Piggyback Satellite Payload Universal Adapter Integration

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Solution Overview

Problem

Current methods for integrating secondary payloads with primary satellites are costly and inflexible, requiring significant redesign and non-recurring costs, especially when integrating payloads into the parent spacecraft during manufacturing, and lack efficient standardized interfaces for easy attachment and detachment.

Innovation Solution

A piggyback satellite payload system utilizing a universal adapter to securely attach at least one secondary payload to the nadir end of a primary satellite, employing an ESPA-compatible adapter cone and clamp band for shock absorption and easy assembly/disassembly, allowing for flexible and cost-effective access to space.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Reliability

If significant-integration is used to install payload hardware during manufacturing of the parent spacecraft, then the payload can be securely integrated into the parent satellite, but non-recurring costs increase due to spacecraft redesign and manufacturing complexity increases

Engineering Contradiction:

Improvepayload integration reliabilityVSAvoidspacecraft manufacturing complexity

Core Design Contradiction:

ReliabilityVSEase of manufacture

Solution Approach 1:

The system is divided into separate modules: the parent spacecraft, the adapter assembly, and the hosted payload. The adapter serves as an independent intermediary component that interfaces with both the parent satellite and the payload, allowing each module to be manufactured and tested separately before integration. This segmentation eliminates the need for redesigning the parent spacecraft manufacturing process while ensuring reliable integration.

Inventive Principle:

Principle #1Segmentation

Solution Approach 2:

A standardized adapter assembly acts as an intermediary between the parent spacecraft and the hosted payload. The adapter includes a first interface that couples to the parent satellite's nadir deck and a second interface that couples to the payload. This intermediary component simplifies the integration process by providing a universal coupling mechanism that does not require modifications to the parent spacecraft manufacturing process.

Inventive Principle:

Principle #24Intermediary (Mediator)

2Reliability

If hosted hardware is integrated during parent spacecraft manufacturing, then secure integration is achieved, but non-recurring costs increase due to redesign requirements

Engineering Contradiction:

Improveintegration securityVSAvoidspacecraft redesign complexity

Core Design Contradiction:

ReliabilityVSDevice complexity

Solution Approach 1:

The adapter assembly is designed with universal interfaces that can accommodate different payload types and parent satellite configurations. The first interface couples to the standardized nadir deck of various parent satellites, while the second interface can accommodate different payload forms factors. This universality eliminates the need for redesigning the parent spacecraft for different payloads, maintaining integration security without increasing redesign complexity.

Inventive Principle:

Principle #6Universality (Multi-functionality)

Solution Approach 2:

By separating the integration function into a standalone adapter assembly rather than integrating it directly into the parent spacecraft, the system allows the adapter to be designed and manufactured independently. This segmentation means the adapter can be optimized for secure integration without requiring changes to the parent spacecraft's design or manufacturing process.

Inventive Principle:

Principle #1Segmentation

3Ease of operation

If standardized adapter interfaces (ESPA, SIV, SET) are used, then ease of attachment and detachment is improved, but device complexity increases due to multiple adapter types

Engineering Contradiction:

Improveattachment and detachment easeVSAvoidadapter interface variety

Core Design Contradiction:

Ease of operationVSDevice complexity

Solution Approach 1:

The adapter assembly incorporates universal coupling mechanisms that can interface with multiple standardized interfaces (ESPA, SIV, SET) through configurable connection elements. The first interface can be configured to match different parent satellite interfaces, and the second interface can accommodate various payload interfaces. This multi-functionality provides ease of operation across different payload types while managing device complexity through a single adaptable design.

Inventive Principle:

Principle #6Universality (Multi-functionality)

Solution Approach 2:

The adapter assembly includes configurable and adaptable connection elements that can be dynamically configured to match different standardized interfaces. The interface configuration can be adjusted based on the specific payload and parent satellite combination, allowing easy attachment and detachment without requiring multiple specialized adapter designs. This dynamic adaptability reduces the need for multiple static adapter types.

Inventive Principle:

Principle #15Dynamics

Data Source

PatentUS7905453B2Piggyback equipment panel payload arrangement, a device for and method of attaching a hosted secondary piggyback payload and adapter to be used for a piggyback secondary payload arrangement for launching the piggyback equipment panel secondary

Publication Date: 2011.03.15 INTELSAT CORP

AI summary

The invention relates to piggyback secondary payloads, a device for and a method of attaching piggyback secondary payloads, including a primary satellite and at least one secondary payload, such as a deployable microsatellite, affixed instrument package or the like, wherein the secondary payload is mounted on the nadir end of the primary satellite, preferably employing a universal adapter between the primary satellite and the at least one secondary payload.