• 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:
    The present invention relates to an active tie for maintaining and release without shock appendages. According to the invention, the device (10) comprises: • a fixed base (11), • a tie rod (12) extending along an axis (21) between two ends (14, 15), • a mechanism (13) secured to the base and ensuring the temporary retention of a first end (14) of the tie rod (12), a maneuver mechanism for releasing the tie rod (12) of the base (11), • a tip (16 ) integral with one second of the ends (15) of the tie rod (12), • at least one appendix (AP) temporarily held between the base (11) and the end piece (16), • a component (20) arranged between the mechanism (13) and the tip (16), and a control (25) of the component (20) for modifying a characteristic dimension of the component (20) along the axis (21) between two values, for a first of the two values, the component (20) providing tension of the tie rod (12) and for a second of the two values, the tension of the tie rod (12) being reduced.
    公开号:FR3045851A1
    申请号:FR1502636
    申请日:2015-12-18
    公开日:2017-06-23
    发明作者:Alain Vincent Blanc；Thomas Combernoux；Francois Michellet；Damien Chassoulier
    申请人:Thales SA；
    IPC主号:
    专利说明:

    Device for holding and releasing appendages
    The present invention relates particularly but not exclusively to the spatial field and, more specifically, consists of an active tie rod for the maintenance and release without shock of appendages, for example, space.
    Spatial appendages are spatial devices intended to be deployed in space, such as solar generators or antennas, for example. The invention consists of a simple and robust solution for the release without shock of such spatial appendages.
    An active pulling has the function, initially, of keeping in stored configuration one or more spatial appendices, that is to say, in general, movable elements deployable on either side of the satellite box , and, in a second time, to release these appendages without shock in order to deploy them. The maintenance system in stored configuration and release appendages is conventionally mainly consisting of a petal nut and a tensioning tie. Specifically, in the known devices, the tie participates, with the nut, in the tensioning of a series of stacked elements, such as solar generators folded over each other in order to minimize the volume of the satellite when placed in a launcher's headdress.
    However, it is known that, in this type of device, the tie rod has geometric defects that can be significant, particularly if the number of stacked elements is high. The geometric defects may be inclination or delocalization defects for example. These geometric defects can cause dynamic defects resulting in radial forces or moments exerted at the ends of the tie rod.
    Failure to take these faults into account can lead to serious malfunctions, up to the non-deployment of spatial appendices, and may therefore imply a loss of the mission.
    Another known problem lies in the shock that can occur during the release of the tie rod. The nut, mentioned previously, is responsible for releasing the tie rod. However, the pull rod is, at the time of its release, in a constrained state and its abrupt release can cause shocks that can alter the spatial appendages or the satellite itself. In the context of some current devices, the problem is twofold. Indeed, at first, the tie is released by a pyrotechnic lock whose explosion generates a first shock. Then, the pulling being energized before being released, its abrupt release, already mentioned, can cause degradations at the level of the spatial appendages or the supporting structure.
    In order to minimize this problem, so-called nuts without shock, or "low shock" according to the English expression devoted, have been developed. This type of nuts, complex, is usually single-shot and can be repackaged. However, the "shock-free" ability of these nuts is only applicable to triggering the release of the tie rod, and not to releasing the appendages themselves. Indeed, the geometrical defects of the tie rod are not really compensated and, particularly in the case where the tie rod is of large dimension, there remains a sudden relaxation of the pull rod which can generate a shock sometimes important, the pulling from the percussion space appendages. This is explained in particular by the fact that the release of the tie rod under stress remains sensitive to the angular deviations of the tie rod. The Applicant has even found that the shocks generated by the relaxation of the tie rod are usually much larger than those generated by the nut, even pyrotechnic.
    The patent EP2 319 764B1 filed on October 1, 2010 in the name of the applicant describes a tie rod made of a material having a controlled thermal expansion. Thanks to the heating of the tie rod it is possible to lengthen it before releasing the nut and thus to limit the shocks due to the sudden relaxation of the tie rod. This solution has the disadvantage of limiting the choice of material in which the tie rod is made. Indeed, there may be incompatibility between the desired thermal expansion and the mechanical strength required to perform the function of maintaining appendages, especially during the launch phase where the satellite is subjected to significant vibration. In addition, the tie rod may be of great length and it is then necessary to heat it along its entire length to ensure its expansion. The implementation of the heater over the entire length of the tie rod is complicated to implement. The invention proposes a simple and robust solution for limiting the shocks due to the relaxation of the tie while allowing the use of conventional tie rods without worrying about the thermal properties thereof.
    The solution lies mainly in the dissociation of the mechanical resistance properties on the one hand and the thermal properties on the other hand. The invention proposes the addition of an additional component filling only the expansion function, for example thermal. The invention proposes a component that can be standardized in particular so that it can be mounted at any position in the assembly holding the appendages before they are released. To this end, the subject of the invention is an appendage holding and release device, the device comprising: • a fixed base, • a tie rod extending along an axis between two ends, • a mechanism integral with the base and ensuring the temporary maintenance of a first end of the tie rod, a maneuver mechanism for releasing the tie rod from the base, • an integral end of a second of the ends of the tie rod, • at least one appendix temporarily held between the base and the tip, • a component disposed between the mechanism and the tip, • and a component control for modifying a characteristic dimension of the component along the axis between two values, for a first of the two values, the component providing tension of the tie rod and for a second of the two values, the tension of the tie rod being reduced.
    The component advantageously has a washer shape configured to slide along the tie rod during assembly of the device.
    The tie has a characteristic dimension perpendicular to its axis between its two ends. The component is advantageously drilled with a characteristic dimension greater than the characteristic dimension of the tie rod so as to be able to slide along the tie rod during assembly of the device.
    The component may be arranged at different positions in the assembly such as between the mechanism and the base or between the base and the at least one appendix or between the at least one appendix and the tip. The device may comprise at least two appendages. The component can then be disposed between two appendices.
    The component advantageously comprises a thermal expansion material determined. The control then comprises an element for supplying or extracting the thermal energy of the component. The material is advantageously with shape memory. The element may be a heater allowing a temperature rise of the component material.
    For the second of the two characteristic dimension values of the component along the axis, the tension of the tie rod is advantageously zero.
    The device advantageously further comprises a spring disposed between the second end of the tie rod and the at least one appendix, the spring being configured to extract the first end of the tie rod out of the mechanism after operation of the mechanism. The invention will be better understood and other advantages will appear on reading the detailed description of an embodiment given by way of example, a description illustrated by the attached drawing in which: FIG. 1a schematically represents a satellite comprising spatial appendages in stored position; Figure 1b shows the satellite of Figure 1a whose spatial appendages are being deployed; FIG. 1c represents the satellite of FIG. 1a whose spatial appendages are in the deployed position; Figure 2a shows an alternative device according to the invention in a configuration where a tie is under tension; Figure 2b shows the device of Figure 2a in a configuration where the tension of the tie rod is released, Figures 3, 4 and 5 show other variants of devices according to the invention.
    For the sake of clarity, the same elements will bear the same references in the different figures.
    The following description is made in relation to a satellite and the deployment of its appendices. It is understood that the invention is not limited to the spatial domain and can be implemented in other areas where appendices can be deployed. It can be terrestrial antennas, underwater sensors ...
    Figures 1a, 1b, 1c are intended to present in a very simple way an example of a satellite with deployable spatial appendages. In these three figures, there is shown a satellite consisting of a box S with, on either side of the body S, AP spatial appendages, such as solar generators. In FIG. 1a, the spatial appendages AP are in the stored position. The AP space appendages here each consist of four panels folded against each other and held in place by a suitable device. This adapted device here comprises tripods P on which come to rest the folded AP spatial spacers, each tripod P cooperating with a not shown device consisting for example of a petalable nut associated with a tie rod, each tie passing through each panel at a level of socket 1 arranged and integrated in the panel. As can be seen in FIGS. 1a, 1b, 1c, there are in this context, for each of the two AP spatial appendages, six P tripods, associated with six nuts and six tie rods, and six sockets per panel.
    The stored position allows the satellite to be integrated into the cap of a space launcher responsible for its shipment.
    Figure 1b shows the same satellite as in Figure 1a, but the AP space appendages are being deployed. Indeed, the adapted means for holding in place the AP space appendices allows the release of the AP space appendices at the appropriate time, and the solar panels unfold. The deployment can be controlled by an electric motor or self-powered joints not shown.
    In Figure 1c, the AP space appendages are deployed, allowing the satellite to carry out its mission.
    To simplify the representation of Figures 2a and 2b, AP appendages are not shown. In addition, the length of the tie rod must be adapted to the number of appendices that it is desired to maintain in the stored position.
    Figures 2a and 2b show a first variant of device 10 for maintaining and releasing AP appendages. In the different variants described, two AP appendices are represented. It is understood that the invention can be implemented regardless of the number of AP appendages. The device 10 comprises a base 11, formed for example of a tripod P, a tie rod 12 ensuring the maintenance of the appendices AP in stored configuration and a mechanism 13 for releasing the tie rod 12. The mechanism 13 is integral with the base 11. The tie rod 12 extends between two ends 14 and 15. In the configuration of Figure 2a, the AP appendages are held against each other. This configuration is used in particular in a satellite when the satellite panels are folded against the satellite box. This configuration is used for the launch of the satellite when it is stored in the cap of a launcher and is commonly called storage configuration. In this configuration, the end 14 is held integral with the base 11 by means of the mechanism 13 and at the end 15, for example is disposed a tip 16 forming a stop against which abut the appendages AP. The position of the tip 16 may be fixed on the end 15. The tip 16 may be a simple shoulder forming an integral part of the tie rod 12. Alternatively, the position of the tip 16 may be adjustable along the tie rod 16. To achieve this adjustment, the tip may be a nut 16 screwed onto the tie rod 12. The tie rod 12 passes through the appendices AP which are pinched between the base 11 and the nut 16. Use an adjustable tip 16, in particular like a nut, allows to adjust the clamping force of the AP appendages. This effort is calibrated in particular according to the vibrations that the satellite may undergo during its launch and the inertia of the AP appendages.
    The mechanism 13, allowing the release of the tie rod 12, comprises a clamp for holding the end 14 of the tie rod 12 in the storage configuration. The mechanism 13 can maintain the tie rod 12 by exerting a radial clamping on the tie rod 12. In other words, the holding of the tie rod 12 is achieved by adhesion. Alternatively, the mechanism 13 can maintain the tie rod 12 by an obstacle, for example by bearing against a collar 17 of the tie rod 12. When it is desired to deploy the appendages AP, the clamp is operated to release the end 14 of the tie rod 12.
    Maneuvering the clamp can be performed by a conventional mechanical device for example cam operated by a motor. To ensure a faster deployment, it is possible to open the clamp by means of a pyrotechnic device.
    When launching a satellite, it may be subject to significant vibration. It is then important to ensure the mechanical maintenance AP appendages bearing against the body S and more precisely against the base 11. To ensure this maintenance, even in the presence of vibration, the tie rod 12 is prestressed. More specifically, the tie rod 12 is held in tension between its two ends 14 and 15. As has been seen above, this preload can be adjusted by means of the nut 16. This adjustment makes it possible to overcome the tolerances of the various mechanical parts pinched between the base 11 and the nut 16 and tolerances of the pull itself.
    According to the invention, in order to limit the shocks when the clamp is opened, the device 10 comprises a component 20 allowing on command to reduce or cancel the tension of the tie rod 12. The component 20 is distinct from the tie rod 12 which allows to choose more freely the material of the tie rod 12 as a function of the mechanical strength necessary to maintain AP appendices under tension, even in case of significant vibration. The tie rod 12 is for example made of steel.
    The component 20 has for example the shape of a washer traversed by the tie rod 12. The component 20 has a coaxial shape of the tie rod 12. The shape of a coaxial washer makes it possible to axially balance the forces exerted by the washer on the base 11 and on the mechanism 13 and avoid radial forces. Other forms for component 20 are of course possible. The washer is a separate mechanical part of the tie rod 12. The washer is configured to slide along the tie rod 12 during the assembly of the device 10. The tie rod 12 extends along an axis 21 which, in the stored configuration, is perpendicular to the plane of the AP appendages folded against each other. The tie rod 12 has a characteristic dimension perpendicular to its axis 21 between its two ends 14 and 15. In the simplest way, the tie rod 12 is for example a circular section rod. The diameter of this section forms the characteristic dimension of the tie rod 12 perpendicular to its axis 21. It is understood that other forms of section are possible within the scope of the invention. The component 20 is pierced with a characteristic dimension greater than the characteristic dimension of the tie rod 12. The characteristic dimension of the piercing of the component 20 is defined so as to allow the component 20 to slide along the tie rod 12 during assembly of the device 10 .
    A control of the component 20 makes it possible to modify another characteristic dimension of the component 20. In the example shown, this other characteristic dimension is the thickness of the washer measured along the axis 21 of the tie rod 12.
    The characteristic dimension of the component 20 along the axis 21 can change between two values. For a first of the two values, the component 20 ensures a tension of the tie rod 12 and for a second of the two values the tension of the tie rod 12 is reduced or canceled. In order to completely avoid the occurrence of shocks during the release of the tie rod 12, it is advantageous to define the component 20 so as to cancel the tension in the tie rod 12. Physically to be certain to obtain the complete cancellation of the voltage, it is necessary to provide a positive functional clearance after maneuvering the component 20. This game can nevertheless be detrimental to the deployment of appendices AP. Alternatively, after maneuvering the component 20, we can keep a slight tension in the tie rod 20 to ensure contact between the AP appendages.
    In the example shown, the component 20 shrinks to release the tension of the tie rod 12 between its configuration of Figure 2a and that of Figure 2b. It is also possible to design a reverse assembly where the component 20 expands to release the tension of the tie rod 12.
    The dimensional variation of the component 20 along the axis 21 can be ensured by means of a mechanical device in which two opposite faces of the component 20 are displaced, for example by means of motorized cams.
    More simply, the component may comprise a determined and controlled thermal expansion material. The dimensional variation of the component 20 is provided by an element 25 for supplying or extracting the thermal energy of the component. In a simple manner, the element 25 may be a heater formed of an electrical resistance surrounding the component 20. Indeed, on board a satellite, it is possible to use electrical energy stored in batteries. Among the appendages, there are commonly solar panels for recharging the batteries later after deployment of AP appendages.
    The determined thermal expansion material of the component 20 may be a conventional material with a high coefficient of thermal expansion. Among the metal alloys, it is possible to use a zinc alloy known for its significant coefficient of thermal expansion. Some plastic materials based on polypropylene or polyamide have higher coefficients of thermal expansion but are also subject to creep which may reduce the tension of the tie rod 12 if the maintenance in stored configuration is prolonged. The dimensions of the component 20 and in particular its thickness along the axis 21 are defined as a function of the coefficient of thermal expansion to achieve the desired dimensional variation as a function of the temperatures that can take the component 20 when the heater 25 is activated or not.
    Advantageously, in order to reduce the dimensions of the component 20, its material is shape memory. For example, an alloy of titanium and nickel may be chosen. With this type of material it is possible to reach a large dimensional amplitude for a small thickness at an ambient temperature. This large amplitude is obtained by modification of the metallographic structure of the alloy. The passage between two structures often called martensitic at low temperature and austenitic at high temperature makes it possible to obtain an important dimensional variation. FIG. 2a shows the component 20 at room temperature and FIG. 2b at a temperature higher than the transition temperature between the metallographic structures, for example of the order of 100 ° C., if the material has a transition temperature of order of 85 ° C. FIG. 2b is shown schematically and in practice, when the component 20 is closed, the mechanism 13 remains in contact with the component 20, which makes it possible to reduce the tension in the tie rod 12.
    The device comprises a spring 30 to move the tie rod 12 from the base 11 in a translation movement along the axis 21. The spring 30 is independent of the tension of the tie rod 12 obtained by the component 20 in its configuration of the Figure 2a. Thus it is possible to extend the tie rod 12 so as to ensure that the AP appendages remain in contact with the base 11 during the launch of the satellite even if it is subjected to significant vibrations and independently obtain a force determined assisting the tie rod 12 to disengage from the appendages during the deployment when the satellite has reached the position where it will fulfill its mission.
    More specifically, at the end 15 of the tie rod 12, the nut 16, cooperating with a thread of the tie rod 12, makes it possible to keep in pressure the appendages AP and one or more spacers 32, 33, 34 between the nut 16 and the 11.11 base is even possible to dispense spacers and even the nut 16 by arranging the spring 30 between the end 15 of the tie rod 12 and the base 11.
    The tightening of the nut 16 makes it possible to adjust the tension of the tie rod 12, which tension will subsequently be released by the component 20. A second nut 35 cooperating with the same thread of the tie rod 12 (or possibly a separate thread) holds the spring 30 between the spacer 32 and the nut 35. Thus after releasing the tension of the tie rod 12 by means of the component 20, the spring 30 pushes the spacer 32 of the nut 16 thus allowing the tie rod 12 to disengage.
    Figure 3 shows a variant of the device 10 in which the component 20 is disposed between the base and one of the appendages AP.
    FIG. 4 represents another variant of the device 10 in which the component 20 is disposed between an appendage AP and the endpiece formed by the nut 16. It is possible, but not obligatory, to arrange the spacer 38 between the nut 16 and appendix AP.
    Figure 5 shows a further variant of the device 10 in which the component 20 is disposed between two AP appendages.
    More generally, the component 20 can be arranged between two parts held in pressure by the tie rod 12. The choice of the position of the component 20 can be done according to the ease of access to the control 25.
    权利要求:
    Claims (12)
    [1" id="c-fr-0001]
    An appendage holding and release device (AP), the device (10) comprising: • a fixed base (11), • a tie rod (12) extending along an axis (21) between two ends (14) , 15), • a mechanism (13) integral with the base and ensuring the temporary maintenance of a first end (14) of the tie rod (12), a maneuver mechanism for releasing the tie rod (12) of the base (11), • a tip (16) secured to one second of the ends (15) of the tie rod (12), • at least one appendix (AP) temporarily held between the base (11) and the end piece (16). ), A component (20) disposed between the mechanism (13) and the tip (16), and a control (25) of the component (20) for modifying a characteristic dimension of the component (20) along the axis (21) between two values, for a first of the two values, the component (20) ensuring tension of the tie rod (12) and for a second of the two values, the tension of the tie rod (12) and ant reduced.
    [2" id="c-fr-0002]
    2. Device according to claim 1, wherein the component (20) has a washer shape configured to slide along the tie rod (12) during assembly of the device (10).
    [3" id="c-fr-0003]
    3. Device according to one of the preceding claims, wherein the tie rod (12) has a characteristic dimension perpendicular to its axis (21) between its two ends, and wherein the component (20) is pierced with a characteristic dimension greater than the characteristic dimension of the tie rod (12) so as to slide along the tie rod during assembly of the device (10).
    [4" id="c-fr-0004]
    4. Device according to one of the preceding claims, wherein the component (20) is disposed between mechanism (13) and the base (11).
    [5" id="c-fr-0005]
    5. Device according to one of claims 1 to 3, wherein the component (20) is disposed between the base (11) and the at least one appendix (AP).
    [6" id="c-fr-0006]
    6. Device according to one of claims 1 to 3, wherein the component (20) is disposed between the at least one appendix (AP) and the tip (16).
    [7" id="c-fr-0007]
    7. Device according to one of claims 1 to 3, comprising at least two appendices (AP), and wherein the component (20) is disposed between two appendices (AP).
    [8" id="c-fr-0008]
    8. Device according to one of the preceding claims, wherein the component (20) comprises a thermal expansion material determined and wherein the control comprises an element (25) for supplying or extracting thermal energy from the component (20).
    [9" id="c-fr-0009]
    9. Device according to claim 8, wherein the material is shape memory.
    [10" id="c-fr-0010]
    10. Device according to one of claims 8 or 9, wherein the element is a heater (25) for a temperature rise of the component material (20).
    [11" id="c-fr-0011]
    11. Device according to one of the preceding claims, wherein for the second of the two dimension values characteristic of the component (20) along the axis (21), the tension of the tie rod (12) is zero.
    [12" id="c-fr-0012]
    12. Device according to one of the preceding claims, further comprising a spring (30) disposed between the second end (15) of the tie rod (12) and the at least one appendix (AP), the spring (30) being configured to extract the first end (14) of the tie rod (12) out of the mechanism (13) after operation of the mechanism (13).
    类似技术:
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    同族专利:
    公开号 | 公开日
    ES2847999T3|2021-08-04|
    EP3181461A1|2017-06-21|
    FR3045851B1|2018-05-25|
    EP3181461B1|2020-10-07|
    US10723488B2|2020-07-28|
    US20170174366A1|2017-06-22|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US5248233A|1992-09-25|1993-09-28|Webster Richard G|No-shock separation mechanism|
    US20050084364A1|2003-10-20|2005-04-21|Hi-Shear Technology Corporation|Non-pyrolytically actuated reduced-shock separation fastener|
    EP2319764A1|2009-11-10|2011-05-11|Thales|System of tie rods enabling shock-free holding and release of space appendages|
    US20120076614A1|2010-09-27|2012-03-29|Baghdasarian Varouj G|Preload releasing fastener and release system using same|
    FR2857936B1|2003-07-22|2005-09-30|Cit Alcatel|GERMATING TICKER RELEASING DEVICE FOR DEPLOYABLE STRUCTURE|US10717548B2|2017-09-25|2020-07-21|United States Of America As Represented By The Administrator Of Nasa|Deployable multi-section boom|
    CN109305391B|2018-08-08|2021-12-21|上海宇航系统工程研究所|Compression release mechanism and method thereof|
    CN109515753A|2018-12-07|2019-03-26|上海宇航系统工程研究所|A kind of load plate expansion module of spacecraft|
    法律状态:
    2016-11-28| PLFP| Fee payment|Year of fee payment: 2 |
    2017-06-23| PLSC| Search report ready|Effective date: 20170623 |
    2017-11-27| PLFP| Fee payment|Year of fee payment: 3 |
    2019-11-28| PLFP| Fee payment|Year of fee payment: 5 |
    2020-11-25| PLFP| Fee payment|Year of fee payment: 6 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1502636|2015-12-18|
    FR1502636A|FR3045851B1|2015-12-18|2015-12-18|DEVICE FOR HOLDING AND RELEASING APPENDICES|FR1502636A| FR3045851B1|2015-12-18|2015-12-18|DEVICE FOR HOLDING AND RELEASING APPENDICES|
    ES16203881T| ES2847999T3|2015-12-18|2016-12-13|Device for holding and releasing appendages|
    EP16203881.4A| EP3181461B1|2015-12-18|2016-12-13|Device for holding and releasing appendages|
    US15/382,219| US10723488B2|2015-12-18|2016-12-16|Device for retaining and releasing appendages|
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