MMA Design

United States

The Stand-Off Mechanism (SOM) is a deployable structure with space flight heritage. It provides payload clearance in applications in which a fixed bracket is not feasible. The typical payload is the MMA Design De-Orbit Module; however, the SOM can be scaled for use with other payloads.Highly scalableRedundant composite tapesNo motors passive mechanismIncludes an optional mechanical inhibit for the attached payloadDoes not rotate during deploymentNo end-of-motion lockout neededElectrical feed-thruEnd-of-motion shock is lessened using Belleville washerUndamped deployment. Damping can be added

MMA successfully developed a deployable RF antenna structural system that can be scaled and leverages space heritage of mechanisms utilized on other similar deployable systems. The goal of this program was to develop an antenna whose entire footprints could be stowed within a Minotaur IV. Earlier development versions designed by MMA were over twice as large, but by using a modular system, and utilizing legacy technology developed and deployed on previous missions, MMA was able to create a solution that met challenging mission requirements with high reliability and low mass.

MMAs dragNET De-Orbit system has been qualified to meet DoD and NASA requirements for de-orbiting satellites in low earth orbit (LEO), and was flight demonstrated to achieve TRL 9 with the successful launch and deployment in November 2013 on the ORS-3 Mission.An elegant bolt-on solution that minimizes impact to integration and operationsDe-orbit < 25 years from 850 km14 m2 of effective aerodrag deployed areaEfficient, highly scalable packagingMass < 2.8 kgFrangibolt actuated releaseHigh margin, robust and reliable spring-powered deploymentShaped, deployed membrane to support vehicle passive stability

MMAs team successfully completed development, flight testing, and delivery of the USAFA FalconSAT-7 deployment system for a photon sieve payload (called Peregrine), the worlds first space-based thin membrane telescope. Peregrine is a thin membrane with billions of holes that duplicates the function of a traditional lens but folds into a smaller space. The FalconSAT-7 mission is scheduled to launch in 2017, and its primary objective will be to image the sun. Successful technology development will enable scaled, deployable telescopes for space-based imaging at a significantly lower mass and cost than traditional fixed optics.

Based on the innovative HaWK solar array series, the zHaWK consists of two 3-panel trifold array wings each mounted on opposite 1U x3U faces. Like other HaWK configuratuons, the complete array system is stowed for launch and released after power is applied to a melt rod release mechanism. Deployment of the flip-out panels and wings is accomplished using stored energy provided by springs. The deployment is a low energy event and does not require any damping. Once deployed the array wings are in position for power development. If the mission requires, the sun tracking single axis SADA is used to track the sun position and provide maximum average orbital power.

MMAs patented HaWK (High Watts per Kilogram) solar array technology is a state-of-the-art deployable satellite power solution, providing best-in-class performance metrics for MicroSat platforms. Our modular and scalable components offer a variety of architecture designs to meet mission requirements. Our focus is on maintaining common components for elegant, deployable power solutions that are reliable at a competitive price point.The HaWK system is designed for the CubeSat and Small Sat platforms, and provides a building block approach which allows modularity and scalability. Its innovative packaging and restraint scheme seamlessly mount to the outer surface of any CubeSat and meets 6.5mm envelope requirements. On-command deployment using an integrated heater circuit provides command and control versatility to mission operators. Increase orbital average power (OAP) through a uniquely designed single-axis, dual-wing, sun tracking gimbal assembly at 6.5mm thick.The HaWK system is designed for the CubeSat and Small Sat platforms, and provides a building block approach which allows modularity and scalability. Its innovative packaging and restraint scheme seamlessly mount to the outer surface of any CubeSat and meets 6.5mm envelope requirements. On-command deployment using an integrated heater circuit provides command and control versatility to mission operators. Increase orbital average power (OAP) through a uniquely designed single-axis, dual-wing, sun tracking gimbal assembly at 6.5mm thick.

Current state-of-the-art mesh antennas use ribbed umbrella and hoop structures for deployment. While these are potentially scalable to some extent, they inherently have high parts counts and require significant touch labor at a high number of attach points to form the desired mesh surface. These systems have constraints on their stowed volume which present challenges with small launch vehicle fairings and dispensers. The DaHGR sets a new standard for deployable antennas with 13 the parts count, less than 15 the volume (with a more favorableflexible aspect ratio), and 13 the cost of current SOA deployable mesh antennas.

The patent pending MMA Spine APM uses a stack of pivoting vertebra elements forming a spine. The spine cross-section has a hole in the center, similar to the spinal cord in the backbone, where a flexible RF coaxial cable or wave guide is routed. The curvature of the spine assembly is shallow and repeatable, thus minimizing the bend radius of the FR coaxial cable or wave guide. This approach eliminates complex rotary joints and their associated RF losses and preclude the need for rotate or twist the aperture while pointing.Within the spine there are four tensioned cables. Two of the cables are attached to stepper or brushless DC motor driven reels. The other two cables are held under constant tension by extensible springs. To actuate the spine assembly to any point within the pointing range 2 of the 4 cables that control the spines position and curvature are extended or retracted by the appropriate reel. Changing the cable lengths moves the APM to a predetermined position. Testing at MMA has proven the APM pointing angles are very repeatable.

MMA has designed spring-energy deployable booms that are cost effective, reliable and minimally complex. Deployment energy is managed with a rotary mechanical damper and its expansion ratio is up to 30:1.Composite tape structureDeployment force sourceNo moving partsLow CTE longeronsFew metal parts for improved antenna performanceIntegral launch restraint with non-complex electrical interfacePayloadWire harness friendlyNo canisterNon-rotating deploymentPlenty of envelope for harnessing