Quick fastening device for a solar array, vehicle and method using said quick fastening device

Abstract

In order to improve the manufacturing of solar powered spacecraft, the invention proposes a quick fastening device (16) configured for fastening a solar array (14) to a vehicle, preferably a spacecraft (10), the device comprising: - a solar array driving mechanism (SAM) adapter (24) that is configured to be mounted to a SAM (66) of the vehicle; - a root hinge adapter (RHA) (44) that is configured to be positively joined to the SAM adapter (24), wherein one of the SAM adapter (24) and the RHA (44) includes a first interface structure (30) and the other of the SAM adapter (24) and the RHA (44) includes a second interface structure (32), wherein the first interface structure (30) has a first mounting surface (34) and the second interface structure (32) has a second mounting surface (46) that, when in the mounted position, face each other, wherein the first and second interface structure (30, 32) are configured to be mechanically and connectable by moving the RHA (44) and the SAM adapter (24) relative to each other along a direction perpendicular each of the first and second mounting surfaces (34, 46).

Description

[0001] Airbus Defence and Space GmbH 2317 0393 P-WO

[0002] Willi-Messerschmitt-Stra(3>e 1 20048-WO-PCT

[0003] 82024 Taufkirchen

[0004] QUICK FASTENING DEVICE FOR A SOLAR ARRAY, VEHICLE AND METHOD USING SAID QUICK FASTENING DEVICE

[0005] The invention relates to a quick fastening device. The method further relates to a vehicle, preferably a spacecraft, with such a quick fastening device and a method for assembly.

[0006] Electrical power for space missions is mainly generated by solar power. This is typically done by connecting multiple panels together by self-driven hinges. Other common types are electrically-driven or cable-driven hinges. The panels may be rigid or flexible structures. The panels are typically covered on the sun side with solar cell assemblies. The panels are attached to the spacecraft via a yoke structure. This complete assembly is sometimes referred to as a solar array.

[0007] Before and during launch of the spacecraft, the SAs are folded to the sidewall of the satellite in a manner known per se. After the separation of the rocket dispenser the solar arrays are deployed and continuously rotated around the SA longitudinal axis to achieve the best possible position of the photovoltaic assembly (PVA) with respect to the sun. This rotation is typically driven by a solar array drive mechanism (SADM) which also provides the mechanical and electrical interface between the SA and the spacecraft.

[0008] The electrical power generated by the solar array is transferred to the satellite passing through the interface connectors on the SA yoke hinge, e.g. via brushes and slip rings of the SADM.

[0009] Mounting the SA to the SADM usually requires several steps. In a first step, the stowed SA needs to be at least partially deployed in order to have access to the mechanical and electrical interface. In following steps, the SA is attached via the yoke hinge flange to the SADM and fastened with several screws and washers. In addition, cable bundles may need to be routed from the SADM via the Yoke hinge to the SA Interface connectors and fixed onto the yoke structure.

[0010] Finally, the SA can be folded back into its launch configuration and secured to the spacecraft by a hold down mechanism. These steps typically require several days. Furthermore, there is an increased effort involved to avoid mishandling, avoid wrong connections, and overall ensure reliability of deployment during the mission.

[0011] It is the object of the invention to improve the manufacturing of solar powered spacecraft.

[0012] The object is achieved by the subject-matter of the independent claims. Preferred embodiments are subject-matter of the dependent claims.

[0013] The invention provides a quick fastening device configured for fastening a solar array to a vehicle, preferably a spacecraft, the device comprising:

[0014] - a solar array mount (SAM) adapter that is configured to be mounted to a SAM of the vehicle;

[0015] - a root hinge adapter (RHA) that is configured to be positively joined to the SAM adapter, wherein one of the SAM adapter and the RHA includes a first interface structure and the other of the SAM adapter and the RHA includes a second interface structure, wherein the first interface structure has a first mounting surface and the second interface structure has a second mounting surface that, when in the mounted position, face each other, wherein the first and second interface structure are configured to be mechanically and connectable by moving the RHA and the SAM adapter relative to each other along a direction perpendicular each of the first and second mounting surfaces.

[0016] Preferably, the solar array mount (SAM) is configured as a solar array driving mechanism (SADM).

[0017] Preferably, the quick fastening device further comprises a coupling member that is configured to hold the RHA in place relative to the SAM adapter.

[0018] Preferably, the first interface structure includes a mechanical connector that protrudes from the first mounting surface wherein the mechanical connector is configured to from a press-fit with the second interface structure.

[0019] Preferably, the second interface structure includes a mechanical connector that is configured to receive a protruding mechanical connector of the first interface structure, wherein the mechanical connectors are configured to form a press-fit.

[0020] Preferably, the first interface structure includes a dowel pin as the protruding mechanical connector. Preferably, the second interface structure includes a dowel hole as the receiving mechanical connector.

[0021] Preferably, at least one dowel hole is formed as an elongated hole, in which the dowel pin is received to be movable along one direction.

[0022] Preferably, the first interface structure includes an electrical connector that is fixedly attached and that is configured to cause the second interface structure to align so that an electrical connection can be formed.

[0023] Preferably, the second interface structure includes an electrical connector that is attached in a floating manner. Preferably, when the RHA engages the SAM adapter, the floating electrical connector gets aligned and electrically connected to a fixed electrical connector.

[0024] Preferably, the fixed electrical connector includes at least one aligning pin that engages a connector hole of the floating electrical connector to align the floating electrical connector with the fixed electrical connector.

[0025] Preferably, the floating electrical connector includes a floating plate that is fixedly attached thereto and is movably supported between a cover plate and a recess in the second mounting surface.

[0026] Preferably, the SAM adapter comprises a threaded portion for threading on the coupling member to fasten the RHA to the SAM adapter.

[0027] Preferably, the coupling member comprises at least one locking screw that is disposed to prevent unthreading of the coupling member.

[0028] The invention provides a solar array for a vehicle, preferably a spacecraft, wherein the solar array comprises a plurality of panels for generating electrical power and a previously described quick fastening.

[0029] The invention provides a vehicle, preferably a spacecraft, comprising a solar array driving mechanism and a solar array that is attached to the solar array driving mechanism by a quick fastening device, or a solar array.

[0030] The invention provides a method for mounting a solar array to a solar array mount (SAM) using a quick fastening device, the method comprising installation of a solar array driving adapter on the solar array driving mechanism and installing the RHA on the solar array, moving the RHA along a movement axis that is perpendicular to the first and second mounting surfaces so that the first and second interface structures couple in a mechanical and an electrical manner, and securing the RHA to the SAM adapter.

[0031] In some embodiments, a method for the rapid electrical and mechanical assembly of foldable and rotating solar generators to a solar array drive mechanism (SAM) of a spacecraft is provided. It is an idea to avoid intermediate steps to achieve the rapid connection.

[0032] Another idea is to provide a solution for simplifying the assembly (also called final coupling) of the solar array (SA) to the spacecraft. The fastener device, which may also be referred to as “Quick Fastener Device”, may include two main assemblies. One such assembly is referred to as “Root Hinge Adapter” (RHA), while the other may be referred to as “SAM Adapter”. The RHA and the SAM adapter are positively joined, e.g. by two dowel pins, to allow torque transmission during rotation. The RHA and the SAM adapter may be held in place by a coupling ring.

[0033] The RHA is preferably articulated, e.g., via deployment hinges, to the solar array, and generally serves as the electrical and mechanical interface between the SA and the spacecraft. The RHA may include an adapter plate, the different interfaces to the deployment joint(s), one or more floating plugs, and / or one or more fitting holes. Two fitting holes are preferred. At least one fitting hole, but not all of them, may be shaped as an elongated hole for tolerance compensation.

[0034] The interface to the deployment hinge(s) typically depends on the specific mechanism used and generally does not influence the disclosed ideas. In other words, the ideas presented herein are applicable to all kinds of deployment hinge mechanisms that are known.

[0035] The adapter plate can be made from any material and with any manufacturing technique, provided that the resulting adapter plate meets the mechanical and electrical requirements for the respective application, e.g. in space missions.

[0036] The plugs or plug connectors are used to transmit the generated electrical power. Furthermore, the plug connectors may transmit electrical (control) signals that are useful in operating the SA. In some embodiments the plug may have a flange with mounting holes, or be large enough to add some mounting holes. In general, the type or shape of the plug can be freely selected among those that are suitable for space applications. A typical connector type used may be a D-sub connector.

[0037] The number of connectors may be chosen in accordance with the available installation space. In some embodiments, the connector may have a floating plate attached to its backside, i.e. , cabling side. The floating plate may be glued to the connector. In some embodiments the floating plate serves as a guide plate within the connector recess for the plug and has an opening for cable entry. In some embodiments the fastening holes of the connector flange are transferred in advance to the floating plate in order to enable a guiding pin to penetrate during final assembly.

[0038] In some embodiments after all pins or sockets including the cables are assembled with the connector half, the assembled floating plug can be mounted into the connector recess. The connector recesses are preferably slightly deeper and bigger than the floating plate that is attached to the connector flange, in order to allow the plug to float slightly about ± 0.5 mm within the recess.

[0039] In some embodiments to keep the plug in place, the connector recess may be covered with a cover plate that is held on with several screws. The cover plate may have a pocket to guide the cables through and is preferably fastened via several holes and screws onto the adapter plate. The root hinge adapter can be pre-assembled and mounted together with the coupling ring onto the solar array.

[0040] The SAM Adapter functions as the complementary counterpart to the root hinge adapter and serves as interface to the SAM, respectively to the spacecraft. The adapter can be provided as an interface by the SAM manufacturer from the outset or can be added later as an adapter. In the latter it is preferred that the adapter contains a drilling pattern of the SAM interface.

[0041] The SAM adapter plate may contain the dowel holes for dowel pins, an external mounting thread for a coupling ring, one or more plug recesses for the counterparts of the plugs on the root hinge adapter side and / or one or more guiding pins. In another embodiment, dowel pins and / or the external mounting thread are arranged on the RHA plate side, whereas the dowel holes and / or the coupling ring are arranged on the SAM adapter plate side. The depth of the plug recesses is preferably chosen so that the plug halves are sufficiently inserted after both adapters are flush. In contrast to the RHA side plugs, the plugs on the SAM adapter are preferably fixed.

[0042] In the adapter, the dowel pins may be pressed into the designated dowel holes using a slight press fit, which engage into the dowel holes of the root hinge adapter when the two assemblies are assembled. The dowel pins serve as a guide during final assembly. Furthermore, the dowel pins allow to absorb torsional forces during the SA rotation. With this the electrical connectors can be protected.

[0043] The plugs can be wired using an SAM harness and they are mounted into the adapter plate using the guide pins. The guide pins preferably have a conical shape with a base diameter slightly smaller than the guiding holes in the connector counterpart.

[0044] The SAM adapter can be mounted on the SAM, respectively on the spacecraft. The root hinge adapter can be assembled with the solar array. The SA is mounted on a suitable movable device, e.g., ball head mount, in an articulated and height-adjustable manner.

[0045] As the SA approaches its final position during final assembly, corrections can be made regarding the alignment to the SAM interface with greater precision, e.g., by using the dowel pins to opposite dowel holes.

[0046] Shortly after the dowel pins enter the dowel holes the conical tips of the guide pins push into the guiding holes of the floating connector half just before they engage each other, aligning them and ensuring that the connectors are inserted without force.

[0047] As soon as the adapter surfaces are flush with one another, the coupling ring can be screwed onto the mounting thread and tightened with an adequate torque. The type of tool, e.g., strap wrench, hook wrench, hexagon wrench, required for this depends on the shape of the coupling ring and can be selected individually.

[0048] The last step is typically made to protect against loosening of the coupling ring. For this purpose, there may be a number of holes in the coupling ring, e.g., four holes that are offset by 90°, in the outer circumference of the ring. A grub screw can be inserted into each hole in order to clamp the thread in any installation position. Other methods such as locking varnish, self-locking threads, etc. may be used in addition or as an alternative to protect against loosening.

[0049] The invention is described in more detail with reference to the accompanying schematic drawings. Therein:

[0050] Fig. 1 depicts a schematic view of a spacecraft;

[0051] Fig. 2 depicts a detailed view of a solar array;

[0052] Fig. 3 depicts an exploded view of a quick fastener device;

[0053] Fig. 4 depicts an exploded view of a root hinge adapter;

[0054] Fig. 5A and

[0055] Fig. 5B depict a perspective view of the root hinge adapter of Fig. 4 in the installed position;

[0056] Fig. 6 depicts an exploded view of a solar array drive mechanism adapter;

[0057] Fig. 7 illustrates an arrangement during final assembly; and

[0058] Fig. 8 to

[0059] Fig. 10 illustrate the quick fastening device after final assembly.

[0060] Fig. 1 depicts a spacecraft 10 as an example of a vehicle. The spacecraft 10 is preferably a satellite. The spacecraft 10 comprises a spacecraft sidewall 12 at which a solar array (SA) 14 is attached with a quick fastening device 16.

[0061] As shown in Fig. 2 in more detail, the SA 14 comprises a yoke 18. The yoke 18 has a spacecraft side which faces the quick fastening device 16 and a space side which faces away therefrom. The SA 14 comprises a plurality of panels 20. The yoke 18 and the panels 20 are hinged together by self-driven hinges 22. The yoke 18 is attached to the quick fastening device 16 and to one of the panels 20 via the hinges 22. The remaining panels 20 are attached to each other as indicated in the figure. The panels 20 and the hinges 22 are configured to allow a zig-zag-like folding of the panels 20. The spacecraft 10 comprises a solar array mount (SAM) for attaching the panels 20 to the spacecraft 10. The SAM is preferably configured as a solar array driving mechanism (SADM). The SADM is configured to rotate the SA 14 about its longitudinal axis L, when the SA 14 is in the deployed position as shown in Fig. 2.

[0062] Fig. 3 depicts the quick fastening device 16 in more detail. The quick fastening device 16 includes a SAM adapter 24. The SAM adapter 24 has a SAM attachment side 26, which is configured to be attached to the SAM. The SAM adapter 24 includes an SA attachment side 28. The SA attachment side 28 provides a mechanical and electrical first interface structure 30 that is mountable to a complementary mechanical and electrical second interface structure 32. Overall, the first interface structure 30 is configured such that the second interface structure 32 can be engaged by moving it perpendicularly to the first mounting surface 34.

[0063] The first interface structure 30 has a first mounting surface 34. The first interface structure 30 includes at least one mechanical connector 36 that protrudes perpendicularly from the first mounting surface 34. The mechanical connector 36 may be generally cylindrically shaped, e.g., a dowel pin. The mechanical connector 36 is fixedly attached to allow force transmission, preferably of rotational force. The mechanical connector 36 is preferably dimensioned to form a slight clearance-fit with its counterpart on the second interface structure 32.

[0064] The first interface structure 30 further includes at least one electrical connector 38 that is accommodated within a recess 40 within the first mounting surface 34. The electrical connector 38 is fixedly attached. The electrical connector 38 may include one or more aligning pins 41 . The aligning pins 41 extend parallel to the mechanical connector 36.

[0065] The first interface structure 30 includes a threaded portion 42. The threaded portion 42 is formed on a circumferential surface that is adjacent to the first mounting surface 34.

[0066] The quick fastening device 16 includes a root hinge adapter (RHA) 44. The RHA 44 is formed as a cylindrical plate member. The RHA 44 includes the second interface structure 32.

[0067] The second interface structure 32 has a second mounting surface 46. The second interface structure 32 includes at least one complementary mechanical connector 48 that is configured to receive the mechanical connector 36. The complementary mechanical connector 48 may be generally cylindrically shaped. One of the complementary connectors 48 may have an elongated shape for tolerance compensation. The complementary mechanical connector 48 is preferably dimensioned to form a slight clearance-fit with the mechanical connector 36. The second interface structure 32 further includes at least one complementary electrical connector 50 that is accommodated within a recess 52 within the second mounting surface 46. The complementary electrical connector 50 is attached in a floating manner.

[0068] The RHA 44 further comprises a hinge attachment 54 that is configured to attach to the yoke 18 via the hinge 22.

[0069] The quick fastening device 16 comprises a coupling member 56, e.g., in the form of a coupling ring, that can be coupled to the SAM adapter 24 such that the RHA 44 is fixedly mounted thereto. The coupling member 56 may be a threaded coupling ring that can be screwed onto the threaded portion 42 and press the RHA 44 against the SAM adapter 24.

[0070] Referring to Fig. 4, Fig. 5A, and Fig. 5B, the RHA 44 is explained in more detail. The RHA 44 comprises an RHA plate 58. The RHA plate 58 includes the recesses 52 for accommodating the complementary electrical connectors 50. The complementary electrical connectors 50 may be D-sub connectors. A floating plate 60 is attached to the complementary electrical connectors 50, e.g., by gluing. A cover plate 62 is mounted within the recess 52 to form a gap between the recess wall and the cover plate 62, thereby allowing the floating plate 60 to slide therebetween. The complementary electrical connectors 50 include a pattern of guiding holes 64 that matches the pattern of aligning pins 41 .

[0071] As shown in more detail in Fig. 5A and Fig. 5B, the RHA 44 is mounted to the yoke 18 via the hinge 22, and the complementary electrical connectors 50 protrude from the second mounting surface 46. The coupling member 56 is installed between the RHA 44 and the hinge 22.

[0072] Referring to Fig. 6, the SAM adapter 24 is explained in more detail. The SAM adapter 24 is formed as an SAM adapter plate 65 that is fastened to the SAMsolar array mount 66. The SAM adapter plate 65 includes at least one connector hole 68 to receive and fixedly hold the mechanical connector 36. The SAM adapter plate 65 further includes the recess 40. The electrical connector 38 is mounted in the recess 40 using the aligning pins 41 . The SAM adapter plate 65 includes the threaded portion 42, which is preferably formed on the circumferential surface of the SAM adapter plate 65. Furthermore, the coupling member 56 comprises a plurality of locking screws 57 that are threaded through a circumferential portion of the coupling member 56. The locking screws 57 are preferably self-cutting grub screws. The locking screws 57 are configured to prevent unthreading of the coupling member 56.

[0073] Referring to Fig. 7 to Fig. 10, the method for final assembly of the spacecraft 10 using the quick fastening device 16 is described in more detail. The spacecraft 10 has mounted thereon the SAM adapter 24. The SAM adapter 24 is fully connected in an electrical and mechanical manner to the spacecraft 10.

[0074] Furthermore, the RHA 44 is fully connected in an electrical and mechanical manner to the SA 14. As shown in Fig. 7, the SA 14 is temporarily mounted to a movable installing device 70. It should be noted that the SA 14 is in its launch position and not even partially deployed. Both the SAM adapter 24 and the RHA 44 are accessible in this configuration.

[0075] The installing device 70 is moved towards the spacecraft 10 so that the RHA 44 engages the SAM adapter 24. Fig. 8 gives an impression of a view along the axis of movement.

[0076] As illustrated in Fig. 9, the mechanical connectors 36 are introduced into the complementary mechanical connectors 48 forming a slight press-fit. At the same time or immediately after the mechanical connectors 36, 48 are engaged, the aligning pins 41 are introduced into the guiding holes 64. The aligning pins 41 force the floating electrical connector 50 to align with the electrical connector 38, such that the electrical connectors 38, 50 can be electrically connected without exerting significant force.

[0077] Finally, the coupling member 56 is threaded onto the threaded portion 42 and presses the RHA 44 against the SAM adapter 24. The locking screws 57 are inserted and tightened in order to prevent unthreading of the coupling member 56.

[0078] The SA 14 can be released from the installing device 70 and is now securely coupled to the spacecraft 10 in an electrical and mechanical manner without the need for any intermediate steps, such as cable routing etc. List of reference signs:

[0079] 10 spacecraft

[0080] 12 spacecraft sidewall

[0081] 14 solar array (SA)

[0082] 16 quick fastening device

[0083] 18 yoke

[0084] 20 panel

[0085] 22 hinge

[0086] 24 solar array mount (SAM) adapter

[0087] 26 SAM attachment side

[0088] 28 SA attachment side

[0089] 30 first interface structure

[0090] 32 second interface structure

[0091] 34 first mounting surface

[0092] 36 mechanical connector

[0093] 38 electrical connector

[0094] 40 recess

[0095] 41 aligning pin

[0096] 42 threaded portion

[0097] 44 root hinge adapter (RHA)

[0098] 46 second mounting surface

[0099] 48 mechanical connector

[0100] 50 electrical connector

[0101] 52 recess

[0102] 54 hinge attachment

[0103] 56 coupling member

[0104] 57 locking screw

[0105] 58 RHA plate

[0106] 60 floating plate

[0107] 62 cover plate

[0108] 64 guiding holes

[0109] 65 SAM adapter plate 66 solar array mount (SAM)

[0110] 68 connector hole

[0111] 70 installing device L longitudinal axis

Claims

Airbus Defence and Space GmbH 2317 0393 P-WOWilli-Messerschmitt-Stra(3>e 1 20048-WO-PCT82024 TaufkirchenClaims1. A quick fastening device (16) configured for fastening a solar array (14) to a vehicle, preferably a spacecraft (10), the device comprising:- a solar array mount (SAM) adapter (24) that is configured to be mounted to a SAM (66) of the vehicle;- a root hinge adapter (RHA) (44) that is configured to be positively joined to the SAM adapter (24), wherein one of the SAM adapter (24) and the RHA (44) includes a first interface structure (30) and the other of the SAM adapter (24) and the RHA (44) includes a second interface structure (32), wherein the first interface structure (30) has a first mounting surface (34) and the second interface structure (32) has a second mounting surface (46) that, when in the mounted position, face each other, wherein the first and second interface structure (30, 32) are configured to be mechanically and connectable by moving the RHA (44) and the SAM adapter (24) relative to each other along a direction perpendicular each of the first and second mounting surfaces (34, 46).

2. The quick fastening device (16) of claim 1 , further comprising a coupling member (56) that is configured to hold the RHA (44) in place relative to the SAM adapter (24).

3. The quick fastening device (16) of any of the preceding claims, wherein the first interface structure (30) includes a mechanical connector (36, 48) that protrudes from the first mounting surface (34) wherein the mechanical connector (36, 48) is configured to form a press-fit with the second interface structure (32).

4. The quick fastening device (16) of any of the preceding claims, wherein the second interface structure (32) includes a mechanical connector (36, 48) that is configured to receive a protruding mechanical connector of the first interface structure (30), wherein the mechanical connectors (36, 48) are configured to form a press-fit.

5. The quick fastening device (16) of any of the claims 3 or 4, wherein first interface structure (30) includes a dowel pin as the protruding mechanical connector and / or the second interface structure (32) includes a dowel hole as the receiving mechanical connector.

6. The quick fastening device (16) of any of the preceding claims, wherein at least one dowel hole is formed as an elongated hole, in which the dowel pin is received to be movable along one direction.

7. The quick fastening device (16) of any of the preceding claims, wherein the first interface structure (30) includes an electrical connector (50) that is fixedly attached and that is configured to cause the second interface structure (32) to align so that an electrical connection can be formed.

8. The quick fastening device (16) of any of the preceding claims, wherein the second interface structure (32) includes an electrical connector (50) that is attached in a floating manner, wherein, when the RHA (44) engages the SAM adapter (24), the floating electrical connector gets aligned and electrically connected to a fixed electrical connector.

9. The quick fastening device (16) of any of the claims 7 or 8, wherein the fixed electrical connector includes at least one aligning pin (41 ) that engages a connector hole (68) of the floating electrical connector to align the floating electrical connector with the fixed electrical connector.

10. The quick fastening device (16) of any of the claims 8 or 9, wherein the floating electrical connector includes a floating plate (60) that is fixedly attached theretoand is movably supported between a cover plate (62) and a recess (40) in the second mounting surface (46).11 . The quick fastening device (16) of any of the claims 2 to 10, wherein the RHA (44) comprises a threaded portion (42) for threading on the coupling member (56) to fasten the RHA (44) to the SAM adapter (24).

12. The quick fastening device (16) of any of the claims 2 to 11 , wherein the coupling member (56) comprises at least one locking screw (57) that is disposed to prevent unthreading of the coupling member (56).

13. A solar array (14) for a vehicle, preferably a spacecraft (10), wherein the solar array (14) comprises a plurality of panels (20) for generating electrical power and a quick fastening device (16) of any of the preceding claims.

14. A vehicle, preferably a spacecraft (10), comprising a solar array driving mechanism (66) and a solar array (14) that is attached to the solar array driving mechanism (66) by a quick fastening device (16) of any of the claims 1 to 12, or a solar array (14) of claim 13.

15. A method for mounting a solar array (14) to a solar array mount (SAM) (66) using a quick fastening device (16) of any of the claims 1 to 12, the method comprising installation of a solar array driving adapter (24) on the SAM (66) and installing the RHA (44) on the solar array (14), moving the RHA (44) along a movement axis that is perpendicular to the first and second mounting surfaces (34, 46) so that the first and second interface structures (30, 32) couple in a mechanical and an electrical manner, and securing the RHA (44) to the SAM adapter (24).

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