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Pekka Janhunen

Publications and source records attributed to Pekka Janhunen.

At least 19 recordsLinked to original sources

Launching mass from the Moon helped by lunar gravity anomalies

Normally a passive object launched from the Moon at less than the escape velocity orbits the Moon once and then crashes back to the launch site. We show that thanks to lunar gravity anomalies, for specific launch sites and directions, a passive projectile can remain in lunar orbit for up to 9 Earth days. We find that such sites exist at least on the lunar equator for prograde equatorial orbit launches. Three of the sites are located on the lunar nearside. We envision that this can be used to lift material from the Moon at low cost because it gives prolonged opportunities for an active spacecraft to catch the projectile. Passive projectiles can be made entirely from lunar material so that a stream of Earth-imported parts is not needed. To reduce the mass and cost of the launcher, the projectile mass can be scaled down with a corresponding increase in the launch frequency. The projectile launcher itself can be a coilgun, railgun, superconducting quenchgun, sling or any other device that can give a projectile an orbital speed of about 1.7 km/s.

physics.pop-ph

Terraforming the dwarf planet: Interconnected and growable Ceres megasatellite world

We analyse a megasatellite settlement built from Ceres materials in high Ceres orbit. Ceres is selected because it has nitrogen, which is necessary for an earthlike atmosphere. To have $1 g$ artificial gravity, spinning habitats are attached to a disk-shaped megasatellite frame by passively safe magnetic bearings. The habitats are illuminated by concentrated sunlight produced by planar and parabolic mirrors. The motivation is to have a settlement with artificial gravity that allows growth beyond Earth's living area, while also providing easy intra-settlement travel for the inhabitants and reasonably low population density of 500 /km$^2$. To enable gardens and trees, a 1.5 m thick soil is used. The soil is upgradable to 4 m if more energy is expended in the manufacturing phase. The mass per person is $10^7$ kg, most of which is lightly processed radiation shield and soil. The goal is a long-term sustainable world where all atoms circulate. Because intra-settlement travel can be propellantless, achieving this goal is possible at least in principle. Lifting the materials from Ceres is energetically cheap compared to processing them into habitats, if a space elevator is used. Because Ceres has low gravity and rotates relatively fast, the space elevator is feasible.

physics.pop-ph

Shielded dumbbell L5 settlement

We present a two-sphere dumbbell configuration of a rotating settlement at Earth-Moon L5. The two-sphere configuration is chosen to minimize the radiation shielding mass which dominates the mass budget. The settlement has max 20 mSv/year radiation conditions and 1 g artificial gravity. If made for 200 people, it weighs 89000 tonnes and provides 60 m$^2$ of floorspace per person. The radiation shield is made of asteroid rock, augmented by a water layer with 2 % of the mass for neutron moderation, and a thin boron-10 layer for capturing the thermalized neutrons. We analyze the propulsion options for moving the material from asteroids to L5. The FFC Cambridge process can be used to extract oxygen from asteroid regolith. The oxygen is then used as Electric Propulsion propellant. One can also find a water-bearing asteroid and use water for the same purpose. If one wants to avoid propellant extraction, one can use a fleet of electric sails. The settlers fund their project by producing and selling new settlements by zero-delay teleoperation in the nearby robotic factory which they own. The economic case looks promising if LEO launch costs drop below $\sim$ \$300/kg.

physics.pop-ph

Particle Telescope aboard FORESAIL-1: simulated performance

The Particle Telescope (PATE) of FORESAIL-1 mission is described. FORESAIL-1 is a CubeSat mission to polar Low Earth Orbit. Its scientific objectives are to characterize electron precipitation from the radiation belts and to observe energetic neutral atoms (ENAs) originating from the Sun during the strongest solar flares. For that purpose, the 3-unit CubeSat carries a particle telescope that measures energetic electrons in the nominal energy range of 80--800 keV in seven energy channels and energetic protons at 0.3--10 MeV in ten channels. In addition, particles penetrating the whole telescope at higher energies will be measured in three channels: one $>$800 keV electron channel, two integral proton channels at $>$10 MeV energies. The instrument contains two telescopes at right angles to each other, one measuring along the spin axis of the spacecraft and one perpendicular to it. During a spin period (nominally 15 s), the rotating telescope will, thus, deliver angular distributions of protons and electrons, at 11.25-degree clock-angle resolution, which enables one to accurately determine the pitch-angle distribution and separate the trapped and precipitating particles. During the last part of the mission, the rotation axis will be accurately pointed toward the Sun, enabling the measurement of the energetic hydrogen from that direction. Using the geomagnetic field as a filter and comparing the rates observed by the two telescopes, the instrument can observe the solar ENA flux for events similar to the only one so far observed in December 2006. We present the Geant4-simulated energy and angular response functions of the telescope and assess its sensitivity showing that they are adequate to address the scientific objectives of the mission.

astro-ph.IM

Natural illumination solution for rotating space settlements

Cylindrical kilometre-scale artificial gravity space settlements were proposed by Gerard O'Neill in the 1970s. The early concept had two oppositely rotating cylinders and moving mirrors to simulate the diurnal cycle. Later, the Kalpana One concept exhibited passively stable rotation and no large moving parts. Here we propose and analyse a specific light transfer solution for Kalpana One type settlements. Our proposed solution is technically reliable because it avoids large moving parts that could be single failure points. The scheme has an array of cylindrical paraboloid concentrators in the outer wall and semi-toroidal reflectors at the equator which distribute the concentrated sunlight onto the living surface. The living cylinder is divided into a number of $φ$-sections (valleys) that are in different phases of the diurnal and seasonal cycles. To reduce the mass of nitrogen needed, a shallow atmosphere is used which is contained by a pressure-tight transparent roof. The only moving parts needed are local blinders installed below the roof of each valley. We also find that settlements of this class have a natural location at the equator where one can build multi-storey urban blocks. The location is optimal from the mass distribution (rotational stability) point of view. If maximally built, the amount of urban floorspace per person becomes large, up to 25,000 m$^2$, which is an order of magnitude larger than the food-producing rural biosphere area per person. Large urban floorspace area per person may increase the material standard of living much beyond Earth while increasing the total mass per person relatively little.

physics.pop-ph

Control of habitat's carbon dioxide level by biomass burning

Consider a free-space settlement with a closed ecosystem. Controlling the habitat's carbon dioxide level is a nontrivial problem because the atmospheric carbon buffer per biosphere area is smaller than on Earth. Here we show that the problem can be solved by burning agricultural waste. Waste biomass is stored and dried, and burned whenever plant growth has lowered the atmospheric carbon dioxide level so that replenishment is needed. The method is robust, low-tech and scalable. The method also leaves the partial pressure of oxygen unchanged. In the initial growth phase of the biosphere, one can obtain the carbon dioxide by burning sugar or carbon, which can be sourced from carbonaceous asteroid materials. This makes it possible to bootstrap the biosphere without massive biomass imports from Earth.

physics.pop-ph

Steam balloon concept for lifting rockets to launch altitude

Launching orbital and suborbital rockets from a high altitude is beneficial because of e.g. nozzle optimisation and reduced drag. Aeroplanes and gas balloons have been used for the purpose. Here we present a concept where a balloon is filled with pure water vapour on ground so that it rises to the launch altitude. The system resembles a gas balloon because no onboard energy source is carried and no hard objects fall down. We simulate the ascent behaviour of the balloon. In the baseline simulation, we consider a 10 tonne rocket lifted to an altitude of 18 km. We model the trajectory of the balloon by taking into account steam adiabatic cooling, surface cooling, water condensation and balloon aerodynamic drag. The required steam mass proves to be only 1.4 times the mass of the rocket stage and the ascent time is around 10 minutes. For small payloads, surface cooling increases the relative amount of steam needed, unless insulation is applied to the balloon skin. The ground-filled steam balloon seems to be an attractive and sustainable method of lifting payloads such as rockets into high altitude.

physics.pop-ph

TI tether rig for solving secular spinrate change problem of electric sail

The electric solar wind sail (E-sail) is a way to propel a spacecraft by using the natural solar wind as a thrust source. The problem of secular spinrate change was identified earlier which is due to the orbital Coriolis effect and tends to slowly increase or decrease the sail's spinrate, depending on which way the sail is inclined with respect to the solar wind. Here we present an E-sail design and its associated control algorithm which enable spinrate control during propulsive flight by the E-sail effect itself. In the design, every other maintether ("T-tether") is galvanically connected through the remote unit with the two adjacent auxtethers, while the other maintethers ("I-tethers") are insulated from the tethers. This enables one to effectively control the maintether and auxtether voltages separately, which in turn enables spinrate control. We use a detailed numerical simulation to show that the algorithm can fully control the E-sail's spin state in real solar wind. The simulation includes a simple and realistic set of controller sensors: an imager to detect remote unit angular positions and a vector accelerometer. The imager resolution requirement is modest and the accelerometer noise requirement is feasible to achieve. The TI tether rig enables building E-sails that are able to control their spin state fully and yet are actuated by pure tether voltage modulation from the main spacecraft and requiring no functionalities from the remote units during flight.

astro-ph.IM

Thrust vectoring of an electric solar wind sail with a realistic sail shape

The shape of a rotating electric solar wind sail under the centrifugal force and solar wind dynamic pressure is modeled to address the sail attitude maintenance and thrust vectoring. The sail rig assumes centrifugally stretched main tethers that extend radially outward from the spacecraft in the sail spin plane. Furthermore, the tips of the main tethers host remote units that are connected by auxiliary tethers at the sail rim. Here, we derive the equation of main tether shape and present both a numerical solution and an analytical approximation for the shape as parametrized both by the ratio of the electric sail force to the centrifugal force and the sail orientation with respect to the solar wind direction. The resulting shape is such that near the spacecraft, the roots of the main tethers form a cone, whereas towards the rim, this coning is flattened by the centrifugal force, and the sail is coplanar with the sail spin plane. Our approximation for the sail shape is parametrized only by the tether root coning angle and the main tether length. Using the approximate shape, we obtain the torque and thrust of the electric sail force applied to the sail. As a result, the amplitude of the tether voltage modulation required for the maintenance of the sail attitude is given as a torque-free solution. The amplitude is smaller than that previously obtained for a rigid single tether resembling a spherical pendulum. This implies that less thrusting margin is required for the maintenance of the sail attitude. For a given voltage modulation, the thrust vectoring is then considered in terms of the radial and transverse thrust components.

astro-ph.IM

CubeSat testing of Coulomb drag propulsion

In Coulomb drag propulsion, a long high voltage tether or system of tethers gathers momentum from a natural plasma stream such as solar wind or ionospheric plasma ram flow. A positively polarised tether in the solar wind can be used for efficient general-purpose interplanetary propellantless propulsion (the electric solar wind sail or E-sail), whereas a negatively polarised tether in LEO can be used for efficient deorbiting of satellites (the plasma brake). Aalto-1 is a 3-U cubesat to be launched in May 2016. The satellite carries three scientific experiments including 100 m long Coulomb drag tether experiment. The tether is made of four 25 and 50 micrometre diameter aluminium wires that are ultrasonically bonded together every few centimetre intervals. The tether can be charged by an onboard voltage source up to one kilovolt positive and negative. The Coulomb drag is measured by monitoring the spin rate.

astro-ph.IM

Boltzmann electron PIC simulation of the E-sail effect

The solar wind electric sail (E-sail) is a planned in-space propulsion device that uses the natural solar wind momentum flux for spacecraft propulsion with the help of long, charged, centrifugally stretched tethers. The problem of accurately predicting the E-sail thrust is still somewhat open, however, due to a possible electron population trapped by the tether. Here we develop a new type of particle-in-cell (PIC) simulation for predicting E-sail thrust. In the new simulation, electrons are modelled as a fluid, hence resembling hydrid simulation, but in contrast to normal hybrid simulation, the Poisson equation is used as in normal PIC to calculate the self-consistent electrostatic field. For electron-repulsive parts of the potential, the Boltzmann relation is used. For electron-attractive parts of the potential we employ a power law which contains a parameter that can be used to control the number of trapped electrons. We perform a set of runs varying the parameter and select the one with the smallest number of trapped electrons which still behaves in a physically meaningful way in the sense of producing not more than one solar wind ion deflection shock upstream of the tether. By this prescription we obtain thrust per tether length values that are in line with earlier estimates, although somewhat smaller. We conclude that the Boltzmann PIC simulation is a new tool for simulating the E-sail thrust. This tool enables us to calculate solutions rapidly and allows to easily study different scenarios for trapped electrons.

astro-ph.IM

Safety criteria for flying E-sail through solar eclipse

The electric solar wind sail (E-sail) propellantless propulsion device uses long, charged metallic tethers to tap momentum from the solar wind to produce spacecraft propulsion. If flying through planetary or moon eclipse, the long E-sail tethers can undergo significant thermal contraction and expansion. Rapid shortening of the tether increases its tension due to inertia of the tether and a Remote Unit that is located on the tether tip (a Remote Unit is part of typical E-sail designs). We analyse by numerical simulation the conditions under which eclipse induced stresses are safe for E-sail tethers. We calculate the closest safe approach distances for Earth, Moon, Venus, Mars, Jupiter, Ceres and an exemplary 300 km main belt asteroid Interamnia for circular, parabolic and hyperbolic orbits. We find that any kind of eclipsing is safe beyond approximately 2.5 au distance, but for terrestrial planets safety depends on the parameters of the orbit. For example, for Mars the safe distance with 20 km E-sail tether lies between Phobos and Deimos orbits.

astro-ph.IM

EMMI - Electric Solar Wind Sail Facilitated Manned Mars Initiative

The novel propellantless electric solar wind sail concept promises efficient low thrust transportation in the Solar System outside Earth's magnetosphere. Combined with asteroid mining to provide water and synthetic cryogenic rocket fuel in orbits of Earth and Mars, possibilities for affordable continuous manned presence on Mars open up. Orbital fuel and water enable reusable bidirectional Earth-Mars vehicles for continuous manned presence on Mars and allow smaller fuel fraction of spacecraft than what is achievable by traditional means. Water can also be used as radiation shielding of the manned compartment, thus reducing the launch mass further. In addition, the presence of fuel in the orbit of Mars provides the option for an all-propulsive landing, thus potentially eliminating issues of heavy heat shields and augmenting the capability of pinpoint landing. With this E-sail enabled scheme, the recurrent cost of continuous bidirectional traffic between Earth and Mars might ultimately approach the recurrent cost of running the International Space Station, ISS.

astro-ph.IM

Electric sail control mode for amplified transverse thrust

The electric solar wind sail produces thrust by centrifugally spanned high voltage tethers interacting with the solar wind protons. The sail attitude can be controlled and attitude maneuvers are possible by tether voltage modulation synchronous with the sail rotation. Especially, the sail can be inclined with respect to the solar wind direction to obtain transverse thrust to change the osculating orbit angular momentum. Such an inclination has to be maintained by a continual control voltage modulation. Consequently, the tether voltage available for the thrust is less than the maximum voltage provided by the power system. Using a spherical pendulum as a model for a single rotating tether, we derive analytical estimations for the control efficiency for two separate sail control modes. One is a continuous control modulation that corresponds to strictly planar tether tip motion. The other is an on-off modulation with the tether tip moving along a closed loop on a saddle surface. The novel on-off mode is introduced here to both amplify the transverse thrust and reduce the power consumption. During the rotation cycle, the maximum voltage is applied to the tether only over two thrusting arcs when most of the transverse thrust is produced. In addition to the transverse thrust, we obtain the thrusting angle and electric power consumption for the two control modes. It is concluded that while the thrusting angle is about half of the sail inclination for the continuous modulation it approximately equals to the inclination angle for the on-off modulation. The efficiency of the on-off mode is emphasized when power consumption is considered, and the on-off mode can be used to improve the propulsive acceleration through the reduced power system mass.

astro-ph.IM

Coulomb drag devices: electric solar wind sail propulsion and ionospheric deorbiting

A charged tether or wire experiences Coulomb drag when inserted into flowing plasma. In the solar wind the Coulomb drag can be utilised as efficient propellantless interplanetary propulsion as the electric solar wind sail (electric sail, E-sail). In low Earth orbit (LEO) the same plasma physical effect can be utilised for efficient low-thrust deorbiting of space debris objects (the plasma brake). The E-sail is rotationally stabilised while the deorbiting Coulomb drag devices According to numerical estimates, Coulomb drag devices have very promising performance figures, both for interplanetary propulsion and for deorbiting in LEO. Much of the technology is common to both applications. E-sail technology development was carried out in ESAIL FP7 project (2011-2013) which achieved TRL 4-5 for key hardware components that can enable 1 N class interplanetary E-sail weighing less than 200 kg. The thrust of the E-sail scales as inverse solar distance and its power consumption (nominally 700 W/N at 1 au) scales as the inverse distance squared. As part of the ESAIL project, a continuous 1 km sample of E-sail tether was produced by an automatic and scalable "tether factory". The manufacturing method uses ultrasonic wire to wire bonding which was developed from ordinary wire to plate bonding for the E-sail purpose. Also a "Remote Unit" device which takes care of deployment and spin rate control was prototyped and successfully environmentally tested. Our Remote Unit prototype is operable in the solar distance range of 0.9-4 au. The 1-U CubeSat ESTCube-1 was launched in May 2013 and it will try to measure the Coulomb drag acting on a 10 m long tether in LEO when charged to 500 V positive or negative. A more advanced version of the experiment with 100 m tether is under preparation and will be launched in 2015 with the Aalto-1 3-U CubeSat to polar LEO.

astro-ph.IM

Simulation study of the plasma brake effect

The plasma brake is a thin negatively biased tether which has been proposed as an efficient concept for deorbiting satellites and debris objects from low Earth orbit. We simulate the interaction with the ionospheric plasma ram flow with the plasma brake tether by a high performance electrostatic particle in cell code to evaluate the thrust. The tether is assumed to be perpendicular to the flow. We perform runs for different tether voltage, magnetic field orientation and plasma ion mass. We show that a simple analytical thrust formula reproduces most of the simulation results well. The interaction with the tether and the plasma flow is laminar (i.e., smooth and not turbulent) when the magnetic field is perpendicular to the tether and the flow. If the magnetic field is parallel to the tether, the behaviour is unstable and thrust is reduced by a modest factor. The case when the magnetic field is aligned with the flow can also be unstable, but does not result in notable thrust reduction. We also fix an error in an earlier reference. According to the simulations, the predicted thrust of the plasma brake is large enough to make the method promising for low Earth orbit (LEO) satellite deorbiting. As a numerical example we estimate that a 5 km long plasma brake tether weighing 0.055 kg could produce 0.43 mN breaking force which is enough to reduce the orbital altitude of a 260 kg object mass by 100 km during one year.

astro-ph.IM

Fast E-sail Uranus entry probe mission

The electric solar wind sail is a novel propellantless space propulsion concept. According to numerical estimates, the electric solar wind sail can produce a large total impulse per propulsion system mass. Here we consider using a 0.5 N electric solar wind sail for boosting a 550 kg spacecraft to Uranus in less than 6 years. The spacecraft is a stack consisting of the electric solar wind sail module which is jettisoned roughly at Saturn distance, a carrier module and a probe for Uranus atmospheric entry. The carrier module has a chemical propulsion ability for orbital corrections and it uses its antenna for picking up the probe's data transmission and later relaying it to Earth. The scientific output of the mission is similar to what the Galileo Probe did at Jupiter. Measurements of the chemical and isotope composition of the Uranian atmosphere can give key constraints to different formation theories of the Solar System. A similar method could also be applied to other giant planets and Titan by using a fleet of more or less identical probes.

astro-ph.IM

An intrinsic way to control E-sail spin

We show that by having the auxtethers made partly or completely of conducting material and by controlling their voltages, it is possible to control the spin rate of the electric solar wind sail by using the electric sail effect itself. The proposed intrinsic spin rate control scheme has enough control authority to overcome the secular change of the spin rate due to orbital Coriolis effect.

astro-ph.IM