New infrastructure and propulsion designs for deep space missions
As NASA's Nancy Grace Roman Space Telescope moves into a SpaceX hangar ahead of its targeted launch to probe dark energy and dark matter, engineers are laying the groundwork for more complex deep space operations. Researchers have proposed orbital traffic-management rules to prevent collisions in the moon's crowded halo orbit, while NASA and General Atomics engineers are designing a dual-loop nuclear rocket concept capable of providing both high thrust and continuous electric power for future Martian missions.
Science··Midday
Preparations for the Roman Space Telescope
NASA's Nancy Grace Roman Space Telescope has been relocated to the SpaceX hangar at Launch Complex 39A in preparation for its integration with a Falcon Heavy rocket. Scheduled for a targeted liftoff on Sunday, the observatory remains sealed inside its protective nose capsule. The telescope's primary mission focuses on investigating dark energy, the force driving the accelerating expansion of the universe, and tracing the influence of dark matter on the formation and clustering of galaxies.[1]
Traffic rules for lunar orbit
As lunar exploration expands, engineers from Texas A&M, Purdue, and NASA's Johnson Space Center have developed traffic-management strategies for the moon's near-rectilinear halo orbit. This specific path, originally designated for the now-canceled Gateway outpost, will still host multiple spacecraft, including the Orion crew capsule and various robotic landers. Computer simulations reveal that implementing slightly more frequent station-keeping maneuvers allows spacecraft to maintain tighter, predictable positions relative to each other, which reduces collision risks in the crowded orbital environment without demanding significant extra propellant.[3]
Dual-loop propulsion concept
Looking toward more distant destinations, engineers from NASA and General Atomics have proposed the synchronal bimodal nuclear rocket, a design that splits a single reactor core into two hydraulically separate loops. One open loop heats hydrogen propellant to generate high thrust, while a closed loop continuously generates electric power. This configuration removes the need for complex switching valves used in earlier concepts and allows the power loop to passively carry away residual decay heat after a burn, avoiding the waste of propellant solely for reactor cooling.[2]
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