Systems, methods, and devices for low moment conical hold and release mechanism

Abstract

To provide an improved hold and release mechanism that overcomes at least some of the disadvantages of existing hold and release mechanisms such as occurrence of failures due to bending and torsion at the interface.SOLUTION: Provided is a bracket for use in a hold and release mechanism system for releasably holding a deployable payload in a stowed configuration. The bracket includes a conical portion for nesting with a conical portion of a second bracket for forming a first separation interface therebetween. The conical portion of the bracket is configured as a cone and the conical portion of the second bracket is configured as a cup. The bracket includes one or more bracket connectors for connecting the bracket to the deployable payload or a platform on which the deployable payload is stowed. The second bracket connects to whichever of the deployable payload or the platform the first bracket is not connected.SELECTED DRAWING: Figure 2

Description

[Technical Field]

[0001] The following disclosure relates generally to retention and release mechanisms, and more particularly to retention and release mechanisms for space applications. [Background technology]

[0002] Existing designs for hold and release mechanisms (HRMs) experience various issues related to high levels of bending and twisting at the HRM interfaces during manufacturing, assembly, and testing, resulting in failure (fretting / wear). These issues create challenges, especially for deployable structures (reflectors, orientable antennas, thrusters, etc.). These issues can manifest during various stages, including ground testing, launch, and deployment. A failed or suboptimal HRM can result in costly and potentially unsuccessful missions, including during ground testing, which can lead to subsequent design modifications. [Prior art documents] [Patent documents]

[0003] [Patent Document 1] French Patent No. 3120856(B1) Summary of the Invention [Problem to be solved by the invention]

[0004] Therefore, a need exists for an improved retention and release mechanism that overcomes at least some of the shortcomings of existing retention and release mechanisms. [Means for solving the problem]

[0005] A retention and release mechanism ("HRM") system is provided for releasably retaining a deployable payload in a stowed configuration. The system includes a first HRM bracket, a second HRM bracket, and a retention device. The first HRM bracket includes a first bracket body having a conical portion and one or more first bracket connectors (or connections) for connecting the first HRM bracket to the deployable payload. The second HRM bracket includes a second bracket body having a conical portion and one or more second bracket connectors for connecting the second HRM bracket to a platform on which the first deployable payload is stowed. The retaining device is configured to releasably hold the first bracket body and the second bracket body together in the storage configuration, with the conical portion of the first bracket body overlapping the conical portion of the second bracket body or the conical portion of the second bracket body being received in and overlapping the conical portion of the first bracket body to form a separation interface for the HRM system.

[0006] The first HRM bracket further includes one or more first struts connecting the first bracket body to the one or more first bracket connectors, and the first struts may be configured to relieve a moment due to an interface between the first bracket body and the second bracket body at a separation interface in the stowed configuration.

[0007] One or more of the first bracket body and the second bracket body may include a coaxial cone that may be coaxially disposed with a cone of a corresponding bracket body such that the corresponding bracket body includes a dual coaxial cone, the coaxial cone being for overlapping within or receiving a third HRM bracket to form a subsequent separation interface of the HRM system.

[0008] The first struts may be configured such that the line of action of each first strut converges to a first convergence point.

[0009] The first convergence point may be located at the separation plane of the separation interface.

[0010] The first bracket body may include a first hole configured to receive a rod or bolt of the retention device, and the first convergence point may be located on a longitudinal axis of the first hole.

[0011] The second HRM bracket may include one or more second struts, and the one or more second struts may be configured such that the line of action of each second strut converges to a second convergence point.

[0012] The first and second convergence points may be co-located.

[0013] The first struts may be arranged in a simple lattice structure or a complex lattice structure.

[0014] The one or more conical portions of the first bracket body and the second bracket body may be frustoconical in shape.

[0015] Also provided is a bracket, a first bracket, for use in an HRM system for releasably holding a first deployable payload in a stowed configuration. The first bracket includes a first bracket body and one or more first bracket connectors. The first bracket body includes a first bracket cone-shaped portion, which exists to overlap a second bracket cone-shaped portion of the HRM system to form a first separation interface therebetween. The first bracket cone-shaped portion may be configured as a cone-shaped portion, and the second bracket cone-shaped portion may be configured as a cup-shaped portion for receiving the first bracket cone-shaped portion, or the two may be configured inversely. The one or more first bracket connectors are attached to the first bracket body and configured to connect the bracket to the first deployable payload or a platform on which the first deployable payload is stowed. The second bracket is configured to connect to the first deployable payload and the remainder of the platform.

[0016] The first cone of the first bracket may be configured as a cone, and the first bracket body may further include a second cone of the first bracket configured as a cup cone, the second cone of the first bracket configured to receive and overlap the cone of a third bracket of the HRM system to form a second separation interface, the third bracket configured to connect to a second mount.

[0017] The first conical portion of the first bracket may be positioned longitudinally opposite the second conical portion of the first bracket, and the cup shape of the second conical portion of the first bracket may be positioned and configured to align with the conical shape of the first conical portion of the first bracket.

[0018] The bracket body may include a hole for receiving a rod or bolt of the retention device therethrough. The retention device may be configured to releasably retain the first bracket and the second bracket together at a first separation interface of the HRM system and the first bracket and the third bracket together at a second separation interface of the HRM system.

[0019] The bracket may further include one or more first struts connecting the first bracket body to the one or more first bracket connectors, and the one or more struts may be configured to relieve a moment due to an interface of the first bracket with at least one other bracket in the stowed configuration.

[0020] The first struts may be configured such that the line of action of each first strut converges to a first convergence point.

[0021] The first bracket body may include a first hole configured to receive a rod or bolt of a retention device therethrough, and the retention device may be configured to releasably hold the first bracket and the second bracket together at a first separation interface of the HRM system. The first convergence point may be located on a longitudinal axis of the first hole.

[0022] The first convergence point may be co-located with a convergence point of lines of action of struts at one or more of the second and third brackets of the HRM system.

[0023] The bracket further includes one or more first struts connecting the first bracket body to the one or more first bracket connectors, the one or more struts configured to relieve moments originating from interfaces between the first bracket and one or more of the second bracket body and the third bracket at the first and second separation interfaces, respectively, in the stowed configuration. The first struts may be configured such that a line of action of each first strut converges to a first convergence point. The first convergence point may be located on one or more of a first separation plane of the first separation interface, a second separation plane of the second separation interface, and a plane that is the average of the first and second separation planes.

[0024] The first bracket body may further include a cylindrical portion adjacent the end of the conical portion having the largest diameter, and the one or more first struts may connect to the bracket body at the cylindrical portion.

[0025] The cylindrical portion may be integrally formed with the conical portion.

[0026] The first bracket may be formed by one or more of printing, additive manufacturing, and adhesive.

[0027] An HRM system for releasably holding deployable payloads in a stowed configuration is also provided. The system includes a first HRM bracket configured to connect to a first deployable payload, a second HRM bracket configured to connect to a second deployable payload, a third HRM bracket configured to connect to a platform on which the first and second deployable payloads are stowed, and a retention device. The retention device includes an HRM bolt and is configured to releasably hold the first and second HRM brackets together at a first separation interface of the HRM system and the second and third HRM brackets together at a second separation interface of the HRM system. The retention device retains the first, second, and third HRM brackets by retaining the HRM bolt. The retention device is configured to release the retention state upon receiving a release input to the retention device that allows separation at the first and second separation interfaces.

[0028] The HRM bolt is configured to break when the retention device receives a release input, thereby releasing the retention state of the retention device.

[0029] A method for holding a deployable payload by an HRM system in a stowed configuration for later release is also provided. The method includes overlapping a cone-shaped portion of a first bracket within a cone-shaped portion of a second bracket to form a first separation interface in the stowed configuration. The method further includes coupling the first bracket to the deployable payload and the second bracket to a platform on which the first deployable payload is stowed in the stowed configuration, or vice versa. The method further includes releasably holding the first bracket and the second bracket together at the separation interface by a retention device configured to release its retention state upon receiving a release input.

[0030] At least one of the first bracket and the second bracket may include a plurality of struts configured to dissipate moments resulting from an interface of the first bracket with at least one other bracket.

[0031] The retention device may include a breakable component configured to break when the retention device receives a release input, the breakable component breaking to allow separation at the separation interface.

[0032] The step of releasably holding the first bracket and the second bracket together may include placing a bolt of a holding device through the first bracket and the second bracket, holding the bolt at the second end of the bolt, and retracting the bolt from the first end to apply a preload to the bolt and tighten the first bracket and the second bracket together.

[0033] Retracting the bolt may include torquing down the bolt.

[0034] The method may further include delivering a release input to the holding device to release the held state.

[0035] Other aspects and features will become apparent to those skilled in the art upon review of the following description of several exemplary embodiments.

[0036] The drawings accompanying this specification show various examples of the objects, methods, and devices described herein. [Brief explanation of the drawings]

[0037] [Figure 1] FIG. 1 is a block diagram of an HRM system according to one embodiment. [Figure 2] 2 is a cross-sectional schematic diagram of the HRM system of FIG. 1 according to one embodiment. [Figure 3] FIG. 3 is a perspective schematic diagram of a spacecraft including the HRM system of FIG. 2 coupled to two radially extending arrays, according to one embodiment. [Figure 4A] 2 is a perspective schematic diagram of the HRM system of FIG. 1 with complete struts and constrictions, according to one embodiment. [Figure 4B] FIG. 4B is a cross-sectional perspective schematic diagram of the HRM of FIG. 4A. [Figure 5A] 2 is a perspective schematic diagram of the HRM system of FIG. 1 having struts according to another embodiment. [Figure 5B] 2 is a perspective schematic diagram of the HRM of FIG. 1 with only two brackets removed, according to one embodiment. [Figure 6A] FIG. 3 is a front perspective view of the HRM system of FIG. 2 with only the first bracket removed. [Figure 6B] FIG. 3 is a side view of the HRM system of FIG. 2, showing only the first bracket. [Figure 6C] FIG. 3 is a front view of the HRM system of FIG. 2, showing only the first bracket. [Figure 6D] FIG. 3 is a rear view of the HRM system of FIG. 2 with only the first bracket removed. [Figure 6E] FIG. 3 is a top view of the HRM system of FIG. 2 with only the first bracket removed. [Figure 6F] FIG. 3 is a bottom view of the HRM system of FIG. 2 with only the first bracket removed. [Figure 7A] FIG. 3 is a front perspective view of the HRM system of FIG. 2 with only the second bracket removed. [Figure 7B] FIG. 3 is a side view of the HRM system of FIG. 2 with only the second bracket removed. [Figure 7C] FIG. 3 is a front view of the HRM system of FIG. 2 with only the second bracket removed. [Figure 7D] FIG. 3 is a rear view of the HRM system of FIG. 2 with only the second bracket removed. [Figure 7E] FIG. 3 is a top view of the HRM system of FIG. 2 with only the second bracket removed. [Figure 7F] FIG. 3 is a bottom view of the HRM system of FIG. 2 with only the second bracket removed. [Figure 8A]FIG. 3 is a view of only the bolt of FIG. 2 according to one embodiment. [Figure 8B] FIG. 3 is a view of only the bolt of FIG. 2 according to one embodiment. [Figure 8C] FIG. 3 is a view of only the bolt of FIG. 2 according to one embodiment. [Figure 8D] FIG. 3 is a view of only the bolt of FIG. 2 according to one embodiment. [Figure 8E] FIG. 3 is a view of only the bolt of FIG. 2 according to one embodiment. [Figure 9A] FIG. 1 is a side view of a payload carried by four HRM systems according to one embodiment. [Figure 9B] FIG. 1 is a perspective schematic diagram of a payload carried by four HRM systems according to one embodiment. [Figure 10A] FIG. 3 is a cross-sectional schematic diagram of an embodiment of the HRM system of FIG. 2 in a stowed configuration with the bolt in a released position. [Figure 10B] FIG. 3 is a cross-sectional schematic diagram of an embodiment of the HRM system of FIG. 2 in a stowed configuration with the bolt retracted. [Figure 11A] 2 is a partial cross-sectional side view of the HRM system of FIG. 1 according to one embodiment. [Figure 11B] FIG. 2 is a partial perspective view of the HRM system of FIG. 1 according to one embodiment. [Figure 12A] FIG. 11A is a side view of the HRM system of FIGS. 11A-B with a power connection bracket, according to one embodiment. [Figure 12B] FIG. 12C is a perspective view of a buffer plate interface of the HRM system of FIGS. 11A-12B according to one embodiment. DETAILED DESCRIPTION OF THE INVENTION

[0038] Various devices or processes are described below to provide examples of each claimed embodiment. The embodiments described below do not limit any claimed embodiment, and any claimed embodiment may include different processes or devices than those described below. A claimed embodiment is not limited to a device or process having all of the features of any one device or process described below, or to features common to many or all of the devices described below.

[0039] Furthermore, although process steps, method steps, algorithms, etc. may be described (in the disclosure and / or claims) in a sequential order, such processes, methods, and algorithms may be configured to function in other orders. In other words, any sequence or order of steps that may be described does not necessarily indicate a requirement that the steps be performed in that order. Process steps described herein may be performed in any order that is practicable. Additionally, some steps may be performed simultaneously.

[0040] Where a single device or thing is described herein, it will be readily apparent that more than one device / thing (whether or not cooperating with each other) may be used in place of the single device / thing. Similarly, where more than one device or thing (whether or not cooperating with each other) is described herein, it will be readily apparent that a single device / thing may be used in place of the more than one device or thing.

[0041] The following disclosure relates generally to retention and release mechanisms, and more specifically to a conical HRM of a pinned joint supported by a combination of struts and constrictors. In the joint, the pin condition is mimicked by compliant or surrounding struts and constrictors. The joint connects each of the members to be joined by a common rod or bolt passing through a hole. The joint's contact surface, typically a conical surface, is clamped by a tensioned rod or bolt, providing joint rigidity. The stiffness of a conical joint is significant in three translational directions and two rotational directions about an axis perpendicular to the bolt axis. The less significant stiffness acts in the rotational direction about the bolt axis, because this stiffness relies on friction at the contact surface due to the preload caused by the bolt. Thus, the joint design described herein is a connection between two objects that allows relative rotation only about a single axis. Translation and rotation about any other axis are restricted, thus the joint has one free degree of freedom. When at least two joints join two objects together, the joints ensure that all relative movement of the objects is restricted.

[0042] The struts and stiffeners provide support near the joint, advantageously minimizing rotational stiffness of the joint assembly and maximizing the load capacity of the joint. The struts and stiffeners advantageously minimize moments on the conical surface.

[0043] In existing systems, spherical bearings can release rotational degrees of freedom. However, the joint design of the present disclosure is advantageously more compact and allows for greater rigidity. Furthermore, the integration of a spherical bearing into the joint inevitably creates a misalignment between the center of rotation of the spherical bearing and the contact surface of the joint, which causes significant bending due to this misalignment and translational loads acting on the spherical bearing. The joint design of the present disclosure advantageously avoids this misalignment, allowing for increased joint capacity over existing systems with integrated spherical bearings. The HRM design of the present disclosure is highly scalable for applications where geometries are larger or smaller, sometimes due to predetermined load and packaging constraints. Furthermore, this design of the HRM allows it to be manufactured by additive manufacturing (i.e., printing) each side of the HRM with the complete struts and constrictions present as a single part, as described in French Patent No. 3120856 (B1), or by combining each side of the HRM with existing or standard strut towers (bonded struts and constrictions).

[0044] Referring now to FIG. 1, a retention and release mechanism (HRM) system 100 is shown according to one embodiment.

[0045] The HRM system 100 is configured as a mechanism for providing releasable retention between any number of payloads 102 and a vehicle 103. The payloads 102 are referred to herein collectively as payloads 102, generically as payloads 102, and individually as payloads 102-1, 102-2, ... 102-n. In some embodiments, the vehicle 103 is a space vehicle or spacecraft. While the vehicles 103 described herein are deployable in space and translatable from one location to another, it is expressly contemplated that the vehicle 103 may be any structure to which payloads 102 may be attached and releasably retained.

[0046] The HRM system 100 is configured to fire or move from a holding configuration to a release configuration. Firing the HRM system 100, also known as triggering, releases the hold between the payload 102 and the vehicle 103. In some embodiments, firing the HRM system 100 releases one payload 102-1. In these embodiments, additional firings may release additional payloads 102-2...102-n. In some embodiments, each firing of the HRM system 100 releases many or all of the payloads 102 attached to the HRM system 100.

[0047] The release of the payload 102 may be to deploy the payload 102 from a stowed configuration to a deployed configuration. Typically, in space applications of the HRM system 100, the payload 102 is launched in a stowed configuration and is operable in a deployed configuration. The HRM system 100 holds the payload 102 in the stowed configuration until it is released. Release by the system 100 allows the payload 102 to move from the stowed configuration to the deployed configuration. Exemplary payloads 102 include reflectors, power feeds, antennas, thrusters, solar panels, etc.

[0048] In the stored configuration, the HRM system 100 has a longitudinal axis 104. In some embodiments, the longitudinal axis 104 is located at the center of the main body of the HRM system 100. In the stored configuration, a first end 106 of the HRM system 100 is positioned opposite a second end 108 of the HRM system 100 along the longitudinal axis 104.

[0049] The HRM system 100 includes a holding device 109. The holding device 109 releasably holds the payload 102 while attaching it to the vehicle 103. The holding device 109 releases the HRM system 100 from holding one or more payloads 102 when the HRM system 100 fires.

[0050] The retaining device 109 includes a bolt assembly 110, also known as a bolt extractor 110, for extracting and ejecting a bolt 112.

[0051] Pulling out and extending the bolt 112 correspond to releasing and holding the HRM system 100, respectively.

[0052] The bolt assembly 110 includes a bolt housing 114. The bolt housing 114 forms the exterior structure of the bolt assembly 110. The components of the bolt assembly 110 are generally housed within the bolt housing 114. It will be appreciated that the bolt 112, when ejected, protrudes beyond the bolt housing 114. In some embodiments, the bolt housing 114 protects the bolt assembly 110 from environmental factors, such as radiation.

[0053] The bolt assembly 110 includes a bolt 112. It will be understood that the bolt 112 may also be known or referred to as a rod or a pin. The bolt 112 is disposed along the longitudinal axis 104 of the HRM system 100.

[0054] In the withdrawn position, the bolt 112 is withdrawn into the bolt assembly 110. Withdrawing the bolt 112 allows it to be released from its hold by the HRM system 100. Specifically, withdrawing the bolt 112 minimizes the extent to which the bolt 112 is positioned outside of the HRM system 100 by withdrawing the bolt 112 into the bolt assembly 110 and / or one or more brackets 140, described further below.

[0055] In the extended position, the bolt 112 extends beyond the bolt housing 114. The extended bolt 112 allows the bolt 112 to be held by the HRM system 100. Specifically, the extended bolt 112 positions at least a portion of the bolt 112 in a position that allows the bolt 112 to be held by the HRM system 100.

[0056] The bolt 112 includes a shaft 116. The shaft 116 provides a length for operating the bolt 112. The shaft 116 may be cylindrical.

[0057] The bolt 112 further includes a shank 118. The shank 118 is located at the end of the bolt 112 that protrudes beyond the bolt housing 114 when the bolt 112 is in the extended position. When in the retained configuration, the shank 118 is retained by a split nut assembly 130 (described further below).

[0058] In some embodiments, the bolt 112 includes a bolt head 120. The bolt head 120 may be fixedly attached to the shaft 116 at the end of the bolt 112 opposite the shank 118. The head 120 is threadedly engaged with internal threads 122 on the inner surface of the bolt housing, and is configured to allow the bolt 112 to be easily extended or withdrawn when the bolt 112 is rotated.

[0059] The bolt 112 is actuated (ejected or withdrawn) by the bolt operating mechanism 124. The bolt operating mechanism 124 withdraws the bolt 112 after the separation nut 132 is released. The bolt operating mechanism 124 may be configured to withdraw the bolt 112 after the components of the HRM system 100 are separated or deployed. The withdrawal of the bolt 112 by the bolt operating mechanism 124 may be complete to ensure that the bolt passes completely through the plane of any separation interface. The bolt operating mechanism 124 may keep the bolt in a fixed position (i.e., immobile) during deployment of the payload 102. The degree of withdrawal may be monitored and / or controlled based on measurements from a load cell sensor (not shown).

[0060] In some embodiments, the bolt operating mechanism 124 includes a motor configured to operate the bolt 112 by rotating the bolt 112 or the internal threads 122. In some embodiments, the bolt operating mechanism 124 is heat activated, such as a bolt operating mechanism having a heat-activated shape memory metal or alloy. In some embodiments, the bolt operating mechanism 124 includes a spring, such as a helical spring. The spring may be preloaded to extract the bolt when a binding force is released, for example, by firing an HRM system. In some embodiments, the bolt operating mechanism 124 may be preloaded by torquing the bolt. A preload of several thousand kilograms (e.g., 5,000 pounds) may be applied to enable launch of the vehicle 103.

[0061] The profile of the bolt assembly 110 at the first end is referred to herein as the bolt assembly profile 126. The bolt assembly profile 126 is configured to make surface contact with the bracket 140, described further below. In some embodiments, the bolt assembly 110 is configured to separate from the bracket 140 at an interface between the bolt assembly profile 126 and the bracket 140 upon firing in the HRM system 100. In such embodiments, the interface is referred to as a separation interface. The plane at the separation interface is referred to herein as a separation plane.

[0062] The retaining device 109 further includes a separation nut assembly 130, also known as a release device 130.

[0063] The splitter nut assembly 130 is configured to hold the bolt 112 (i.e., in a stowed configuration). In some embodiments, the bolt 112 is held by the splitter nut assembly 130 at the shank 118. In some embodiments, upon firing, the splitter nut assembly 130 releases its hold on the bolt 112. In some embodiments, upon firing, the hold on the bolt 112 is released by breaking the bolt 112 or the splitter nut 132, described further below. For example, the bolt 112 or splitter nut may be broken by an explosive or by withdrawing the bolt 112 to or beyond breakage.

[0064] In some embodiments, bolt assembly 110 or separation nut assembly 130 may be secured to space vehicle 103 .

[0065] The splitter nut assembly 130 includes a splitter nut 132. The splitter nut 132 is configured to receive the shank 118 of the bolt 112 in a splitter nut bore 134. When received, the splitter nut bore 134 is disposed opposite the longitudinal axis 104 such that the shank 118 moves into the splitter nut bore 134 as the bolt 112 is extended.

[0066] The separation nut 132 is further configured to retain or restrain the bolt 112 in the stowed configuration. In some embodiments, the separation nut 132 specifically retains the shank 118. In some embodiments, the separation nut 132 is configured to release the bolt 112 in the deployed configuration. Releasable separation nuts 132 are typically reusable and used for long-term installations and can be manually removed.

[0067] In some embodiments, the separation nut 132 comprises a shape memory alloy configured to transition between a retaining configuration and a releasing configuration. In the retaining configuration, the separation nut 132 is configured to securely fasten the shank 118, such as by radially retaining the shank 118. The separation nut 130 may be fired by passing an electric current through the separation nut 130. Passing an electric current causes the separation nut 132 to reconfigure to release its retention of the shank 118. In some embodiments, the separation nut 130 includes a helical spring, such as a linear helical spring, configured to separate (i.e., push apart) retained components of the HRM system 100.

[0068] In some embodiments, the separation nut assembly 130 includes a separation nut housing 136. The separation nut housing 136 forms the exterior structure of the separation nut assembly 130. The components of the separation nut assembly 130 are generally contained within the separation nut housing 136. In some embodiments, the separation nut housing 136 protects the separation nut assembly 130 from environmental factors, such as radiation.

[0069] The profile of the separation nut assembly 130 at the first end is referred to herein as a first nut profile 138. The first nut profile 138 is configured to make surface contact with the bracket 140 (described further below). In some embodiments, the separation nut assembly 130 is configured to separate from the bracket 140 at an interface between the separation nut assembly 130 and the bracket 140 when the HRM system 100 is fired. In such embodiments, the interface is referred to as a separation interface. It will be appreciated that when the HRM system 100 is fired, the pressure exerted by the separation nut assembly 130 is released, such that no pressure remains between the bracket 140 (described further below). The release of pressure allows the payload 102 to deploy and separate from the vehicle 103. The payload 102 may be further separated or deployed by an electric motor or a potential energy spring (not shown).

[0070] The HRM system 100 further includes a bracket 140 for each payload 102 and vehicle 103. It will be appreciated that the retention device 109 may function as, be integrated with, or be part of the bracket 140, in whole or in part.

[0071] The brackets 140 are collectively referred to as brackets 140, generically as bracket 140, and individually as brackets 140-1, 140-2, ..., 140-#. Subcomponents of bracket 140 corresponding to the generic payload 102 or bracket 140-n are referred to herein as payload 102-n or component ###-n, respectively, and similarly for the former corresponding to the latter. For example, bracket 140-1 corresponds to payload 140-1 and bracket body 142-1, described further below. While bracket 140-n is described below as corresponding to payload 120-n, it is understood that it is expressly contemplated that any bracket 140-n or 140-# may correspond to vehicle 103 instead of payload 120-n. Each bracket 140-n provides a structure for holding payload 120-n in the HRM system 100 stowed configuration.

[0072] Each bracket 140-n is attached to a payload 102-n. In the stowed configuration, the HRM system 100 supports the bracket 140-n, and thus the attached payload 102-n. The geometry of each bracket 140 is optimized for moment reduction and rigid support in all degrees of freedom.

[0073] Each bracket 140 has a bracket body 142. The bracket body 142 provides a structure for the retention device 109 to retain the payload 102 while attaching it to the vehicle 103. The retention may be achieved by tightening together the bracket bodies 142 of two or more consecutive brackets 140. In some embodiments, the bolt housing 114 and / or the separate nut housing 136 may function as, be integral with, or be part of the bracket body 142.

[0074] The bracket body 142 includes a first body profile 144 or conical portion 144 at a first end. The bracket body 142 may include a second body profile 146 or conical portion 146 at a second end longitudinally opposite the first end. The first body profile 144 and the second body profile 146 may be referred to as dual coaxial conical portions 144, 146. The first body profile 144 and the second body profile 146 are referred to herein collectively as body profile 144 and body profiles 146. In the stored configuration, each bracket body 142 is in surface contact with the remaining bracket 140 at a surface of the body profile 144 to form a series of separation interfaces.

[0075] In the storage configuration, when the interface between consecutive bracket bodies 142 is a separation interface, the body profile of each bracket body 142 at the separation interface is conical. It will be understood that each conical body profile 144 can be an outwardly conical protrusion (i.e., conical body profile 144) or an inwardly conical recess (i.e., cup body profile 144). Each conical body profile 144 is configured to overlap within the cup body profile 144 of an adjacent bracket 140 to achieve a cup-to-cone interface. For cup-to-cone interfaces, the only contact between the brackets 140 at the interface is a single conical contact surface. It will be understood that which brackets 140 have the cup body profile 144 and which have the conical body profile 144 is not based on the absolute or relative positions of the brackets 140 in the HRM system and can be swapped to accommodate other design considerations.

[0076] The cup-to-cone interface directs interface moments to a single interface, such as the interface between the first body profile 144-1 of the first bracket 140-1 and the second body profile 146-2 of the second bracket 140-2. Directing the moment to this interface minimizes moment, bending, and twist at the interface. This minimization advantageously allows for a high load capacity while maintaining a compact size that meets a positive safety margin and is more rigidly secured than existing systems, such as the HRM system 100, which includes spherical bearings. It will be appreciated that the HRM system 100 includes a conical interface that serves as the primary interface of the separable structure between the structure 103 and the payload 102. The separation plane may require high in-plane shear resistance. A conical surface at the separation plane advantageously increases in-plane shear resistance.

[0077] The cup and cone interface advantageously allows any number of brackets 140 and corresponding payloads 102 to be stacked. Such stacking advantageously facilitates simultaneous deployment and allows multiple separation planes to have a single bolt 112. The stack may be configured so that any outboard panels are stacked away from the vehicle 103. The cup and cone surfaces may be titanium, which may be conventionally machined or printed by additive manufacturing.

[0078] In some embodiments, the apex of the first body profile 144 is located at the longitudinal axis 104. This positioning causes any rotation of the bracket to occur about the longitudinal axis 104, thereby avoiding or reducing bending or twisting that the bolts 112 may experience due to such rotation. Rotation of each payload 102 may be constrained by multiple HRM systems 100. Each HRM system 100 has torsional tolerance and can resist some torsion. This resistance may be due to bolt preload and friction. Each payload 102 may be further constrained by a structure connecting the payload 102 to the spacecraft 103. The structure may be a beam, a deployable strut, or the like.

[0079] In some embodiments, the cup body profile 144 is a conical inverse or relief of a corresponding conical body profile 144. It is expressly contemplated that the inverse may not be symmetrical, particularly in size.

[0080] In one embodiment, the conical first body profile 144-1 of the first bracket 140-1 overlaps within the cup-shaped second body profile 146-2 of the second bracket 140-2, or vice versa. It will be appreciated that the conical profile of the first body profile 144 or the second body profile 146 may be a frustoconical shape.

[0081] In some embodiments, the bolt assembly profile 126 or the nut profile 138 is configured to make facial contact with the first body profile 144-1 of the bracket 140-1. For example, if the first body profile 144-1 is a conical profile, the nut profile 138 may be configured as a conical profile that receives the first body profile 144-1 in the storage configuration.

[0082] In some embodiments, the bolt assembly 110 or the breakaway nut assembly 130 is fixed to the bracket 140. This fixed connection is non-separable, such that the bolt assembly 110 or the breakaway nut assembly 130 remains with the corresponding bracket 140 even when separation and deployment occur during firing of the HRM system 100. Fixed interfaces typically exist at each end of the HRM system 100 (i.e., at the initial and final interfaces of the HRM system 100). In these embodiments, the second body profile 146 does not contact the separation plane (i.e., is not a separation interface). In this manner, the second body profile 146 may be substantially flat, planar, configured to accommodate existing attachment means, or configured in any shape desirable to accommodate the equipment attached to it. This advantageously allows for fabrication of or surface contact with existing attachment means, such as bolts, bolt assemblies 110, or breakaway nut assemblies 130. For example, when the second body profile 146 is fixedly connected to the flat / planar or interlocking bolt assembly profile 126, the second body profile may be configured such that the flat or interlocking profile creates an attachment portion and allows the separation nut assembly 130 or the like to come into surface contact with a corresponding attachment device such as a bolt.

[0083] In some embodiments, the second body profile 146 is not separate from the corresponding split nut assembly 130 or bolt assembly 110. For example, if the bracket 140 is integral with the bolt assembly 110 or split nut assembly 130, it may not be clear where the bracket 140 ends and the integrated component begins. The integrated bracket 140 may be formed by additive manufacturing, drilling and setting, or the like, or a combination thereof.

[0084] When the bolt assembly 110 or the split nut assembly 130 is secured to or integral with the bracket 140-n, the bolt 112 or split nut bore 134, respectively, is aligned with the longitudinal axis 104 of the bracket 140-n. It will be appreciated that this alignment does not change when the payload 102-n coupled to the bracket 140-n is deployed. By maintaining this alignment, the process of stowing the bracket 140-n and the corresponding payload 102-n can be beneficially simplified by avoiding reconfiguration of the alignment.

[0085] Each bracket 140 includes one or more bracket connectors 160 .

[0086] Each bracket connection 160 is a structure of the bracket 140-n that is used to attach the bracket 140-n to the mount 102-n or vehicle 103 (e.g., by receiving a fastener such as a bolt therethrough). The bracket connection 160 may be configured such that a plane defined by the interface of each bracket connection 160 with the mount 102-n or vehicle 103 is parallel to the longitudinal axis of the bolt 112.

[0087] At least one bracket 140 of the HRM system 100 further includes two or more struts 162. Each strut 162 may be referred to as a rod 162 or a leg 162.

[0088] Struts 162 connect bracket body 142 to bracket connector 160. Each strut is substantially straight.

[0089] In some embodiments, the strut 162 may include a constriction 164. The constriction 164 is flexible to relieve moments at the interface of the components of the HRM system 100. The constriction 164 may be the entire strut 162 or any portion thereof.

[0090] The placement of struts 162 and constrictions 164 minimizes moments, bending, and twisting at the interface, which advantageously allows for higher load capacity while maintaining a compact size that is more capable of being rigidly fastened than existing systems, such as HRM systems that include spherical bearings.

[0091] The struts 162 are arranged in a lattice structure 166. In some embodiments, the lattice structure is a simple lattice structure 166, with each strut 162 having a first end terminating in the bracket connector 160 and a second end terminating in the bracket body 142. The simple lattice structure 166 may provide more stability than the complex lattice structure 166 described further below.

[0092] In some embodiments, the lattice structure 166 is a complex lattice structure 166. In a complex lattice structure 166, the end of each strut 162 terminates at a bracket connector 160, a bracket body 142, or a node (i.e., an end point of multiple struts 162). At least one strut 162 of the lattice structure 166 terminates at the bracket body 142. Also, at least one strut 162 terminates at each bracket connector 160. It will be understood that the strut 162 terminating at the bracket body 142 and the strut 162 terminating at the bracket connector can be the same or different struts 162.

[0093] The struts 162 are configured in a lattice structure 166 to reduce load transfer through the lattice structure 166 and reduce stress at the interface between the bracket connection 160 and the corresponding payload 102 or vehicle 103. The lattice structure 166 configuration of the rods 162 allows the bracket 140 to be flexible in bending and torsion, yet remain rigid in all translational degrees of freedom. This flexibility can accommodate coefficient of thermal expansion (CTE) gradients, also referred to as misalignment, between two joined structures, such as two brackets 140. The lattice structure configuration 166 allows rotational moments of the bracket 140 to be substantially concentrated. For example, the lines of motion of each strut 162 of each bracket converge to a single point, as shown in FIGS. 5A and 5B described below. This point may be at the separation plane or the sealed interface of the bracket 140. In some embodiments, the convergence point corresponding to each bracket 140 is the same across all brackets 140. This configuration of the lattice structure 166 advantageously minimizes moments, bending, and torsion between the conical interfaces of the first body profile 144, the second body profile 146, and the separation nut assembly 130. This minimization advantageously allows for higher load capacity while maintaining a compact size that further enables larger masses to be secured more securely than existing systems. The lattice structure 166 is configured so that any corresponding separation plane is perpendicular to the longitudinal axis of the bolt 112. The lattice structure 166 may be axisymmetric about the longitudinal axis of the bolt 112. This axisymmetricality may be partial, particularly near the bracket body 142. The lattice structure 166 may vary from the bracket body 142 to the bracket connection portion 160.

[0094] In some embodiments, the axes of each strut 162 of bracket 140 intersect (i.e., converge) at a single point. This point may be at the first body profile 144, and specifically at the apex of first body profile 144.

[0095] In some embodiments, bracket 140, or a substantial portion thereof, is a unitary structure. For example, bracket 140 may be formed as a single piece by additive manufacturing. It is expressly contemplated that a unitary structure may be part of bracket 140. For example, bracket body 142 and struts 162 may be formed as a single piece by additive manufacturing, while bracket connector 160 is fabricated separately. A unitary structure avoids or simplifies complex assembly due to the manufacturing process. This simplification is particularly beneficial in space applications where manufacturing and assembly options may be limited.

[0096] Each bracket 140 may be printed with the complete struts 162 and constrictors 164 as a single part using additive manufacturing. Printing the brackets 140 may be for small assemblies. Each bracket 140 may also be fabricated by existing methods, such as conventionally fabricating and bonding the struts 162 and constrictors 164. Such methods may be for larger assemblies.

[0097] Referring now to Figure 2, there is shown a cross-sectional perspective schematic view of an HRM system 100 according to one embodiment. The HRM system 100 is an embodiment of the HRM system 100 of Figure 1, and its components are similarly referenced.

[0098] It will be appreciated that FIG. 2 illustrates the placement of the HRM system 100 between the stowed and deployed configurations.

[0099] Specifically, in the illustrated arrangement, the retention state of the separation nut 132 is shown in a released configuration and the bolt 112 is shown in a withdrawn configuration, while the HRM system 100 is otherwise in a stowed configuration. The withdrawal of the bolt 112 is in a direction 272 along the longitudinal axis 104 from the second end 108 to the first end 106.

[0100] In this embodiment, the bolt assembly 110 is disposed at the first end 106. The bolt assembly 110 is secured to the first bracket 140-1 at the interface between the bolt assembly profile 126 and the second body profile 146-1 of the first bracket 140-1. This interface is substantially planar and secured by conventional means. This securement aligns the longitudinal axes of the bolt assembly 110 and the first bracket 140-1. It will be appreciated that in the deployed configuration, the bolt assembly 110 remains secured to the bracket 140-1, thereby maintaining the alignment of the longitudinal axes of the two.

[0101] The bolt 112 is disposed along the longitudinal axis 104. A portion of the bolt 112, and in particular the shank 118, protrudes beyond the bolt housing 114.

[0102] 8A-8C show a schematic of a bolt 112 according to one embodiment in a first perspective view, a side view, and a second perspective view. Figures 8D-8E show a schematic of a bolt 112 having a bolt head 120 according to a further embodiment in a perspective view and a side view.

[0103] Each bracket 140 and split nut assembly 130 includes a bolt hole 270. Collectively, the bolt holes 270 provide a path for the bolt 112 to be drawn through and protrude into the split nut 132. In the stowed configuration, the bolt holes 270 are aligned along the longitudinal axis 104. The bolt holes 270 extend through the bracket 140 and split nut assembly and into the split nut bore 134.

[0104] The first body profile 144-1 of bracket 140-1 is configured as a conical profile, and the second body profile 146-2 of bracket 140-2 is configured as a corresponding cup profile. In the stowed configuration, the conical profile of the first body profile 144-1 overlaps within the second body profile 146-2. Similarly, the first body profile 144-2 of bracket 140-2 is configured as a conical profile, and the nut assembly profile 138 is configured as a corresponding cup profile. In the stowed configuration, the conical profile of the first body profile 144-1 overlaps within the second body profile 146-2. This overlap aligns the bolt holes 270. This arrangement and alignment causes moments experienced at each of the cup-cone separation interfaces 144-1:146-2 and 144-2:138 to be directed to a point on the longitudinal axis 104. This point may be the common apex of the cup and the cone. This interface minimizes moments, bending, and twisting of the HRM system 100 .

[0105] Bracket body 142-1 is connected to bolted connections 160-1a and 160-1b by lattice structure 166-1. Bracket body 142-2 is connected to bolted connections 160-2a and 160-2b by lattice structure 166-2. Lattice structures 166-1 and 166-2 are configured to direct moments experienced by each bracket 140-1, 140-2 to a single point on longitudinal axis 104. By directing the moments to a single point, moments, bending, and twisting of HRM system 100 are minimized.

[0106] Bracket 140-1 connects to mount 102-1 via bolted connections 160-1a and 160-1b. In some embodiments, the connection is via panel 274-1. Bracket 140-2 connects to mount 102-2 via bolted connections 160-2a and 160-2b. In some embodiments, the connection is via panel 274-2.

[0107] Brackets 140-1 and 140-2 are each an integrated bracket. For example, bracket body 142-1, lattice structure 166-1, and bracket connectors 160-1a and 160-1b are formed as a single piece. Brackets 140-1 and 140-2 may be formed by additive manufacturing, such as 3D printing.

[0108] 6A-6F show perspective, side, front, rear, top, and bottom views of one embodiment of bracket 140-1. A first body profile of bracket body 142-1 of bracket 140 is a conical profile. Bracket body 142 is connected to four bracket connectors 160a-160d by a lattice structure 166.

[0109] 7A-7F show perspective, side, front, rear, top, and bottom views of one embodiment of bracket 140-2. A first body profile of bracket body 142-2 of bracket 140-2 is a cup profile. Bracket body 142-2 is connected to four bracket connectors 160-2a-160-2d by lattice structure 166-2.

[0110] Various embodiments of the HRM system are distinguished by the rearrangement of the bolt assembly 110, the separation nut assembly 130, and the bracket 140, and the interfaces of the objects to which they are connected are explicitly envisioned. In one example, the arrangement of the bolt assembly 110 and the separation nut 120 may be reversed from that shown. Specifically, the bolt assembly 110 may be connected to the vehicle (not shown) and disposed at the second end 108, and the separation nut assembly 130 may be disposed at the first end 106 and connected to the bracket 140. In a further example, the payload 102-1 may be connected to the separation nut assembly 130, and the vehicle 103 (not shown) may be connected to the bracket 140-1.

[0111] The bolted or pinned conical bracket body 142 arrangement and the strut 162 and constriction 164 arrangement, individually and in combination, minimize moments, bending, and torsion at the HRM separation interface. Such minimization beneficially optimizes the load capacity of the HRM system 100, reduces damage to mating surfaces, optimizes mass-to-volume efficiency, provides in-plane flexibility to the HRM system 100, enables attachment to structures with different coefficients of thermal expansion (CTE), enables pre-existing and advanced strut towers, enables additive manufacturing, and is adaptable and scalable to various size geometries based on a balance between required load range and packaging constraints.

[0112] Referring now to FIG. 3, a perspective schematic diagram of a space vehicle system 300 in a stowed configuration is shown, according to one embodiment.

[0113] Space vehicle system 300 may be one example of two payloads 102-1 and 102-2 attached to and held by space vehicle 103 by HRM system 100 of Figure 1. Space vehicle 103, payloads 102-1 and 102-2, and HRM system 100 are configured similarly to those described in Figure 1. Specifically, bolt assembly 110, separation nut assembly 130, and brackets 140-1 and 140-2 are similarly configured. Separation nut assembly 130 is connected to space vehicle 103 by three vehicle struts 302-1, 302-2, and 302-3.

[0114] It is expressly contemplated that each payload 102-1 or 102-2 may be held attached to the space vehicle 103 by one or more HRM systems 100. As an example, Figures 9A and 9B show a payload 102 held by four HRM systems 100a-100d, according to one embodiment.

[0115] 4A and 4B, a perspective schematic view 400 and a cross-sectional schematic view 450 of the HRM system 100 in a storage configuration are shown, according to one embodiment.

[0116] The HRM system 100 is configured to be similar to the HRM system 100 of Figure 1. The HRM system 100 is a single stage, separate HRM system 100.

[0117] In this embodiment, the first bracket 140-1 is integrated with the bolt assembly 110 and is not a separate component from the bolt assembly 110.

[0118] Struts 162-1a and 162-1b connect bolt assembly 110 to bracket connectors 160-1a and 160-1b. Struts 162-1a and 162-1b and bracket connectors 160-1a and 160-1b may also be integral with bracket 140-1 and bolt assembly 110.

[0119] The tether 474 is communicatively and electrically connected to the bolt operating mechanism 124 to provide signals and power, respectively, to the bolt operating mechanism 124 to operate the bolt 112 to extract the bolt 112. It will be appreciated that the illustrated embodiment is a single-stage separation embodiment in which the bolt 112 is a breakaway bolt and the separation nut assembly 130 is configured to hold the bolt until the bolt 112 or separation nut 132 breaks, fractures, or splits into two pieces upon firing. The breaking, fracture, or splitting may be achieved by withdrawing the bolt 112 to failure or by an explosive core. If the separation nut 132 is fractured, the bolt 112 may be reused. Firing an explosive core fastener, also known as a pyrotechnic fastener, provides a controlled, rapid or rapid release and structural separation (fracture or other form) of the extracted bolt 112. This may be beneficial or necessary in some applications, including spacecraft, missile, and marine applications. The explosive core may be activated by a command given by, for example, an electric current.

[0120] Similarly, the bracket body 142-2 of the second bracket 140-2 is integrated with the split nut assembly 130 so as not to be a separate component from the split nut assembly 130.

[0121] Struts 162-2a, 162-2b, and 162-2c connect the separation nut assembly 130 to the bracket connectors 160-2a and 160-2b. Struts 162-2a and 162-2b and bracket connectors 160-2a and 160-2b may also be integral with the bracket body 142-2 and the separation nut assembly 130.

[0122] Each of the bolt assemblies 110 and the corresponding bracket connection 160 of the split nut assembly 130 are configured to connect to a space vehicle 103 or payload (not shown). It will be understood that the connected components (i.e., space vehicles or payloads) may be interchangeable.

[0123] In the illustrated embodiment, first body profile 144-1 of first bracket 140-1 is a cup profile configured to make face-to-face contact with cone second body profile 146-2 of second bracket 140-2, although embodiments in which the cup-cone profile is inverted are expressly contemplated.

[0124] 11A and 11B show an HRM system 100 that is a further embodiment of the HRM system 1100 of FIG. 1. The HRM system 1100 is configured similarly to the HRM system 100 of FIGS. 1 and 2. The HRM system 1100 is a single-stage decoupling HRM system 100 in which a decoupling nut 1130 is configured to release the bolt 1112 upon firing. The HRM system 1100 includes a power connection bracket 1176, further shown in FIG. 12A, and a shock plate interface 1278, shown in FIG. 12B.

[0125] 5A and 5B, there are shown perspective schematic views of an HRM system 500 having struts 562-2a through 562-2d and an HRM system 550 having lattice structures 566-1 and 566-2, respectively. HRM system 500 and HRM system 550 may be examples of HRM system 100 of FIG. 1.

[0126] Each moment and force experienced by HRM systems 500 and 550 is illustrated by a line of action 576. The lines of action 576 are referred to collectively as lines of action 576, specifically as lines of action 576a-576d, and collectively as lines of action 576. The lines of action 576 for each HRM system 500 and 550 converge at a point 578 or vertex 578.

[0127] Struts 562-2a through 562-2d and struts of lattice structures 566-1 and 566-2 are configured such that line of action 576 generally passes through each corresponding longitudinal axis. Struts 562-2a through 562-2d and lattice structures 566-1 and 566-2 are further configured such that each point 578 lies on a corresponding longitudinal axis 504.

[0128] 5B, HRM system 100 includes two cup-cone separation planes (not shown). The cup-cone separation planes are interface planes of cup-cone separation interfaces, such as cup-cone separation interfaces 144-1:146-2 and 144-2:138 in FIG. 2. In some embodiments, point 578 is located at the midpoint between the separation planes along axis 504.

[0129] 10A and 10B, there are shown side cross-sectional schematic views of one example of the HRM system 100 of FIG. 2 in a storage configuration 1000a and with the bolt 112 released and withdrawn 1000b.

[0130] In its fully deployed configuration, brackets 140-1 and 140-2 will be understood to have bolt 112 retracted into bolt hole 270 such that shaft 116 is substantially disposed within bolt housing 114 and shank 118 is substantially disposed within bolt hole 270 of bracket 140-1. This positioning of bolt 112 advantageously protects bolt 112 from environmental factors, such as radiation, during deployment.

[0131] Although the above description provides examples of one or more devices, methods, or systems, it will be understood that other devices, methods, or systems may be within the scope of the claims as interpreted by one of ordinary skill in the art.

Claims

1. 1. A retention and release mechanism (HRM) system for releasably retaining a deployable payload in a stowed configuration, comprising: A first HRM bracket, a first bracket body having a conical portion; and a first bracket connector for connecting the first HRM bracket to the deployable payload; a first HRM bracket having A second HRM bracket, a second bracket body having a conical portion; and a second bracket connector for connecting the second HRM bracket to a platform carrying the first deployable payload; a second HRM bracket having a retaining device configured to releasably hold the first bracket body and the second bracket body together in the stored configuration, wherein the conical portion of the first bracket body overlaps the conical portion of the second bracket body, or the conical portion of the second bracket body overlaps within the conical portion of the first bracket body, to form a separation interface of the HRM system; An HRM system having:

2. 2. The HRM system of claim 1, wherein the first HRM bracket further comprises a first strut connecting the first bracket body to the first bracket connector, the first strut configured to release a moment at the interface between the first bracket body and the second bracket body at the separation interface in the stowed configuration.

3. 2. The HRM system of claim 1, wherein the first bracket body or the second bracket body has a second conical portion coaxial with the conical portion of the respective bracket body, the second conical portion configured to overlap a third HRM bracket, thereby forming a second separation interface of the HRM system.

4. The HRM system of claim 2 , wherein the first strut is configured such that a line of action of the first strut converges to a first convergence point.

5. The HRM system of claim 4 , wherein the first convergence point is located at a separation plane of the separation interface.

6. 5. The HRM system of claim 4, wherein the first bracket body includes a first hole configured to receive a rod or bolt of the retention device, and the first convergence point is located on a longitudinal axis of the first hole.

7. 4. The HRM system of claim 3, wherein the second HRM bracket has a second strut configured such that lines of action of the second strut converge to a second convergence point.

8. The HRM system of claim 7 , wherein the first convergence point and the second convergence point are at the same location.

9. The HRM system of claim 2 , wherein the first struts are configured in a simple lattice structure or a complex lattice structure.

10. The HRM system of claim 1 , wherein the conical portion of the first bracket body or the conical portion of the second bracket body is frustoconical.

11. 1. A retention and release mechanism (HRM) system for releasably retaining a deployable payload in a stowed configuration, comprising: a first HRM bracket configured to couple to a first deployable payload; a second HRM bracket configured to couple to a second deployable payload; a third HRM bracket configured to couple to a platform on which the first deployable payload and the second deployable payload are stowed; a retention device having an HRM bolt, the retention device configured to retain the HRM bolt to releasably retain the first and second HRM brackets and the second and third HRM brackets together at first and second separation interfaces, respectively, of the HRM system, the retention device configured to release the retention upon receiving a release input to the retention device that allows separation at the first and second separation interfaces; HRM system having HRM bracket

12. The HRM system of claim 11 , wherein the HRM bolt is configured to break when the retention device receives the release input, thereby releasing the retention of the retention device.

13. 1. A method for retaining a deployable payload by an HRM system in a stowed configuration for later release, comprising: nesting a cone-shaped portion of a first bracket within a cone-shaped portion of a second bracket to form a first separation interface in the storage configuration; coupling the first bracket to the deployable mount and the second bracket to a platform on which the first deployable mount is stowed in the stowed configuration, or vice versa; releasably holding the first bracket and the second bracket together at the separation interface with a retention device, the retention device configured to release the retention of the retention device when the retention device receives a release input; A method having the following.

14. 14. The method of claim 13, wherein at least one of the first bracket and the second bracket has a plurality of struts configured to relieve moments due to the interface of the first bracket with at least one other bracket.

15. 14. The method of claim 13, wherein the retention device has a breakable component configured to break when the retention device receives the release input, the breaking of the breakable component enabling separation at the separation interface.

16. releasably holding the first and second brackets together placing a bolt of the retention device through the first bracket and the second bracket; holding the bolt at a second end of the bolt; preloading the bolt by withdrawing it from a first end, thereby clamping the first bracket and the second bracket together; 14. The method of claim 13, comprising:

17. The method of claim 16 , wherein retracting the bolt comprises torquing the bolt.

18. The method of claim 13 , further comprising delivering the release input to the holding device to release the held condition.

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