• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    In a positioning mechanism for space applications with at least one flexible media line (9) for supplying at least one adjustable component, in particular an engine, comprising at least one pivot axis (2) pivotally mounted between two pivoting extreme positions arm (1), the flexible media line ( 9) helically around a pivot axis parallel to the axis (2) coiled helix, the helical media line (9) in a lying between the two pivoting extreme positions starting position at a radial distance from an inside or outside the helical coil arranged cylindrical stop surface (8) of a stop element ( 6) is arranged.
    公开号:AT512487A1
    申请号:T922012
    申请日:2012-01-25
    公开日:2013-08-15
    发明作者:Paul Janu；Christian Neugebauer
    申请人:Ruag Space Gmbh；
    IPC主号:
    专利说明:

    The invention relates to a positioning mechanism for space applications with at least one flexible media line for supplying at least one adjustable component, in particular an engine, comprising a pivotally mounted about at least one pivot axis between two pivoting extreme positions arm.
    Spacecraft engines, e.g. Satellites require a fuel supply to operate. The fuel is supplied to the drivers via at least one media line. In particular, in the case of corrosive fuels or gaseous fuels, e.g. Xenon for electrostatic engines, the media lines are made of steel or titanium alloys. Such media lines can only be subjected to limited stresses and bending moments, so that impermissible bending radii must be avoided.
    Engine adjustment mechanisms serve to adjust the thrust vector of an engine. For example, in many cases it is necessary for the thrust vector of the drive to pass through the center of gravity of the spacecraft so that the spacecraft does not experience an angular momentum which could lead to self-rotation. It must be taken into account that the center of gravity of the spacecraft is subject to changes with increasing fuel consumption.
    Actuating mechanisms generally comprise at least one arm pivotably mounted about at least one pivot axis between two pivoting extreme positions. The pivoting of the arm is accomplished by a servomotor.
    The pivoting of the arm in this case causes an adjustment of the position or orientation of a component, in particular an engine. Due to the pivoting of the arm leading to the component or the engine media line is subjected to bending. From the prior art, various measures are known to limit the bending loads. For example, it is known to form the media line helical, wherein the helix is arranged so that it comes with a pivoting of the arm to a bending transverse to the helical axis. The advantage of this design is the low mass and in that a bending of the helix about two orthogonal axes is possible. Disadvantages are the complicated production of the free coil, the high deformation of the components under sinusoidal load in the natural frequency range of the coil, the high computational effort for the correct design, the limited bending angle (the larger the bending angle, the softer the coil must be and the lower the natural frequency) and the high restoring torque (this requires a high engine and thus heavy engines). Furthermore, this arrangement of the helix is possible only near the axis intersection of the servo motors.
    The invention therefore aims to further develop the leadership of the flexible media line in an actuating mechanism of the type mentioned above that even with large adjustment angles of up to ± 40 ° unacceptably high voltages and impermissible bending moments are avoided on the media line and thus significantly increases the reliability becomes. Furthermore, the invention aims to at least partially meet the following requirements:
    Recording high mechanical vibration loads Enabling large bending angles
    Low resistive torque and low restoring moment The starting position (pivoting position of the pivotable arm when launching the spacecraft from the earth) should not be limited to an extreme positioning angle position Simple design Low mass Simple calculation
    Use of materials approved for space travel
    Low production costs
    To achieve this object, the invention provides that the flexible media line is helically wound about a helical axis parallel to the pivot axis, wherein the helical media line in a lying between the two pivot angle extreme positions start position at a radial distance from an inside or outside the helix arranged cylindrical stop surface a stop element is arranged. The fact that the flexible media line is helically wound around a helical axis parallel to the pivot axis, the bending load of the media line is reduced and at the same time larger swivel angle are allowed. With a pivoting of the pivotable arm, the diameter of the coil changes slightly and caused by this change in diameter bending load is minimal. The higher the number of turns of the helical media line, the lower the mechanical load on the media line at a pivoting of the pivot arm. Preferably, the helical media line comprises at least two, in particular at least three turns.
    The inventive arrangement of the coil results in a high natural frequency, whereby high mechanical loads are possible. Another advantage is that the change in diameter of the helix runs without friction, whereby the pivoting process is only influenced by a possibly, existing restoring moment. The restoring torque can be minimized but easily by a soft design of the media line or the coil.
    Characterized in that the helical media line is disposed in a lying between the two pivot angle extreme positions starting position at a radial distance from at least one stop element, the media line can move radially freely in the start position. This radial freedom of movement allows during operation a pivoting of the pivot arm, starting from the starting position in both directions. The diameter of the helical coil can increase or decrease unhindered during the operation without touching the at least one stop element. Only with larger deformations, for example due to starting vibration, does the media line touch the at least one stop element. The stop element has the function to limit the amplitude of vibration movements of the media line and thus their mechanical stress during the starting phase.
    In this case, the starting position of the swivel arm or the media line is understood to be that position which is set when the spacecraft starts from the earth. When starting high forces and vibrations occur, so that all moving parts of the actuating mechanism must be fixed during start in their respective starting position. For the operation of the positioning mechanism in space fixation of the starting position is canceled by suitable remote controllable release elements. Due to the fact that the starting position according to the invention is located between the pivoting extreme positions, the starting position corresponds to a useful position, so that in case of failure of the mechanism nevertheless a meaningful engine operation - although also without direction vector control - is possible.
    Due to the fact that the stop element arranged inside or outside the helix has a cylindrical stop surface, a Hertzian contact occurs upon contact of the media line and the stop surface, namely a contact between a toroid and a cylinder, whereby the local stresses at the point of contact are minimized in the event of an impact become. The cylindrical abutment surface can be arranged either inside or outside the helix, wherein an arrangement of two abutment surfaces, each with a cylindrical abutment surface - one outside and one within the helix - is conceivable.
    A preferred embodiment of the invention provides that the helical axis coincides with the pivot axis, whereby the bending load of the helical media line is particularly well minimized.
    Preferably, the media conduit is made of steel or a titanium alloy. Preferably, the media line is designed here as a round tube. • «I P« «I * · # I t I p p> p p * p PPP * p
    P PP QP P PP P PP P
    The local stresses in the contact point between the media line and the stop element can be further minimized by the fact that the stop element made of plastic, in particular a high-performance plastic, such. a polyimide or polyetheretherketone (PEEK). On the one hand, such materials are relatively soft and on the other hand offer space-compatible properties.
    The polyimide used is particularly preferably, for example, the material Vespel® SP1 or Vespel® SP3 from DuPont.
    The turns of the helical media line are preferably arranged axially spaced from each other, wherein the axial mobility of the media line is preferably limited by the fact that between adjacent turns of the helical media line in each case at least one spacer is arranged.
    Due to the required redundancy for increasing the reliability, it is usually necessary to provide at least two such media lines, in particular fuel lines per drive. A preferred development provides in this context that a plurality of parallel media lines is helically wound, between each of which at least one axial spacer is arranged.
    The said spacers can in this case be arranged with play between the helical media lines or their turns, which allows, for example, thermal expansion of the media line and its low-friction movement.
    The invention will be explained in more detail with reference to an embodiment schematically illustrated in the drawing. 1 shows a perspective view of the adjusting device and FIG. 2 shows a view according to the arrow II of FIG. 1.
    In Fig. 1, the adjusting mechanism according to the invention is shown, wherein a pivotally mounted arm 1 by means of a bearing not shown about the pivot axis 2 starting from the starting position shown in Fig. 1 in the direction of arrow 3 upwards or in the direction of arrow 4 down can be pivoted. The pivoting of the arm 1 takes place relative to a stationary component 5 shown schematically. With the pivotally mounted arm 1, a coiled stop element 6 is rotatably connected, that rotates in a pivoting of the arm 1 according to the double arrow 7 with the arm 1 about the axis 2 becomes. The coiled stop element 6 has a cylindrical stop surface 8, whose axis coincides with the pivot axis 2.
    On the adjusting mechanism, three parallel media lines 9 are guided with which, for example, fuel from the stationary element 5 can be transported to an arranged on the pivotable arm 1 engine. The media lines 9 are held on the stationary element 5 in a rigidly connected to the stationary member 5 terminal 10. The media lines 9 are further held in a rigidly connected to the pivotally mounted arm 1 terminal 11. Upon pivoting of the arm 1, there is thus a pivoting of the clamp 11 relative to the terminal 10, so due to the non-displaceable in the longitudinal direction recording the media lines 9 in the terminals 10 and 11 and
    Length compensation of the running between the terminals 10 and 11 portion of the media lines 9 required is. The media lines 9 are helically wound around the stop element 6 in the mentioned section for this purpose. In the embodiment shown in Fig. 1, the helical media lines comprise two and a half turns, wherein the media lines in the starting position shown in Fig. 1 at a radial distance from the cylindrical stop surface 8 is arranged. This distance decreases with a pivoting of the arm in the direction of the arrow 4 and increases with a pivoting of the arm in the direction of the arrow. 3
    In Fig. 2 it can be clearly seen that the helical media lines 9, the cylindrical abutment surface 8 touch at any point. Furthermore, it can be seen that 9 axial spacers 12 and 13 are arranged between the adjacent media lines, which are formed like a rake.
    In summary, the invention allows a guidance of media lines in positioning mechanisms for space applications, which brings a number of advantages:
    High mechanical vibration loads possible: Due to the soft cylinder material and due to the Hertzian contact "toroid on cylinder". the local stresses at the contact point are minimized, so that no damage to the line occurs during impact and yet a large free path can be selected. • · · · · · · · · · · · · · ft · ft · ft · ft ··· · ft · ft · ft · ft ·
    Large bending angle: By increasing the number of
    Schraubenwindungen large bending angles can be realized without the restoring torque increases significantly, or the mechanical stress of the tube exceeds the resistance to change of the material.
    Low resistive moment: The helical coiled media line can move freely, so no friction occurs.
    Low return torque: A very soft design of the cable is possible because the vibration loads are supported by the stops. As a result, the restoring moment is small.
    Furthermore, by increasing the number of screw turns, the restoring torque can be reduced to such an extent that actuation is possible even with low motorization.
    Starting position not in an extreme setting angle position: The bending can take place in both directions. Thus, a starting position in a payload position is possible, so that in case of failure of the mechanism still a meaningful engine operation - albeit without direction vector control - is possible.
    Simple construction: An attachment to the actuator is possible, so that a space-saving concept is possible. Low mass: Only the plastic parts come to the tube mass itself.
    Simple calculation: Formulas for calculating coil springs are sufficient for the mechanical dimensioning of the cable.
    Use of materials approved for space travel.
    Low production costs.
    权利要求:
    Claims (9)
    [1]


    1. A positioning mechanism for space applications with at least one flexible media line for supplying at least one adjustable component, in particular an engine, comprising one at least one pivot axis between two extreme pivoting angle positions pivotally mounted arm, characterized in that the flexible media line (9) helically around a pivot axis (2) parallel helix axis is coiled, wherein the helical media line {9} lying in a lying between the two pivoting extreme positions starting position at a radial distance from within or outside the helix arranged cylindrical stop surface (8) of a stop element (6) is arranged.
    [2]
    2. adjusting mechanism according to claim 1, characterized in that the helical axis coincides with the pivot axis (2}.
    [3]
    3. adjusting mechanism according to claim 1 or 2, characterized in that the media line (9) consists of steel or a titanium alloy.
    [4]
    4. adjusting mechanism according to claim 1, 2 or 3, characterized in that the media line (9) is designed as a round tube.
    [5]
    5. Actuator mechanism according to one of claims 1 to 4, characterized in that the stop element (6) made of plastic, in particular a high-performance plastic, such. a polyimide or polyetheretherketone. · »» »» »» »» »» »» »» »4 4 4 4 4 m
    [6]
    6. Actuator mechanism according to one of claims 1 to 5, characterized in that the turns of the helical media line (9) are axially spaced apart.
    [7]
    7. Stellmechanisraus according to one of claims 1 to 6, characterized in that between adjacent turns of the helical media line (9} in each case at least one spacer (12) is arranged.
    [8]
    8. adjusting mechanism according to one of claims 1 to 7, characterized in that a plurality of parallel media lines (9) is helically wound, between which at least one axial spacer (12) is arranged.
    [9]
    9. adjusting mechanism according to claim 7 or 8, characterized in that the spacers (12) with play between the helical media lines (9) and whose windings are arranged. Vienna, 25 January 2012 Applicant by: Haffner and Keschmann Patentanwälte OG

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    同族专利:
    公开号 | 公开日
    EP2620371A1|2013-07-31|
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    EP2620371B1|2014-12-03|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    DE3045421C2|1979-12-03|1986-11-27|Société Nationale Industrielle Aérospatiale, Paris|Device for deploying the elements of an extension arm of equipment for a spacecraft|
    US4465253A|1983-04-19|1984-08-14|The United States Of America As Represented By The Secretary Of The Air Force|Flexible line support assembly|
    DE3713506C1|1987-04-22|1988-10-06|Max Planck Gesellschaft|Multiple cable rotating union between two limited rotatable components|
    DE19649739A1|1996-11-30|1998-06-04|Daimler Benz Aerospace Ag|Release device for Solar generator hold-down unit|
    JP2004314659A|2003-04-11|2004-11-11|Sumitomo Heavy Ind Ltd|Wire pay-out device in deployment mechanism|
    AT3647U1|1999-04-22|2000-06-26|Austrian Aerospace Gmbh|PIPE TUBE|NL1040678C2|2014-02-19|2015-08-25|Wavin Bv|System for providing at least a part of a fluid connection between a supply pipeline positioned in the ground and a branched-off pipeline part and use of such a system.|
    CN104760708B|2015-02-12|2017-03-08|西北工业大学|The manufacture method of hollow magnetic torquer|
    US20190359356A1|2016-09-29|2019-11-28|Mitsubishi Electric Corporation|Cable wrap mechanism|
    法律状态:
    2017-09-15| MM01| Lapse because of not paying annual fees|Effective date: 20170125 |
    优先权:
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    ATA92/2012A|AT512487B1|2012-01-25|2012-01-25|LOCK MECHANISM|ATA92/2012A| AT512487B1|2012-01-25|2012-01-25|LOCK MECHANISM|
    EP20130450004| EP2620371B1|2012-01-25|2013-01-24|Positioning mechanism|
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