The two‐body interception problem with an upper‐bounded tangent impulse for the interceptor on an elliptic parking orbit to collide with a nonmaneuvering target on a hyperbolic orbit is studied. Firstly, four special initial true anomalies whose velocity vectors are parallel to either of the lines of asymptotes for the target hyperbolic orbit are obtained by using Newton‐Raphson method. For different impulse points, the solution‐existence ranges of the target true anomaly for any conic transfer are discussed in detail. Then, the time‐of‐flight equation is solved by the secant method for a single‐variable piecewise function about the target true anomaly. Considering the sphere of influence of the Earth and the upper bound on the fuel, all feasible solutions are obtained for different impulse points. Finally, a numerical example is provided to apply the proposed technique for all feasible solutions and the global minimum‐time solution with initial coasting time.