Nanosat Launch Adaptor System Independent Deployment Sequencing

Resolve Bottlenecks,
Find Innovative SolutionsGenerate Solutions

Solution Overview

Problem

The challenge in the space industry is to develop a cost-effective system for launching smallsat/nanosat spacecraft that can safely coexist with primary payloads on shared launch vehicles, ensuring independent deployment and minimizing risks to the primary spacecraft.

Innovation Solution

A nanosat launch adaptor system (NLAS) that includes an adapter assembly and a sequencer with controller boards, power supply, and detectors, allowing for independent deployment sequences and actuation of secondary payloads, decoupling their deployment from the primary payload and launch vehicle.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Productivity

If multiple payloads are deployed using a shared launch vehicle, then the productivity and cost-effectiveness of space launches is improved, but the risk to the primary spacecraft from secondary payload deployment increases

Engineering Contradiction:

Improvelaunch throughputVSAvoidprimary spacecraft safety

Core Design Contradiction:

ProductivityVSReliability

Solution Approach 1:

The deployment system is segmented into independent controller boards, each responsible for a specific payload or deployment function. This modular architecture allows secondary payloads to be controlled independently from the primary spacecraft, enabling simultaneous deployment operations without interfering with primary mission safety.

Inventive Principle:

Principle #1Segmentation

Solution Approach 2:

A dedicated sequencer acts as an intermediary between the launch vehicle and secondary payloads. The sequencer receives commands from the primary spacecraft or ground control and coordinates payload deployments in a controlled sequence, ensuring that deployment operations do not compromise primary spacecraft safety while maximizing launch vehicle utilization.

Inventive Principle:

Principle #24Intermediary (Mediator)

2Device complexity

If secondary payloads are integrated with the primary spacecraft, then the device complexity is reduced, but the reliability of the primary spacecraft is compromised due to potential adverse interactions

Engineering Contradiction:

Improveintegration complexityVSAvoidprimary spacecraft integrity

Core Design Contradiction:

Device complexityVSReliability

Solution Approach 1:

The system divides control functions into separate controller boards for each payload type, with each board having dedicated hardware and software. This segmentation maintains physical and functional separation between primary and secondary payloads, reducing integration complexity while preserving primary spacecraft reliability through independent failure modes.

Inventive Principle:

Principle #1Segmentation

Solution Approach 2:

Each controller board is designed with specialized local quality - specific hardware configurations, power management, and deployment mechanisms tailored to particular payload types. This allows secondary payloads to be integrated without requiring the primary spacecraft to accommodate all payload requirements, maintaining system reliability while managing complexity.

Inventive Principle:

Principle #3Local quality

3Device complexity

If a unified control system is used for all payloads, then the device complexity is minimized, but the ability to independently manage deployment sequences is reduced

Engineering Contradiction:

Improvecontrol system structureVSAvoiddeployment sequence flexibility

Core Design Contradiction:

Device complexityVSAdaptability or versatility

Solution Approach 1:

The sequencer is designed as a universal control system that can manage multiple different payload types through standardized interfaces and controller boards. Each controller board maintains specialized functionality for its specific payload while communicating through a common protocol, providing both structural simplicity and deployment sequence flexibility.

Inventive Principle:

Principle #6Universality (Multi-functionality)

Solution Approach 2:

The control system employs dynamic configuration where controller boards can be selectively activated or deactivated based on the specific mission requirements and payload combinations. This allows the system to adapt its complexity level - operating as a simplified unified system when possible, or expanding to more granular control when deployment sequence flexibility is required.

Inventive Principle:

Principle #15Dynamics

Data Source

PatentUS11305896B1System and methods for deploying payloads

Publication Date: 2022.04.19 UNITED STATES OF AMERICA AS REPRESENTED BY THE ADMINISTRATOR NAT AERONAUTICS & SPACE ADMINISTRATION

AI summary

Embodiments of the present invention include systems for launching primary or secondary payloads or actuating other launch vehicle or payload or instrumentation devices. The system includes an adapter assembly and at least one sequencer mounted to the adapter assembly. The sequencer includes: controller boards, each of the controller boards having a controller for controlling deployment of the payloads and data files; output ports coupled to the controller boards and configured to transmit signals from the controller boards to dispensers therethrough, deployment mechanisms containing the payloads, the adapter assembly having channels for accommodating the dispensers; and a detector coupled to the controller boards and adapted to detect an external signal and, in response to the external signal, to send an initiation signal to the controller boards. The system also includes at least one power supply coupled to the sequencer and adapted to provide an electrical power to the sequencer.