Framework For A Software-defined Global Positioning System (GPS) Receiver For Precision Munitions Applications

Ilg, Mark

doi:10.21236/ada559589

Cited by 5 publications

(4 citation statements)

References 6 publications

(6 reference statements)

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Different ideas like Software-Controlled Hardware Architecture, Fully Software-Controlled or Hybrid Approaches are explained in [2] and [14] but those are focusing the GNSS functionality itself, without any extensions or GNSS performance analyses or improvements. The same holds true for applicationspecific research projects like [5]. Hereby, a SDR approach will be developed, which enables a hardware-independent control and steering using highly precise GPS positioning.…”

Section: Research Topics On Software-defined Gnss Receivers and Amentioning

confidence: 99%

Smart constellation selection for precise vehicle positioning in urban canyons using a software-defined receiver solution

Niehoefer

Schweikowski

Wietfeld

2013

2013 IEEE 20th Symposium on Communications and Vehicular Technology in the Benelux (SCVT)

View full text Add to dashboard Cite

Abstract-Positioning techniques based on satellite navigation systems are nowadays standard in most commercial vehicles. But GPS receivers in general are effected by multipath and atmospheric effects and hence their performance may be decreased, especially in challenging environments that directly affects the usage of satellite-based positioning in traffic-relevant and by that safety-critical systems.

show abstract

Section: Research Topics On Software-defined Gnss Receivers and Amentioning

confidence: 99%

Smart constellation selection for precise vehicle positioning in urban canyons using a software-defined receiver solution

Niehoefer

Schweikowski

Wietfeld

2013

2013 IEEE 20th Symposium on Communications and Vehicular Technology in the Benelux (SCVT)

View full text Add to dashboard Cite

show abstract

“…Over the past several decades, numerous solutions have been proposed primarily for large artillery projectiles [1,2] or for slowly-rolling airframes [3][4][5]. The general methodology employed by most of these studies has been to use GPS [1,6], inertial measurements [7], and seekers [8] to provide feedback to a flight control system. Course correction maneuvers are then initiated through aerodynamic mechanisms [2,4,9] or jet control [10].…”

Section: Introductionmentioning

confidence: 99%

Guidance and Control of a Man Portable Precision Munition Concept

Fresconi

Rogers

2015

AIAA Atmospheric Flight Mechanics Conference

View full text Add to dashboard Cite

Small diameter, gun-launched projectiles pose a challenging platform on which to implement closed-loop guidance and control. This paper presents a novel imager-based guidance and control algorithm for small diameter, spin-stabilized projectiles. The control law is specifically formulated to rely on feedback only from a strap-down detector and roll angle sensors.Following introduction of the projectile nonlinear dynamic model, an integrated guidance and control algorithm is presented in which control commands are computed directly from detector feedback using a gain-scheduled proportional control. Time-varying controller gains are derived through a surrogate modeling approach, and controller performance is further enhanced through use of an observer that filters unwanted angular motion components from detector feedback.Example closed-loop flight simulations demonstrate performance of the proposed control system, and Monte Carlo analysis shows a factor of two accuracy improvement for the closed-loop system over ballistic flight. Results indicate that delivery system improvements are achievable in small, gyroscopically-stabilized projectiles containing low cost guidance elements using the proposed integrated guidance and control approach. mass [kg]This material is declared a work of the U.S. Government and is not subject to copyright protection in the United States. AIAA SciTech I moment of inertia matrix [kg-m 2 ] , ⁄ total velocity of projectile with respect to the wind, velocity of center of gravity with respect to inertial frame in body-fixed coordinates [m/s] atmospheric density [kg/m 3 ] dynamic pressure at projectile mass center [N/m 2 ] q M dynamic pressure at wing actuator center of pressure [N/m 2 ] Mach number √ pitch angle-of-attack [rad] √ yaw angle-of-attack [rad] √ √ total angle-of-attack [rad] aerodynamic roll angle [rad] , , aerodynamic forces acting on projectile [N] , , gravity forces acting on projectile [N] , , aerodynamic moments acting on projectile [Nm] , , total, zero-yaw, and yaw-dependent axial force coefficient , , , total, trim, linear and nonlinear normal force coefficient roll damping moment coefficient , , , total, trim, linear and nonlinear pitching moment coefficient pitch damping moment coefficient Magnus force coefficient Magnus moment coefficient , , , Wind actuator aerodynamic coefficients , axial center-of-pressure, radial CP [m] → vector from center-of-gravity to i th moveable Downloaded by NANYANG TECHNICAL UNIVERSITY on October 1, 2015 | http://arc.aiaa.org | aerodynamic surface center-of-pressure [m] , , , Φ, Earth-fixed commanded, Earth-fixed control, body-fixed control, relative, and stowed roll angles [rad] 1 0 0 0 Φ Φ 0 Φ Φ transformation matrix from body-fixed to moveable aerodynamic surface coordinates transformation matrix from body-fixed to Earthfixed coordinates transformation matrix from body-fixed to wing surface coordinates transformation matrix from velocity vector coordinates to Earth-fixed coordinates , , inertial position [m] , , inertial translational veloc...

show abstract

“…The global positioning system (GPS) (1,2), inertial measurement units (3), and seekers (4) often navigate munitions to the target. Course correction may be achieved through aerodynamic (5) or jet (6) control.…”

Section: Introductionmentioning

confidence: 99%

Guidance and Control of a Man-Portable Precision Munition Concept

Fresconi¹,

Rogers²

2014

View full text Add to dashboard Cite

Approved for public release; distribution is unlimited.ii REPORT DOCUMENTATION PAGE Form Approved OMB No. 0704-0188Public reporting burden for this collection of information is estimated to average 1 hour per response, including the time for reviewing instructions, searching existing data sources, gathering and maintaining the data needed, and completing and reviewing the collection information. Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for reducing the burden, to Department of Defense, Washington Headquarters Services, Directorate for Information Operations and Reports (0704-0188), 1215 Jefferson Davis Highway, Suite 1204, Arlington, VA 22202-4302. Respondents should be aware that notwithstanding any other provision of law, no person shall be subject to any penalty for failing to comply with a collection of information if it does not display a currently valid OMB control number. PLEASE DO NOT RETURN YOUR FORM TO THE ABOVE ADDRESS. REPORT DATE (DD-MM-YYYY)June 2014 ARL-TR-6966 SPONSORING/MONITORING AGENCY NAME(S) AND ADDRESS(ES) 10. SPONSOR/MONITOR'S ACRONYM(S) SPONSOR/MONITOR'S REPORT NUMBER(S) DISTRIBUTION/AVAILABILITY STATEMENTApproved for public release; distribution is unlimited. SUPPLEMENTARY NOTES ABSTRACTThe hypothesis of this report is that delivery accuracy of small-diameter spin-stabilized projectiles can be improved through novel guidance and control techniques using low-cost components. A gyroscopically stable projectile equipped with a strap-down detector and rotary actuation assembly is introduced. Flight models are formulated to enable nonlinear simulation. The unique guidance challenges posed by characteristics of spin-stabilized flight dynamics such as limit cycles, center-ofgravity swerve, instability, and practical feedback are illustrated. New guidance and control techniques to circumvent these difficulties are proposed. Modeling, parameter estimation, and stability analysis results underpin control design. Representative feedback, control commands, and flight behaviors from nonlinear simulations demonstrate the efficacy of this guidance approach. Monte Carlo analysis shows more than a factor of two in accuracy improvement of the guided over the ballistic flight. These results indicate that delivery system improvements are achievable in small, gyroscopically stable projectiles containing low-cost guidance elements using integrated control formulations. iii SUBJECT TERMS

show abstract

Framework For A Software-defined Global Positioning System (GPS) Receiver For Precision Munitions Applications

Cited by 5 publications

References 6 publications

Smart constellation selection for precise vehicle positioning in urban canyons using a software-defined receiver solution

Smart constellation selection for precise vehicle positioning in urban canyons using a software-defined receiver solution

Guidance and Control of a Man Portable Precision Munition Concept

Guidance and Control of a Man-Portable Precision Munition Concept

Contact Info

Product

Resources

About