Development of a flush airdata sensing system on a sharp-nosed vehicle for flight at Mach 3 to 8

Davis, Mark C.; Pahle, Joseph W.; White, John T.; Marshall, Laurie A.; Mashburn, Michael J.; Franks, Rick

doi:10.2514/6.2000-504

Cited by 25 publications

(8 citation statements)

References 3 publications

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“…The intent of the HXRV FADS system research is to collect pressure data and evaluate the FADS algorithms 6 which are used to estimate angle of attack and dynamic pressure. During the descent, the inertial angle of attack is augmented with the FADS-estimated angle of attack to generate the estimated angle of attack as a means of developing confidence in the FADS algorithms for applications of this type.…”

Section: Gnc Research Objectivesmentioning

confidence: 99%

The X-43A Hyper-X Mach 7 Flight 2 Guidance, Navigation, and Control Overview and Flight Test Results

Bahm

Baumann²,

Martín

et al. 2005

AIAA/CIRA 13th International Space Planes and Hypersonics Systems and Technologies Conference

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Section: Gnc Research Objectivesmentioning

confidence: 99%

The X-43A Hyper-X Mach 7 Flight 2 Guidance, Navigation, and Control Overview and Flight Test Results

Bahm

Baumann²,

Martín

et al. 2005

AIAA/CIRA 13th International Space Planes and Hypersonics Systems and Technologies Conference

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“…The FADS system using the variational solution algorithms was applied to three premier hypersonic flight programs in the late 1990's, the X-33, 9 X38, 10 and X-43. 11 In 2017 a FADS system was developed and flight tested for the Sierra Nevada Corporation's Dream Chaser Space plane. 12 For these early programs, the sensed pressures were related to the desired airdata parameters using a non-physical mapping.…”

Section: Introductionmentioning

confidence: 99%

An optical-scan method for measuring the as installed surface port incidence angles for flush air data sensing (FADS) systems

A Whitmore

2024

AAOAJ

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The Flush Air Data Sensing (FADS) System, where air data are inferred from non-intrusive surface pressure measurements, uses natural contours of the vehicle forebody, wing leading edge, or probe. Although multiple methods have been developed to derive airdata from the sensed pressure matrix, all methods rely on accurate knowledge of local surface contours at the port locations. One of the most well-developed solution methods curve-fits the surface pressure distribution against the associated surface incidence angles using a quasi-Newtonian model. The well-known "Triples" algorithm extracts airdata from the curve-fit model. This solution method requires precise knowledge of as-installed incidence angles, i.e. the angles between the surface normal and the longitudinal axis of the vehicle. This study investigates the feasibility and accuracy of using an inexpensive optical-scanning system to measure the in-situ FADS pressure ports surface incidence angles. Here, two legacy 3-D printed probe shapes, as previously tested during a series of very low-speed wind tunnel tests, were used to develop and evaluate this method. The shapes 1) a hemispherical head cylindrical forebody, and 2) a Rankine-Body, were scanned along the longitudinal axis and the resulting point-cloud was edited using open-source software to generate three concentric "loops" surrounding each surface port. Each annular loop was assumed as co-planar with the surface port, and the singular-value decomposition (SVD) was used calculate the local surface gradient vector from the null-space solution. From the resulting gradient vector, geometric relationships calculate the port's polar coordinates including the surface incidence angle. For both body contours the resulting calculations are compared to the "known" design surface angles as prescribed for the 3-D prints. Error plots are presented for each individual ring-set, and for the collected set using all three ring together. For the collected data sets, the incidence angle calculations are accurate to within a quarter-degree.

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“…As a result, FADS can be suitably used in unconventional vehicles such as hypersonic vehicles [ 5 ] and Mars entry vehicles [ 6 ]. Besides that, compared with the probe type structure, such a built-in stucture makes the vehicle have the lower radar reflective area, leading to the better stealth performance which is critical for the future airplane to escape potential hazards and enhance its survival adaptation [ 7 ]. More importantly, further studies on FADS need to be integrated with other technologies such as the vehicle modeling [ 8 ], flight control law design [ 9 ] and performance evaluation [ 10 ] in order to take the advantage of FADS, while improving the overall performance of the unconventional vehicle.…”

Section: Introductionmentioning

confidence: 99%

Comparative Study on a Solving Model and Algorithm for a Flush Air Data Sensing System

Liu

Xiao

2014

Sensors

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With the development of high-performance aircraft, precise air data are necessary to complete challenging tasks such as flight maneuvering with large angles of attack and high speed. As a result, the flush air data sensing system (FADS) was developed to satisfy the stricter control demands. In this paper, comparative stuides on the solving model and algorithm for FADS are conducted. First, the basic principles of FADS are given to elucidate the nonlinear relations between the inputs and the outputs. Then, several different solving models and algorithms of FADS are provided to compute the air data, including the angle of attck, sideslip angle, dynamic pressure and static pressure. Afterwards, the evaluation criteria of the resulting models and algorithms are discussed to satisfy the real design demands. Futhermore, a simulation using these algorithms is performed to identify the properites of the distinct models and algorithms such as the measuring precision and real-time features. The advantages of these models and algorithms corresponding to the different flight conditions are also analyzed, furthermore, some suggestions on their engineering applications are proposed to help future research.

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Development of a flush airdata sensing system on a sharp-nosed vehicle for flight at Mach 3 to 8

Cited by 25 publications

References 3 publications

The X-43A Hyper-X Mach 7 Flight 2 Guidance, Navigation, and Control Overview and Flight Test Results

The X-43A Hyper-X Mach 7 Flight 2 Guidance, Navigation, and Control Overview and Flight Test Results

An optical-scan method for measuring the as installed surface port incidence angles for flush air data sensing (FADS) systems

Comparative Study on a Solving Model and Algorithm for a Flush Air Data Sensing System

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