In this paper it is presented the concept and design of a new type of spacecraft that could be used to make the rst manned interstellar travel. Solar one would integrate three near-term technologies, namely: the US Navy CFR fusion reactor, a larger version of NASA's Sunjammer light sail, and an array of DE-STAR laser systems. A system of Fresnel lenses and exible mirrors to propel the sail with sunlight is suggested as an alternative to this array. With a mile-long light sail, Solar One could reach an average of 22 percent the speed of light, arriving to the closest potentially habitable exoplanet in less than 19 years with the help of a Bussard scoop. Key challenges are reducing the weight of continuous-wave lasers and compact fusion reactors as well as achieving cryo-sleep and arti cial gravity. Key words: solar sails, light sails, breakthrough starshot, laser propulsion, interstellar travel. 1 Introduction Several light-sail spacecrafts have already been tested. Some examples are Light- Sail 1 and LightSail 2, from the Planetary Society. However, these light-sails are propelled by sun light, and the solar radiation pressure is very small (just 6.7 Newtons per gigawatt, which equals to 9 Newtons/km2or 1,400 watts/m2at 1 AU). Lasers can provide radiation pressures much higher than the Sun, unless Fresnel lenses are used. Previous experiments with directed-energy weapons have proved successful. The Boeing YAL-1, a spacecraft equipped with a Kilowatt-laser, was able to deliver a power density over 100 watts/cm2at a distance of 1 km (US Air Power, 2008). In 2016, scientists announced the rst design for a beamed-powered spacecraft that could reach speeds of 0.2c. The project, called StarShot, entailed the idea of sending 1,000 nanocrafts with light sails attached that would be powered by a 100 GW laser array. As of today, the concept is still considered to be the best option for unmanned interstellar travel. Potentially habitable exoplanets such as Proxima b could be reached in only 20 years. However, the idea is to send the Starshot nanocrafts 1 AU away from Proxima b. This distance would be enough to photograph the exoplanet, but perhaps not 1 sucient to notice the presence of a possible intelligent civilization less advanced than humanity. For this reason, and to better study the exoplanet, a manned interstellar spaceship becomes necessary. The proposal more similar to Solar One was presented by Robert Forward in 1984. Forward proposed a 64-tonne and 30-km payload sail surrounded by a 644- tonne and 100-km decelerator sail, launched by a 7.2-Terawatt laser system to reach 21 percent the speed of light. As the spacecraft approaches Alpha Centauri, another 26-TW laser is pointed towards a 1000-km Fresnel lens that decelerates the spacecraft. Another similar proposal is the Laser Powered Interstellar Rocket (Jackson, 1978). In this case, a laser array beams to a collector on the spacecraft, without the use of a light sail. 2 Concept Solar One is a design for a manned spaceship that would be powered by beamed and photon propulsion. The name `Solar One' has been chosen to better represent our civilization: the term `Solar' refers to the solar system and the term `One' refers to the rst design of a possible eet of future spaceships. Three are the technologies that would be used: the US Navy CFR nuclear fusion reactor, a slightly larger version of the NASA's Sunjammer light sail, and a laser system called DE-STAR (Directed Energy System for Targeting of Asteroids and exploRation). Firstly, the US Navy CFR (Compact Fusion Reactor) is a mobile unit that could provide one Terawatt of power (Forbes, 2019). Instead of using large su- perconducting magnets, this reactor uses small conical dynamic fusors (Salvatore Pais, 2018). Solar One would carry a 1-Terawatt reactor on board to power the laser system needed for deceleration. The system would have to incorporate radiators to dissi- pate the heat. Lockheed Martin has already suggested the possibility of building 200-ton reactors of 200 Megawatts (Besa Center, 2018). Although this would be far from what Solar One needs, it would be a starting point. Antimatter would be a better source of energy for the laser. Only a few mil- ligrams of antimatter could yield power densities in the Terawatt order. To pro- duce the antimatter needed, an engine such as the VARIES Mk 1 could generate Schwinger antiparticle pairs directly from the vacuum (Next Big Future, 2012). The problem with this resides in the fact that a laser in the Petawatt order would be needed. The matter-antimatter GeV gamma ray laser proposed by Winterberg in 2012 could also be used to decelerate Solar One, but creating the antimatter needed would be dicult with current technology. Secondly, the Sunjammer light sail is a proposed NASA sail with a size of 38 x 38 m (1,444 square meters) (NASA, 2017). Solar One would need a 1 mile-light 2 sail (1,609 by 1609 meters). A robust structure would be needed to support such light sail. Thirdly, DE-STAR is a 100-GW proposed laser intended for asteroid destruction and beamed-power propulsion. Solar One would need 260 of these Terawatt lasers in order to achieve the power output suggested by Forward (1984) of 26 TW. The laser system could be placed either on Earth or a Lagrange point. Current DE- STAR proposals would be useless for Solar One, but more powerful and lighter versions of the system could be used. To accelerate the spacecraft, an alternative solution would be to use Fresnel lenses 85 meters wide, which could collect around 10 MW/m2. A system of exible mirrors would be needed to continuously focus the light into the sail. The problem is that more than 2.5 million lenses would be needed to propel a one-mile sail. Therefore, it would probably be easier to build just one lens of around 137 km able to provide 26 TW of power, or several lenses of an intermediate size. Another alternative would be to build and place on Earth a large parabolic mirror able to gather those 26 TW of power needed. In order to obtain such energy, a 137-km mirror would be needed. The problem in this case is that at least two primary mirrors would be needed, one on each side of the Earth. The light would be sent to a exible secondary mirror placed in orbit or a Lagrange point. As it was mentioned before, Solar One would have a 1-TW laser system at the front of the cockpit in order to decelerate at destination using photon propulsion. The spacecraft would need 10 DE-STAR lasers in order to achieve the required power output. A similar project called HELLADS (High Energy Liquid Laser Area Defense System) has a target mass of 5 tons for a 1 MW-laser (5 kg per kW) (Air Force Technology, 2018). Although this is, again, far from what Solar One needs, it could be a starting point. Carrying the necessary nuclear fuel on board might not be the best option. As in the Bussard Ramjet, it would be possible to collect hydrogen from space with a scoop placed at the front of the cockpit. The electromagnetic elds produced would drastically reduce the time of deceleration. To accelerate Solar One, if we use the power output of 26 TW suggested by Forward (1984), a 500-mm laser placed at a Lagrange point and with, for example, a divergence of 0.07owould produce an irradiance of more than 10 MW/m2. These calculations were made with an online calculator provided by Kvant lasers (2020), a company specialized in lasers.1 1Full value not shown for laser power. 3 Figure 1: Power density at the beginning of the acceleration Source: Kvant Lasers Due to the square inverse law, as the spacecraft moves away from the laser, the power density reduces. To maintain the same power density all the time, it would be necessary to incorporate in the laser system an automatic parabolic mirror that would gradually increase its diameter in order to reduce the divergence of the beam to a value close to zero. The mirror could be formed by several small mirrors, each of them with a speci c orientation every time. An alternative would be to place the mirrors outside the laser system, or even in space. Figure 2: Power density at the end of the acceleration Source: Kvant Lasers The idea behind Solar One is to combine the three projects. A 4-crew spaceship with a target mass of 300 tons could be powered by a mile-long light sail and 4 achieve the speed of 0.3c with a constant acceleration during the rst 5 years of the trip. The major breakthrough would have to come for reducing the mass of both the nuclear reactor and laser. Portable Terawatt pulsed laser systems such as Teramobile have already been built, but Solar One would need a continuous-wave laser. No light sail is able to re ect 100 percent of the light. A carbon bre sail with a re ectivity of 90 percent and able to withstand 2,770 K could be used. Such sail would have a density of 2.65 g/cc, a thickness of 1 micron, and a total mass of 10.7 tons.2The resulting force is calculated with the following equation: F= 2(PA)=c F= 2(10 ;043;6302;588;881)=300;000;000 F= 173 ;345 newtons F* = force / thrust (newtons) P*= power (watts / m2) A*= surface area of light sail (m2) c* = speed of light The acceleration obtained would be 0.57 m/s2: a = F =M a = 173 ;345=300;000 a = 0:57 m=s2 a* = acceleration (m/s2) M* = mass (kg) And it would take almost 5 years to reach 0.3 c (89 million m/s): t = v=a t = 89 ;940;000=0:57 t = 155 ;659;397 sec = 4 ;9 years For the deceleration, considering that photons have a thrust to power ratio of 3.34 x 109newtons per watt, the 1-TW laser system would provide the following opposite force: F= 11012watts 3:34109= 3;340 N 2Calculations made with this Solar Sail Calculator: http://www.georgedishman.f2s.com/solar/Calculator.html. 5 To use the power and deceleration time just mentioned, the spacecraft would have to detach from the light sail, ideally just after the acceleration stage nishes. The deceleration with the laser and without light sail would be 0.011 m/s2: a = F =M a = 3;340=289;300 a = 0:011 m =s2 Considering that a proton-proton fusion reaction can produce up to 645 TW, 3.8 grams of hydrogen per second would provide a thrust similar to during the acceleration. The density of hydrogen atoms is about one H-atom per cubic cen- timeter. For the scoop to generate the electromagnetic elds, an annular copper cylinder coated with a layer of superconducting tin-niobium alloy (Nb3Sn) has already been proposed. The device would only measure 400 meters in length and 800 meters in diameter, providing an e ective diameter of 10,000 kilometers (Mat- lo , 1974). Considering that a 1,000-km e ective scoop would weight around 200 tons and collect 60 grams of hydrogen per second at 0.15c, a 10,000-km e ective scoop would weight less than 1 ton and collect 600 grams. In order to collect 3.8 grams per second, the physical scoop would only have to be a few meters wide. Moreover, using the photon rocket on-board to ionize the hydrogen would in- crease the amount of fuel scooped and reduce the size of the scoop. The CNO cycle would reduce the fusion reactor size to at least 10 times in dimension (Centauri Dreams, 2020). The electromagnetic elds would help to decelerate the spacecraft. The drag is calculated with the following equation (Zubrin, 1990): d = m v d = 0;003844;969;000 d = 170 ;882 N d* = drag (N) m* = mass of collected hydrogen (kg/s) v* = average speed during deceleration (m/s) This force together with the force produced by the photon rocket would be 174,222 Newtons. The resulting acceleration would be 0.6 m/s2, and it would take 4,75 years to stop a spacecraft travelling at 0.3c. t = v=a t = 89 ;940;000=0:6 t = 149 ;940;000sec = 4 ;75years 6 At an average speed of slightly more than 0.22 c, the crew would arrive to the Alpha Centauri system in slightly less than 19 years. The spacecraft would be either accelerating or decelerating during half of the travel. Average speed = 0 :510:15 + 0:490:3 = 0:2235 c 0.51* = percentage of trip time during acceleration and deceleration 0.15* = average speed during acceleration and deceleration 0.49* = percentage of trip time with constant speed 0.3* = cruise speed Duration of the trip to Alpha Cen = Distance / Average speed = 4 :24=0:2235 18.9 years 3 Design The spaceship would be composed of the following main elements: a laser sys- tem, a light sail, a nuclear micro-reactor, a Bussard scoop, and a cockpit protected from space radiation. An extra amount of light sail would be ideal in case of dam- age caused by micro-meteorites. Detaching the sail after the acceleration stage would be ideal to reduce weight for the deceleration. The spacecraft could be located behind the light sail, as in the following image. Figure 3: Solar One Illustrations made by Marco Purich 7 During the acceleration, the light of the laser re ected by a primary mirror placed inside the laser system would be sent to a secondary parabolic or hyperbolic mirror that would also gradually change its form in order to give the divergence needed at any given moment. Instead of using xed mirrors, they could gradually change their orientation in order to change the divergence of the beam. However, as it was mentioned before, these mirrors could be placed outside the laser system. The light sail could be placed in the middle of the sail instead of behind, reducing the amount of structure needed and probably the overall weight of the spacecraft. As with the spacecraft collecting fuel from space, the ideal would be to use sunlight to propel the light sail. Several systems composed by one Fresnel lens and two parabolic mirrors could be sent to di erent places of the Solar System. As they rotate around the Sun, each of them would be aimed at the light sail of Solar One during a speci c time. These mirrors would also have to gradually change their orientation to continuously keep the laser beam focused. Figure 4: Solar One - From right to left, nuclear reactor, cockpit, laser system, and Bussard scoop Illustration made by Marco Purich Once the destination is reached, the crew could orbit the exoplanet, take images and send a robot to the surface. If the conditions are safe, the crew could choose to land in order to personally explore the exoplanet. 8 4 Challenges Engineers would likely face several challenges while building Solar One. One of them would be to build a large array of DE-STAR lasers and, most importantly, produce the necessary energy to power them during ve years. Another obstacle would be to reduce the weight of the on-board nuclear reactor and laser system. Other challenges would be to protect all the modules from dust and micro- asteroid impacts, to protect the cockpit from cosmic radiation, to reduce the amount of energy and supplies needed by the crew, and to reduce the e ects of zero gravity. All the modules would have a special shielding. Cryo-sleep would be the most ecient way to make a 19-year trip. In this line, NASA has been working on a cryo-sleep design called TORPOR (Torpor Inducing Transfer Habitat For Human Stasis To Mars) (NASA, 2013). Lastly, rotational simulated gravity has been proposed as a solution to zero gravity. 5 Conclusions In this paper it has been analysed the possibility of building a manned inter- stellar spaceship with a light sail propelled by an external laser system or Fresnel lenses. To decelerate, the spacecraft would use an on-board laser system that would receive the necessary electricity from a small nuclear fusion reactor. This reactor would obtain fuel from a Bussard scoop which, in turn, would help to decelerate the spacecraft. Small modular reactors such as the US Navy CFR have already been patented, large light sails such as Sunjammer have already been built, and directed energy weapons such as DE-STAR have been proposed for interstellar travel. Nuclear fusion is the most near-term technology that could be used to power Solar One. However, research on antimatter propulsion is advancing at a rapid rate. If scientists are able to produce more antimatter than the energy used to generate it, this would be the best way to power Solar One.