CranSpace Idriss SISAÏD Edward ANASTASSACOS Anees AHMAD Laia RAMIÓ Kaitlyn MORRIS Enrique GARCIA BOURNE Daniel PASTOR Mairéad BEVAN Thomas AURIEL Jack LONGLEY International Student Design Competition INSPIRATION MARS Cranspace.com Inspiration Mars Student Design Competition Section 0 Acknowledgments We would like to thank Dr. Jennifer Kingston (Cranfield University) for her support through- out the project, particularly for the advice she gave us regarding cost estimation; Professor Michael J. Rycroft (University of Cambridge) for his keen interest in the project and con- tributions especially with regard to radiation shielding components. We also extend our thanks to Dr. Donald Rapp (former research professor, University of Southern California) for his professional insight and in-depth knowledge specifically regarding radiation related to Mars travel. Furthermore, Dr. Don Boroson (MIT Lincoln Laboratory) for sharing his ex- pertise on laser communication systems and Dr. Arturo Casadevall (Albert Einstein College of Yeshiva University) for his contribution to our understanding of the shielding proper- ties of Melanin Nano-Shells. Finally, we would like to thank Dr. Joseph Hamaker (Senior Cost Analyst - SAIC / The Millennium Group International; former Director of Cost Anal- ysis Division, NASA) for his invaluable contribution to the development of our cost analysis.. We would also like to acknowledge the contributions made to the project by Andrew McMil- lan and Daphne De Jong. i Inspiration Mars Student Design Competition Section 0 Contents 1ReportOverview 1 2 Inflatable Space Habitat 2 2.1 General Assumptions and Considerations of Sundancer . 2 2.1.1 Specifications . 2 2.2 AdvantagesandDisadvantages. 4 3 Radiation Shielding 5 3.1 Radiation and Water . 6 3.2 WasteManagementSystem . 11 3.2.1 Waste Collection and Delivery . 11 3.3 ApplicationofMelanin .............................. 12 3.4 SPE Events . 13 3.5 MagneticFieldProbe............................... 13 3.6 SPE Shelter . 13 4 Internal Housing and ECLSS 14 4.1 Bubble Configuration . 14 4.2 Food Management . 16 4.2.1 FoodRequirements ............................ 16 4.2.2 Food Storage . 17 4.3 WasteManagementConfiguration. 17 5 Communications 18 5.1 Traditional Communications System . 18 5.2 Remote Communications System . 19 5.3 CommunicationSatelliteDesign . 20 5.3.1 Design Drivers . 20 5.3.2 Design . 20 5.3.3 AddedPayloads.............................. 21 5.3.4 Structure . 22 5.3.5 Power . 22 6 Science 24 6.1 Extended Boom and General Sensors . 24 6.2 Analysis of the e↵ectivenessofMelaninNano-shells . 24 ii Inspiration Mars Student Design Competition Section 0 6.3 The E↵ects of Deep Space Radiation on the Growth of Plants . 24 6.4 CrewActivity................................... 25 6.4.1 Psychological evaluation . 25 6.5 Laser-based Communication System Demonstration and Mars Reconaissance 25 6.5.1 Technology Demonstration . 25 6.5.2 Scientific Observations . 25 6.5.3 Earth Re-entry . 26 7 Launch Vehicles 26 7.1 Launcher Comparison . 26 7.2 MaximumNumberofLaunchesandLEOLaunchMass . 27 7.3 In-Orbit Propulsion . 27 7.3.1 Delta-V Budget . 27 7.3.2 In-SpacePropulsionSystem . 28 8Reentry 29 8.1 Reentry Vehicle Configurations . 29 8.2 Reentry Trajectory . 30 8.3 HeatFlux ..................................... 31 8.4 HeatLoad..................................... 32 8.5 TPS material . 32 9 Electrical Power Systems 33 9.1 Dragon . 33 9.1.1 Power Generation . 33 9.1.2 Energy Storage . 33 9.2 Sundancer . 34 9.2.1 Power Consumption . 34 9.2.2 Life Support . 34 9.2.3 Waste Management . 34 9.2.4 Communications . 35 9.2.5 CrewActivities/Science. 35 9.3 PowerGeneration................................. 35 9.3.1 Case A . 36 9.3.2 Case B . 36 9.4 Energy Storage . 36 iii Inspiration Mars Student Design Competition Section 0 10 Cost Evaluation 37 10.1Firstapproach................................... 37 10.2 Detailed Cost Study - QuickCost 5.0 Model . 37 10.2.1 Main Spacecraft . 37 10.2.2 CommunicationsSatellite . 38 10.3 QuickCost Results . 39 10.4 Cost Scheduling . 39 10.5 Validation . 39 10.5.1 Communicationssatellite. 39 10.6 Mainspacecraft-NAFCOMWeight-BasedModel . 40 11 Mission Phases and Scheduling 42 11.1 Development Schedule . 42 11.2 Launch and Docking Schedule . 43 11.2.1 Launch and mass distribution . 43 11.2.2 Launch sequence . 44 11.2.3 Docking and in-orbit assembly . 44 11.3 Interplanetary Events . 45 11.4 Risk mitigation and 2021 launch window . 47 12 Conclusion 48 iv Inspiration Mars Student Design Competition Section 1 1ReportOverview The following report proposes a design for a two-person Mars fly-by mission to be launched in 2018. Building on the foundation laid out by Inspiration Mars, Cranspace has sought to resolve areas of weakness and propose the designs outlined in this report. The key ar- eas addressed include the provision of a suitable environment for the crew, ensuring safety from radiation, the identification of science experiments that can be carried on board, and an analysis of the re-entry phase, whilst ensuring that the cost of the mission is as low as possible. Other areas such as launch vehicles and propulsion systems are discussed as they need to accommodate these systems. As minimising the cost of the mission is one of the main overall objective, o↵-the-shelf technologies and structures have been incorporated wherever possible. One such structure is the Sundancer Inflatable Habitat by Bigelow Aerospace. As Bigelow has ceased development of the Sundancer in favour of developing the larger BA 330 module, the cost analysis in this report has allocated funding for the completion of its development []. However, this cost will be greatly reduced as Bigelow has used similar technology to develop the BA 330. The Sundancer will contain six bubble rooms that will accomodate the astronauts. The purpose of these bubbles is primarily radiation protection. They will be surrounded by water, which will be transferred between one bubble and the next as the crew moves between them. This system will aim to minimise the amount of water needed for shielding on the spacecraft. For further shielding, the waste management system will treat solid waste and store within tubes around the spacecraft. The radiation shielding and waste management systems are areas for which development costs will be higher. The mission will also carry a small satellite carrying a laser communication payload that will enable a high data transmission rate during the interplanetary trajectory. This satellite will be left in Martian orbit as a future communications relay from the Red Planet. SpaceXs Dragon capsule was chosen as a re-entry vehicle. Minor modifications will be required to resist the high re-entry velocity. A literary survey of materials used in re-entry has been made. The mission will employ four Falcon Heavy launches, and will cost an estimated 2.1 to 2.85 billion FY14 U.S. dollars. There are a number of constraints that have, so far, limited man’s reach in the solar system and a great many considerations that need to be made in 1 Inspiration Mars Student Design Competition Section 2 order to ensure the well-being of those that take the risk to travel out there. This mission is intended to act as a technological stepping stone, demonstrating the necessary techniques and providing the technologies as the next phase for the human race to finally fulfil the universal dream of establishing an extraterrestrial human colony on Mars. This report considers how to overcome the constraints of interplanetary travel such as galac- tic cosmic rays, solar particle events, waste management problems and the associated cost with a mission of this magnitude. Configurations of primary subsystems are proposed to suit the requirements of the astronauts. Food management is investigated and scientific experiments are suggested to take advantage of the spacecraft’s unique position. Following a comprehensive literary survey of Launch Vehicles, this report outlines the requirements and parameters of the launch configurations, engine specifications, capabilities and payload constraints. For additional information, simulations and videos, please visit our website: http://www.cranspace.com 2 Inflatable Space Habitat CranSpace design proposes the implementation of the Sundancer inflatable module [1] de- veloped at Bigelow Aerospace [2]. Bigelow Aerospace are currently preparing for the first rendezvous of an inflatable spacecraft with the International Space Station [3] providing a system demonstration of the technology to be implemented on-board the Bigelow BA 330 [4] and the Sundancer [1]. The Sundancer has been designed to accommodate up to 3 people in Earth Orbit. This section considers the advantages and disadvantages of implementing the Bigelow Sundancer module and possible modifications to ensure that it is suitable for long-term deep space flight. 2.1 General Assumptions and Considerations of Sundancer The assumptions made of the Sundancer’s capabilities are presented below and are based on the specifications outlined by Bigelow Aerospace [2] (see table 1). 2.1.1 Specifications The assumptions made of the Sundancers capabilities are presented below and are based on the specifications outlined by Bigelow Aerospace (see table 1). 2 Inspiration Mars Student Design Competition Section 2 Occupancy Up to three on a long-term basis Volume 180 m3 Radiation Protection Bigelow Aerospaces shielding is equivalent to or better than the Inter- national Space Station and substantially reduces the dangerous impact of secondary radiation. Ballistic Protection The Sundancer utilises an innovative Micrometeorite and Orbital De- bris Shield. Hyper-velocity tests conducted by Bigelow Aerospace have demonstrated that this shielding structure provides protection superior to that of the traditional aluminium can designs. Propulsion The Sundancer utilises two propulsion systems on the fore and aft of the spacecraft. The aft propulsion system can be refuelled and reused. Electric Power Every Sundancer habitat will include an independent power system comprised of solar arrays and batteries. Avionics Each module will contain an independent avionics system to support navigation, re-boost, docking, and other manoeuvring activities.