Normal acceleration response to canard control with wind for spin-stabilized projectiles

2020 ◽  
Vol 234 (9) ◽  
pp. 1473-1490
Author(s):  
Yu Wang ◽  
Jiyan Yu ◽  
Xiaoming Wang
Keyword(s):  
Deflection Angle ◽  
Coupling Effect ◽  
Low Cost ◽  
Translational Motion ◽  
Measurement Information ◽  
Control Input ◽  
Acceleration Response ◽  
Guidance And Control ◽  
And Control ◽  
Normal Acceleration

In this investigation, the normal acceleration response to the control inputs of spin-stabilized projectiles considering the atmospheric wind with the coupled effects of canard control, gravity, and aerodynamic forces, being an important reference for the guidance design of low-cost guided projectiles with less measurement information (only translational motion), is deduced and analyzed. Based on the approximate formulas predicting the angle of attack under canard control and considering the atmospheric wind obtained by a linear model of the pitch and yaw motion, estimated expressions for the normal acceleration response to canard control are deduced and analyzed. To analyze the cross-coupling between pitch and yaw and simplify the design of guidance and control, the acceleration response is divided into controllable and uncontrollable parts. The phase shift between the controllable acceleration response and the direction of the control input is defined to represent the coupling effect between the pitch and the yaw; this is found to be strongly dependent on the projectiles' state parameters rather than the control parameters. The results indicate that the acceleration and phase are dramatically altered under different control directions. This condition adversely affects guidance and control because uncontrollable directions arise when the deflection angle is smaller than the critical angle.

scholarly journals Design, Optimal Guidance and Control of a Low-cost Re-usable Electric Model Rocket

2021 ◽  
Author(s):  
Lukas Spannagl ◽  
Elias Hampp ◽  
Andrea Carron ◽  
Jerome Sieber ◽  
Carlo Alberto Pascucci ◽  
...  
Keyword(s):  
Low Cost ◽  
Electric Model ◽  
Guidance And Control ◽  
Optimal Guidance ◽  
And Control

Suboptimal Guidance and Control Design for a Missile with Onboard Strapdown Seeker

2011 ◽  
Vol 110-116 ◽  
pp. 2513-2520
Author(s):  
Netra Singh ◽  
Manoranjan Sinha
Keyword(s):  
Coupling Effect ◽  
Three Dimensional ◽  
Impact Angle ◽  
Terminal Phase ◽  
Dynamic Inversion ◽  
Control Laws ◽  
Guidance And Control ◽  
Guidance Law ◽  
Hamilton Jacobi Bellman ◽  
And Control

Dynamic inversion control in conjunction with nonlinear suboptimal three dimensional (3-D) guidance law, in terminal phase, is implemented in both the pitch and yaw plane for a short range surface to surface missile with onboard active strapdown seeker. The implemented guidance and control laws intercept the target with a minimum miss distance in addition to meeting the various constraints such as line of sight, seeker field-of-view (FOV), and impact angle. This is achieved using approximate solution to Hamilton-Jacobi-Bellman (HJB) equation [1]. Dynamic inversion control is implemented in two time scales for the inner loop body rate and outer loop angles. Various nonlinearities including that due to the coupling effect between pitch and yaw channels are accounted for in the six-degree-of-freedom (6-DOF) formulation.

scholarly journals Integrated Guidance and Control Method for the Interception of Maneuvering Hypersonic Vehicle Based on High Order Sliding Mode Approach

2015 ◽  
Vol 2015 ◽  
pp. 1-19 ◽  
Author(s):  
Kang Chen ◽  
Bin Fu ◽  
Yuening Ding ◽  
Jie Yan
Keyword(s):  
Fourth Order ◽  
Control Method ◽  
Sliding Mode ◽  
High Order ◽  
Control Input ◽  
Guidance And Control ◽  
Near Space ◽  
Sliding Manifold ◽  
Integrated Guidance And Control ◽  
And Control

This paper focuses on the integrated guidance and control (IGC) method applied in the interception of maneuvering near space hypersonic vehicles using the homogeneous high order sliding mode (HOSM) approach. The IGC model is derived by combining the target-missile relative motion and dynamic equations. Then, a fourth-order sliding mode controller is implemented in the augmented IGC model. To estimate the high order derivatives of the sliding manifold which is required in the HOSM method, an Arbitrary Order Robust Exact Differentiator is presented. At last, the idea of virtual control is introduced to alleviate the chattering of the control input without using any saturation functions which may lead to a loss of the robustness. And the stability of the closed-loop system with presented fourth-order homogeneous HOSM controller is also proved theoretically. Finally, simulation results are provided and analyzed to demonstrate the effectiveness of the proposed method in three typical engagement scenarios.

scholarly journals Adaptive Command Filtered Integrated Guidance and Control for Hypersonic Vehicle with Magnitude, Rate and Bandwidth Constraints

2018 ◽  
Vol 151 ◽  
pp. 05004
Author(s):  
Liang Wang ◽  
Weihua Zhang ◽  
Ke Peng ◽  
Donghui Wang
Keyword(s):  
Sliding Mode ◽  
Integrated Design ◽  
Hypersonic Vehicle ◽  
Convergence Time ◽  
Control Surface ◽  
Control Input ◽  
Guidance And Control ◽  
Surface Deflection ◽  
Integrated Guidance And Control ◽  
And Control

This paper proposes a novel integrated guidance and control (IGC) method for hypersonic vehicle in terminal phase. Firstly, the system model is developed with a second order actuator dynamics. Then the back-stepping controller is designed hierarchically with command filters, where the first order command filters are implemented to construct the virtual control input with ideal states predicted by an adaptive estimator, and the nonlinear command filter is designed to produce magnitude, rate and bandwidth limited control surface deflection finally tracked by a terminal sliding mode controller with finite convergence time. Through a series of 6-DOF numerical simulations, it’s indicated that the proposed method successfully cancels out the large aerodynamics coefficient uncertainties and disturbances in hypersonic flight under limited control surface deflection. The contribution of this paper lies in the application and determination of nonlinear integrated design of guidance and control system for hypersonic vehicle.

Algorithms of Measurement System for a Micro UAV

2013 ◽  
Vol 198 ◽  
pp. 165-170 ◽  
Author(s):  
Grzegorz Kopecki ◽  
Andrzej Tomczyk ◽  
Paweł Rzucidło
Keyword(s):  
Measurement System ◽  
Navigation System ◽  
Measurement Errors ◽  
System Development ◽  
Low Cost ◽  
Measurement Information ◽  
Gps Data ◽  
Differential Gps ◽  
Measurement Units ◽  
And Control

The article presents a measurement system for a micro UAV designed at the Department of Avionics and Control Systems of Rzeszów University of Technology. Since the project is based on earlier projects, e.g.[[[[1[[[1, the introduction begins with their short presentation [they are mentioned in the introduction firs. Then, the current project is discussed. The major objective of the project is to create a miniature autopilot cooperating with navigation units, data transmission units and measurement units. The system is based on Polish technological solutions. The autopilot is designed as a single unit, however the system is open and it allows you to use different elements. The system development is also possible. In-flight testing will be realized with the use of two unmanned flying platforms equipped with an electrical engine and a piston engine. The total mass of the platforms is 5 kg and 25 kg respectively. The article presents the structure of the control and navigation system and then, the structure of the measurement system. The measurement units consist of a GPS receiver, an attitude and heading reference system (AHRS) and an air data computer (ADC). Similar configuration is used in other micro UAV solutions, such as Micropilot or Kestrel. Then, algorithms of the measurement system are described. Navigation is based on GPS data with a DGPS (Differential GPS) advanced module. If the measurement information is complete, GPS data are used to correct measurements from other units. The system estimates wind disturbances and calculates accelerometers errors. In the case of missing GPS signals implementation of low-cost sensors may lead to significant measurement errors, and hence navigation only by means of the INS is impossible. In such a case, navigation is realized with the use of an inertial navigation system (INS), the magnetic heading measurement and ADC. AHRS unit algorithms use quaternion algebra for attitude calculation. For correction, complementary filtering is implemented [, [. The correction signal for the attitude (pitch and roll angles) is calculated with the use of acceleration measurements. Measurements of accelerations and yaw rates are used for the correction switching mechanism, since in dynamic states signals calculated from accelerations cannot be used for correction. Heading is corrected by means of magnetic heading measurement. ADC algorithms are based on typical aerodynamic dependences.

Research on Missile System with Strapdown Guidance Technology

2013 ◽  
Vol 785-786 ◽  
pp. 1560-1563
Author(s):  
De Long Feng ◽  
Suo Chang Yang ◽  
Ying Xi Liu
Keyword(s):  
Inertial Measurement Unit ◽  
Simulation Experiment ◽  
Low Cost ◽  
Guidance System ◽  
Measurement Unit ◽  
Missile Guidance ◽  
Inertial Measurement ◽  
Guidance And Control ◽  
And Control ◽  
Missile System

This paper presents a project of missile guidance system based on the strapdown guidance technology. The project is composed of strapdown seeker and inertial measurement unit. The integrated guidance and control technology have been adopted. The project raise accuracy of missiles on the premise that the low cost should be guaranteed. According to simulation experiment, this paper proves the feasiblity of the scheme, and it has good ballistic missile.

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