SBIR-STTR Award

An standardized canister and satellite for 6 to 25 Kg satellites is presented. The baseline size is 6U (6 Kg, 30 x 30 x 10 cm). The baseline is expandable to 9U and 2U. An Engineering Design Unit (EDU) that clearly demonstrates the feasibility for the proposed satellite canister concept is outlined. Innovation sufficiently preload the satellite to the canister are shown. A thermal design to beneficially insulate the satellite from extreme temperatures is presented. A standardizing means to fix the dynamic response of the payload is presented. An outline of a standard interface for satellites and and launch veicles is presented.

Benefit:
An inexpensive, broadly useful standard for canisterized satellites to be flown as secondary payloads on a wide range of manned and unmanned launch vehicles. A standard larger and more capable than the existing 3U satellite (3 Kg, 30 x 10 x 10 cm) used on canistera like P-POD and substantially smaller than an ESPA class secondary payload (181 Kg, 61 x 61 x 96 cm)

Keywords:
Canisterized Satellite, Operationally Responsive Space, Small Payload, Secondary Payload, Cubesat, Standard.

As a baseline design and with the lessons learned from the EDU built for the Phase I effort, fabricate, test and flight validate a family of proof-of-concept of Canisterized Satellite Dispensers (CSD) based on a common core. This family will include a 1/4U, 3U, 6U and 12U. A 1U is as much as 2.3Kg in mass and is 10x10x10 cm in dimension. Simultaneously, make CSDs very useful to the end-users and launch services by substantially reducing weight, cost, procurement time and increasing ease of use. Write a detailed user’s manual that thoroughly details capabilities and how the CSDs will be used. All the CSDs will be lighter and smaller that competitive design. As a first option, design, build, test and flight validate an Isolated, Rotary Wafer (IRW). Based on the 38.81 inch bolt circle payload interface common to all US unmanned launch vehicles, this 10 inch tall wafer would encapsulate and dispense payloads contained in the CSDs. It would reside between the final stage an the primary payload allowing each launch to attain a greater utility. It would incorporate an vibration isolation system allowing both the primary and secondary payloads a substantial and useful reduction in launch environment loading.

Benefit:
An inexpensive, broadly useful Canisterized Satellites dispensers (CSD) to be flown as secondary payloads on a wide range of manned and unmanned launch vehicles and from within other larger satellites. A substantial increase in the performance of CSDs. A variation in CSDs that are both smaller and larger than currently available. A demonstrated capability that convinces launch service providers of safety and of the low risk of CSDs on their larger missions.

Keywords:
Canisterized Satellite Dispenser, Operationally Responsive Space, Payload, Cubesat, Separation System, Microsatellite