Systems and methods for holding and releasing large antenna reflector

Abstract

To provide systems and methods for holding and releasing a deployable component.SOLUTION: The system includes a plurality of latching mechanisms each including a first component attached to a deployable component and a second component attached to a spacecraft. In a hold position, the first components are held by the second components, respectively. A pivoting mechanism rotating to move the first components into the hold position, is disposed on a lower surface of the deployable component. A release mechanism holds the pivoting mechanism in a retracted configuration. In the retracted configuration, the pivoting mechanism is rotated in a first direction and the first components are held by the second components, respectively. Releasing the release mechanism rotates the pivoting mechanism in a second direction and releases the first components from the hold position.SELECTED DRAWING: Figure 1A

Description

Technical Field

[0001] The following generally relates to a latching retainer release mechanism, and more particularly to a latching mechanism for a large antenna reflector in a space-based application.

Background Art

[0002] A hold and release mechanism (HRM) is required to secure a large antenna reflector to a satellite spacecraft during launch. These HRMs typically include disconnect nuts and control lines from the spacecraft to the reflector, but their long lead times increase cost and schedule. Some HRMs require additional components such as motors to effect release, resulting in increased weight and cost due to such additional materials.

Summary of the Invention

Problems to be Solved by the Invention

[0003] Accordingly, there is a need for an improved latching mechanism for an antenna reflector that addresses at least some of the drawbacks of existing systems and methods.

Means for Solving the Problems

[0004] A latching mechanism system for holding and releasing deployable components. The latching mechanism system includes a plurality of latching mechanisms disposed on a spacecraft, each latching mechanism including a first component attached to a deployable component and a second component attached to the spacecraft. In a stowed configuration, each of the first components is held by a respective second component. Further, the latching mechanism system includes a rotation mechanism disposed on a lower surface of the deployable component and configured to rotate in a first direction to move the first component to the stowed configuration and to rotate in a second direction opposite the first direction to release the first component from the stowed configuration.

[0005] This rotating mechanism may be a pivoting mechanism, and the aforementioned system may further include a release mechanism for holding the pivoting mechanism in a stored configuration. In the stored configuration, the pivoting mechanism is in a state where potential energy is accumulated, and by releasing the release mechanism, the accumulated potential energy is released to rotate the pivoting mechanism in a second direction, and the first component is released from the stored configuration.

[0006] The rotating mechanism may be a rotary actuator.

[0007] The first component may be a pin, and the second component may be a latch.

[0008] The first component may be a pin, and the second component may be a latch with a groove. Here, this pin is oriented radially with respect to the rotating mechanism.

[0009] The first component may be a cone, and the second component may be a cup. Here, the cone-in-cup contact portion forms an engagement portion with a conical shaft oriented circumferentially with respect to the rotating mechanism.

[0010] The release mechanism may be a split nut, a high-output paraffin (HOP) mechanism, a cable cutter, or a bolt-breaking device.

[0011] The deployable component may be connected to the boom by a rotary joint at approximately the geometric center of the deployable component.

[0012] The release mechanism may be connected to the boom.

[0013] The pivotal mechanism may include a plurality of radially flexible blades. When the pivotal mechanism is rotated in a first direction and held by the release mechanism, the radially flexible blades are distorted. When the release mechanism is released, the accumulated positional energy in the distorted flexible radial blades rotates the pivotal mechanism in a second direction, rotates the deployable component, releases the first component from the second component, thereby releasing the deployable component.

[0014] Each of the plurality of latching mechanisms may include a spring mechanism that holds the first component and the second component in a holding position. Each spring mechanism may be a torsion spring, and this torsion spring releases the first component when sufficient torque is applied by the release of the release mechanism and the rotation of the pivotal mechanism in the second direction.

[0015] The plurality of latching mechanisms may constrain the deployable component along the axial and radial directions with respect to the pivot axis.

[0016] The deployable component may be an antenna reflector.

[0017] A method of latching a deployable component holding and releasing latching mechanism system is provided herein. The method includes rotating a rotating mechanism about a rotation axis of the rotating mechanism in a first direction until each of the plurality of first components of the latching mechanism system is held by a respective second component of the plurality of second components of the latching mechanism system, wherein the plurality of first components are mounted to a first surface of the deployable component and the plurality of second components are mounted to a spacecraft.

[0018] This rotating mechanism may be a pivotal mechanism mounted to the first surface of the deployable component and the boom, and includes a plurality of radially flexible blades that are distorted when rotated in the first direction. The method may further include the step of restraining the pivotal mechanism in a stored configuration by a release mechanism, in which stored configuration each of the plurality of first components is held by a respective second component, and in which stored configuration the plurality of radially flexible blades store torsional energy in a second direction opposite to the first direction.

[0019] The method may further include the step of restraining each of the plurality of first components within a respective second component by a spring mechanism.

[0020] The first component may be a pin and the second component may be a latch.

[0021] The first component may be a pin and the second component may be a latch with a groove, and the pin is oriented radially with respect to the rotating mechanism.

[0022] The first component may be a cone and the second component may be a cup, and the cone-in-cup contact forms an engagement with a conical axis oriented circumferentially with respect to the rotating mechanism.

[0023] The spring mechanism may be a torsion spring.

[0024] The rotating mechanism may be a rotary actuator coupled to the deployable component.

[0025] This specification provides a method for releasing a latching mechanism for holding and releasing a large deployable component. The method includes the step of releasing, by operating a release mechanism, torsional energy stored from a plurality of radially flexible blades of a pivoting mechanism held in a stowed configuration by the release mechanism, wherein the pivoting mechanism is attached to a surface and a boom of the deployable component and the plurality of radially flexible blades are distorted by rotation of the pivoting mechanism in a first direction. By releasing the stored torsional energy, the pivoting mechanism is rotated in a second direction opposite the first direction such that a plurality of first components attached to a non-reflective surface of the deployable component are released from a plurality of respective second components attached to a spacecraft, whereby the deployable component is moved to a deployed configuration.

[0026] The release mechanism may be one of a split nut, a high output paraffin (HOP) mechanism, a cable cutter, and a bolt breaking device.

[0027] The release mechanism may be actuated by application of heat.

[0028] A system is provided for storing and later releasing a deployable component. The system includes a rotation mechanism for rotating in opposite first and second directions, such that rotation in the first direction accumulates a preload in the form of rotational potential energy. The rotation mechanism is attached to the deployable component such that rotation of the rotation mechanism is transmitted to the deployable component or causes rotation of the deployable component in the same direction. A release mechanism locks the rotation mechanism in a fixed position when the pivot mechanism is rotated to a locked position in the first direction, thereby preventing the rotation mechanism from rotating in the second direction. A latching mechanism includes a first hardware component on a lower surface of the deployable component and a second hardware component on a spacecraft, the first and second hardware components being configured to engage to latch and hold the deployable component relative to the spacecraft. When the release mechanism is released, the rotation mechanism rotates in the second direction via release of the preload, and rotation of the rotation mechanism rotates the deployable component in the second direction, thereby disengaging the first hardware component of the latching mechanism from the second hardware component, thereby releasing the deployable component from the spacecraft.

[0029] This specification provides a method for storing a deployable component for later release. The method includes the steps of providing (i) a latching mechanism comprising a first hardware component on the deployable component and a second hardware component on a spacecraft that houses the spacecraft, (ii) a pivoting mechanism, and (iii) a release mechanism; accumulating rotational potential energy in the pivoting mechanism by rotating the pivoting mechanism to a locked position in a first direction, the locked position being located in the first direction at a distance sufficient to latch the latching mechanism by engaging the second hardware component with the first hardware component; latching the latching mechanism while the pivoting mechanism is in the locked position; locking the pivoting mechanism in the locked position using the release mechanism to prevent rotation of the pivoting mechanism in a second direction, wherein when the release mechanism is released, the pivoting mechanism rotates in the second direction with sufficient force to disengage the first hardware component from the second hardware component, thereby releasing the deployable component from the spacecraft.

[0030] This specification provides a method for deploying a deployable component from a stowed configuration. The method includes setting the pivot mechanism to a locked position where the pivot mechanism stores a preload in the form of rotational potential energy, the locked position being achieved by rotating the pivot mechanism in a first direction, and the pivot mechanism being attached to the deployable component such that rotation of the pivot mechanism is transmitted to the deployable component or causes rotation of the deployable component in the same direction; releasing a release mechanism that holds the pivot mechanism in the locked position to enable release of the preload in the pivot mechanism; unlatching a latching mechanism via a rotational movement of the pivot mechanism in a second direction caused by releasing the preload accumulated in the pivot mechanism when in the locked position, the rotation of the pivot mechanism disengaging a first hardware component of the latching mechanism attached to the deployable component from a second hardware component of the latching mechanism attached to a spacecraft that houses the deployable component with sufficient force to rotate the deployable component in the second direction, thereby releasing the deployable component from the spacecraft.

[0031] This specification provides a method for stowing a deployable component for later release. The method includes providing (i) a latching mechanism including a first hardware component on the deployable component and a second hardware component on a spacecraft that houses the spacecraft, and (ii) a rotary actuator; and rotating the rotary actuator in a first direction to a locked position, the locked position being located in the first direction at a distance sufficient to latch the latching mechanism by engaging the second hardware component with the first hardware component.

[0032] Furthermore, the method may further include locking the first hardware component in the locked position using a release mechanism to prevent rotation of the deployable component in a second direction opposite the first direction, and disengaging the first hardware component from the second hardware component by rotating the deployable component when the release mechanism is released, thereby releasing the deployable component from the locked position.

[0033] In the locked position, the deployable element may accumulate potential energy for automatically releasing the deployable element from the locked position when the release mechanism is released.

[0034] The rotation actuator may rotate the deployable element in the second direction when the release mechanism is released.

[0035] Other aspects and features will become apparent to those of ordinary skill in the art by considering the following description of some exemplary embodiments.

[0036] The drawings attached hereto are for the purpose of illustrating various examples of the articles, methods, and apparatuses herein.

Brief Description of the Drawings

[0037]

Figure 1A

Figure 1B

Figure 1C

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Figure 5D

Figure 6A

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Figure 8C

[0038] The following describes various devices or processes in order to present examples of each of the claimed embodiments. None of the embodiments described below limit the claimed embodiments, and any of the claimed embodiments may include processes or devices different from those described below. These claimed embodiments are not limited to all of the features of any one device or process described below, or to devices or processes having features common to a plurality or all of the devices described below.

[0039] Furthermore, although process steps, method steps, algorithms, etc. may be described in sequence (in this disclosure and / or in the claims), these processes, methods, and algorithms may be configured to function in other sequences. In other words, the order or sequence of steps that may be described does not necessarily imply that those steps need to be performed in that order. The steps of the processes described herein may be performed in any practicable order. Additionally, some steps may be performed simultaneously.

[0040] It will be readily apparent that where a single device or article is described herein, two or more devices / articles (regardless of whether they cooperate) may be used in place of the single device / article. Similarly, it will be readily apparent that where two or more devices or articles (regardless of whether they cooperate) are described herein, a single device / article may be used in place of the two or more devices / articles.

[0041] The present disclosure generally relates to a latching retainer release mechanism, and more particularly to a latching mechanism for deployable components (such as large antenna reflectors) in space-based applications. Further, the present disclosure relates to a disposable latching mechanism for deployable components such as large antenna reflectors.

[0042] The systems, methods, and devices of the present disclosure can be used to hold and release deployable components. Such deployable components can be, for example, antennas, antenna reflectors, propulsion systems, scientific instruments, cameras, or other optical systems. The deployable components may be components or devices intended for use in space. Although the present disclosure refers throughout to the holding and releasing of an antenna reflector, this is a non-limiting example of a deployable component for which the systems and methods of the present disclosure can be used, and it should be understood that the holding and releasing of other deployable components is clearly contemplated herein.

[0043] The latching system of the present disclosure uses a rotating mechanism mounted to the mirror and boom. This rotating mechanism may be a pivotal mechanism, a rotary actuator, or other mechanism capable of effecting rotation of the mirror. The rotating mechanism is rotated in a first direction to insert a first component on the mirror into a second component on a spacecraft (or other base of the mirror). The first component may be a latching pin on the mirror that is inserted into a latching groove of a latch (second component) on the spacecraft. This rotating mechanism can be held in a fixed position by a release mechanism. The rotating mechanism has a rotation axis positioned at the center of the mirror (preferably the center of this mirror is the center of gravity of the mirror). The rotating mechanism is oriented along the normal plane of the mirror.

[0044] The latching system includes at least three latching mechanisms spaced concentrically around the rotation axis of the rotating mechanism. Each latching mechanism includes a latch and a latching pin. Each latch includes a groove for receiving the latching pin.

[0045] When the latching pin is located within the groove of the latch, a spring can hold the latching pin in a fixed position within this groove.

[0046] When the rotating mechanism is a pivotal mechanism, the rotation of this pivotal mechanism can be prevented by a release mechanism. The release mechanism may be a bolt-breaking device (such as a flange bolt), or any other releasable or breakable / fracturable connection that can be released without the use of a motor.

[0047] The pivotal mechanism may include a radially flexible blade. This radially flexible blade is distorted when the pivotal mechanism is rotated in a first direction and held by the release mechanism. This distortion of the radially flexible blade accumulates potential energy. When the release mechanism is released or actuated, this accumulated potential energy causes the pivotal mechanism to rotate the mirror along the latching groove with sufficient torque and displacement to release the spring holding the latching pin in the latching groove, thereby releasing the mirror. When released, the boom becomes the only remaining link between the mirror and the spacecraft.

[0048] The latching mechanism of the present disclosure can provide various advantages including reduction in materials, time, and cost when compared to conventional HRMs. Further, there is only one release mechanism required to release a payload such as an antenna mirror from a stowed configuration.

[0049] Referring now to FIGS. 1A - 1C, a portion of an antenna system 100 including a latching system for realizing a holding function and a release function by a pivotal mechanism according to an embodiment is shown.

[0050] The antenna system 100 includes a mirror 110 for reflecting a radio frequency (RF) signal, and a boom 120 for maneuvering or moving the mirror 110 in one or more directions. The boom 120 is connected to the mirror 110 at one end and to the spacecraft on which the antenna system is disposed at the other end.

[0051] The mirror 110 includes a first surface 112 (or upper surface 112) and an opposite second surface 114 (or lower surface 114). The upper surface 112 is a reflective surface and is used to reflect RF signals. The lower surface 114 is used to attach various components, including components of the latching system, to the mirror 110.

[0052] The top view of FIG. 1A is a view of the upper surface or reflective surface 112 of the mirror 110. For purposes of illustration, in FIG. 1A, the mirror 110 is shown as a transparent portion so that elements located below the mirror 110 are visible. Note that all elements shown within the circle of the mirror 110 in FIG. 1A are located at points below or behind the mirror 110.

[0053] The boom 120 is coupled to the mirror 110 by a rotary joint (not shown) located substantially at the geometric center of the mirror 110 to enable movement of the mirror during the release operation. This rotary joint may include an electric rotary actuator.

[0054] The antenna system 100 includes a latching system for implementing a pressing function and a release function with respect to the mirror 110. Generally, this latching system holds the mirror 110 in a stowed configuration or stowed position when the latching system is released. When released, the mirror 110 can be deployed by the boom 120.

[0055] This latching system includes a pivoting mechanism 130, a release mechanism 140, and three latching mechanisms 150. In other embodiments, the number of latching mechanisms 150 may be four or more.

[0056] The pivoting mechanism 130 is coupled to both the mirror 110 and the boom 120. The pivoting mechanism 130 has a rotation axis at the center of the mirror 110. The pivoting mechanism 130 is oriented along the normal plane of the mirror 110.

[0057] The pivot mechanism 130 is a bracket comprising two concentric circular components 132 (inner circle) and 134 (outer circle) connected by a plurality of radially flexible blades 136. In the embodiments of FIGS. 1A - 1C, the number of blades 136 is eight. In other embodiments, the number of blades 136 may vary depending on the length and cross-sectional dimensions of the blades, and the design of the blades 136 is determined by the torque and rotation required to release the pin 154 from the latch 152.

[0058] The pivot mechanism 130 comprises a retention release mechanism linkage component 138. The retention release mechanism linkage component 138 forms a linkage portion with the release mechanism 140.

[0059] Furthermore, the release mechanism 140 is also mounted to the boom 120. The pivot mechanism 130 and the release mechanism 140 cooperate to achieve a release function (described below) that releases the mirror 110 from the stowed configuration.

[0060] In one embodiment, the pivot mechanism 130 is a metal bracket. This metal may be, for example, aluminum, titanium, steel, or invar. The pivot mechanism 130 may be manufactured by machining or additive manufacturing.

[0061] The latching mechanism 150 is positioned concentrically with respect to the center of gravity of the mirror 110. The latching mechanisms 150 are positioned at approximately equal distances from each other.

[0062] In some embodiments, the latching mechanism 150 may be a pin-in-groove latching mechanism having a pin 154 oriented radially with respect to the pivot mechanism 130, a cone-in-cup contact linkage having a conical shaft oriented circumferentially with respect to the pivot mechanism 130, or any configuration that provides at least two degrees of freedom restriction with respect to the pivot mechanism 130.

[0063] Each latching mechanism 150 comprises a latch 152 and a latching pin 154.

[0064] Latch 152 is mounted to a spacecraft (see, e.g., spacecraft panel 160 of FIG. 1B) on which mirror 110 (and antenna system 100) is disposed. For example, latch 152 may be mounted on a structure on the spacecraft such as a spacecraft platform or bus panel.

[0065] Latching pin 154 is mounted to the lower surface 114 of mirror 110. When latching pin 154 is held within latch 152, mirror 110 is mounted to the spacecraft via the latching mechanism (by latch 152 being mounted to the spacecraft, latching pin 154 is mounted to mirror 110, and latching pin 154 is held within latch 152).

[0066] Each latch 152 has a groove 153 into which respective latching pin 154 can be received.

[0067] Each latch 152 includes a spring mechanism 157. Spring mechanism 157 holds latching pin 154 within groove 153.

[0068] The direction in which latching pin 154 enters / exits into / out of groove 153 is a tangential direction with respect to a vector extending from latch 152 to the center of gravity of mirror 110.

[0069] The layout and number of latching mechanisms 150 limit out-of-plane and in-plane radial movement of mirror 110.

[0070] During operation, the rotating section 134 of pivot mechanism 130 and the fixed mirror 110 are rotated about the axis of rotation to a stowable position.

[0071] By the rotation of the pivoting mechanism 130, each latching pin 154 moves into each groove 153 on each latch 152. When the latching pin 154 is positioned within the groove 153, the release mechanism engagement portion 138 is placed in a position where interaction with the release mechanism 140 and retention in a fixed position by the release mechanism 140 are achieved. The rotational direction of the pivoting mechanism 130 for moving the latching pin 154 into the latch 152 is a first direction opposite to the second rotational direction of the pivoting mechanism 130 when the release mechanism is released. That is, when the rotation of the pivoting mechanism 130 for moving the latching pin 154 into the latch 152 is in the "clockwise direction", the rotation of the pivoting mechanism 130 for moving the latching pin 154 out of the latch 152 is in the "counterclockwise direction", and vice versa.

[0072] When the latching pin 154 and the release mechanism engagement portion 138 are held in a fixed position, the mirror 110 is placed in a retracted configuration.

[0073] When the pivoting mechanism 130 assumes the retracted configuration, the radially flexible blade 136 is distorted circumferentially and accumulates potential energy so that the pivoting mechanism 130 has a preload. That is, in this retracted configuration, due to the distortion of the radially flexible blade 136, a force is generated that applies pressure to the release mechanism in a direction opposite to the direction in which the pivoting mechanism rotates into the retracted configuration.

[0074] When the release mechanism 140 is released, the preload (i.e., potential energy) of the radially flexible blade 136 is released, and as a result, the resulting movement of the pivoting mechanism 130 (in the second direction) releases the latching pin 154 from the groove 153 of the latch 152, thereby releasing the mirror 110 from the retracted configuration.

[0075] The torque generated by the release of the potential energy of the radially flexible blade 136 is a torque strong enough to release the spring mechanism 157 that holds the latching pin 154 within the groove 153.

[0076] The flexibility of the radially flexible blade 136 generates potential energy when distorted, but also ensures that the pivoting mechanism 130 is not damaged by the actual movement that occurs.

[0077] The release mechanism 140 may be any mechanism that can be released without the use of a motor. For example, the release mechanism 140 may be a split nut, a bolt-breaking device (such as a flange bolt), a shape memory alloy-based actuator (such as having an explosively separable nut), a high-output paraffin (HOP) mechanism, or a cable cutter, etc. The release mechanism 140 is generally a single component and is a disposable component.

[0078] In one embodiment, the release mechanism 140 may be a bolt-breaking device (such as a flange bolt). The flange bolt may be configured to break when heated. By using a thermal line from the spacecraft to the flange bolt, the flange bolt may be heated to the breaking point.

[0079] In one embodiment, the release mechanism 140 may be a split nut. This split nut restrains the threaded section of the bolt, and this nut separation device is formed by two or more nut sub-sections that are split along the axial-radial plane of the threaded section. These nut sub-sections are compressed together by a coil wound spirally on the outer surface of the nut assembly. This coil receives a load in the circumferential direction when the bolt is preloaded. The coil is restrained by a fuse located at the end of the coil. This fuse is cut by an electrical input during release. Then, the coil is unwound from the nut assembly. Then, the bolt is released under the sudden release of the preload that the bolt itself has.

[0080] After release, the mirror 110 is connected to the spacecraft only indirectly via the boom 120 (i.e., the boom 120 is connected to the spacecraft at one end and to the mirror 110 at the other end).

[0081] FIG. 1B is a schematic cross-sectional view of the antenna system 100 along line A-A of FIG. 1A, showing the single latching mechanism 150 and the mirror 110 separately.

[0082] The latching mechanism 150 includes a latch 152 that is coupled to or otherwise associated with a spacecraft panel 160 (e.g., a satellite platform) of the spacecraft.

[0083] The latching mechanism 150 includes a latching pin 154 that is coupled to the lower surface 114 of the mirror 110.

[0084] The latch 152 includes a groove 153 in which the latching pin 154 can move in (and out). In FIG. 1B, the latching pin 154 is located within the groove 153.

[0085] The latching pin 154 includes a body 155 and a head 156. The width of the body 155 is such that the latching pin 154 can move into (and out of) the groove 153 (in the horizontal direction of FIG. 1B), and the width of the head 156 is such that it prevents the latching pin 154 from moving upward out of the groove 153 when the mirror 110 moves upward and away from the latch 152 (in the vertical direction of FIG. 1B).

[0086] The latching pin 154 is held in a fixed position within the groove 153 indirectly by a release mechanism 140 (not shown) that holds the pivot mechanism 130 (not shown) when the pivot mechanism 130 is in a stowed configuration, and directly by a spring mechanism 157.

[0087] The spring mechanism 157 does not have sufficient strength to hold the pin 154 in a fixed position when the release mechanism 140 is not holding the pivot mechanism 130, but ensures that the latching pin 154 remains within the groove 153.

[0088] In one embodiment, the spring mechanism 157 is a torsion spring that releases the latching pin 154 when a torque of sufficient magnitude is applied by the release of the release mechanism 140. A lever that rotates about a shaft is present between this torsion spring and the movable pin, thereby providing a mechanical advantage and enabling the mirror 110 to be returned to its fixed position and stored. FIG. 4 shows an embodiment of a latching mechanism 150 including a torsion spring as the spring mechanism 157 and a latching pin 154. FIGS. 5A-5D and FIGS. 6A-6D show the latching release operation 500 and the latching operation 600 of the latching mechanism of the example of FIG. 4, respectively.

[0089] FIG. 4 shows an example of a latching mechanism. This latching mechanism is shown in a state of being connected to a spacecraft or a mirror (or other deployable component), not shown. Only the elements of the latching mechanism described in the latching operation and the latching release operation are numbered. This latching mechanism includes a latch body, a cam 158 and a cam shaft for rotation of the cam 158, a guide groove in the latch body, a deployment lever of the cam 158, a reset lever of the cam 158, a torsion spring 157, and a pin 154.

[0090] FIGS. 5A-5D show aspects of the latching release operation for the embodiment of FIG. 4. For the sake of clarity, the components are numbered only in FIG. 5A. In FIG. 5A, the latching pin 154 is located at the bottom (or back) of the latch, and the spring mechanism 157 holds the cam 158 in a fixed position. In FIG. 5B, the cam 158 prevents the latching pin 154 from moving out of the latch. In FIG. 5C, the cam 158 is at an inflection point, at which point, under an external pressure (e.g., due to the release of accumulated potential energy), the latching pin 154 remains held within the latch, but the cam 158 is pressing on the spring mechanism 157. In FIG. 5D, the cam 158 presses sufficiently on the spring mechanism 157, thereby releasing the latching pin 154 from the latch.

[0091] Figures 6A - 6D illustrate aspects of the latching operation for the embodiment of FIG. 4. For clarity, components are numbered only in FIG. 6A. In FIG. 6A, the latching pin 154 is released from the latch and the cam 158 is in a stable open position. In FIG. 6B, the latching pin 154 moves into the latch and contacts the reset lever. In FIG. 6C, the cam 158 is unlocked from the open position and captures the latching pin 154, where the spring mechanism 157 holds the cam 158 in the closed position. In FIG. 6D, the latching pin 154 is in a fully latched position at the bottom or back of the latch.

[0092] In other embodiments, the latching mechanism may hold the mirror in the stowed configuration by utilizing functions other than the spring mechanism.

[0093] Referring now to FIG. 1C, a schematic cross - sectional view of the antenna system 100 along line B - B of FIG. 1A is shown (without the latch 152).

[0094] View B - B of FIG. 1C shows the mirror 110, boom 120, pivot mechanism 130, and release mechanism 140. The pivot mechanism 130 includes a plurality of stiffening ribs 133 integral with a portion of the pivot mechanism 130 fixed to the mirror 110.

[0095] The boom 120 includes a boom segment 122 and a boom bracket 124. The boom segment 122 is coupled to the spacecraft. The boom bracket 124 is coupled to the mirror 110 and the pivot mechanism 130. The boom segment 122 may be metal or a composite material. The boom bracket 124 is disposed between the boom segment 122 and the pivot mechanism 130. The boom bracket 124 may be composed of a metal material. In one embodiment, the boom segment 122 and the boom bracket 124 are a single integral metal part. The boom segment 122 can be deployed from the stowed position to the operating position when in orbit. The boom bracket 124 provides a pre - loaded rigid load path that acts between the pivot mechanism 130 and the hold - release mechanism 140.

[0096] Similar to that in FIG. 1A, the pivoting mechanism 130 includes two concentric circular components 132, 134 (an inner circular component 132 and an outer circular component 134). The inner circular component 132 is connected to the outer circular component 134 by a plurality of radially flexible blades 136. In other embodiments, these circular components 132, 134 may be square, hexagonal, or any other suitable shape.

[0097] The circular component 132 is mounted to the boom bracket 124.

[0098] The release mechanism 140 is connected to both the pivoting mechanism 130 (via the linkage component 138) and the boom 120 (via the boom bracket 124). In some embodiments, a shim may be added between the boom bracket 124 and the pivoting mechanism 130 (e.g., the linkage component 138) to adjust the preload applied to the mirror 110.

[0099] FIG. 7 shows the connection (including the separation surface 702) between the pivoting mechanism 130, the release mechanism 140, and the boom bracket 124. This figure is a cross-sectional view of the flange bolt and the separation surface for releasing the stored energy.

[0100] The pivoting mechanism 130 is mounted to the mirror 110 by a connection portion 139. The connection portion 139 may be integral with the outer circular component 134, or may be a separate part connected by bolting or adhesion. In some embodiments, the boom bracket 124, the pivoting mechanism 130, and the mirror 110 may be integrally formed parts.

[0101] In the storage configuration, the pivoting mechanism 130 is pivoted such that the release mechanism 140 holds the release mechanism linkage component 138 of the pivoting mechanism 130. As the pivoting mechanism 130 pivots into the storage configuration, the radially flexible blades 136 are distorted to store potential energy. When this stored potential energy is released, torque is generated.

[0102] Next, referring to FIG. 2, a method 200 for holding a mirror of an antenna system in a stowed configuration using a plurality of latching mechanisms according to an embodiment is shown. This antenna system may be the same as or identical to the antenna system 100 of FIGS. 1A - 1C.

[0103] This method 200 includes, at 202, rotating a pivotal mechanism mounted to the lower surface of the mirror and boom (the surface closest to the spacecraft) about the axis of rotation of the pivotal mechanism until each of a plurality of latching pins mounted to the lower surface of the mirror is positioned within a respective latch mounted to the surface of the spacecraft (e.g., a spacecraft panel).

[0104] That is, a pivotal mechanism including a bracket having two concentric circular components (outer and inner) connected by a plurality of radially flexible blades is rotated relative to the boom. The pivotal mechanism is mounted to the lower surface of the mirror, and thus the mirror rotates with the pivotal mechanism. The latching pins also exist on the lower surface of the mirror and move with the mirror to interact with the latches. These latches have grooves, and the latching pins hold the mirror in the stowed configuration by moving within these grooves. The stowed configuration is closer to the spacecraft than the deployed configuration.

[0105] Method 200 further includes, at 204, restraining the pivotal mechanism using a release mechanism on the boom. This release mechanism may be a flange bolt. The pivotal mechanism has a release mechanism linkage mounted to an outer circular part that interacts with the release mechanism. The release mechanism holds the pivotal mechanism in the stowed configuration.

[0106] As the pivotal mechanism rotates, the radially flexible blades of the pivotal mechanism are distorted, thereby generating potential energy stored in the radially flexible blades while the pivotal mechanism is in the stowed configuration.

[0107] Preferably, the method 200 includes, at 206, restraining the latching pin using a spring mechanism.

[0108] That is, the spring mechanism on each latch holds the latching pin within the groove of the latch. The spring mechanism may be a torsion spring mechanism or any mechanism that holds the latching pin within the groove and is released when the release mechanism is released.

[0109] The distance through which the pivoting mechanism is rotated need not be large. For example, this distance may be as small as 0.5 inches or greater than 1 inch, as long as there is sufficient potential energy in the radially flexible blades for the release mechanism and the latching pin to hold the mirror in the stowed configuration and move the mirror to the deployed position.

[0110] Next, referring to FIG. 3, a method 300 for releasing the latching mechanism of FIGS. 1A - 1C according to one embodiment is shown.

[0111] This method 300 includes, at 302, releasing the release mechanism. That is, regardless of the form the release mechanism takes, the release mechanism is released such that the mirror is in a released state from the stowed configuration.

[0112] In one embodiment where the release mechanism is a flange bolt, heat is applied to the flange bolt until the flange bolt breaks. When it breaks (or in the case of a non - flange - bolt release mechanism, when another release form occurs), the pivoting mechanism is released from the release mechanism, and the potential energy stored in the distorted radially flexible blades of the pivoting mechanism is released, thereby generating torque by the return rotation in the reverse direction required for the pivoting mechanism to assume the stowed configuration.

[0113] The latching pin is released from the groove of the latch as the pivoting mechanism rotates.

[0114] In one embodiment having a spring mechanism, the torque generated by the radially flexible blades overcomes the pressure of the spring mechanism, thereby causing the spring mechanism to open and release the latching pin from the latch.

[0115] When the pivoting mechanism and the latching pin are released, the mirror assumes the deployed position.

[0116] Figures 1A - 1C illustrate and describe an antenna system having a latching system with a pivoting mechanism. This pivoting mechanism releases the antenna from the stowed configuration by using stored energy. In another embodiment, the latching system may comprise a rotary actuator that is actuated to release the antenna from the stowed configuration as shown in Figures 8A and 8B.

[0117] Figure 8A is a schematic top view of a portion of an antenna system 800 comprising a latching system for latching an antenna mirror 810. This latching system comprises a rotary actuator 870, and the antenna mirror is shown as a transparent portion. The latch of Figure 8A may be similar or identical to the latch described above with respect to Figure 1B and the latches of other embodiments described herein.

[0118] The antenna system 800 comprises a mirror 810 that reflects radio frequency ( "RF") signals and a boom 820 for steering or moving the mirror 810 in one or more directions. The boom 820 is connected to the mirror 810 at one end and to a spacecraft on which the antenna system is disposed at the other end.

[0119] The mirror 810 comprises a first surface 812 (or upper surface 812) and an opposite second surface 814 (or lower surface 814). The upper surface 812 is a reflective surface and is used to reflect RF signals. The lower surface 814 is used to attach various components, including components of the latching system, to the mirror 810.

[0120] The top view of FIG. 8A is a view of the upper surface or the reflective surface 812 of the mirror 810. For the purpose of explanation, in FIG. 8A, the mirror 810 is shown as a transparent portion so that the elements located below the mirror 810 can be seen. Note that all the elements shown within the circle of the mirror 810 in FIG. 8A are located at points below or behind the mirror 810.

[0121] In FIGS. 8A - 8C, the boom 820 is coupled to the mirror 810 by a rotary actuator mechanism positioned substantially at the geometric center of the mirror 110, enabling movement of the mirror during the release operation. This rotary actuator mechanism includes an electric rotary actuator 870 coupled to a rotary actuator connector 872 attached to the mirror 810.

[0122] The antenna system 800 includes a latching system that implements a holding function and a release function for the mirror 810. Generally, this latching system holds the mirror 810 in a stowed configuration or stowed position until the latching system is released. When released, the mirror 810 can be deployed by the boom 820.

[0123] This latching system includes a rotary actuator mechanism including the rotary actuator 870 and the rotary actuator connector 872, and three latching mechanisms 850. In other embodiments, the number of latching mechanisms 850 may be four or more.

[0124] As described above, the rotary actuator 870 is coupled to the rotary actuator connector 872 and the boom 820. The rotary actuator 870 has a rotation axis at the center of the mirror 810 and rotates the mirror along the normal plane of the mirror 810.

[0125] The rotary actuator 870 implements both a stowing mechanism for stowing the mirror 810 in the stowed configuration and a release mechanism for releasing the mirror 810 from the stowed configuration.

[0126] The latching mechanism 850 is positioned concentrically with respect to the center of gravity of the mirror 810. The latching mechanisms 850 are positioned at approximately equal distances from each other.

[0127] In some embodiments, (and as shown in FIG. 8B), the latching mechanism 850 may be a pin-in-groove latching mechanism having a pin 854 oriented radially with respect to the rotary actuator mechanism, a cone-in-cup contact engagement having a conical shaft oriented circumferentially with respect to the rotary actuator mechanism, or any configuration that provides at least two degrees of freedom of restraint with respect to the rotary actuator mechanism.

[0128] Each latching mechanism 850 includes a latch 852 and a latching pin 854 (illustrated in FIG. 8B).

[0129] The latch 852 is attached to a spacecraft (e.g., refer to the spacecraft panel 860 in FIG. 8B) on which the mirror 810 (and the antenna system 800) is disposed. For example, the latch 852 may be attached to a structure on the spacecraft such as a spacecraft platform or a bus panel.

[0130] The latching pin 854 is attached to the lower surface 814 of the mirror 810. When the latching pin 854 is held within the latch 852, the mirror 810 is attached to the spacecraft via the latching mechanism (by attaching the latch 852 to the spacecraft, the latching pin 854 is attached to the mirror 810 and the latching pin 854 is held within the latch 852).

[0131] Each latch 852 has a groove 853, and each latching pin 854 can be received within this groove 853.

[0132] Unlike the embodiments of FIGS. 1A - 1C, the latch 152 does not include a spring mechanism. The movement of the pin 854 into and out of the latch is effected by the force of the rotary actuator 870. However, in other embodiments, the latch 852 includes a spring mechanism that is released by the movement of the rotary actuator 870.

[0133] The direction in which the latching pin 854 enters / exits the groove 853 is the tangential direction with respect to the vector extending from the latch 852 to the center of gravity of the mirror 810.

[0134] The layout and number of the latching mechanisms 850 limit the out - of - plane and in - plane radial movement of the mirror 810.

[0135] During operation, the rotary actuator 870 and the fixed mirror 810 are rotated about the axis of rotation to a stowable position.

[0136] By the rotation of the rotary actuator 870, each latching pin 854 moves into its respective groove 853 on each latch 852. The direction of rotation of the rotary actuator 870 for moving the latching pin 854 into the latch 852 is the first direction, which is opposite to the second direction of rotation of the rotary actuator 870 for releasing the mirror 810 from the latch 852. That is, if the rotation of the rotary actuator 870 for moving the latching pin 854 into the latch 852 is in the "clockwise direction", then the rotation of the rotary actuator 870 for moving the latching pin 854 out of the latch 852 is in the "counter - clockwise direction", and vice versa.

[0137] After release, the mirror 810 is connected to the spacecraft only indirectly via the boom 820 (i.e., the boom 820 is connected to the spacecraft at one end and to the rotary actuator 870 and the mirror 810 at the other end).

[0138] FIG. 8B is a schematic cross-sectional view of the antenna system 800 along line A-A of FIG. 8A, showing the single latching mechanism 850 and the mirror 810 separately.

[0139] The latching mechanism 850 includes a latch 852 that is coupled to or otherwise associated with a spacecraft panel 860 (e.g., a satellite platform) of the spacecraft.

[0140] The latching mechanism 850 includes a latching pin 854 coupled to the lower surface 814 of the mirror 810.

[0141] The latch 852 includes a groove 853 into which (and out of which) the latching pin 854 can move. In FIG. 8B, the latching pin 854 is located within the groove 853.

[0142] The latching pin 854 includes a body 855 and a head 856. The width of the body 855 is such that the latching pin 854 can move (in the horizontal direction of FIG. 8B) into and out of the groove 853, and the width of the head 856 is such that it prevents the latching pin 854 from moving upward out of the groove 853 when the mirror 810 moves upward and away from the latch 852 (in the vertical direction of FIG. 8B).

[0143] The latching pin 854 is held in a fixed position within the groove 853 when the rotary actuator 870 is in the stowed configuration.

[0144] Referring now to FIG. 8C, a schematic cross-sectional view of the antenna system 100 along line B-B of FIG. 8A is shown (without the latch 852).

[0145] View B-B of FIG. 8C shows the mirror 810, the boom 820, the rotary actuator 870, and the rotary actuator connector 872.

[0146] The boom 820 may be made of metal or composite material. The boom 820 can be deployed from the stowed position to the operating position when on orbit.

[0147] Similar to that in FIG. 8A, the rotary actuator mechanism includes a rotary actuator 870 and a rotary actuator connector 872. The rotary actuator 870 is of a bidirectional type that moves the mirror to and from the stowed configuration.

[0148] The rotary actuator connector 872 may be integral with the mirror 810 or may be a separate part connected by bolting or adhesion. In some embodiments, the boom 820, the rotary actuator mechanism, and the mirror 810 may be integrally formed parts.

[0149] The above description presents examples of one or more devices, methods, or systems, but it will be understood that other devices, methods, or systems may also be included within the scope of the claims as interpreted by those skilled in the art.

Description of Reference Numerals

[0150] 100 Antenna system 110 Mirror 112 First surface, upper surface, reflective surface 114 Second surface, lower surface, bottom surface 120 Boom 122 Boom segment 124 Boom bracket 130 Pivoting mechanism 132 Inner circular component, concentric circular component 133 Reinforcing rib 134 Outer circular component, concentric circular component, rotating section 136 Radially flexible blade 138 Holding release mechanism linkage component, release mechanism linkage 139 Connecting portion 140 Holding release mechanism 150 Latching mechanism 152 Latch 153 Groove 154 Pin, Latching Pin 155 Body 156 Head 157 Spring Mechanism, Torsion Spring 158 Cam 160 Spacecraft Panel 500 Latching Release Operation 600 Latching Operation 702 Separation Plane 800 Antenna System 810 Antenna Reflector 812 First Surface, Upper Surface, Reflective Surface 814 Second Surface, Lower Surface, Bottom Surface 820 Boom 850 Latching Mechanism 852 Latch 853 Groove 854 Latching Pin 855 Body 856 Head 860 Spacecraft Panel 870 Electric Rotary Actuator 872 Rotary Actuator Connector

Claims

1. A latching mechanism system for retaining and releasing the deployable components, comprising: a plurality of latching mechanisms disposed on the spacecraft, each latching mechanism comprising a first component mounted to the deployable component and a second component mounted to the spacecraft, wherein in a stowed configuration, each of the first components is held by a respective second component; a rotation mechanism disposed on a lower surface of the deployable component and configured to rotate in a first direction to move the first component to the stored configuration and to rotate in a second direction opposite the first direction to release the first component from the stored configuration; A latching mechanism system comprising:

2. The rotation mechanism is a pivot mechanism, and the system comprises: a release mechanism for holding the pivot mechanism in the stored configuration, wherein the pivot mechanism stores potential energy, and releasing the release mechanism releases the stored potential energy to rotate the pivot mechanism in the second direction and releases the first component from the stored configuration. The system of claim 1 further comprising:

3. The system of claim 1 , wherein the rotation mechanism is a rotation actuator.

4. The system of claim 1 , wherein the first component is a pin and the second component is a latch.

5. 2. The system of claim 1, wherein the first component is a pin and the second component is a latch with a groove, the pin being oriented radially relative to the rotating mechanism.

6. 2. The system of claim 1, wherein the first component is a cone and the second component is a cup, the cone-in-cup interface forming an interface with a cone axis oriented circumferentially relative to the rotating mechanism.

7. 10. The system of claim 1, wherein the deployable component is coupled to a boom by a revolute joint at approximately a geometric center of the deployable component.

8. The system of claim 2 , wherein the release mechanism is coupled to the boom.

9. 3. The system of claim 2, wherein the pivot mechanism comprises a plurality of radially flexible blades that are distorted when the pivot mechanism is rotated in the first direction and held by the release mechanism, and when the release mechanism is released, stored potential energy in the distorted flexible radial blades causes the pivot mechanism to rotate in the second direction to rotate the deployable components and release the first component from the second component, thereby releasing the deployable components.

10. The system of claim 2 , wherein each latching mechanism of the plurality of latching mechanisms comprises a spring mechanism that holds the first component and the second component in a retaining position.

11. 11. The system of claim 10, wherein each spring mechanism is a torsion spring that releases the first component when sufficient torque is applied by the release of the release mechanism and rotation of the pivot mechanism in the second direction.

12. The system of claim 1 , wherein the plurality of latching mechanisms restrain the deployable component along axial and radial directions relative to a pivot axis.

13. The system of claim 1 , wherein the deployable component is an antenna reflector.

14. 1. A method of latching a retention and release latching mechanism system of a deployable component, comprising: rotating a rotation mechanism in a first direction about a rotation axis of the rotation mechanism until each of a plurality of first components of a latching mechanism system is held by a respective second component of a plurality of second components of the latching mechanism system, the plurality of first components being mounted to a first surface of the deployable component and the plurality of second components being mounted to a spacecraft; A method comprising:

15. the rotation mechanism is a pivot mechanism attached to the first surface and a boom of the deployable component and includes a plurality of radially flexible blades that are distorted upon rotation in the first direction; restraining the pivot mechanism with a release mechanism to a stowed configuration, wherein each of the plurality of first components is held by a respective second component, and wherein in the stowed configuration, the plurality of radially flexible blades store torsional energy in a second direction opposite the first direction.

15. The method of claim 14, further comprising:

16. The method of claim 14 , further comprising constraining each of the plurality of first components within the respective second components with a spring mechanism.

17. 15. The method of claim 14, wherein the first component is a pin and the second component is a latch.

18. 15. The method of claim 14, wherein the first component is a cone and the second component is a cup, the cone-in-cup interface forming an interface with a cone axis oriented circumferentially relative to the rotating mechanism.

19. The method of claim 14 , wherein the rotation mechanism is a rotation actuator coupled to the deployable component.

20. 1. A method of releasing a latching mechanism for retaining and releasing a large deployable component, comprising: releasing stored torsional energy from a plurality of radially flexible blades of a pivot mechanism held in a stowed configuration by said release mechanism by actuating a release mechanism, said pivot mechanism being mounted relative to a surface of said deployable component and a boom, said plurality of radially flexible blades being distorted by rotation of said pivot mechanism in a first direction. Including, Releasing the stored torsional energy causes the pivot mechanism to rotate in a second direction opposite to the first direction to disengage a plurality of first components mounted to a non-reflective surface of the deployable component from a plurality of respective second components mounted to a spacecraft, thereby moving the deployable components to a deployed configuration.

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