38 results about "Space rendezvous" patented technology

The invention relates to a space rendezvous docking assembly which comprises an anode assembly and a cathode assembly. The anode assembly is installed on a served spacecraft, the cathode assembly is installed on a serving spacecraft, the anode assembly is inserted into the cathode assembly and is locked by the cathode assembly, the safe and reliable rendezvous docking between the served spacecraft and the serving spacecraft is achieved, and thus different in-obit service tasks are completed.

The invention provides a multi-medium complex-environment high-precision vision / inertia combination navigation method which is suitable for combination navigation of an underwater vehicle under a complex electromagnetic environment in a transparent medium. By means of the underwater vehicle for simulating rendezvous and docking of a spaceship and a satellite in a space micro-gravity environment, important test data and test verification are provided for the rendezvous and docking. The whole experiment system is used on ground. By means of buoyancy of water and adjustment of the direction of the ground electromagnetic field and the intensity of the electromagnetic field, the underwater vehicle is in a neutral buoyancy level, thereby satisfying an equivalent test condition of coincidence of space and ground. The multi-medium complex-environment high-precision vision / inertia combination navigation method can be used for controlling the underwater vehicle for simulating rendezvous and docking in space, so that the attitude, the speed, the position and the acceleration information of the underwater vehicle can be measured accurately.

The invention discloses a balance point Halo orbit phasing orbit transfer method taking the time constraint into consideration, relates to a Halo orbit phasing orbit transfer method based on an earth-moon three-body dynamic model and belongs to the technical field of aerospace. According to the method, a dynamic equation is established under a restrictive three-body model formed by the earth, the moon and the star, and a Halo orbit near the point L2 is generated under an earth-moon rotation system; the Halo orbit initial phase position of a detector and the phase position difference needing to be changed are determined, and the optimal fuel phasing orbit meeting the phase position constraint condition and the transfer time constraint condition is obtained through an optimization algorithm with the initial anchoring time and transfer time as optimization variables; and the time difference delta t, the task Halo orbit or the upper limit tmax of the transfer time are adjusted according to the task which the detector needs to fulfill, and the orbit shadow detection avoiding task or the spatial intersection detection task of the detector on the Halo orbit is fulfilled. The method can obtain the optimal fuel phasing orbit meeting the phase position constraint condition and the transfer time constraint condition, and has the advantages of good convergence, high flexibility and the like.

The invention discloses a space intersection control method of two-stage constant thrust, which is used for solving the technical problem that the engine is opened and closed frequently during the intersection process when the prior intersection control method of constant thrust is achieved. The technical solution is that the minimum opening-closing time Tmin constraint of the engine is introduced to the intersection control problem of the two-stage constant thrust engine; and the optimal intersection thrust under quadratic optimization function index is designed by rolling forecast principle. Because of considering the minimum opening-closing time constraint of the engine, the problem that the engine is opened and closed frequently is solved and the design difficulty of the engine is reduced; and the optimal design method has good robustness for design model error, measurement error and intersection thrust error.

The invention provides a space rendezvous system gain scheduling control method with linearization errors taken into consideration, and relates to a spacecraft orbit rendezvous gain scheduling control method. The space rendezvous system gain scheduling control method solves the problem that due to the fact that according to an existing aircraft orbit rendezvous control method, input saturation and parameter uncertainty caused by the linearization errors are ignored, time consumption is high when an aircraft orbit rendezvous task is completed. According to the space rendezvous system gain scheduling control method, the parameter uncertainty caused by the linearization errors is taken into consideration and endowed with exact meanings, an aircraft orbit rendezvous relative movement model is established, a gain scheduling controller of an aircraft orbit rendezvous is then designed, the aircraft orbit rendezvous is controlled through the gain scheduling controller, and the rendezvous task is completed. The space rendezvous system gain scheduling control method is mainly used for controlling the aircraft orbit rendezvous.