In response to the loss of seven astronauts in the Space Shuttle Columbia disaster, large, lightweight, inflatable atmospheric-entry vehicles have been proposed as means of emergency descent and landing for persons who must abandon a spacecraft that is about to reenter the atmosphere and has been determined to be unable to land safely. Such a vehicle would act as an atmospheric decelerator at supersonic speed in the upper atmosphere,and a smaller, central astronaut pod could then separate at lower altitudes and parachute separately to Earth.

A Spherical Ballute (upper) and a Lens-Shaped Ballute (lower) have been considered for inflatableemergency atmospheric-entry vehicles.
Astronaut-rescue systems that have been considered previously have been massive, and the cost of designing them has exceeded the cost of fabrication of a space shuttle. In contrast, an inflatable emergency- landing vehicle according to the proposal would have a mass between 100 and 200 kg, could be stored in a volume of approximately 0.2 to 0.4 m3, and could likely be designed and built much less expensively. When fully inflated, the escape vehicle behaves as a large balloon parachute, or ballute. Due to very low mass-per-surface area, a large radius, and a large coefficient of drag, ballutes decelerate at much higher altitudes and with much lower heating rates than the space shuttle. Although the space shuttle atmospheric reentry results in surface temperatures of about 1,600 °C,ballutes can be designed for maximum temperatures below 600 °C. This allows ballutes to be fabricated with lightweight ZYLON®, or polybenzoxazole (PBO), or equivalent.

Two preliminary cocoon ballute "lifeboat" concepts are shown in the figures. The cocoon portion of the vehicle would be, more specifically, a capsule pressurized to 1 bar (0.1 MPa — approximately 1 standard atmosphere). Crewmembers would enter the cocoon pod and then zip it shut. The spacecraft would be placed on a reentry trajectory, and the inflated cocoon with deflated ballute would be ejected.

Once the vehicle was safely away from the spacecraft, the entire ballute would be inflated. For this inflation at high altitude ,the ballute would be pressurized to about 0.01 bar (1 kPa). As low as this pressure is, it is at least ten times the expected dynamic pressure on the vehicle during the heating portion of very high atmospheric reentry, and hence it is sufficient to enable the ballute to retain its shape.

From thermal reentry heating analyses performed at JPL, the diameter of the inflated ballute would be made large enough (30 to 40 m) to limit the maximum temperature to about 500 °C — safely below the 600 °C limit for PBO, or equivalent.

The spherical ballute shown in the upper figure would have a mass of about 200 kg for a seven-astronaut rescue mission, while the lens-shaped ballute in the lower figure has been further improved by reducing the overall mass required and increasing the coefficient of drag. To maintain stability, the center of mass of both concepts must be kept low, and spin stabilization may be necessary.

This work was done by Jack Jones,Jeffrey Hall,and Jiunn Jeng Wu of Caltech for NASA's Jet Propulsion Laboratory. NPO-40156

Topics:
Aerodynamics Aircraft Balloons Design processes Downsizing Drag Entry, descent and landing Entry, descent, and landing Fabrication Manufacturing processes Mechanical Components Mechanics Pressure Spacecraft Vehicles
This Brief includes a Technical Support Package (TSP).
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Inflatable Emergency Atmospheric-Entry Vehicles

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    NASA Tech Briefs Magazine

    This article first appeared in the August, 2004 issue of NASA Tech Briefs Magazine (Vol. 28 No. 8).

    Read more articles from the archives here.

    Overview

    The document is a Technical Support Package from NASA's Jet Propulsion Laboratory, focusing on Inflatable Emergency Atmospheric-Entry Vehicles, designated as NPO-40156. It is part of NASA Tech Briefs, which aim to disseminate aerospace-related developments with broader technological, scientific, or commercial applications.

    The document includes various figures illustrating the design and functionality of atmospheric entry vehicles, particularly emphasizing different configurations of ballutes—inflatable structures used to slow down vehicles during atmospheric entry. Key figures include:

    • Figure 1: Depicts the three basic ballute configurations, which are essential for understanding how these vehicles operate under different conditions.
    • Figure 2: Shows a spherical atmospheric entry vehicle, highlighting its design and potential applications.
    • Figure 3: Features a lens-shaped atmospheric entry vehicle, which may offer advantages in terms of aerodynamics and stability during descent.
    • Figure 4: Presents temperature plots for spherical entry ballutes of varying sizes (60 m and 40 m spheres), providing insights into thermal dynamics during atmospheric entry.

    The document serves as a resource for those interested in the development and application of inflatable vehicles designed for emergency atmospheric entry, which could be crucial for various missions, including planetary exploration and potential rescue operations.

    Additionally, the Technical Support Package emphasizes the importance of the Commercial Technology Program of NASA, which aims to make aerospace innovations accessible for wider use. It encourages further exploration of research and technology in this field through the NASA Scientific and Technical Information (STI) Program Office, providing contact information for inquiries and additional resources.

    The document also includes a disclaimer stating that the U.S. Government and its representatives do not assume liability for the use of the information contained within, nor do they endorse any specific trade names or manufacturers mentioned.

    In summary, this Technical Support Package is a comprehensive overview of inflatable emergency atmospheric-entry vehicles, detailing their configurations, thermal dynamics, and potential applications, while also promoting further research and development in the field of aerospace technology.