Universal spacecraft separation node

Details Universal spacecraft separation node Universal spacecraft separation node

1999-08-17

2003-04-15

Browne, Lynne H. (Department: 3629)

Joints and connections

Manually releaseable latch type

Having operating mechanism

C403S321000, C244S164000

Reexamination Certificate

active

06547476

ABSTRACT:

FIELD OF THE INVENTION
The present invention relates generally to space vehicle separation systems and, in particular, to a separation system employing an interface ‘node’ between a deployable space vehicle and a space launch vehicle. The invention provides a standardized interface for space vehicles thereby reducing, or substantially eliminating, interface integration efforts between the space vehicle and launch vehicle builders. The invention also provides improved structural response characteristics under applied loading when compared to other interface designs.
BACKGROUND OF THE INVENTION
Separation systems are used in a variety of contexts to provide controlled deployment of a deployable unit from a support structure. For example, in aerospace applications, separation systems are used in the space launch business to attach a space vehicle (i.e. spacecraft or satellite) to, and deploy from, a launch vehicle. They may also be used to deploy solar panels, scientific equipment, or other units from a stowed position on the space vehicle. Other possible applications of separation systems include, for example, aircraft ejection seat release, parachute actuation, and other applications involving controlled separation of two surfaces or structures. It will thus be appreciated that separation and associated deployment may involve complete detachment of the deployable unit from the support structure or movement from a non-deployed position to a deployed position. Although the present invention has been developed primarily for use in attaching a space vehicle to a space launch vehicle, it is apparent that further applications and adaptations of the invention are possible.
Generally, the interface between the space vehicle and the launch vehicle is defined by abutting interface surfaces between the two. The separation system typically includes one or more release assemblies that hold the spacecraft and launch vehicle together until the desired time of release. At the desired time of release, the separation system detaches, or disengages, releasing the space vehicle from the launch vehicle. Common separation systems include pyrotechnically actuated clamp-bands, separation nuts, and separation bolts. The present invention is intended for use where an interface incorporates a separation nut or bolt. These types of interfaces can incorporate any number of release mechanisms, typically the same type and size. This type of interface is sometimes referred to as a ‘hard-point’ or ‘node’ interface.
The interface between a space vehicle and a launch vehicle must be capable of transferring loads between the two structures. These loads can include vibration, acceleration, thermal, and static loads. For this reason, features of the interface must be tightly controlled with respect to tolerances associated with machining or forming processes. The longitudinal loads acting along the primary axis of the launch vehicle (i.e. the axis parallel to the primary vector of travel) are reacted by the separation bolt and bearing surfaces between the two structures. The shear loads, or side loads (those normal to the longitudinal loads), are reacted by shear pins or lips.
Because the interface features of a space vehicle and launch vehicle are generally controlled by separate manufacturers or groups within an organization, extensive integration efforts are required to ensure compatibility between the two pieces of hardware. In addition, typically a space vehicle will not be fit checked with a launch vehicle until both are nearly fully assembled. Moreover, it may be required that a space vehicle be compatible with several launch vehicles from the same manufacturer or different manufacturers. As a result, existing separation systems and associated interface configurations entail significant risk associated with new unit development, complicated integration efforts, and limited system interchangability. Furthermore, historically, each unique space vehicle has incorporated a unique, and often dramatically different, node design for the launch vehicle interface. The present invention is an attempt to provide a standardized node design.
SUMMARY OF THE INVENTION
The present invention is directed to a novel interface structure for interfacing a space vehicle or other deployable unit and a launch vehicle or other support structure, and to an associated separation system. The invention allows for interfacing the space vehicle and launch vehicle via an intermediate node that preferably incorporates both the separation system and structural interface functions. In this manner, the space vehicle and launch vehicle can be interfaced without extensive integration of the associated designs. Such an interface structure lends itself to standardization so as to mitigate risk associated with new support structure and/or deployable unit development, streamlines integration efforts, and provides a unique capability with widespread application.
The present invention incorporates the complex interface features within the system itself while providing an easily controlled interface to both the space vehicle and launch vehicle. The tightly controlled load carrying features are internal to the ‘node’ while simple bolt hole patterns, controlled by common tooling, provide easy to produce interfaces to the two vehicles. The load carrying features can be verified at the node component level while bolt hole patterns are verified through ‘matched’ tooling. This virtually eliminates any concerns of mismatch between the two vehicles.
According to one aspect of the present invention, an interface apparatus is provided for selectively connecting a deployable unit such as a space vehicle and a support structure such as a launch vehicle. The deployable unit includes a first interface surface and the support structure includes a second interface surface wherein, prior to deployment, the first and second interface surfaces are disposed in opposing relationship to define an interface. As set forth below, the interface surfaces need not be abutting. The deployable unit is deployable from an undeployed state where the first and second interface surfaces are proximate to one another in a deployed state wherein the interface surfaces are separated. The interface apparatus includes a support structure node member, interconnected to the support structure including a first contact surface and a deployable unit node member, interconnected to the deployable unit including a second contact surface. The first and second contact surfaces are disposed in an abutting relationship when the deployable unit is in the undeployed state so as to define a separation plane. The separation plane is located at the interface and separated from at least one of the first and second interface surfaces such that the support structure node member and deployable unit node member provide an interface structure, thereby reducing first and second interface surface design integration.
Preferably, the support structure node member and the deployable unit node member are configured so that the interface surfaces of the support structure and deployable unit are separated. In this manner, the need to integrate the support structure and deployable unit designs can be reduced or substantially eliminated. Such separation can be achieved with a variety of node configurations. For example, each of the node members can extend from its respective interface surface such that the contact surfaces are disposed between the interface surfaces prior to deployment, one of the node members can extend from its interface surface such that the contact surfaces are substantially flush with the other interface surface prior to deployment, or one of the node members can extend from one interface surface and the other node member can be recessed relative to the other interface surface such that the contact surfaces are outside of the area between the interface surfaces prior to deployment. In the last of these cases, it will be appreciated that the depth of the recessed node member will generally be less than

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