This paper presents a novel autonomous inertial relative navigation technique with a sight-line-stabilized integrated sensor system for midrange (20-1 km) spacecraft rendezvous. A continuous-discrete six-state extended Kalman filter is developed for this purpose. The integrated sensor suite onboard an active chaser satellite comprises an imaging sensor, a coboresighted laser range finder, the space-integrated Global Positioning System/inertial navigation system, and a star tracker. For high accuracy of the relative navigation, the Kalman filter state vector consists of the inertial position and velocity of the client satellite governed by a high-fidelity nonlinear orbital dynamics model. The error covariance matrix is formulated in terms of the estimation error in the relative position and velocity of the client satellite, consistent with the sensor measurements. Inertial attitude pointing and rate commands for tracking the client satellite are determined using the estimates of the client's inertial relative position and velocity. To estimate the inertial attitude of the chaser satellite outside the space-integrated Global Positioning System/inertial navigation system, a new three-axis steady-state analytical attitude estimator is developed that blends the gyro-and the star-tracker-measured attitudes. The simulation results of a midrange spacecraft rendezvous using glideslope guidance validate this new six-state autonomous inertial relative navigation technique. The simulation results show that the imaging sensor's sight line can be stabilized at the client satellite in midrange accurately enough to enable the laser range finder to measure the range occasionally, but these measurements are not necessary for the midrange rendezvous phase, because the extended Kalman filter can estimate the range with the angle measurements of the imaging sensor.