Design and Simulation of Guidance Law for a Kind of Flight Test Missile

2012 ◽  
Vol 538-541 ◽  
pp. 2887-2891
Author(s):  
Yu Qian ◽  
Xiao Jun Xiang ◽  
Jun Li Yang
Keyword(s):  
Flight Test ◽  
Target Point ◽  
Impact Point ◽  
Integral Term ◽  
Guidance Law ◽  
Velocity Information ◽  
The Difference ◽  
Miss Distance ◽  
Midcourse Guidance ◽  
The Impact

To reduce the miss distance of flight test missile, the midcourse guidance law is studied in this paper. The nonlinear projectile dynamic model is developed at first, and then designed the midcourse guidance law with the impact point prediction information. The guidance law was designed using the difference between predicting impact point and target point. To improve the guidance law’s performance, this research inducted the predicted impact point’s velocity information and integral term into guidance law command. At the end, the simulation was developed. The results of simulation show that the guidance law designed in this study is successful and it can satisfy the test missile’s flight mission requirements.

scholarly journals Stability of temperatures from TIMED/SABER v1.07 (2002–2009) and Aura/MLS v2.2 (2004–2009) compared with OH(6-2) temperatures observed at Davis Station, Antarctica

2010 ◽  
Vol 10 (9) ◽  
pp. 21547-21565 ◽  
Author(s):  
W. J. R. French ◽  
F. J. Mulligan
Keyword(s):  
Cold Bias ◽  
Spatial And Temporal Scales ◽  
Ground Station ◽  
Volume Emission ◽  
The Difference ◽  
Miss Distance ◽  
Hydroxyl Layer ◽  
The Impact ◽  
Long Term Studies

Abstract. Temperature profiles from two satellite instruments – TIMED/SABER and Aura/MLS – have been used to calculate hydroxyl-layer equivalent temperatures for comparison with values measured from OH(6-2) emission lines observed by a ground-based spectrometer located at Davis Station, Antarctica (68° S, 78° E). The profile selection criteria – <500 km from the ground station and solar zenith angles >97° – yielded a total of 2359 SABER profiles over 8 years (2002–2009) and 7407 MLS profiles over 5.5 years (2004–2009). The availability of simultaneous OH volume emission rate (VER) profiles from the SABER (OH-B channel) enabled an assessment of the impact of several different weighting functions in the calculation of OH-equivalent temperatures. The maximum difference between all derived hydroxyl layer equivalent temperatures was less than 3 K. Restricting the miss-distance and miss-time criteria showed little effect on the bias, suggesting that the OH layer is relatively uniform over the spatial and temporal scales considered. However, a significant trend was found in the bias between SABER and Davis OH of ~0.7 K/year over the 8-year period with SABER becoming warmer compared with the Davis OH temperatures. In contrast, Aura MLS exhibited a cold bias of 9.9 ± 0.4 K compared with Davis OH, but importantly, the bias remained constant over the 2004–2009 year period examined. The difference in bias behaviour of the two satellites has significant implications for multi-annual and long-term studies using their data.

Modeling and Simulation of Impact Point Prediction Algorithm

2013 ◽  
Vol 347-350 ◽  
pp. 438-442 ◽  
Author(s):  
Zai Ke Tian ◽  
Suo Chang Yang ◽  
De Long Feng ◽  
Yun Zhi Yao
Keyword(s):  
Perturbation Theory ◽  
Degrees Of Freedom ◽  
Prediction Algorithm ◽  
Impact Point ◽  
Guidance Law ◽  
Trajectory Simulation ◽  
Correction Scheme ◽  
Trajectory Correction ◽  
6 Degrees Of Freedom ◽  
The Impact

Trajectory correction projectiles significantly improved shooting accuracy of conventional ammunition.This paper designed an impact point prediction algorithm based on perturbation theory, and proposed trajectory correction scheme based on the impact point prediction algorithm. Based on perturbation theory, getting samples by solving ideal trajectory and typical disturbed trajectory, and solving the coefficients of the prediction model by regression.The 6-degrees of freedom trajectory simulation shows that adopting this correction guidance law, the standard error of the longitudinal falling points of projectiles reduced significantly.

scholarly journals Stability of temperatures from TIMED/SABER v1.07 (2002–2009) and Aura/MLS v2.2 (2004–2009) compared with OH(6-2) temperatures observed at Davis Station, Antarctica

2010 ◽  
Vol 10 (23) ◽  
pp. 11439-11446 ◽  
Author(s):  
W. J. R. French ◽  
F. J. Mulligan
Keyword(s):  
Cold Bias ◽  
Spatial And Temporal Scales ◽  
Ground Station ◽  
Volume Emission ◽  
The Difference ◽  
Miss Distance ◽  
Hydroxyl Layer ◽  
The Impact ◽  
Long Term Studies

Abstract. Temperature profiles from two satellite instruments – TIMED/SABER and Aura/MLS – have been used to calculate hydroxyl-layer equivalent temperatures for comparison with values measured from OH(6-2) emission lines observed by a ground-based spectrometer located at Davis Station, Antarctica (68° S, 78° E). The profile selection criteria – miss-distance <500 km from the ground station and solar zenith angles >97° – yielded a total of 2359 SABER profiles over 8 years (2002–2009) and 7407 MLS profiles over 5.5 years (2004–2009). The availability of simultaneous OH volume emission rate (VER) profiles from the SABER (OH-B channel) enabled an assessment of the impact of several different weighting functions in the calculation of OH-equivalent temperatures. The maximum difference between all derived hydroxyl layer equivalent temperatures was less than 3 K. Restricting the miss-distance and miss-time criteria showed little effect on the bias, suggesting that the OH layer is relatively uniform over the spatial and temporal scales considered. However, a significant trend was found in the bias between SABER and Davis OH of ~0.7 K/year over the 8-year period with SABER becoming warmer compared with the Davis OH temperatures. In contrast, Aura/MLS exhibited a cold bias of 9.9 ± 0.4 K compared with Davis OH, but importantly, the bias remained constant over the 2004–2009 year period examined. The difference in bias behaviour of the two satellites has significant implications for multi-annual and long-term studies using their data.

Development and Validation of Generic Maneuvering Flight Noise Abatement Guidance for Helicopters

2021 ◽  
Author(s):  
James H. Stephenson ◽  
Michael E. Watts ◽  
Eric Greenwood ◽  
Kyle A. Pascioni
Keyword(s):  
Flight Test ◽  
Vortex Interaction ◽  
Noise Abatement ◽  
Maneuvering Flight ◽  
Blade Vortex Interaction ◽  
The Difference ◽  
Band Limited ◽  
Miss Distance ◽  
Development And Validation ◽  
Peak Value

An extensive flight-test campaign has been conducted to look into developing actionable advice for pilots of today's vehicles to reduce their acoustic footprints. Ten distinct vehicles were tested at three different test ranges, with nine of the vehicles' data being documented here. Twelve pairs of turning conditions were tested to determine their effect on blade–vortex interaction noise. Each turning flight condition was evaluated using the peak A-weighted, band-limited (50–2500 Hz), sound pressure level measured throughout the maneuver. This metric was a surrogate for blade–vortex interaction (BVI) noise, and the difference between the peak values of each turning pair was investigated. That peak value difference was subsequently corrected by the offset from the intended vehicle altitude at turn initiation from the actual altitude at initiation. The corrected amplitudes were investigated and grouped into six validated actionable guidance principles that can be given to pilots to immediately reduce their acoustic footprint during operations. This generic guidance works by keeping the rotor well away from the wake throughout the maneuver, thus increasing miss distance and reducing the occurrence of objectionable BVI noise.

The Impact of Vertical Deflection on the Ballistic Missiles for Direction and Positioning

2014 ◽  
Vol 568-570 ◽  
pp. 938-943 ◽  
Author(s):  
Jian Qiang Wang ◽  
Hua Ling Wu
Keyword(s):  
Long Range ◽  
Target Point ◽  
Impact Point ◽  
Vertical Deflection ◽  
Point Position ◽  
Simulation Based ◽  
Ballistic Missiles ◽  
The Impact

The direction and positioning of the missile could be affected by the vertical deflection which is at the launch point, so the impact point errors will increase. Based on the launch coordination, the target point position deviation formula which is caused by vertical deflection is deduced in this paper. The correction precise of the vertical deflection is also a factor of the impact point error. The simulation based on the deviation formula is conducted to analyze the affection of the vertical deflection and the correction precise of the vertical deflection. And the results show that the vertical deflection can lead to 1km error for the long range missile. In addition, if the precision of vertical deflection were improved , the impact point errors will be reduced 85m.

scholarly journals Stochastic Model Predictive Control for Guided Projectiles Under Impact Area Constraints

2014 ◽  
Vol 137 (3) ◽  
Author(s):  
Jonathan Rogers
Keyword(s):  
Stochastic Model ◽  
Uncertainty Propagation ◽  
Uncertainty Modeling ◽  
Guidance System ◽  
Guidance Law ◽  
Impact Area ◽  
Deterministic Control ◽  
Miss Distance ◽  
The Impact ◽  
Stochastic Model Predictive Control

The dynamics of guided projectile systems are inherently stochastic in nature. While deterministic control algorithms such as impact point prediction (IPP) may prove effective in many scenarios, the probability of impacting obstacles and constrained areas within an impact zone cannot be accounted for without accurate uncertainty modeling. A stochastic model predictive guidance algorithm is developed, which incorporates nonlinear uncertainty propagation to predict the impact probability density in real-time. Once the impact distribution is characterized, the guidance system aim point is computed as the solution to an optimization problem. The result is a guidance law that can achieve minimum miss distance while avoiding impact area constraints. Furthermore, the acceptable risk of obstacle impact can be quantified and tuned online. Example trajectories and Monte Carlo simulations demonstrate the effectiveness of the proposed stochastic control formulation in comparison to deterministic guidance schemes.

Guidance law to control impact angle and time based on optimality of error dynamics

2018 ◽  
Vol 233 (10) ◽  
pp. 3577-3588 ◽  
Author(s):  
Bin Li ◽  
Defu Lin ◽  
Jiang Wang ◽  
Song Tian
Keyword(s):  
Impact Angle ◽  
Error Feedback ◽  
Time Error ◽  
Optimal Error ◽  
Impact Time ◽  
Guidance Law ◽  
The Difference ◽  
Error Dynamics ◽  
Miss Distance ◽  
Impact Angle Constraint

In this work, a new guidance law with a meaningful performance index is designed to satisfy terminal impact angle and impact time constraints based on optimal error dynamics, which can be used for salvo attacks or cooperative missions of multi-missile. The analytical solution of the proposed guidance law is a combination of trajectory shaping guidance law and an additional impact time error feedback term that is proportional to the difference between the desired and the true impact times. Trajectory shaping guidance law aims to achieve the desired terminal impact angle and zero miss distance, whereas the extra term aims to meet the desired impact time. The minimum and maximum feasible impact times that consider the seeker's field-of-view limit, terminal impact angle constraint, and missile's maneuvering acceleration limit are calculated to provide the feasible boundary range of the desired impact time. Numerical simulations of several engagement situations demonstrate the effectiveness of the proposed guidance law in the accuracy of terminal impact angle and impact time.

scholarly journals Midcourse Guidance Law Based on High Target Acquisition Probability Considering Angular Constraint and Line-of-Sight Angle Rate Control

2016 ◽  
Vol 2016 ◽  
pp. 1-20 ◽  
Author(s):  
Xiao Liu ◽  
Shengjing Tang ◽  
Jie Guo ◽  
Yuhang Yun ◽  
Zhe Chen
Keyword(s):  
Rate Control ◽  
Line Of Sight ◽  
Distance Restraint ◽  
Random Disturbance ◽  
Target Acquisition ◽  
Proportional Navigation ◽  
Long Distance ◽  
Guidance Law ◽  
Midcourse Guidance ◽  
The Impact

Random disturbance factors would lead to the variation of target acquisition point during the long distance flight. To acquire a high target acquisition probability and improve the impact precision, missiles should be guided to an appropriate target acquisition position with certain attitude angles and line-of-sight (LOS) angle rate. This paper has presented a new midcourse guidance law considering the influences of random disturbances, detection distance restraint, and target acquisition probability with Monte Carlo simulation. Detailed analyses of the impact points on the ground and the random distribution of the target acquisition position in the 3D space are given to get the appropriate attitude angles and the end position for the midcourse guidance. Then, a new formulation biased proportional navigation (BPN) guidance law with angular constraint and LOS angle rate control has been derived to ensure the tracking ability when attacking the maneuvering target. Numerical simulations demonstrates that, compared with the proportional navigation guidance (PNG) law and the near-optimal spatial midcourse guidance (NSMG) law, BPN guidance law demonstrates satisfactory performances and can meet both the midcourse terminal angular constraint and the LOS angle rate requirement.

Optimal Guidance Law Design for Reentry Vehicles with Terminal Velocity and Angle Constraints

2012 ◽  
Vol 459 ◽  
pp. 505-509 ◽  
Author(s):  
Dao Cheng Xie ◽  
Zhong Wei Wang
Keyword(s):  
Attitude Control ◽  
Angle Of Attack ◽  
Terminal Velocity ◽  
Target Point ◽  
Impact Point ◽  
Sideslip Angle ◽  
Reentry Vehicle ◽  
Guidance Law ◽  
Optimal Guidance ◽  
Lateral Plane

To achieve better impact effect, impact point error is of first importance, terminal velocity and angle of reentry vehicle are also needed to satisfy the expected value. This paper investigates the optimal guidance law for reentry vehicle. Guidance equation is expressed in longitudinal and lateral plane respectively, needed guidance command of angle of attack and sideslip angle is generated. Guidance command of angle of attack and sideslip angle is appended when considering reentry velocity. Synthesized guidance command is the sum of needed guidance command and appended guidance command. Effect of attitude control for reentry vehicle is analyzed using optimal guidance; the attitude of vehicle is stable and is guided to target point precisely. Trendline of landing error, reentry velocity and terminal angle varying with reentry time are analyzed, simulation results show that optimal guidance law is proper and satisfies the demand of impact point error, terminal velocity and angle.

Neural-Network Midcourse Guidance with Consideration of the Head-on Attack Condition

2005 ◽  
Vol 277-279 ◽  
pp. 857-864
Author(s):  
Eun-Jung Song ◽  
Miok Joh ◽  
Gwang Rae Cho
Keyword(s):  
Neural Network ◽  
Coordinate Transformation ◽  
Dimensional Space ◽  
Three Dimensional ◽  
Impact Angle ◽  
Training Data ◽  
Guidance Law ◽  
The Neural Network ◽  
Midcourse Guidance ◽  
The Impact

The objective of this study is to enhance neural-network guidance to consider the impact condition. Missile impact angle error, a measure of the degree to which the missile is not steering for a head-on attack, can have a significant influence on the final miss distance. Midcourse guidance using neural networks is employed to reduce the deviation angle from head-on effectively in the three-dimensional space. In addition, a coordinate transformation is introduced to simplify the three-dimensional guidance law and reduce training data for the neural network. Computational results show that the current neural-network guidance law with the coordinate transformation can be used to reduce the impact angle errors.

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