Simulation Modeling of Strapdown Inertial Navigation Systems Functioning as a Means to Ensure Cybersecurity of Unmanned Aerial Vehicles Navigation Systems for Dynamic Objects in Various Correction Modes*

Inertial navigation systems (INS) are widely used for controlling piloted or unmanned aerial vehicles (UAV). Automatic control equipment with INS has error budget making a huge impact on the accuracy of UAV navigation. The paper analyzes INS errors and types of errors. Experiments have been done using small UAV. Santrauka Inerciniai navigacijos įrenginiai (INS) plačiai naudojami pilotuojamuose ir nepilotuojamuose orlaiviuose. Nepilotuojamo orlaivio skrydžio tikslumui didelę įtaką turi orlaivio automatinio valdymo sistemos įrenginių paklaidos. Tyrime nagrinėjamas nepilotuojamas orlaivis, kurio automatinio valdymo sistemos dalis yra inercinis navigacijos įrenginys. Analizuojami INS įrenginių paklaidų šaltiniai, paklaidų tipai. Eksperimentiniai tyrimai atlikti naudojant mažo nepilotuojamo orlaivio automatinio valdymo sistemą.

Download Full-text

Optimizing Strap-down Inertial Navigation Systems Characteristics and External Correction Sensors for Autonomous Navigation of Different UAV Classes

Radio Engineering ◽

10.36027/rdeng.0320.0000166 ◽

2020 ◽

pp. 1-19

Author(s):

E. I. Starovoytov

Keyword(s):

Unmanned Aerial Vehicles ◽

Autonomous Navigation ◽

Inertial Navigation ◽

Sensor Data ◽

Navigation Systems ◽

Inertial Navigation Systems ◽

Aerial Vehicles ◽

Atmospheric Path ◽

Payload Mass ◽

Laser Gyroscopes

Currently, unmanned aerial vehicles (UAVs) can be used in topographic works, condition monitoring and diagnostics of extended engineering structures, delivering goods to hard-to-reach places, etc. To provide the widespread UAVs applications and raise the number of tasks to be solved through their using, it is necessary to increase their autonomy degree in terms of navigation support, in particular. Unmanned aerial vehicles (UAV) control systems for autonomous navigation use the strap-down inertial navigation systems (SINS) based on various types of gyroscopes. SINS based on the laser gyroscopes, which have a large mass, have the best accuracy. UAVs with a payload mass that is commensurable with the mass of navigation equipment require optimization of SINS characteristics. An optimization method has been developed to enable obtaining a Pareto set for the mass and accuracy of SINS based on laser gyroscopes. A comprehensive assessment of the characteristics of SINS and UAV carrier with different payload mass has been performed. Various SINS correction methods are considered when satellite navigation is unavailable.For overland flights, the correlation-extreme navigation systems (CENS) and SLAM methods (for simultaneous localisation and mapping) can be used. CENS require a reference lay-of-the-land description and a sufficient density of landmarks. In navigation based on SLAM algorithms, there is no need in the reference lay-of-the-land description, and the initial data can be obtained through the optical sensors under appropriate condition of the atmospheric path.Regardless of the condition of the atmospheric path, type of the underlying surface and its information available in detail, the UAV coordinates can be determined by Doppler dead reckoning using a Doppler system (DISS). At low and medium altitudes SINS correction is possible, only heading sensor data are needed to calculate the path angle.In combining with DISS and 3D Flash Ladar sensors (for implementing SLAM algorithms), it is more optimal to use low-accuracy SINS based on fibre-optic gyroscopes rather than laser gyro-based systems.The results obtained can be used when developing navigation systems for medium, light and heavy-medium UAVs.

Download Full-text