Abstract: Deployment apparatus for use in deploying an articulating structure. The deployment apparatus includes two pivotally connected hinge members and a spring that biases the hinge members in their open or deployed positions. An attenuator is also connected to one of the hinge members that prevents oscillatory movement between the hinge members as they are assuming their deployed positions and a cam member and a lobe on one of the hinge members lock the hinge members in position together as the hinge members are being extended to their deployed positions. The attenuator is adjustable and can be used to precisely fix the position of the deployed hinge members. The deployment apparatus is particularly suited for a wide variety of spacecraft applications where it can be used to extend spacecraft structures such as solar panels.