Satellite Fleet Deployment via Nodal Drift and Spinning Bus
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Solution Overview
Problem
Current satellite fleet deployment methods are economically uneconomical due to high launch costs and complexity, particularly in non-geostationary orbits (NGSO) where solar beta angles and complex steering mechanisms increase mass and complexity, making traditional methods costly and inefficient.
Innovation Solution
Implementing a satellite fleet with satellites in Molniya orbits, phased to follow a common ground track, using a direct broadcast satellite system that allows for efficient nodal separation and reduced fuel consumption by leveraging Earth's gravitational field, rather than relying on booster rocket burns or dedicated launch vehicles, and employing a spinning bus and despin control mechanism to maintain solar panel orientation and antenna directionality.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If multiple satellites are launched within a single launch vehicle using traditional adapters or dispensers, then launch cost is reduced, but launch mass and device complexity increase due to the special adapters or dispensers
Solution Approach 1:
The patent merges the functions of multiple satellites into a single integrated satellite structure that can be launched together in one vehicle. The satellite includes multiple payloads or functional modules that can operate independently or together, eliminating the need for separate satellites and their associated adapters or dispensers.
Solution Approach 2:
The satellite is designed with multi-functionality, incorporating multiple payloads or operational capabilities within a single platform. This universal design allows one satellite to perform the functions of multiple traditional satellites, reducing launch mass while maintaining productivity.
2Speed
If satellites perform booster rocket burn operations to establish nodal separation, then appropriate orbital plane separation is achieved, but fuel consumption and launch mass increase
Solution Approach 1:
The patent establishes nodal separation through preliminary orbital parameters selected during mission planning, rather than requiring active booster burns. The satellites are inserted into orbits with pre-calculated inclination and ascending node differences that automatically provide the required nodal separation, eliminating the need for additional fuel consumption.
Solution Approach 2:
The patent replaces the mechanical/propulsive system of booster rocket burns with an orbital mechanics-based solution. By carefully selecting initial orbital parameters, the natural gravitational dynamics of the Earth-satellite system achieve the desired nodal separation without requiring additional propulsion.
3Ease of operation
If NGSO satellites include complex steering mechanisms and multiple gimbals to orient solar panels and antennas, then solar panel orientation and antenna directionality are maintained, but device complexity and mass increase
Solution Approach 1:
The patent employs asymmetric orbital configurations and satellite positioning strategies that naturally maintain optimal orientation. By carefully selecting orbital parameters such as inclination and right ascension of the ascending node, the satellite's solar panels and antennas maintain their desired orientations relative to the Sun and Earth without requiring complex active steering mechanisms.
Applied Scientific Principles
This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.
Function Achieved in This Case
This approach reduces launch costs and complexity by enabling efficient nodal separation and fuel conservation, while maintaining consistent thermal loads and simplifying thermal control, thus providing continuous coverage with reduced satellite mass and complexity.
Implementation Method 1
leveraging Earth's gravitational field, rather than relying on booster rocket burns or dedicated launch vehicles
Implementation Method 2
NGSO satellites include relatively complex steering mechanism and multiple gimbals to achieve solar panel orientation and downlink antenna steering
Data Source
AI summary
A method for implementing a satellite fleet includes launching a group of satellites within a launch vehicle. In an embodiment, the satellites are structurally connected together through satellite outer load paths. After separation from the launch vehicle, nodal separation between the satellites is established by allowing one or more of the satellites to drift at one or more orbits having apogee altitudes below an operational orbit apogee altitude. A satellite is maintained in an ecliptic normal attitude during its operational life, in an embodiment. The satellite's orbit is efficiently maintained by a combination of axial, radial, and canted thrusters, in an embodiment. Satellite embodiments include a payload subsystem, a bus subsystem, an outer load path support structure, antenna assembly orientation mechanisms, an attitude control subsystem adapted to maintain the satellite in the ecliptic normal attitude, and an orbit maintenance/propulsion subsystem adapted to maintain the satellite's orbit.