Spacecraft multifunction connecting mechanisms, and associated systems and methods are described herein. A representative spacecraft system includes a connecting device, which in turn includes a housing having a common port opening, a first connecting element carried by the housing and positioned to connect with a corresponding first spacecraft connecting structure having a first configuration, and a second connecting element carried by the housing and positioned to connect with a corresponding second spacecraft connecting structure having a second configuration different than the first configuration. At least one of the first and second connecting elements is moveable relative to the other between an operational position and a non-operational position, and each of the first and second connecting elements, when connected to the corresponding first or second spacecraft connecting structure, is positioned to allow transport through the common port opening.

A fluid extraction apparatus includes a first chamber within which waste material is configured to be disposed and a second chamber having a vacuum source interface. The first chamber may be in selective fluid communication with the second chamber. In various embodiments, the fluid extraction apparatus further includes an intermediate valve disposed on a conduit extending between the first chamber and the second chamber, wherein the intermediate valve is selectively actuatable to control the selective fluid communication. In various embodiments, the selective fluid communication between the first chamber and the second chamber is exclusively via the intermediate valve and the conduit.

Vehicles with control surfaces and associated systems and methods are disclosed. In a particular embodiment, a rocket can include a plurality of bidirectional control surfaces positioned toward an aft portion of the rocket. In this embodiment, the bidirectional control surfaces can be operable to control the orientation and/or flight path of the rocket during both ascent, in a nose-first orientation, and descent, in a tail-first orientation for, e.g., a tail-down landing. Launch vehicles with fixed and deployable deceleration surfaces and associated systems and methods are also disclosed.

Vehicles with control surfaces and associated systems and methods are disclosed. In a particular embodiment, a rocket can include a plurality of bidirectional control surfaces positioned toward an aft portion of the rocket. In this embodiment, the bidirectional control surfaces can be operable to control the orientation and/or flight path of the rocket during both ascent, in a nose-first orientation, and descent, in a tail-first orientation for, e.g., a tail-down landing. Launch vehicles with fixed and deployable deceleration surfaces and associated systems and methods are also disclosed.

Embodiments provide a spacecraft airlock system. Embodiments provide a method and apparatus for attaching space exposed payloads to a space station.

Embodiments provide a spacecraft airlock system. Embodiments provide a method and apparatus for attaching space exposed payloads to a space station.

A pressure control system includes at least one tank storing a mixture of oxygen and nitrogen. The system further includes a first branch of a pressure control line configured to transport a first portion of the mixture of oxygen and nitrogen to a pressurized enclosed volume. The system also includes a second branch of the pressure control line configured to transport a second portion of the mixture of oxygen and nitrogen to at least one flight suit removably coupled to the second branch.

A pressure control system includes at least one tank storing a mixture of oxygen and nitrogen. The system further includes a first branch of a pressure control line configured to transport a first portion of the mixture of oxygen and nitrogen to a pressurized enclosed volume. The system also includes a second branch of the pressure control line configured to transport a second portion of the mixture of oxygen and nitrogen to at least one flight suit removably coupled to the second branch.

A method of treating fecal waste according to an example of the present disclosure includes bringing a reactor containing fecal matter to a first temperature and a first pressure, exposing the reactor to an environment with a second temperature and a second pressure such that the water in the fecal waste undergoes flash evaporation, and pyrolizing the fecal waste. A fecal waste processing unit is also disclosed.

A method of treating fecal waste according to an example of the present disclosure includes bringing a reactor containing fecal matter to a first temperature and a first pressure, exposing the reactor to an environment with a second temperature and a second pressure such that the water in the fecal waste undergoes flash evaporation, and pyrolizing the fecal waste. A fecal waste processing unit is also disclosed.