Satellite Stacked Launch Orbit Raising Optimization
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Solution Overview
Problem
Conventional launch vehicle payload configurations are inefficient in accommodating multiple spacecraft within a single fairing and optimizing orbit raising capabilities, leading to increased costs and reduced payload capacity when each spacecraft performs separate orbit transfer maneuvers.
Innovation Solution
A stacked launch configuration where the first satellite handles most or all orbit transfer maneuvers, utilizing high specific impulse electric propulsion or high thrust bipropellant equipment, while the second satellite uses monopropellant thrusters or cold gas thrusters, optimizing propulsion system capability across the payload stack through quantitative design parameter optimization.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If each spacecraft performs separate orbit transfer maneuvers, then each spacecraft maintains independent orbit raising capability, but total propulsion system mass and costs increase
Solution Approach 1:
The patent combines the orbit raising operations of multiple spacecraft into a single coordinated maneuver. The primary spacecraft performs the orbit transfer while the secondary spacecraft is passively transported, merging what would traditionally be separate propulsion functions into one shared operation. This reduces the total propulsion system mass required across the payload stack.
Solution Approach 2:
The primary spacecraft's propulsion subsystem is designed to serve multiple functions: it provides orbit raising capability not only for itself but also for the secondary spacecraft. This multi-functionality allows a single propulsion system to accomplish what would traditionally require separate propulsion systems on each spacecraft.
2Quantity of substance
If conventional stacked dual-launch configurations are used, then two spacecraft are accommodated within a single fairing, but payload capacity and fairing volume utilization are reduced
Solution Approach 1:
The secondary spacecraft is nested within or attached to the primary spacecraft structure, with the secondary payload being supported by the primary spacecraft's adapter structure. This nested arrangement optimizes the use of fairing volume by efficiently packing multiple spacecraft into the available space without requiring excessive separation distance.
Solution Approach 2:
The patent employs a stacked vertical configuration where spacecraft are arranged along the vertical axis of the fairing rather than side-by-side horizontal arrangement. This dimensional change maximizes the utilization of fairing volume by taking advantage of the height dimension, allowing better packing efficiency.
3Device complexity
If the lower spacecraft supports the upper spacecraft during launch, then load bearing structure is simplified, but the lower spacecraft's payload capacity is reduced
Solution Approach 1:
The load bearing function is segmented between the launch vehicle adapter structure and the primary spacecraft structure. The primary spacecraft's adapter serves as an intermediate load-bearing element that connects to both the launch vehicle and the secondary payload, distributing the structural requirements and minimizing the impact on the primary spacecraft's payload capacity.
4Productivity
If quantitative optimization of design parameters is performed, then orbit transfer maneuver capability is optimized, but design and analysis complexity increases
Solution Approach 1:
The patent systematically varies key design parameters such as the mass ratio between primary and secondary spacecraft, the allocation of propellant mass, and the timing of separation maneuvers to optimize orbit transfer efficiency. By identifying the critical parameters that most influence performance and systematically optimizing them, the patent achieves high productivity in orbit transfer while managing design complexity through focused parameter optimization rather than exhaustive analysis of all possible design variables.
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 total costs, propulsion system mass, and ground segment requirements, increasing payload performance by optimizing orbit transfer capabilities and fairing volume utilization, allowing simultaneous orbit raising for both spacecraft.
Implementation Method 1
high specific impulse electric propulsion equipment
Implementation Method 2
high thrust bipropellant equipment
Implementation Method 3
monopropellant thruster
Implementation Method 4
cold gas thruster
Data Source
Figure 1A~1C
Figure 1D
Figure 2A~2C
AI summary
A first satellite (210(1)) and a second satellite (210(2)) are configured to be disposed together, in a launch configuration, for launch by a single launch vehicle. The launch vehicle includes a primary payload adapter (225) and the first satellite includes a secondary payload adapter (215). In the launch configuration, the first satellite is mechanically coupled with the primary payload adapter and the second satellite is mechanically coupled with the secondary payload adapter. Following injection into a first orbit by the launch vehicle, the first satellite separates from the primary payload adapter while the second satellite is mechanically coupled with the secondary payload adapter. The second satellite is detached from the secondary payload adapter of the first satellite only after an orbit transfer maneuver executed by a propulsions system of the first satellite. In the launch configuration, the mass of the second satellite is at least 30% of the mass of the first satellite.