Dispenserless Satellite Bundle for Launch Mass Reduction
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Solution Overview
Problem
The high cost and mass of satellite launches due to the need for complex and heavy dispenser structures that support multiple satellites during launch, which add to the fuel cost and structural rigidity challenges.
Innovation Solution
A dispenserless multi-satellite launch configuration where satellites form a composite beam structure, interconnected with simple connectors to provide stability independently of the launch vehicle, reducing mass and part count, and allowing for a more efficient use of fairing volume.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a conventional satellite launch restraint and dispensing structure is used to support multiple satellites during launch, then the satellites are securely held and dispensed, but the mass of the launch vehicle increases considerably
Solution Approach 1:
The patent removes the central post and dispenser structure from the launch configuration, allowing satellites to be directly attached to the launch vehicle. This extraction of unnecessary components significantly reduces the mass of the launch vehicle while maintaining the ability to securely hold and dispense satellites through direct attachment mechanisms.
Solution Approach 2:
The satellites are configured to attach directly to the launch vehicle without requiring a separate dispenser structure. Each satellite has its own attachment mechanism that interfaces directly with the launch vehicle, making the system self-sufficient and eliminating the need for additional supporting infrastructure.
2Strength
If the satellite launch restraint and dispensing structure is designed with adequate structural rigidity to support satellite weight during launch, then the satellites are securely held, but the mass of the structure increases
Solution Approach 1:
The patent divides the support function into individual satellite attachment points distributed across the launch vehicle, rather than using a single centralized dispenser structure. This segmentation allows each attachment point to be optimized for minimal mass while providing sufficient local support, and the collective arrangement provides overall structural rigidity.
Solution Approach 2:
The patent transitions from a vertical stacking configuration supported by a central post to a distributed arrangement where satellites are attached at multiple points around the launch vehicle. This dimensional redistribution of support points creates structural rigidity through geometric distribution rather than vertical stacking, reducing the need for heavy central support structures.
3Ease of operation
If a complex dispensing mechanism is used to dispense satellites from the restraint and dispensing structure, then the satellites can be released in orbit, but the mass of the structure increases
Solution Approach 1:
The patent extracts the complex dispensing mechanism entirely, replacing it with a simple release system where satellites are held by straightforward attachment mechanisms that can be easily released. This eliminates the need for complex actuators, motors, and control systems while maintaining the ability to dispense satellites in orbit.
Solution Approach 2:
The attachment mechanisms are designed as simple, lightweight, single-use components that secure satellites during launch and are then easily released. These disposable attachment points are much lighter than reusable complex dispensing mechanisms, achieving the same function with minimal mass.
4Productivity
If multiple satellites are launched with one launch vehicle to reduce cost per satellite, then the payload mass increases, but the fuel cost increases considerably
Solution Approach 1:
The patent segments the payload configuration into individually attachable satellites that can be efficiently arranged around the launch vehicle. This segmentation allows for optimal packing density and mass distribution, maximizing the number of satellites per launch while minimizing the additional mass required for support structures, thereby reducing the fuel penalty.
Solution Approach 2:
The patent changes the structural configuration parameters from a centralized dispenser architecture to a distributed direct-attachment architecture. This parameter change reduces the mass fraction of support structures, allowing a higher proportion of the payload mass to be actual satellites rather than support infrastructure, thereby improving the productivity-to-fuel-cost ratio.
Data Source
AI summary
Technology is disclosed for a dispenserless multi-satellite launch configuration in which multiple satellites are interconnected to form a composite beam structure that provides stability independently of the launch vehicle. When in the launch configuration, the satellites are formed into a bundle, where each satellite connects by one or more simple connector along the edges of its inner facing vertical side to the satellite adjacent on each side. This composite beam structure provides a stable launch configuration independently of the launch vehicle. Each of the satellites also has one or more connectors along the bottom edge of the inner facing vertical side allowing the bundle to be attached to a ring type launch vehicle interface. Once launched, the satellites can be dispensed by releasing the connector.