scholarly journals Aeroload Simulation of Interceptor Missile using Fin Load Simulator

2021 ◽  
Vol 71 (1) ◽  
pp. 102-107
Author(s):  
M.V.K.S. Prasad ◽  
Patri Sreehari Rao ◽  
Jagannath Nayak
Keyword(s):  
Control Algorithm ◽  
Navigation Algorithm ◽  
Actuation System ◽  
Control Command ◽  
Load Simulator ◽  
The Difference ◽  
Miss Distance ◽  
Hardware In Loop ◽  
Hardware In Loop Simulation ◽  
Mission Objective

Interceptor missiles are designed to destroy enemy targets in air. Targets can be destroyed either in atmosphere or out of atmosphere. So for Air Defence scenario, a two layer protection system is required with one taking care of exo atmosphere and another endo atmosphere. In this Air Defence scenario, irrespective of target trajectory interceptor should neutralise it. So the control, guidance are to be designed and validated thoroughly with various scenarios of interceptor and target. These interceptors sense the rates from rate gyroscopes and accelerations from accelerometers which are fitted on board the interceptor. The navigation algorithm calculates the interceptor’s position and velocity from these rates and accelerations from time to time. Using these interceptor data and target information received from ground RADAR or on board seeker, guidance calculates accelerations demand and subsequently rate demand. The control algorithm runs in on board mission computer along with guidance. The control algorithm calculates the commanded rate and eventually commanded deflections to the control fins to move towards the target. The fins have to move as per commanded deflections to meet the mission objective of hitting the target. But the load known as aeroload which comes on the control fins during mission, causes control fins not to move as per command. Due to the difference between control command and physical movement of fin, the expected path towards target deviates. This increases the miss distance and also misses the target hit. This aeroload scenario is to be simulated on ground and some feature is to be designed to take care of it during mission. By studying the control system behaviour due to load, the control autopilot is to be automatically tuned to compensate for the loss in commanded deflections. This scenario can be carried out in Hardware-in-Loop simulation (HILS) setup. Mission load conditions can be applied on hardware actuation system in HILS setup and mission performance can be seen and also with different loads and different autopilot tunings.

scholarly journals Bridging GPS Outages for Fixed-wing Unmanned Aerial Vehicles

2014 ◽  
Vol 68 (2) ◽  
pp. 308-326 ◽  
Author(s):  
Wenjie Zhao ◽  
Zhou Fang ◽  
Ping Li
Keyword(s):  
Unmanned Aerial Vehicles ◽  
Navigation System ◽  
Force Model ◽  
Gravity Vector ◽  
Integrated Navigation ◽  
Integrated Navigation System ◽  
Navigation Algorithm ◽  
Aerial Vehicles ◽  
Hardware In Loop ◽  
Hardware In Loop Simulation

This paper reports on a new navigation algorithm for fixed-wing Unmanned Aerial Vehicles (UAVs) to bridge Global Position System (GPS) outages, based on a common navigation system configuration. The ground velocity is obtained from wind-compensated airspeed, and a centripetal force model is introduced to estimate the motion acceleration. Compensated by this acceleration, the gravity vector can be extracted from the accelerometer measurement. Finally, fusing the information of the ground velocity, magnetic heading, barometric height, and gravity vector, the Integrated Navigation System (INS) is reconstructed, and an Extended Kalman Filter (EKF) is used to estimate INS errors. Hardware-in-loop simulation results show that compared with INS-only solutions, the proposed method effectively resists long-term drift of INS errors and significantly improves the accuracy for dynamic navigation during GPS outages.

scholarly journals Research of Impact Load in Large Electrohydraulic Load Simulator

2014 ◽  
Vol 2014 ◽  
pp. 1-7 ◽  
Author(s):  
Yongguang Liu ◽  
Xiaohui Gao ◽  
Zhongcai Pei
Keyword(s):  
Impact Load ◽  
Experimental Result ◽  
Actual System ◽  
Good Experimental Condition ◽  
Load Simulator ◽  
Electric Cylinder ◽  
Hardware In Loop ◽  
Hardware In Loop Simulation ◽  
The Impact ◽  
The Mathematical Model

The stronger impact load will appear in the initial phase when the large electric cylinder is tested in the hardware-in-loop simulation. In this paper, the mathematical model is built based on AMESim, and then the reason of the impact load is investigated through analyzing the changing tendency of parameters in the simulation results. The inhibition methods of impact load are presented according to the structural invariability principle and applied to the actual system. The final experimental result indicates that the impact load is inhibited, which provides a good experimental condition for the electric cylinder and promotes the study of large load simulator.

Objective Evaluation of ESP System Based on Hardware-in-Loop Test Bench

2013 ◽  
Vol 694-697 ◽  
pp. 2080-2084
Author(s):  
Sheng Yi Xuan ◽  
Chuan Xue Song ◽  
Guang Wei Meng
Keyword(s):  
Control Algorithm ◽  
Evaluation Method ◽  
Test Bench ◽  
Objective Evaluation ◽  
Control Effect ◽  
Simulation Test ◽  
Pd Control ◽  
Time Test ◽  
Hardware In Loop ◽  
Hardware In Loop Simulation

The evaluation tests play an important role in modern vehicle development. As a mean of judging vehicles performance and quality in the design period, the evaluation tests guide the development and the design. In this paper, objective evaluation of ESP is researched based on the self-correcting threshold PD control algorithm and ESP hardware-in-loop simulation test bench. Real-time test bench is used to simulate the different conditions and the evaluation methods of ESP are tested to verify the effect. By hardware-in-loop simulation, the results demonstrate the objective evaluation method evaluates the ESP system in accordance with the results of self-correcting threshold PD control algorithm and the method could accurately reflect the ESP control effect.

The Analysis and Research of Electric Dynamic Load Simulator

2012 ◽  
Vol 229-231 ◽  
pp. 849-852 ◽  
Author(s):  
Xia Liu ◽  
Rui Feng Yang ◽  
Jian Fang Jia
Keyword(s):  
Dynamic Load ◽  
Physical Modeling ◽  
Coupled System ◽  
Typical Application ◽  
Torque Load ◽  
Load Simulator ◽  
Hardware In Loop ◽  
Hardware In Loop Simulation ◽  
The Mathematical Model ◽  
Aerodynamic Torque

The aero load simulator is a typical application of electric dynamic load simulator in the engineering. It is important half hardware-in-loop simulation equipment, which is often used to simulate the aerodynamic torque load on the missile rudder or elevon actuators in the flight. The mathematical model of the electric dynamic load simulator is built using the physical modeling method. The influence of the rudder performance on the model was considered, and modeled it as the disturbance channel in the model. The electric dynamic load simulator is a typical coupled system. Under the different simplification, the validity of the model is verified by the actual experiment.

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