Satellite Propulsion Device for Orbit Insertion
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
The existing methods for launching satellites into geostationary orbit require significant propellant consumption during the second stage, and direct injection methods necessitate more powerful launchers and pose risks of space debris creation and compatibility issues with various launchers.
Innovation Solution
A method involving a propulsion device controlled by the satellite, which is separably attached to the satellite and launcher, injects the satellite into a transfer orbit and then transitions to an intermediate orbit, allowing the satellite to reach the operational orbit using its own propulsion system, thereby reducing propellant consumption and avoiding the need to reignite thrusters or create debris.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If the satellite uses its own propulsion system to complete the journey to geostationary orbit from transfer orbit, then the satellite can reach operational orbit, but two-thirds of the propellants are consumed during the launch stage leaving only one-third for station keeping and mission operations
Solution Approach 1:
The propulsion function is segmented between the launcher's upper stage and the satellite's propulsion system. The upper stage performs the major orbital insertion maneuver, while the satellite's propulsion system is reduced to minimal station-keeping functions, thereby preserving propellant for mission operations
Solution Approach 2:
The upper stage of the launcher performs the preliminary action of injecting the satellite into geostationary orbit directly, eliminating the need for the satellite to perform the energy-intensive transfer orbit insertion maneuver that would consume two-thirds of its propellant supply
2Quantity of substance
If the launcher directly injects the satellite into geostationary orbit, then propellant consumption on the satellite is reduced, but the launcher must be more powerful and the upper stage must reignite thrusters to reach graveyard orbit creating space debris risk
Solution Approach 1:
The harmful function of reigniting thrusters to reach graveyard orbit is extracted from the system. The upper stage is designed to be passively disposed into graveyard orbit without requiring active propulsion, eliminating the space debris risk associated with thruster reignition
Solution Approach 2:
The upper stage is treated as a disposable component that is passively discarded into graveyard orbit after its primary function of direct geostationary orbit injection is completed, eliminating the need for complex active disposal maneuvers
3Productivity
If the upper stage remains attached to the carrying structure in geostationary orbit for double or multiple launches, then satellite deployment is enabled, but the structure cannot be jettisoned and must be kept attached to reach graveyard orbit
Solution Approach 1:
The disposal function is extracted from the upper stage by designing it to be passively disposed without requiring attached carrying structures. The upper stage is separated and disposed independently, simplifying the disposal process while maintaining multiple satellite deployment capability
Solution Approach 2:
Instead of actively maneuvering the upper stage with attached structures to reach graveyard orbit, the approach is inverted: the upper stage is passively disposed while structures are jettisoned in geostationary orbit, reversing the traditional sequence of separation and disposal
4Reliability
If the upper stage encounters a major problem in orbit close to geostationary orbit, then the launcher can remain locked in that orbit, but it may explode and create debris dangerous to geostationary satellites
Solution Approach 1:
The safe disposal action is performed preliminarily by design: the upper stage is configured to be passively disposed into graveyard orbit from the beginning, eliminating the risk of dangerous maneuvers or explosions near geostationary orbit later in the mission
Solution Approach 2:
The system is designed with inherent safety by pre-configuring passive disposal into graveyard orbit, cushioning against the potential harmful effects of active disposal maneuvers that could result in explosions or debris generation near operational satellites
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 method conserves propellant, reduces operational costs, and ensures compatibility with various launchers, while minimizing the risk of space debris and allowing for efficient satellite design and increased payload capacity.
Implementation Method 1
a propulsion device controlled by the satellite is separably attached to the satellite, and the assembly formed by the satellite and the propulsion device is mounted on the launcher before injection of the assembly into a transfer orbit by the launcher
Data Source
AI summary
A method is disclosed for placing a satellite in an operational orbit. The satellite is equipped with its own satellite propulsion system as well as a detachable separate propulsion device. The satellite and separate propulsion device are launched into a transfer orbit by means of a space launcher. The separate propulsion device is controlled by a satellite. The satellite is transferred from the transfer orbit to an intermediate orbit by means of the separate propulsion device. The separate propulsion device is separated from the satellite in the intermediate orbit. The satellite then enters and operational orbit from the intermediate orbit by means of its own satellite propulsion system. The intermediate orbit is disposed between the transfer and operational orbits, and is in relatively close proximity to the operational orbit but is far enough away from the operational orbit to prevent possible interferences.