Dual Port Payload Attach Ring Satellite Launch
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Solution Overview
Problem
Conventional payload attach ring designs have limited ability to support relatively large satellites for launch, as the maximum height of the ring is dependent on the launch fairing size, restricting the launch of taller satellites.
Innovation Solution
A dual port payload attach ring system where each spacecraft's strongback is attached to two payload ports via beams and port adaptor plates, using mechanical actuators and springs to enable secure attachment and separation, allowing for the distribution of satellite mass and volume across multiple ports.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Volume of moving object
If conventional single-port payload attach ring designs are used, then the structure is simple and easy to manufacture, but the volume and mass capacity are limited
Solution Approach 1:
The attach ring structure is segmented into multiple independent payload ports (first payload port and second payload port), each capable of supporting separate satellites. This segmentation allows the system to accommodate larger total satellite volume and mass by distributing payloads across multiple ports rather than relying on a single large port.
Solution Approach 2:
The payload attach ring is designed with universal port adaptor plates that can be configured for different payload types and sizes. Each port adaptor plate serves multiple functions: structural support, electrical connection interface, and mechanical attachment point. This multi-functionality allows the same basic structure to accommodate various satellite configurations without requiring complete redesign.
2Volume of moving object
If taller payload attach ring designs are used to support larger satellites, then the satellite volume capacity increases, but the design becomes incompatible with standard launch fairing sizes
Solution Approach 1:
Instead of increasing the height (vertical dimension) of the payload attach ring to accommodate larger satellites, the design utilizes the radial and circumferential dimensions by adding multiple payload ports around the ring. This dimensional shift allows larger satellite capacity without increasing the vertical profile that would conflict with launch fairing constraints.
Solution Approach 2:
The port adaptor plates are designed to nest within the standardized payload attach ring structure. Each adaptor plate can be inserted into and secured on the ring, creating a nested configuration that maintains compatibility with standard launch vehicle interfaces while providing expanded payload capacity through the addition of multiple nested adaptor units.
3Volume of moving object
If multiple payload ports are used to increase satellite capacity, then the volume and mass capacity improve, but the attachment and separation mechanisms become more complex
Solution Approach 1:
The attachment system incorporates self-aligning features where the port adaptor plates automatically orient themselves during the attachment process. The mechanical actuators are designed to engage and disengage through self-contained motion sequences that reduce the need for complex external control mechanisms, making the operation simpler despite multiple ports.
Solution Approach 2:
The attachment and separation mechanisms use dynamic mechanical actuators that can rapidly transition between locked and unlocked states. This dynamic capability allows all multiple ports to be secured or released simultaneously through a single command, maintaining operational simplicity even with multiple payload ports. The springs provide dynamic force to ensure reliable engagement and separation.
Applied Scientific Principles
This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.
Function Achieved in This Case
Enables the launch of relatively large satellites by increasing the volume and mass capacity beyond single-port limitations, providing flexibility with various launch vehicle configurations while maintaining structural integrity.
Implementation Method 1
each of the beams comprises at least one spring, and when the strongback of each of the spacecrafts is attached to each of the two respective payload ports, the spring(s) is in a pre-separation position (e.g., a compressed position)
Implementation Method 2
when the strongback of each of the spacecrafts is separated from each of the two respective payload ports, the spring(s) is extended to a post-separation position (e.g., a non-compressed position)
Implementation Method 3
each of the beams comprises at least one mechanical actuator, and the separating of the strongback of each of the spacecrafts from each of the two respective payload ports is achieved by at least one mechanical actuator activating to allow for separation
Implementation Method 4
In at least one embodiment, at least one coupler is a cup/cone interface or a similar load bearing interface
Data Source
Figure 1~2A
Figure 2B~3
Figure 4
AI summary
Systems, methods, and apparatus for dual port ring compatible satellites are disclosed. In one or more embodiments, a method for removably attaching at least one spacecraft (220) to a payload attach ring (310) on a launch vehicle (140) involves attaching a strongback (215) of each of the spacecrafts to two respective payload ports (320) of the payload attach ring on the launch vehicle. In one or more embodiments, the strongback of each of the spacecrafts is attached to each of the two respective payload ports via a respective beam mounted to a respective port adaptor plate. The method further involves separating the strongback of each of the spacecrafts from the two respective payload ports of the payload attach ring on the launch vehicle by using at least one mechanical actuator on each of the beams.