Orbit transition apparatus

Patent metadata

Field	Value
Publication number	US-11926441-B2
Application number	US-202117555848-A
Country	US
Kind code	B2
Filing date	Dec 20, 2021
Priority date	Apr 14, 2021
Publication date	Mar 12, 2024
Grant date	Mar 12, 2024

Abstract

An orbit transition apparatus that transitions an orbit of a payload in outer space includes a rotating body, an adapter disposed on a center part of the rotating body for docking a payload, a launch module disposed outside of the rotating body for launching the payload, and a thruster for rotating the rotating body. The launch module may launch the payload to a target orbit.

First claim

What is claimed is:

1. An orbit transition apparatus that orbits Earth at an initial orbit and that transitions a payload in outer space from the initial orbit to a target orbit around the Earth, the orbit transition apparatus comprising:
a rotating body comprising:
a flywheel center part,
a ring-shaped flywheel peripheral part disposed outside of the flywheel center part,
a connecting part that connects the flywheel center part and the flywheel peripheral part, and
a balancing part on the connecting part and positioned symmetrically to the payload relative to the flywheel center part;

an adapter disposed on the flywheel center part of the rotating body for docking the payload, wherein the adapter is rotatable independently from the flywheel center part in a forward direction and a reverse direction;
a launch module disposed on the flywheel peripheral part of the rotating body for launching the payload; and
a thruster disposed on the flywheel peripheral part for rotating the rotating body,
wherein the payload is conveyed along, via a driver motor, the connecting part of the rotating body from the adapter to the launch module, and wherein the launch module launches the payload to the target orbit using only a rotational force of a rotating body.

2. The orbit transition apparatus of claim 1 , wherein the rotating body further comprises:
the balancing part moving on the connecting part as the payload is conveyed along the connecting part and positioned symmetrically to the payload relative to the flywheel center part.

3. The orbit transition apparatus of claim 2 , wherein the balancing part is adjusted to be symmetrical to a position of the payload such that a rotational balance of the rotating body is maintained as the payload moves from the adapter to the launch module.

4. The orbit transition apparatus of claim 1 , wherein the adapter is rotatable in the forward direction or the reverse direction about the flywheel center part for aligning the rotational direction and a rotational speed of the adapter with the payload.

Assignees

• Korea Aerospace Res Inst
• Korea Aerospace Res Institut

Inventors

• Im Sung Hyuck
• Lee Jun Seong
• Lee Kee Joo
• Park Jae Sung

Classifications

• B64G1/411

  Electric propulsion · CPC title

• B64G1/2427 Primary

  Transfer orbits · CPC title

• B64G1/40

  Arrangements or adaptations of propulsion systems · CPC title

• B64G1/002 Primary

  Launch systems · CPC title

• B64G1/28

  using inertia or gyro effect · CPC title