Abstract: Systems and methods for customizable vacuum testing chambers. Outer shell segments are assembled to conform to and form a sealed enclosure about a test article having air therein. An interstitial region is defined between the test article and the shell segments. A porous support layer is located within the interstitial region. A vacuum pump evacuates air from within the interstitial region to vacuum test the article. Sensors detect leaks within the interstitial region. Zonal barriers may fluidly isolate zones of the interstitial region for locating leaks. The shell segments may be disassembled and the test article removed. The shell segments may be reused for testing other test articles having different shapes and sizes.

Abstract: Systems and methods for customizable vacuum testing chambers. Outer shell segments are assembled to conform to and form a sealed enclosure about a test article having air therein. An interstitial region is defined between the test article and the shell segments. A porous support layer is located within the interstitial region. A vacuum pump evacuates air from within the interstitial region to vacuum test the article. Sensors detect leaks within the interstitial region. Zonal barriers may fluidly isolate zones of the interstitial region for locating leaks. The shell segments may be disassembled and the test article removed. The shell segments may be reused for testing other test articles having different shapes and sizes.

Abstract: Launch vehicles with ring-shaped external elements, and associated systems and methods. An aerospace system in accordance with a particular embodiment includes a launch vehicle having a first end and a second end generally opposite the first end, with the launch vehicle being elongated along a vehicle axis extending between the first and second ends, and having an external, outwardly facing surface. The system can further include an annular element carried by the launch vehicle, the annular element having an external, inwardly-facing surface radially spaced apart from, and extending at least partially circumferentially around, the vehicle axis. The annular element can have a first edge surface facing a first direction along the vehicle axis, and a second edge surface facing a second direction along the vehicle axis, the second direction being opposite the first direction.

Abstract: Launch vehicles with ring-shaped external elements, and associated systems and methods are disclosed. An aerospace system in accordance with a particular embodiment includes a launch vehicle having a first end and a second end generally opposite the first end, with the launch vehicle being elongated along a vehicle axis extending between the first and second ends, and having an external, outwardly facing surface. The system can further include an annular element carried by the launch vehicle, the annular element having an external, inwardly-facing surface radially spaced apart from, and extending at least partially circumferentially around, the vehicle axis. The annular element can have a first edge surface facing a first direction along the vehicle axis, and a second edge surface facing a second direction along the vehicle axis, the second direction being opposite the first direction.

Abstract: Launch vehicles with ring-shaped external elements, and associated systems and methods. A representative aerospace system includes a launch vehicle having a first end and a second end generally opposite the first end, with the launch vehicle being elongated along a vehicle axis extending between the first and second ends, and having an external, outwardly facing surface. The system can further include an annular element carried by the launch vehicle, the annular element having an external, inwardly-facing surface radially spaced apart from, and extending at least partially circumferentially around, the vehicle axis. The annular element can have a first edge surface facing a first direction along the vehicle axis, and a second edge surface facing a second direction along the vehicle axis, the second direction being opposite the first direction. A propulsion system can be carried by the launch vehicle, and can have at least one nozzle positioned toward the first end of the vehicle to launch the vehicle.

Abstract: Launch vehicles with ring-shaped external elements, and associated systems and methods are disclosed. An aerospace system in accordance with a particular embodiment includes a launch vehicle having a first end and a second end generally opposite the first end, with the launch vehicle being elongated along a vehicle axis extending between the first and second ends, and having an external, outwardly facing surface. The system can further include an annular element carried by the launch vehicle, the annular element having an external, inwardly-facing surface radially spaced apart from, and extending at least partially circumferentially around, the vehicle axis. The annular element can have a first edge surface facing a first direction along the vehicle axis, and a second edge surface facing a second direction along the vehicle axis, the second direction being opposite the first direction.