Satellite Orbit Transfer via Segmented Solid Propulsion
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Solution Overview
Problem
Current satellite positioning systems from transfer to working orbit are time-consuming and inefficient, with significant mass and dimension issues for apogee motors, limiting the carrying capacity of satellites and requiring complex, costly machining for each satellite.
Innovation Solution
A system comprising a main propulsion device with parallel solid-propellant cartridges, a re-ignitable secondary propulsion device, position sensors, and a monitoring unit to control the firing and ignition of cartridges for rapid orbit transfer, allowing multiple satellites to share propulsion resources and reduce overall mass and dimension.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a liquid or electric propulsion apogee motor is used on the satellite, then the satellite can be positioned in working orbit, but the transfer time from transfer orbit to working orbit becomes very long (10 days to 1 month)
Solution Approach 1:
The propulsion function is segmented between the launcher (main propulsion device with solid propellant) and the satellite (secondary propulsion device). The launcher provides the main thrust for orbit transfer using solid propellant cartridges, while the satellite retains a smaller re-ignitable propulsion system for final positioning and attitude control. This segmentation allows rapid transfer while maintaining positioning capability.
Solution Approach 2:
The launcher's upper stage acts as an intermediary by providing the primary propulsion function during the critical transfer phase. The solid propellant cartridges in the launcher deliver the necessary thrust to move the satellite from transfer orbit to near working orbit, after which the satellite's own propulsion system takes over for final adjustments.
2Reliability
If a solid propulsion apogee motor with machined propellant is used, then the satellite can be positioned in working orbit, but the manufacturing becomes complex and costly
Solution Approach 1:
The propulsion system is divided into launcher-based solid propellant cartridges and satellite-based re-ignitable propulsion. The launcher's solid propellant uses simple cylindrical cartridges without complex machined profiles, while the satellite's propulsion system uses standardized engines that can be re-ignited for precise positioning.
Solution Approach 2:
The launcher's main propulsion device with solid propellant cartridges serves multiple purposes: it provides the primary thrust for orbit transfer and can accommodate different satellite configurations. The standardized cartridge design eliminates the need for custom-machined propellant for each satellite, reducing manufacturing complexity and cost.
3Reliability
If traditional apogee motors are installed on each satellite, then the satellite can perform orbit transfer, but the mass and overall dimension increase significantly
Solution Approach 1:
The main propulsion function is merged into the launcher's upper stage, where multiple satellites share a common solid propellant propulsion system. This eliminates the need for each satellite to carry a full-sized apogee motor, significantly reducing the mass and dimension of propulsion equipment on each satellite.
Solution Approach 2:
The launcher's upper stage propulsion system serves as a universal platform for multiple satellites. The solid propellant cartridges provide the primary thrust for all satellites in the constellation, while each satellite retains only a small re-ignitable propulsion system for fine positioning, reducing overall mass.
4Reliability
If traditional apogee motors are installed on each satellite, then the satellite can perform orbit transfer, but the overall dimension increases reducing working equipment capacity
Solution Approach 1:
The main propulsion volume is consolidated in the launcher's upper stage rather than being distributed across multiple satellites. This merging allows satellites to have compact propulsion systems, freeing up valuable satellite volume for scientific instruments and working equipment.
Solution Approach 2:
The propulsion system is segmented into a large launcher-based solid propellant system and small satellite-based re-ignitable systems. This segmentation reduces the volume requirement on each satellite, allowing more space for payload equipment while maintaining orbit transfer capability.
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
Enables faster and more efficient satellite positioning, reducing the time required for orbit transfer and allowing more equipment to be carried on satellites, while simplifying the manufacturing process and reducing costs by using modular, re-ignitable propulsion systems.
Implementation Method 1
a main propulsion device with solid propulsion comprising a plurality of parallel solid-propellant cartridges
Implementation Method 2
a secondary propulsion device which is re-ignitable
Data Source
AI summary
A system for positioning at least one satellite in working orbit, characterized in that the system for positioning satellites in working orbit comprises: a first attachment device configured to attach a first satellite to the system for positioning satellites in working orbit; a main propulsion device with solid propulsion comprising a plurality of parallel solid-propellant cartridges; a secondary propulsion device which is re-ignitable; at least one position sensor configured to measure the position of said system; a monitoring unit connected to said at least one position sensor and which is configured to control a firing of the cartridges of the main propulsion device to move said system from a transfer orbit to a working orbit of the first satellite, said monitoring unit being further configured to control an opening of the first attachment device to separate said system from the first satellite.