Providing Means for Precision Airdrop Delivery from High Altitude

Hattis, Philip D.; Campbell, Darryn P.; Carter, David W.; McConley, Marc W.; Tavan, Steve

doi:10.2514/6.2006-6790

Cited by 7 publications

(4 citation statements)

References 3 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…To achieve precision landing capability of less than 100 m miss distance, a precision-guided parafoil is used as a terminal decent stage decelerator for this study [19]. A 3.7 m 2 Mosquito Parafoil with a glide ratio of 3 to 1 has been shown to be capable of achieving 100 m landing accuracy if this system is delivered to within 10 km of the target point at an altitude of 6 km [20].…”

Section: Decelerator Configurationsmentioning

confidence: 99%

Investigation of Drag-Modulated Supersonic Inflatable Aerodynamic Decelerators for Sounding Rocket Payloads

Miller

Steinfeldt

Braun

2015

Journal of Spacecraft and Rockets

View full text Add to dashboard Cite

The goal of this investigation is to understand the sizing and performance of supersonic inflatable aerodynamic decelerators for Earth-based sounding rocket applications. The recovery system under examination is composed of a supersonic inflatable aerodynamic decelerator and a guided parafoil system to achieve sub-100 m miss distances. Three supersonic inflatable aerodynamic decelerator configurations (tension cone, attached isotensoid, and trailing isotensoid) are examined using the metrics of decelerator mass, aerodynamic performance, and vehicle integration. In terms of aerodynamic performance, the tension cone is the preferred choice for the sizes investigated. The attached isotensoid was shown to be the most mass efficient decelerator, whereas the trailing isotensoid was found to be the more ideal decelerator for vehicle integration. A three-degree-of-freedom trajectory simulation is used in conjunction with Monte Carlo uncertainty analysis to assess the landed accuracy capability of the proposed architectures. In 95% of the cases examined, the drag-modulated inflatable aerodynamic decelerator provides arrivals within the 10 km parafoil capability region, meeting the sub-100 m landed recovery goals. In 76% of the cases examined, the dragmodulated inflatable aerodynamic decelerator arrives within 5 km of this target zone. Nomenclaturenumber m = mass, kg q = dynamic pressure, N∕m 2 S = area, m 2 s = downrange, m T = reference temperature, K t = time, s u = eastward wind velocity, m∕s V = velocity, m∕s v = northward wind velocity, m∕s β = ballistic coefficient equal to m∕C D A, kg∕m 2 δDR = change in downrange, km λ = launch elevation angle, deg Subscripts D = drag deploy = deployment est = estimate f = areal max = maximum min = minimum para = parafoil ref = reference target = target

show abstract

Section: Decelerator Configurationsmentioning

confidence: 99%

Investigation of Drag-Modulated Supersonic Inflatable Aerodynamic Decelerators for Sounding Rocket Payloads

Miller

Steinfeldt

Braun

2015

Journal of Spacecraft and Rockets

View full text Add to dashboard Cite

show abstract

“…Missions for guided parafoils include military resupply of troops and humanitarian efforts (Hattis & Tavan, 2007). As described in Hattis, Campbell, Carter, McConley, and Tavan (2006), the goal of the system is to land the payload as close as possible to the target Matthew Stoeckle et al This is an open-access article distributed under the terms of the Creative Commons Attribution 3.0 United States License, which permits unrestricted use, distribution, and reproduction in any medium, provided the original author and source are credited. while minimizing ground speed at impact.…”

Section: Introductionmentioning

confidence: 99%

Fault Detection and Isolation for Autonomous Parafoils

et al. 2013

View full text Add to dashboard Cite

Autonomous precision airdrop systems are widely used to de- liver supplies to remote locations. Payloads that are delivered far from their intended targets or with high impact velocity may be rendered unusable. Faults occurring during flight can severely degrade vehicle performance, effectively nullifying the value of the guided system, or worse. Quickly detecting and identifying faults enables the choice of an appropriate recovery strategy, potentially mitigating the consequences of an out-of-control vehicle and recovering performance. This paper presents a multi-observer, multi-residual fault detection and isolation (FDI) method for an autonomous parafoil system. The detection and isolation processes use residual signals generated from observers and other system models. statistical methods are applied to evaluate these residuals and determine whether a fault has occurred, given a priori knowledge of system uncertainty characteristics. Several examples are used to illustrate the detection and isolation algorithm on- line using available navigation and telemetry outputs. Tests of this FDI method on a large number of high-fidelity simulations indicate that it is possible to detect and isolate some common faults with a high percentage of success and a very small chance of raising a false alarm.

show abstract

“…More detailed analysis reveals that GNC systems developed by Charles Stark Draper Laboratory, [20][21][22][23][24] Georgia Tech [29][30][31] and others implement simple proportional-integral-derivative (PID) controllers to track the reference heading, which is assigned based on a combination of some logics and heuristic rules. For the final stage of descent to the DZ some controllers use a moth mode, others attempted to utilize a precomputed landing trajectories data base.…”

Section: -34mentioning

confidence: 99%

“…So during the last decade, several GNC concepts for gliding parachute applications have been developed and published. [19][20][21][22][23][24][25][26][27][28][29][30][31] …”

mentioning

confidence: 99%

Optimal Control for Terminal Guidance of Autonomous Parafoils

Slegers

Yakimenko

2009

20th AIAA Aerodynamic Decelerator Systems Technology Conference and Seminar

View full text Add to dashboard Cite

This paper deals with the development of guidance, navigation and control algorithms for a prototype of a miniature aerial delivery system capable of high-precision maneuvering and high touchdown accuracy. High accuracy enables use in precision troop resupply, sensor placement, urban warfare reconnaissance, and other similar operations. Specifically, this paper addresses the terminal phase, where uncertainties in winds cause most of the problems. The paper develops a six degree-offreedom model to adequately address dynamics and kinematics of the prototype delivery system and then reduces it to a two degrees-of-freedom model to develop a model predictive control algorithm for reference trajectory tracking during all stages. Reference trajectories are developed in the inertial coordinate frame associated with the target. The reference trajectory during terminal guidance, just prior to impact, is especially important to the final accuracy of the system. This paper explores an approach for generating reference trajectories based on the inverse dynamics in the virtual domain. The method results in efficient solution of a two-point boundary-value problem onboard the aerial delivery system allowing the trajectory to be generated at a high rate, mitigating effects of the unknown winds. This paper provides derivation of the guidance and control algorithms and present analysis through simulation.

show abstract

Providing Means for Precision Airdrop Delivery from High Altitude

Cited by 7 publications

References 3 publications

Investigation of Drag-Modulated Supersonic Inflatable Aerodynamic Decelerators for Sounding Rocket Payloads

Investigation of Drag-Modulated Supersonic Inflatable Aerodynamic Decelerators for Sounding Rocket Payloads

Fault Detection and Isolation for Autonomous Parafoils

Optimal Control for Terminal Guidance of Autonomous Parafoils

Contact Info

Product

Resources

About