Object redirection using energetic pulses

• US 9,938,024 B1
• Filed: 08/19/2016
• Issued: 04/10/2018
• Est. Priority Date: 08/20/2015
• Status: Active Grant

• Current Assignee: Karl Falken
• Original Assignee: Board of Trustees of The University of Alabama (University of Alabama System)
• Inventors: Fork, Richard
• Primary Examiner(s): Sample, Jonathan L
• Application Number:
  US15/241,919
• Time in Patent Office: 599 Days
• CPC Class Codes: B64G 1/1021 Earth observation satellites
• CPC Class Codes: B64G 1/1028 using optical means for mapping, surveying or detection, e.g. of intelligence
• CPC Class Codes: B64G 1/1085 Swarms and constellations
• CPC Class Codes: B64G 1/242 Orbits and trajectories
• CPC Class Codes: B64G 1/245 Attitude control algorithms for spacecraft attitude control
• CPC Class Codes: B64G 1/36 using sensors, e.g. sun-sensors, horizon sensors
• CPC Class Codes: B64G 1/66 Arrangements or adaptations of apparatus or instruments, not otherwise provided for
• CPC Class Codes: B64G 3/00 Observing or tracking cosmonautic vehicles

Abstract

An object redirection system may generate a high-resolution three-dimensional map of a surface of a target. Based on the map, the system may identify locations on the target'"'"'s surface and direct energetic pulses toward the target at the locations. The system may continuously update the map of the target and continue emitting pulses at the target with reference to the map in order to achieve a desired velocity of the target within a desired timeframe.

Claims

1. A system for redirecting an object in outer space, comprising:

a plurality of emitters positioned on a plurality of spacecraft, the plurality of emitters including at least a first emitter positioned on a first spacecraft of the plurality of spacecraft and a second emitter positioned on a second spacecraft of the plurality of spacecraft, wherein the plurality of spacecraft are configured to move with the object as the object travels along a trajectory in outer space;

at least one emitter of a second plurality of emitters positioned on at least one of the plurality of spacecraft;

at least one sensor positioned on at least one of the plurality of spacecraft for sensing returns of optical signals emitted from the at least one emitter;

memory for storing mapping data defining a map of the surface based on the returns;

at least one processor for controlling the plurality of emitters such that each of the plurality of emitters emits a plurality of energetic pulses that impact a surface of the object causing matter from the surface to be ejected from the object, wherein a cumulative momentum of the ejected matter is sufficient to alter the trajectory of the object, the at least one processor configured to select target locations on the surface for the plurality emitters based on the mapping data, wherein the at least one processor is configured to control the plurality of emitters to direct the energetic pulses at the target locations such that the cumulative momentum over time alters the trajectory in order to avoid a collision with the object, wherein the at least one processor is configured to select a plurality of target locations for the first emitter based on the mapping data, and wherein the at least one processor is configured to control the first emitter such that energetic pulses from the first emitter are successively directed at each of the plurality of target locations for the first emitter as the object rotates.

2. A method for redirecting an object in outer space, comprising:

moving a plurality of spacecraft with the object as the object travels along a trajectory;

controlling a plurality of emitters such that each of a first plurality of emitters positioned on the plurality of spacecraft emits a plurality of energetic pulses that impact a surface of the object causing matter from the surface to be ejected from the object, wherein a cumulative momentum of the ejected matter is sufficient to alter a trajectory of the object;

imaging a surface of the object using at least one sensor and a second plurality of emitters positioned on the plurality of spacecraft, thereby defining mapping data indicative of the surface; and

selecting a plurality of target locations on the surface for the first plurality of emitters based on the mapping data,

wherein the selecting comprises selecting target locations for one of the first plurality of emitters based on the mapping data,

wherein the controlling comprises controlling the first plurality of emitters to direct the energetic pulses at the target locations such that the cumulative momentum over time alters the trajectory in order to avoid a collision with the object, wherein the controlling further comprises controlling the one of the first plurality of emitters such that energetic pulses from the one of the first plurality of emitters are successively directed at each of the target locations selected for the one of the first plurality of emitters as the object rotates.