An In-Flight Investigation to Develop Control System Design Criteria for Fighter Airplanes. Volume 1

Neal, T. Peter; Smith, R. E.

doi:10.21236/ad0880426

Cited by 104 publications

(43 citation statements)

References 1 publication

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“…Neal-Smith criterion [8] is a closed-loop system analysis to predict PIO susceptibility of the system and uses a pilot model [5,12,28,29] to close the loop. The pilot model contains a gain K p , lead T L and lag T 1 parameters and a time delay τ as shown below:…”

Section: Neal-smith Criterionmentioning

confidence: 99%

“…Since all flight experiments carried out for "Phastball" are in Category B flight phase, which is defined as gradual maneuvering without precision, for example, climb, cruise, descent etc., a corresponding value of Neal-Smith flight bandwidth ω BW = 1.5 rad/s is considered [8,31]. In the pilot model, τ represents the pilot's neuro-muscular delay, which is assumed to be 0.3 s [8].…”

Section: Neal-smith Criterionmentioning

confidence: 99%

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Analysis of Pilot-Induced-Oscillation and Pilot Vehicle System Stability Using UAS Flight Experiments

Mandal

2016

Aerospace

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This paper reports the results of a Pilot-Induced Oscillation (PIO) and human pilot control characterization study performed using flight data collected with a Remotely Controlled (R/C) unmanned research aircraft. The study was carried out on the longitudinal axis of the aircraft. Several existing Category 1 and Category 2 PIO criteria developed for manned aircraft are first surveyed and their effectiveness for predicting the PIO susceptibility for the R/C unmanned aircraft is evaluated using several flight experiments. It was found that the Bandwidth/Pitch rate overshoot and open loop onset point (OLOP) criteria prediction results matched flight test observations. However, other criteria failed to provide accurate prediction results. To further characterize the human pilot control behavior during these experiments, a quasi-linear pilot model is used. The parameters of the pilot model estimated using data obtained from flight tests are then used to obtain information about the stability of the Pilot Vehicle System (PVS) for Category 1 PIOs occurred during straight and level flights. The batch estimation technique used to estimate the parameters of the quasi-linear pilot model failed to completely capture the compatibility nature of the human pilot. The estimation results however provided valuable insights into the frequency characteristics of the human pilot commands. Additionally, stability analysis of the Category 2 PIOs for elevator actuator rate limiting is carried out using simulations and the results are compared with actual flight results.

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Section: Neal-smith Criterionmentioning

confidence: 99%

Section: Neal-smith Criterionmentioning

confidence: 99%

Analysis of Pilot-Induced-Oscillation and Pilot Vehicle System Stability Using UAS Flight Experiments

Mandal

2016

Aerospace

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“…16. It follows from this basic assumption that good tracking of reference models with desirable handling qualities [16][17][18][19][20] should result in the closed-loop system exhibiting satisfactory behavior.…”

Section: Reference Model Trackingmentioning

confidence: 99%

“…18 The mathematical compensator in Fig. 17 is tuned such that a particular closed-loop bandwidth is achieved while minimizing the resonant peak in the closed-loop response.…”

Section: Neal-smith Criteriamentioning

confidence: 99%

Nonlinear Dynamic Inversion Baseline Control Law: Flight-Test Results for the Full-scale Advanced Systems Testbed F/A-18 Airplane

Miller

2011

AIAA Guidance, Navigation, and Control Conference

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A model reference nonlinear dynamic inversion control law has been developed to provide a baseline controller for research into simple adaptive elements for advanced flight control laws. This controller has been implemented and tested in a hardware-in-the-loop simulation and in flight. The flight results agree well with the simulation predictions and show good handling qualities throughout the tested flight envelope with some noteworthy deficiencies highlighted both by handling qualities metrics and pilot comments. Many design choices and implementation details reflect the requirements placed on the system by the nonlinear flight environment and the desire to keep the system as simple as possible to easily allow the addition of the adaptive elements. The flight-test results and how they compare to the simulation predictions are discussed, along with a discussion about how each element affected pilot opinions. Additionally, aspects of the design that performed better than expected are presented, as well as some simple improvements that will be suggested for follow-on work.

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“…Fur-the continuous wind phenomena, wind and turbulence levels are 9 defined by a probability of excedeneo and altitude. For the low altitude models (belc: cbuut 3,0)0 fret), the prebability of exceederce " deftioes a u~an wind profile.…”

Section: Tmentioning

confidence: 99%

USAF Flying Qualities Requirements for a STOL (Short Takeoff and Landing) Transport

Gerken¹

1979

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An In-Flight Investigation to Develop Control System Design Criteria for Fighter Airplanes. Volume 1

Cited by 104 publications

References 1 publication

Analysis of Pilot-Induced-Oscillation and Pilot Vehicle System Stability Using UAS Flight Experiments

Analysis of Pilot-Induced-Oscillation and Pilot Vehicle System Stability Using UAS Flight Experiments

Nonlinear Dynamic Inversion Baseline Control Law: Flight-Test Results for the Full-scale Advanced Systems Testbed F/A-18 Airplane

USAF Flying Qualities Requirements for a STOL (Short Takeoff and Landing) Transport

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