Auxiliary Payload Support Unit for Launch Vehicle
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Solution Overview
Problem
Existing launch vehicle systems face challenges in efficiently supporting and managing multiple auxiliary payloads without imposing technical or contractual risks on primary spacecraft missions, particularly in terms of launch schedule delays and coordination complexities.
Innovation Solution
A modular assembly system comprising an aluminum honeycomb core sandwiched between structural skins, with a stiffener and engagement inserts, along with an auxiliary payload support unit that includes a processor and communication interface to coordinate the release of payloads, ensuring seamless integration and control of auxiliary payload launches.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Quantity of substance
If multiple auxiliary payloads are accommodated on a launch vehicle, then the quantity of payloads is increased, but the device complexity increases and coordination between manufacturers becomes more difficult
Solution Approach 1:
The auxiliary payload accommodation system is divided into modular auxiliary payload units (APUs), each being a self-contained module that can be independently configured and tested. Each APU contains its own support structure, separation mechanism, and interface fittings, allowing multiple payloads to be accommodated without increasing overall system complexity.
Solution Approach 2:
The patent creates universal interface fittings and standardized mounting points on the launch vehicle platform that can accommodate different types of auxiliary payloads (pico, nano, micro, or mini spacecraft). The standardized separation interfaces and electrical connections allow the same platform structure to support multiple different payload types without requiring custom integration for each payload.
2Adaptability or versatility
If auxiliary payloads are integrated into the launch vehicle system, then the functionality is enhanced, but the reliability decreases due to technical and contractual risks to the primary spacecraft mission
Solution Approach 1:
The auxiliary payload control system is extracted as a separate auxiliary payload support unit (APSU) that operates independently from the primary spacecraft control systems. The APSU has its own processor and control logic, and communicates through a dedicated single cable interface, isolating any potential failures to the auxiliary payload domain and preventing them from affecting the primary mission.
Solution Approach 2:
The patent introduces an intermediary enable signal mechanism where the launch vehicle platform provides a simple enable/disable command to the APSU, but after that point, the APSU autonomously manages all auxiliary payload operations. This intermediary control layer allows the primary system to initiate auxiliary functions without being burdened by the complexity of ongoing auxiliary payload management, thereby protecting primary mission reliability.
3Ease of operation
If the launch vehicle controls the release sequence of auxiliary payloads, then the coordination is improved, but the communication burden on the launch vehicle increases
Solution Approach 1:
The auxiliary payload support unit is pre-programmed with the complete release sequence and timing parameters before launch. Upon receiving a single enable signal from the launch vehicle, the APSU autonomously executes the pre-planned sequence of separating each auxiliary payload at the appropriate time, eliminating the need for continuous communication or command updates during the release process.
Data Source
AI summary
A platform and launch initiation control system for secondary spacecraft for a launch vehicle includes an aluminum honeycomb core sandwiched between top and bottom structural aluminum skins and strengthened by a spider-like stiffener. Spool inserts for engaging the secondary spacecraft are arranged on the platform. A computer processor based auxiliary payload support unit (APSU) is provided on the platform and receives power and enable signals through a single cable from the LV to permit the APSU to control the release of the secondary spacecraft transparently to the LV without impacting LV operations.