Rocket stage thermodynamic protection system

Abstract

A second rocket stage equipped with a heat shield, which is situated at the site of the payload fairing and lies, in a folded state, adjacent the body of the rocket, enters the atmosphere at orbital speed and orients itself nose forward (downward). At the same time, the folded shield opens and creates a spherical surface in the shape of an inverted umbrella. In the open state, the shield protects the rocket against thermal and dynamic loads during descent from orbit. The structure of the shield is in the shape of a circular frustum with a spherical outer cover in the form a metal sheet and an inner folding metal frame consisting of heavy-duty elements. Mounted to the upper part of the surface is a thermal protector in the form of heat-insulating tiles, or a regenerative cooling system.

Description

[0001] ROCKET STAGE THERMODYNAMIC PROTECTION SYSTEM

[0002] The invention relates to rocket and space technology. Reusable rocket systems. Second-stage landing. The current state of the art involves the return of the second stage of the Starship rocket, as well as the Starship rocket itself. This option has several significant drawbacks, namely: descent and deceleration in the atmosphere are accomplished by the transverse surface of the rocket body, while the rocket experiences dynamic and thermal loads in the worst-case scenario—across the body. This can lead to structural deformation. Furthermore, there is a high risk of loss of control. This invention aims to correct these drawbacks.

[0003] At the top of the rocket, above the payload compartment, there is a folded braking (heat shield). It is a metal structure in the form of a frame in the shape of a truncated cone covered with a spherical shell. The structure is reinforced internally with power elements. During descent from orbit, the rocket stage is oriented nose first (down), the engine compartment is at the top, and enters the atmosphere. In this case, the braking (heat shield) unfolds in the form of an umbrella or shield. With this type of entry, all dynamic overloads are directed along the longitudinal axis of the rocket structure and therefore do not have an emergency-hazardous nature; the thermal loads are perceived not by the rocket body, but by the opened shield. After the speed is reduced to the desired result, the rocket turns 180 degrees and continues moving forward (down) using the engines; the opened braking shield folds into the original structure or can remain open and perform the function of an aerodynamic brake.Advantages of this option:

[0004] The location of the brake shield in the place of the head fairing allows it to be positioned compactly and conveniently.

[0005] All external loads are absorbed by the heat shield and therefore the rocket structure is practically not subject to thermal influences; the dynamic load is directed along the longitudinal axis of the structure (in compression), which has the highest strength.

[0006] The possibility of equipping the heat shield with any of the existing thermal protection systems, such as thermal insulation tiles or a regenerative cooling system, using any of the rocket fuel components located on the rocket as a coolant.

Claims

FORMULA A shield- or umbrella-like structure located on the nose of the second rocket stage. When deployed, it serves as thermal and dynamic protection for the rocket stage entering the atmosphere at orbital velocity. During reentry, the rocket stage is oriented nose-first (downward). When folded, it is located on the nose of the second rocket stage in the location of the payload fairing.

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