SINS/BDS tightly coupled integrated navigation algorithm for hypersonic vehicle.

Area of Science:

• Aerospace Engineering
• Navigation Systems
• Hypersonic Flight Dynamics

Background:

• Hypersonic vehicles require robust navigation systems, especially when satellite signals like BeiDou (BDS) are unreliable or jammed.
• Existing navigation systems may struggle with the extreme dynamics and environmental conditions of hypersonic flight.

Purpose of the Study:

• To propose and validate a tightly coupled integrated navigation system (TCINS) for hypersonic vehicles.
• To ensure accurate attitude, velocity, and position estimation during satellite signal disturbances.
• To evaluate system performance through field tests and hardware-in-the-loop (HWIL) simulations.

Main Methods:

• Architecture design integrating fiber SINS, BDS, and a missile-born computer (SOPC).
• Development of SINS mechanization using the J2 model for near-space gravity.
• Algorithm design for updating attitude, velocity, and position, including state/measurement equations.
• Implementation of a satellite data validity scheme.

Main Results:

• Heading angle error within 0.2°.
• Pitch and roll angle errors within 0.05°.
• Maximum velocity error of 0.3 m/s.
• Maximum position error of 10 m.

Conclusions:

• The proposed TCINS demonstrates high accuracy and robustness for hypersonic vehicles.
• The system effectively mitigates issues arising from disturbed satellite navigation signals.
• Validation through field and HWIL tests confirms the system's practical applicability and performance.