side and a back side is arranged on the back side of the first planar element in such a manner that a gap is formed between the back side of the first planar element and the front side of the second element. In the mounted state of the heat shield, the gap widens in the direction from the heat-radiating object toward the outside.

Abstract: A heat shield for mounting on a heat-radiating object, particularly on a rocket engine comprises a first planar element having a front side and a back side. In its mounted state, the first planar element extending from the heat-radiating object toward the outside, with its front side being exposed to the heat radiation at least of a section of the heat-radiating object. A second insulating element having a front side and a back side is arranged on the back side of the first planar element in such a manner that a gap is formed between the back side of the first planar element and the front side of the second element. In the mounted state of the heat shield, the gap widens in the direction from the heat-radiating object toward the outside.

Abstract: An airbag configuration for braking the landing impact of flying payloads has a central airbag (17) and at least one torus ring (11, 12, 13) surrounding the central airbag. A payload (L) is attachable on the central airbag (17). A stabilizing device (19) is provided which extends from the lowermost portion of the at least one torus ring (11, 12, 13) to the central airbag (17). The central airbag provides primarily vertical braking of the landing impact while the torus ring provides primarily horizontal braking of the landing impact.

Abstract: A process for preventing overturning during the landing of an aircraft or spacecraft using an air bag type landing impact-damping system, which is inflated with gas before the landing and from which gas is discharged via discharge valves during the landing. The process includes using as the air bag type landing impact-damping system a system that is divided into a plurality of chambers that can be inflated with gas and from which gas is released independently from one another, and that a pressure difference is generated during landing in the individual chambers of the air bag type landing impact-damping system.