The present invention relates generally to spacecraft engineering and design. More particularly, the present invention relates to structural, fluid, and electrical connectors for interconnection of spacecraft modules. Furthermore, the present invention relates to spacecraft docking and separation systems for providing structural, fluid, and electrical connection between components.
There is an enormous benefit to docking or connecting spacecraft and spacecraft components. The many applications include launching a spacecraft for rendezvous in orbit with another spacecraft. Furthermore, the ability to connect or disconnect spacecraft modules has application where a broken module can be jettisoned and replaced. Electronic and structural components are also connected prior to launch to form a spacecraft.
Structural, fluid and electrical connectors are often combined to create an “interface” connection which is employed in a wide variety of applications. Current spacecraft and launch vehicle interfaces employ various electrical connectors and separation systems including pyrotechnically actuated clamp bands, separation nuts, and separation bolts. The interface must be capable of transferring loads between the two structures. The loads may include vibration, acceleration, thermal conduction, and static loads. For example, U.S. Patent Application Publication No. 2002/0164204 describes a spacecraft interface structure for mechanically connecting various spacecraft components including a spacecraft to a launch vehicle.
Structural, fluid and electrical interface connectors have been developed for in-space docking and separation. For example, U.S. Pat. No. 8,006,937 describes a docking interface in which alignment cups are heated to an austenitic temperature to form a mechanical connection. Power and fluids may be transferred between the two spacecrafts. Fluid, such as a propulsion fluid, is transferred through a central conduit, and data and power can be transferred through the mechanical coupling. Similarly, U.S. Patent Application Publication No. 2012/0000575 describes a docking interface for refueling satellites in space. The docking assembly includes a connector including male and female components for providing fluid transfer. The connector provides electrical power and data transfer as well.
Past spacecraft have been custom designed and optimized for a particular mission or payload wherein electronic components are mounted inside box-like modules. The spacecraft electronic components provide a single spacecraft function, such as power, thermal, structural, telemetry, tracking, control or processing, or a specific payload function, such as communications or surveillance. The modules are mounted to a spacecraft frame and interconnected with extremely complex wiring harnesses. Unfortunately, the designs cannot be adapted to accomplish different missions as changing any part or sub-system typically has required significant rework of the design.
Modular spacecraft are attempts to transition away from custom designed spacecraft toward multi-use designs and mass production in an effort to reduce the cost of spacecraft development. The modular spacecraft include a bus which provides a general purpose spacecraft platform. Various payloads can be mounted to the spacecraft platform utilizing a standard structural, fuel and electric interface. Again, the interface connector is of paramount importance.
Even more recently, spacecraft have been designed by combing homogeneous cells. Each cell possesses the traditional architecture of a spacecraft including structure, power, fuel, attitude control and determination, satellite processing, etc. Each cell is substantially identical so as to be manufactured inexpensively and quickly. These cells are combined to create larger and larger platforms to support payload functions such as communications and surveillance. Though there is substantial redundancy by each cell incorporating all spacecraft sub-system capabilities, the extra costs are more than made up for by mass production savings and rapid assembly. Of course, the satellite reconfigurable cell concept also requires that cells be interconnected by a structural, fluid and electrical interface.
Unfortunately, previous structural, fluid and electrical interface connectors have suffered from various drawbacks.
Thus, there is a need for an improved structural, fluid and electrical connector.
There is also a need for an improved spacecraft connector which can be docked and separated in space.
Additionally, it would be advantageous to provide a connector that can be utilized as a launch lock for affixing a spacecraft to a launch vehicle.
Also desirable would be a spacecraft connector that can be utilized to connect and function as an interface between homogeneous cells of a spacecraft.
Furthermore, it would be desirable to provide a spacecraft connector which is capable of functioning as a propulsion thruster when not functioning as a spacecraft interface connector.