LEO Spacecraft Dual-Use Antenna Crosslink Relay

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Solution Overview

Problem

Low earth orbiting spacecraft face challenges in achieving low-latency transmission of imaging data to ground stations due to periods when they are not in view, leading to significant delays in data access.

Innovation Solution

Establishing a crosslink with a second satellite in a higher orbit using a dual-use directional antenna that can alternate between downlinking with a ground station and linking with the higher orbit satellite, allowing data to be relayed to a ground station even when the LEO spacecraft is not in view.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Productivity

If a LEO spacecraft uses a directional antenna to downlink data to ground stations, then data transmission rate is improved, but data availability deteriorates during periods when the spacecraft is not in view of any ground station

Engineering Contradiction:
Improvedata transmission rateVSAvoiddata access latency
Core Design Contradiction:
ProductivityVSLoss of time

Solution Approach 1:

The patent introduces a geosynchronous relay satellite as an intermediary to receive data from the LEO spacecraft via crosslink and forward it to ground stations. This mediator enables continuous data transmission even when the LEO spacecraft is not in direct view of ground stations, reducing data access latency from hours to minutes while maintaining high transmission rates during active downlink periods.

Inventive Principle:
Principle #24Intermediary (Mediator)

2Reliability

If a LEO spacecraft maintains continuous communication capability, then data availability is improved, but antenna complexity increases due to requiring multiple antennas or complex pointing mechanisms

Engineering Contradiction:
Improvedata availabilityVSAvoidantenna system complexity
Core Design Contradiction:
ReliabilityVSDevice complexity

Solution Approach 1:

The patent makes the LEO spacecraft's directional antenna universal by enabling it to perform multiple functions: direct downlink to ground stations during visible periods and crosslink communication with the geosynchronous relay satellite during non-visible periods. This multi-functionality achieves continuous data availability without requiring additional antennas or complex pointing mechanisms, as the same antenna alternates between two communication modes.

Inventive Principle:
Principle #6Universality (Multi-functionality)

3Adaptability or versatility

If ground stations are distributed globally to improve coverage, then data accessibility is improved, but the number and cost of ground stations increases

Engineering Contradiction:
Improvegeographic coverageVSAvoidnumber of ground stations
Core Design Contradiction:
Adaptability or versatilityVSQuantity of substance

Solution Approach 1:

The geosynchronous relay satellite acts as a mobile intermediary that provides global coverage without requiring a distributed network of ground stations. The satellite can communicate with the LEO spacecraft anywhere in its orbital path and relay data to any ground station within its coverage zone, achieving worldwide data accessibility with minimal ground infrastructure.

Inventive Principle:
Principle #24Intermediary (Mediator)

Data Source

PatentEP3381812B1A low earth orbiting spacecraft
Publication Date: 2021.12.08 SPACE SYST LORAL INC
  • EP3381812B1 patent drawingFigure 1A~1B
  • EP3381812B1 patent drawingFigure 2~3
  • EP3381812B1 patent drawingFigure 4

AI summary

A low earth orbiting spacecraft (LEO spacecraft) operable in a first earth orbit includes a main body, a data collection payload, and a first directional antenna, each of the data collection payload and the first directional antenna being coupled with the main body. During a first period of time, the main body is oriented such that the data collection payload views a region of interest on the earth. During a second period of time, the main body and the first directional antenna are oriented such that the first directional antenna is directed toward a first ground station. During a third period of time, the main body and the first directional antenna are oriented such that the first directional antenna is directed toward a second spacecraft operating in a second orbit.