Patent Publication Number: US-2022240363-A1

Title: Static eliminator

Description:
TECHNICAL FIELD 
     The present invention relates to a static eliminator. 
     BACKGROUND ART 
     Airplanes have many static dischargers installed on their wings and reduce static electricity through self-discharge. On high-altitude aircraft that fly in low pressure environments, dischargers are particularly effective since discharge is more likely to occur than at ground level according to Paschen curves. On the other hand, since helicopters have rotors that rotate at high speed, it is difficult to install static dischargers with sharp protruding parts because people will come close to the fuselage. Satellites and space probes have surfaces covered with metal, and when unavoidable, it is recommended that a conductive coating is applied to a dielectric to set the entire surface at the same potential. Although creeping discharge will not occur when the entire surface is at the same potential, as before, it is not possible to prevent dielectric breakdown of the dielectric between the surface and internal electric circuits. 
     Japanese Laid-open Patent Publication No. 2005-267962 (Patent Literature 1) states that although conventional surface discharge suppression technology has used a conductive material or a conductive coating in order to prevent charging from occurring, many conductive materials used on satellites are expensive and also prone to exfoliation and dissociation of the coating material. In addition, there are the disadvantages of difficult handling and difficult application in only parts with a uniform and flat surface. Patent Literature 1 discloses a low-cost and simple configuration that suppresses the influence of surface discharge through the provision of a discharge electrode in the periphery of the dielectric. That is, the discharging apparatus disclosed in Patent Literature 1 includes a conductive panel, a dielectric that covers one surface of the panel, and a discharge electrode that has one end electrically connected to the panel and another end that overhangs the surface of the dielectric that is not in contact with the panel. 
     SUMMARY OF INVENTION 
     For objects that are difficult to ground, mostly aerospace devices and in particular satellites and space probes (spacecraft) in outer space, it is necessary to eliminate static electricity to prevent failures that would be caused by such static electricity. That is, since an aerospace device cannot be grounded, the fuselage is susceptible to becoming charged with static electricity, which will damage electrical equipment used for communication or the like. In particular, since satellites and space probes are surrounded by a vacuum, it is difficult to reduce static electricity through self-discharge (that is, corona discharge). When there is a large potential difference between the surface of the fuselage and internal electric circuits, the dielectric positioned in between becomes damaged due to dielectric breakdown (insulation breakdown). For this reason, there are many examples of satellites that have stopped operating unexpectedly. Also, when conductive areas are spread out on the surface of the fuselage and potential differences are produced between these conductive areas, creeping discharge will occur at the dielectric located at the boundaries, resulting in gradual damage to the fuselage. When a dielectric on the surface of the fuselage becomes charged, the dielectric will itself undergo dielectric breakdown due to the discharge between the dielectric and the periphery. When these phenomena occur in a solar cell panel, the operating life will be limited. 
     In the example in Patent Literature 1 described above, although a spacecraft as a whole will have a potential of several kV due to the inflow and outflow of space particles during orbit, since the dielectric floats with respect to the potential of the spacecraft, the dielectric will have a different potential to the potential of the spacecraft as a whole. When the potential difference between the spacecraft potential and the potential of the dielectric reaches 400V or more, discharge that occurs between the dielectric and fibrous discharge electrodes are used to try to eliminate the potential difference between the spacecraft potential and the potential of the dielectric. However, it is believed that with the discharging apparatus in Patent Literature 1, creeping discharge will occur at the surface and electric charge will be absorbed and reduced by ejected plasma, but since the surface is converted into plasma and destroyed, there is the risk that long-term operation may not be possible. In addition, at orbital altitudes of several hundred km or more, as examples, at low earth orbit (LEO, an altitude of 2000 km or less) to medium earth orbit (MEO, an altitude of 2000 km to geosynchronous orbit (35,786 km)), and also at higher orbital altitudes, there is a large decrease in ambient pressure. This means that the discharge starting voltage will rise to several thousand kV or higher, which effectively prevents discharge from starting, and even if discharge does occur, there is a risk of breakage due to the resulting discharge voltage. 
     One aspect of the present invention is a static eliminator (electrostatic eliminator, static elimination equipment, static eliminator apparatus, static eraser, static electricity eliminating device) including: a first conductor that is electrically connected to at least a part of a static elimination target object; and a dielectric shell that is exposed to an external space and forms, between the first conductor and the dielectric shell, a first space in which a first gas (first type of gas) providing a condition of lowering a discharge starting voltage is sealed. By sealing the gas for the predetermined condition in the first space, this static eliminator can maintain a discharge starting voltage that is unaffected by the conditions in the external space. Accordingly, it is possible to use the surface potential of the static elimination target object to cause electric discharge inside the first space with an electric field in the external space that passes through the dielectric shell. Discharge is a phenomenon where energy such as heat, electromagnetic waves, and sound is released, so that electrical energy is converted into other types of energy and released. This means that by causing electric discharge in the first space, static electricity can be removed from a static elimination target object that has become charged with static electricity, which lowers the surface potential of the static elimination target object. 
     The dielectric shell may be dome-shaped, spherical, or ellipsoidal. This makes it easy to withstand the difference in pressure relative to the external space. The dielectric shell may cover at least 50% of the surface area of the first space. The dielectric shell may be exposed in a state of protruding into the external space and without contacting other objects. This makes it easier for the influence of the electric field in the external space to be reflected in the first space through the dielectric shell. 
     The exterior space is typically outer space or space on a planet or satellite with lacking atmosphere. The dielectric shell may be translucent. Even in a vacuum where it is difficult to release energy such as heat and sound to the outside, it is easy for discharge to release energy to the external space in the form of electromagnetic waves (light). The dielectric shell may form a first space that includes the first conductor in the center or inside, the first conductor may cover a part or parts of the surface of the first space, and may form a part or parts of the first space. That is, the first conductor may or may not form a part of the container that acts together with the dielectric shell to seal the gas. 
     The first conductor may be detachably attached to the static elimination target object, and the first conductor may be a part of the static elimination target object. The static eliminator may have a discharge electrode that is installed inside the first space and is electrically connected to the first conductor. This makes it easy to further lower the discharge starting voltage. One favorable example of a discharge electrode is a wire-shaped electrode formed in an upright arc. 
     Another aspect of the present invention is a static elimination target object including the static eliminator described above. The static elimination target object may have a dielectric shell that forms a first space, between at least a part of a surrounding structure of the static elimination target object and an external space, in which a gas providing a condition of lowering (reducing) a discharge starting voltage is sealed. The static elimination target object may be any object whose surface potential may rise due to static electricity. 
     Examples include automobiles, ships, human bodies and their accessories, portable electric devices, and electronic circuits. Since it is often difficult to ground a moving object, it is particularly effective to provide the static eliminator described above with a moving object as the static elimination target object. The most suitable example of a static elimination target object is an aerospace device that travels in a space where it is difficult to release static electricity to the external space. 
    
    
     
       BRIEF DESCRIPTION OF DRAWINGS 
         FIG. 1  is a perspective view schematically depicting an example static eliminator. 
         FIG. 2  is a perspective view schematically depicting the static eliminator, when looking from a bottom surface. 
         FIG. 3  is a cross-sectional view schematically depicting the configuration of the static eliminator. 
         FIG. 4  is a diagram depicting some examples of Paschen curves. 
         FIG. 5  is a diagram schematically depicting an example of a satellite on which static eliminators have been mounted. 
         FIG. 6  is a perspective view depicting another example of a static eliminator. 
         FIG. 7  is a cross-sectional view schematically depicting the configuration of the apparatus depicted in  FIG. 6 . 
         FIG. 8  is a perspective view depicting yet another example of a static eliminator. 
         FIG. 9  is a perspective view depicting yet another example of a static eliminator. 
         FIG. 10  is a perspective view depicting yet another example of a static eliminator. 
         FIG. 11  is a cross-sectional view depicting yet another example of a static eliminator. 
         FIG. 12  is a perspective view depicting yet another example of a static eliminator. 
         FIG. 13  is a cross-sectional view depicting yet another example of a static eliminator. 
     
    
    
     DESCRIPTION OF EMBODIMENTS 
       FIG. 1  depicts an outline of an example static eliminator.  FIG. 2  depicts a state where the static eliminator has been removed from an object, and  FIG. 3  schematically depicts the configuration of the static eliminator by way of a cross-sectional view in a state where the static eliminator is attached to the object. The static eliminator (electrostatic eliminator, static elimination equipment, static eliminator apparatus, static eraser, static electricity eliminating device, eliminator apparatus or static electricity eliminator apparatus)  10  is an apparatus that is attached to the surrounding structure (outer shell, exterior, outer wall, outer wall surface or outer structure)  3  of a static elimination target object  1 , such as a satellite. The static eliminator  10  includes a first conductor  11  that is electrically connected to at least a part of the static elimination target object (elimination target, elimination target object or static electricity elimination target object)  1 , which in this example is the surrounding structure  3 , and a dielectric shell  15  that forms a first space  13  between itself and the first conductor  11  where a first gas (that is, a first type of gas)  12  is sealed for providing (satisfying, establishing) a condition of lowering (reducing) a discharge starting voltage. The dielectric shell  15  is provided so as to be exposed to a space (external space)  9  outside the elimination target  1 . 
     In this eliminator  10 , a closed container  16  in which the gas  12  is sealed is constructed by the first conductor  11 , which is shaped as a plate and forms a bottom portion (base plate), and the dielectric shell  15 , which is dome-shaped and attached onto the first conductor  11 . The eliminator  10  is fixed to the static elimination target object  1  by attaching the first conductor  11 , which protrudes or widened (extended) around the dielectric shell  15  in the form of a flange, to the conductive outer structure  3  using rivets  19 , mounting screws, conductive adhesive, or the like. At the same time, the first conductor  11  becomes electrically connected to the outer structure  3  of the static elimination target object  1 . 
     The gas  12  sealed in the first space  13  of the static eliminator  10  is a noble gas (rare gas) such as argon, helium, neon, xenon, or krypton, an inert gas containing noble gas, nitrogen gas, or the like, or a mixture (or mixed gas) containing at least one of these gases. The gas is adjusted so that the pressure (that is, the internal pressure of the container  16 ) is 0.5 to 20 Torr (50 to 3000 Pa), or further adjusted to 1 to 10 Torr (100 to 1500 Pa) for example. One example of a mixed gas is a Penning mixture containing a quench gas (buffer gas) in addition to a noble gas (a glowing gas) as a main component. A gas that satisfies these conditions is one example of the first gas  12  that lowers or reduces the discharge starting voltage, and may contain other components or may be a gas composed of other components. It is also possible to adjust the pressure according to the components of the gas to lower the discharge starting voltage. 
       FIG. 4  depicts the Paschen curves of a number of gases. According to Paschen&#39;s law, the discharge starting voltage V is given as a function f(pd) of the product of the gas pressure p and the gap (distance) between the electrodes (d). In view of the need to cause discharge in cm units inside the first space  13  of the eliminator  10 , it is desirable for a first gas  12  that contains an inert gas to be sealed in the first space  13  in the range of pressures stated above. 
       FIG. 5  depicts one example where a plurality of static eliminators  10  have been provided on a satellite as the static elimination target object  1 . According to the dominant view, electric discharge (as one example, lightning) is an electric current. On the other hand, electric discharge emits energy such as heat, electromagnetic waves, and sound. Paradoxically, it can be said that when electric discharge occurs, electrical energy, and more specifically, the surface potential of an object that has become charged with static electricity, is lowered. This means that by attaching the eliminator  10  to an object that is difficult to electrically ground, in most cases aerospace devices, and in particular a satellite or space probe in outer space, as the static elimination target object  1 , it is possible to cause electric discharge in the gas  12  sealed in the closed space  13  using the surface potential which derives from the static electricity accumulated in the object  1 . This means that static electricity at the static elimination target object  1  can be reduced or eliminated by releasing the energy through discharge at the eliminator  10 . 
     The dielectric shell  15  may be a wall body formed of a material that allows an electric field in the periphery (external space)  9  to easily penetrate in the first space  13  in which the gas  12  is sealed, and may construct all or part of a container (pressure container or sealed container). In the eliminator  10 , a space electric field (potential difference) relative to the first conductor  11  is formed by an electric field (electrical field) that has penetrated or passed through or via the dielectric shell  15  and entered the first space  13 . This means that in the eliminator  10 , self-discharge occurs inside the first space  13 , which is an environment that facilitates self-discharge, at a much lower potential difference than in the external space  9 . 
     It is desirable that the dielectric shell  15  is protruding into the external space  9  from the outer structure  3  of the static elimination target object  1  and exposed in a non-contract state with (without contact with) other objects. According to experiments and computer simulations, discharge is facilitated when the first space (discharge region)  13  where the discharge occurs protrudes outward beyond the outer structure (outer surface, fuselage surface)  3  of the target  1 . On the other hand, when the dielectric shell  15  is positioned inside a recess formed in the outer structure (a metal surface)  3 , a strong electric field is unlikely to form and electric discharge is unlikely to occur. 
     To efficiently emit or release electromagnetic waves (light) that have been generated by discharge, the dielectric shell  15  may use a translucent member made of a dielectric material, for example, a transparent resin or glass as a transparent member. In particular, glass materials, such as quartz glass and heat-resistant glass (borosilicate glass), are resistant to deteriorate and have a small coefficient of thermal expansion, which makes them ideal for satellites that are cyclically exposed to high and low temperatures. A material, such as germanium glass and chalcogenide glass, that easily transmits infrared rays may be used, and is suited to releasing heat generated in the first space  13  where discharge occurs to the external space  9 . The dielectric shell  15  may cover at least 50% of the surface area of the first space  13  where discharge occurs, which makes it easy for external electric fields to penetrate into the first space  13 . 
     Although there are no particular limitations on the shape of the dielectric shell  15 , the upper part may be hemispherical (dome-shaped), spherical, ellipsoidal, semi-ellipsoidal, or the like in order to withstand the pressure difference between the gas  12  sealed inside the dielectric shell  15  and the outside  9 . The thickness of the dielectric shell  15  may also be selected with consideration to the pressure difference and leakage of the gas  12 . In addition, the material and structure of the dielectric shell  15  may be selected with consideration to the heat generated by discharge. In outer space in particular, heat is emitted or released only by radiation. For this reason, the dielectric shell  15  may also be transparent to infrared rays. To ensure a sufficient amount of energy is released by the discharge, it is desirable to provide a certain volume as the first space  13  where the discharge occurs, so that the dielectric shell  15  may have a diameter (or major axis, diagonal length, or representative length) in a range of several mm to several tens of cm, where the lower limit of the representative diameter (or length) may be 5 mm, 10 mm, or 20 mm and the upper limit may be 500 mm, 300 mm, or 100 mm. The sizes of the dielectric shell  15  and the eliminator  10  may be larger than or smaller than the sizes given above depending on the size of the elimination target object  1 . 
     The first conductor  11  and the dielectric shell  15  of the static eliminator  10  may be made of different materials, or a part of an integral member, for example, a part of the dielectric shell  15 , may be treated so as to become conductive and used as the first conductor  11 . As will be described later, the first conductor  11  may be a part of the static elimination target object  1 , for example, part of a conductive outer structure or wall  3 . The first conductor  11  may be a metal or may be a transparent electrode, such as graphene or indium tin oxide. One part of the static elimination target object  1  to which the static eliminator  10  is connected is typically a conductive part or a part that has been treated with a coating or the like so as to become conductive. 
     If the entire surface of an aerospace device, which is the static elimination target object  1 , does not have an equal potential, the eliminators  10  may be installed on the equipotential parts respectively. The size of the eliminator or eliminators  10  and the number of installed eliminators  10  can be appropriately selected according to the expected buildup of static electricity and the amount of energy derived from discharge. When an aerospace device  1  that cannot be grounded becomes charged with static electricity, the absolute value of the surface potential of the conductive outer surface  3  will rise. When the absolute value of the surface potential reaches a discharge starting voltage in keeping with the state of the gas  12  in the sealed cover (dielectric shell)  15 , discharge will occur in the gas  12 . This discharge emits energy, such as heat, electromagnetic waves (light), and sound. From the viewpoint of the law of conservation of energy, surface potential will drop in place of the released energy. This results in the elimination of static electricity from the aerospace device  1 . 
     Note that the phenomenon referred to as “discharge” for this eliminator  10  is a phenomenon where a gas exposed to a strong electric field is converted to plasma. The discharge that occurs or generated in the eliminator  10  may be creeping discharge along the dielectric shell  15 , may be one-electrode discharge (single-electrode discharge, mono-electrode discharge, also referred to as “corona discharge” or “St. Elmo&#39;s fire”), or may be self-discharge that accompanies conversion of a gas to plasma. When a plurality of aerospace devices  1  approach each other, electric fields are formed in the external space  9  due to differences between the respective surface potentials, and electric discharges will occur in the first spaces  13  of the static eliminators  10  so as to resolve or moderate the electric fields. As a result, it is possible to reduce the risk of discharge occurring between a plurality of aerospace devices  1 . 
       FIG. 6  schematically depicts the construction of a different example of the static eliminator  10  by way of a perspective view, and  FIG. 7  schematically depicts the construction by way of a cross-sectional view. In addition to the static eliminator described above, this static eliminator  10  has discharge electrodes  17  which are installed in the first space  13  inside the sealed cover (dielectric shell)  15  and are connected to the elimination target object  1 , for example, to the conductive outer surface (conductive outer structure)  3  of an aerospace device. The discharge electrodes  17  may be attached to the outer surface (surrounding structure)  3  of the aerospace device  1 . 
       FIGS. 8 to 10  depict example static eliminators  10  equipped with discharge electrodes  17  of different shapes. Discharge occurs according to the density of the lines of electric force. This means that with a static eliminator  10  equipped with one or more discharge electrodes  17  that protrude as depicted in  FIGS. 6 and 7 , an edge-shaped discharge electrode  17  as depicted in  FIG. 8 , or a thin wire-shaped discharge electrodes  17  as depicted in  FIGS. 9 and 10 , it is possible to achieve an effect of increasing the density of the electric lines of force in the first space  13  and lowering the discharge starting voltage. Accordingly, it is possible to cause or generate discharge in the first space  13  more easily, even when the potential difference (electric field) in the external space  9  is small, which makes it possible to lower the surface potential of the aerospace device  1  as much as possible. 
     In particular, a thin wire-shaped discharge electrode  17  formed in an upright arc shape that is erected on the substrate (first conductor)  11  as depicted in  FIG. 10  is one of the examples that had the greatest effect in facilitating or generating discharge in experiments compared to other electrode shapes. In the eliminator  10 , since the electric lines of force are likely to become concentrated at the electrodes  17 , this lowers the discharge starting voltage as much as possible and improves the performance in eliminating static electricity. One example of the discharge electrode  17  is a tungsten wire with a diameter of around 0.01 to 0.05 mm that has been formed into a semicircular shape with a diameter of around 5 to 20 mm or around 8 to 15 mm. The glass dielectric shell  15  is a semi-ellipsoid with a major axis of around 30 to 50 mm and a minor axis of around 10 to 40 mm. The size of this embodiment of eliminator  10  including the substrate (base or first conductor)  11  has a long side of 60 to 80 mm, a short side of 25 to 55 mm, and a height of around 10 to 35 mm, and can be easily attached even to a small satellite. 
     The shape of the discharge electrode  17  is not limited to the shapes described above, and may be any shape that can increase the density of the electric lines of force. To make the discharge electrode  17  resistant to wear and corrosion, tungsten, which has a high melting point, may be subjected to gold plating. To efficiently emit the generated electromagnetic waves, parts of the bottom surface (first conductor)  11 , aside from the discharge electrodes  17 , that contact the gas  12  may be a mirrored surface. In a static eliminator  10  provided with one or more discharge electrodes  17 , the discharge electrodes  17  function as the first conductor  11 . For this reason, it is sufficient for the discharge electrode(s)  17  and the outer surface (outer structure)  3  of the aerospace device, which is the static elimination target object  1 , to be electrically connected, and the part that forms the periphery of the first space  13  does not need to be electrically conductive. That is, the first space  13  may be formed by the dielectric shell  15  only. 
       FIG. 11  depicts yet another example of the static eliminator  10 . In this static eliminator  10 , the first conductor  11  is constructed of a part of the static elimination target object  1 , so that the static eliminator  10  is integrated with the static elimination target object  1 . In more detail, in this static eliminator  10 , a flange-shaped mounting portion  15   a  provided around the dome-shaped dielectric shell  15  is fixed to the conductive outer surface (conductive outer structure)  3  of the aerospace device that is the static elimination target object  1  using rivets  19  or the like with a ring-shaped seal  18  in between. By installing the dielectric shell  15  in an exposed state so as to protrude from the outer structure  3  without contacting other objects, a discharge region (sealed space or first space)  13  is formed so as to protrude from the outer structure  3 . If the mounting portion  15   a  is made of metal, the mounting portion  15   a  may be welded to the outer structure  3  without using a ring-shaped seal. After this, the gas  12  is sealed in the first space  13  formed between the dielectric shell  15 , which is the sealing cover, and the outer structure  3  by any method so as to be at a pressure where the discharge starting voltage can be minimized. As one example, a method may be used where a hole is formed in a part of the dielectric shell  15 , the dielectric shell  15  is evacuated, the gas is sealed inside, and the dielectric shell  15  is then closed. As the gas  12 , an inert gas, such as neon or argon, which is believed to hardly deteriorate due to electric discharge or cosmic rays, may be used to enable long-term use. 
     In this embodiment of static eliminator  10 , the conductive surrounding surface (outer structure, outer shell or exterior)  3  of the aerospace device, which is the target object  1 , contacts the gas  12  in the first space  13 . It is possible to provide a static elimination target object  1 , typically an aerospace device, with a dielectric shell  15  that forms, between at least a part of the surrounding structure  3  and the external space  9 , the first space  13  in which the gas  12  providing or satisfying a condition of lowering the discharge starting voltage is sealed. 
     Unlike the static eliminators  10  depicted in  FIG. 1  or the like, the static eliminator  10  depicted in  FIG. 11  is integrated with the static elimination target object  1  and cannot be attached or detached. The static eliminators  10  of the type where a closed container (or sealed container)  16  is constructed by the dielectric shell  15  or by the dielectric shell  15  and the first conductor  11  can be provided as a separate body to the static elimination target object  1 , can be manufactured and provided in a different manufacturing process, can be mass-produced, and can be provided at low cost. In addition, since the static eliminators  10  can be attached to and detached from the object  1 , even if the static eliminators  10  become damaged by over-discharging, cosmic dust, or the like, it is easy to replace. The task of filling with the gas  12  at the manufacturing site of the aerospace device also becomes unnecessary. A ring-shaped seal  18  is no longer required, and there is no risk of gas leakage due to deterioration of the seal. Since it is not necessary to consider sealing when attaching the static eliminators  10 , the connection with the outer surface of the aerospace device become simplified. As examples, it is possible to attach the static eliminators  10  by using conductive magic tape (registered trademark), conductive adhesive, or the like. If the structure of the static eliminators  10  are standardized, this makes it easier to design aerospace devices. In addition, there are several advantages, such as the ability to add static eliminator  10  to existing aerospace devices. 
       FIG. 12  depicts yet another example of the static eliminator  10 . In cases where the static elimination target object  1  is vulnerable to electromagnetic noise that accompanies electric discharge, electrically connecting the static eliminator  10  and the static elimination target object  1  with a pole  11   a , a conductive wire, or the like makes it possible to install the static eliminator  10  away from the static elimination target object  1 , for example, the fuselage of space equipment. 
       FIG. 13  depicts yet another example of the static eliminator  10 . In this static eliminator  10 , the first space  13  is formed around a first conductor  11  that also serves as the discharge electrode  17  by a spherical dielectric shell  15  (that is, the dielectric shell only). The discharge electrode  17  is connected to the static elimination target object  1  by a conductive support  11   a , a conductive wire, or the like. 
     Note that although the embodiments of static eliminator  10  whose appearances are dome-shaped or spherical have been described above, it is sufficient for the static eliminator  10  to have a shape, such as an ellipsoid or an even flatter shape, that is capable of internally forming the first space  13 . In particular, for use in an environment with an atmosphere, the upper surface of the apparatus  10  may be installed so as to be as flat as possible on the fuselage, which is the static elimination target object  1 , so as not to affect aerodynamics. The static elimination target object  1  may be a wall body of an aerospace system, equipment, device or the like, a mounted apparatus, or the like. As the static elimination target object  1 , the eliminator  10  may be installed on a structure or vehicle or the like, which is installed in a space on a satellite, such as a planet, moon, or the like where there is no or lacking atmosphere and elimination of static electricity is difficult. 
     As described above, the static eliminator or the static eliminator apparatus  10  described above can have a satellite or a space probe as the target object  1  for elimination of static electricity. Objects in outer space are normally incapable of reducing static electricity through self-discharge, but this becomes possible with the static eliminator  10 . The static eliminator  10  functions even in the vacuum of outer space, and is capable of lowering the surface potential of an aerospace device and preventing the occurrence of failures in electrical equipment. Since the static eliminator  10  can lower the surface potential of the aerospace device, it is possible to simplify the insulation between the surface and the internal electric circuits, which contributes to reductions in weight. Since the conductive areas are spread out on the outer surface of an aerospace device, the static eliminator  10  may be installed at the respective conductive positions to lower the surface potential, which makes it possible to prevent creeping discharge at the dielectric between the conductive parts of the outer surface and prevent damage that accompanies such discharge. Since the static eliminator  10  does not depend on the polarity of the static electricity generated in the aerospace device and will cause further discharge to occur automatically according to the strength of the static electricity, no control or electric power is required. This static eliminator  10  will be effective for preventing electric discharge from occurring when aerospace devices come into contact with each other or when people or objects on the ground come into contact with an aerospace device. 
     The target object for the elimination of static electricity by the static eliminator  10  is not limited to an aerospace device. The static eliminator  10  is also effective for objects that move, such as automobiles, ships, and human bodies and their accessories, portable electric devices, electronic circuits, and the like since it is often difficult to ground such objects. For an electronic circuit, it is possible to eliminate a surge voltage by installing the static eliminator  10  on a circuit pattern. When a rescue operation is performed using a helicopter, a conductive rope is first placed in contact with the ground to reduce static electricity, but when the grounding is incomplete, the rescuer may receive an electric shock causing him/her to fall over or fall to the ground. The static eliminator  10  is capable of eliminating static electricity without having dangerous parts, such as protrusions and edges for self-discharge, exposed to the outside, which increases safety. 
     The static eliminator  10  disclosed above is an apparatus with a closed space  13  in which a gas  12  is sealed and is disposed so that the gas  12  is exposed to the surface potential of the static elimination target object  1 . The structure including the first space  13  in which the gas  12  is sealed may be configured as a gas container that can be attached to and detached from the static elimination target object  1 . A discharge electrode or electrodes  17  may be installed inside the closed space  13  and may be electrically connected to the conductive surface of the static elimination target object  1 . By using the static eliminator  10 , discharge is caused in the gas  12  inside the enclosed space by the surface potential of the static elimination target object  1 , which makes it possible to eliminate static electricity from the static elimination target object by releasing energy through discharge. 
     Although specific embodiments of the present invention have been described above, various other embodiments and modifications will be conceivable to those of skill in the art without departing from the scope and spirit of the invention. Such other embodiments and modifications are addressed by the scope of the patent claims given below, and the present invention is defined by the scope of these patent claims.