Agency: Department of Defense | Branch: Air Force | Program: SBIR | Phase: Phase II | Award Amount: 779.40K | Year: 2007
Smart materials have shown promise for fluid power generation within electrohydrostatic actuators (EHAs). The smart material pumps have been successfully built to operate at high frequencies, but valve limitations have consistently reduced overall performance. Both passive and active valve concepts have been designed and tested, but these approaches have resulted in bandwidth limitations and added weight, respectively. A new unified pressurization and valving approach makes use of existing architecture in the pressurization systems, employing piezoelectric, magnetostrictive, or similar smart materials, and couples compact valve sets to the assembly. A current design, which links the valve motion to that of the reciprocating prime mover, has been developed and tested with promising results, including an increase in the optimal drive frequency. Additional design, testing, and analysis are proposed for a Phase 2 effort to further increase the functional bandwidth of the valves and the power density of the actuators. The valves will be incorporated into multiple EHAs that will be built and laboratory tested. The EHAs will then be integrated into the Insitu A-20 unmanned air vehicle (UAV) for flight test and separately into a laboratory morphing wing demonstration to validate the flightworthiness and applicability of the technology.
Agency: National Aeronautics and Space Administration | Branch: | Program: SBIR | Phase: Phase I | Award Amount: 99.99K | Year: 2008
CSA Engineering proposes the design of an adaptive aeroelastic mode suppression for advanced fly-by-wire aircraft, which will partition the modal suppression function from the rigid-body Flight Control System (FCS). CSA is recognized as having world-class expertise in the areas structural dynamics, vibration control, and control-structure interaction. Phase 1 will leverage expertise in structural dynamics and system-identification to develop adaptive filtering algorithms which operate in both the spatial and time domains to identify/estimate key aeroelastic generalized (modal) DOF and suppress aeroservoelastic interactions while minimizing the degradation of phase margin with respect to the FCS. During Phase 1, CSA will develop an end-to-end aeroelastic aircraft dynamic model of appropriate complexity as well as related sensors and measurement systems which will support the adaptive mode suppression effort. Sensors and measurement systems will be evaluated concurrently with adaptive filtering algorithms with regard to convergence, stability, and robustness. Filter architecture parameterization and constraints will be investigated. The goal of this development is to partition the suppression of aeroservoelastic interactions separate from the rigid body FCS, enabling FCS design and configuration/adaptation to be independent of aeroservoelastic considerations.
Agency: Department of Defense | Branch: Air Force | Program: SBIR | Phase: Phase II | Award Amount: 768.37K | Year: 2008
CSA offers a GVT test system that can dramatically reduce down time for AFFTC aircraft. Phase I demonstrated function of critical components that enable a configuration to reduce aircraft downtime by one-half or possibly even more. This proposal offers new techniques that preserve full control of data acquisition for the existing software used by AFFTC, retains identical data quality, and enables acquisition to begin merely minutes after committing the aircraft. Similarly, aircraft may be pulled from test even more quickly. A novel sensor design was demonstrated in Phase I that enables the system without detriment to data quality. Phase II will fabricate and deliver a fully functional system, and train AFFTC personnel in its operation and maintenance.
Agency: Department of Defense | Branch: Air Force | Program: SBIR | Phase: Phase II | Award Amount: 749.99K | Year: 2008
The objective of this study is to develop low cost, modular, multi-functional, primary spacecraft structures using an open-modular architecture which utilizes a "plywood and two-by-four" construction approach for rapid assembly. To be completed MM
Agency: Department of Defense | Branch: Air Force | Program: SBIR | Phase: Phase II | Award Amount: 741.77K | Year: 2008
ABSTRACT: Ground testing of space flight systems is a means of verifying component and system performance, developing new capabilities, and reducing risk. This research will produce a computer-controlled physical system capable of delivering motion, vibration and jitter in six degrees of freedom to a payload up to 300 kg. The payload could be a small spacecraft, or a large or small subassembly or sensor. A means of physical characterization of vibration disturbance sources will also be developed. Requirements for simulation will be gathered from the AIRSS program and other sources. These will drive the design of a hardware and software spacecraft motion and vibration simulator. The six-axis simulator will use a hexapod geometry with electromagnetic actuation and be both portable and suitable for vacuum operation. It will be operated from a user interface and will accept and export data to other ground test systems. The simulator will be delivered to the Air Force and interfaced with new ground test subsystems and payloads. It will reach full capability with inclusion of software for simulating more general mechanical impedances, for example those resulting from spacecraft solar arrays. A separate system for six-axis characterization of vibration disturbances including cryocoolers will also be delivered. BENEFIT: The motion and vibration simulator will have direct application to the Third Generation Surveillance (TGIRS) system and its Integrated Testbed (ITB). It will provide greater realism in the mechanical environment during ground testing and allow verification and improvement of wide field of view infrared sensor performance through physical test. It will reduce risk for space flight components. The companion vibration characterization system will provide a means of verifying properties of vibration disturbance sources and of comparing signatures of different components including cryocoolers. This information will be useful in satellite and sensor models. The simulation capability will be applicable to missile flight motion simulation and generation of synthetic environments for other aerospace and defense systems, including testing and validation of homeland security systems on mobile or harsh environment platforms."