Abstract: A parallel-in-time disturbance region update method for dynamic characteristics of flight vehicles includes reading-in the data; obtaining the components of Chebyshev transformation matrix; initializing the flow field; establishing a dynamic computational domain; solving the flow-governing equations of all time layers simultaneously in the dynamic computational domains; updating the dynamic computational domain; judging whether the parallel computation in the current time period converges and whether the computation completes; if so, outputting the results; if the computation converges but not completes, jumping to the step that initializing the flow field, and performing the computation in next time period; if not, jumping to the step that solving the flow-governing equations of all time layers simultaneously in the dynamic computational domains, and entering the next iterative step.

Abstract: A direct design method for generating an osculating curved waverider based on a complex leading edge, includes obtaining a leading edgeleading edge through determining a leading edge of a waverider according to a spread length, a front-to-rear length, and a sweep angle at each position of an aircraft, and arranging leading-edge discrete points on the leading edgeleading edge; drawing a small shock cone corresponding to each leading-edge discrete point by starting from each leading-edge discrete point, taking a local shock angle as a half cone angle and taking a free streamline direction as an axis; finding envelope surfaces of all small shock cones, namely, a shock curved surface corresponding to the leading edgeleading edge; generating a waverider by using the osculating curved waverider design method.

Abstract: A direct design method for generating an osculating curved waverider based on a complex leading edge, includes obtaining a leading edgeleading edge through determining a leading edge of a waverider according to a spread length, a front-to-rear length, and a sweep angle at each position of an aircraft, and arranging leading-edge discrete points on the leading edgeleading edge; drawing a small shock cone corresponding to each leading-edge discrete point by starting from each leading-edge discrete point, taking a local shock angle as a half cone angle and taking a free streamline direction as an axis; finding envelope surfaces of all small shock cones, namely, a shock curved surface corresponding to the leading edgeleading edge; generating a waverider by using the osculating curved waverider design method.

Abstract: An oblong-shaped rotor engine with improved high sealing performance includes an upper end cover, a lower end cover, a rotor, three combustion chambers, three isolation zones, a fuel spray ignition unit, a sealing pin row and an eccentric driving shaft, a sealing pin row, which seals the transition zone between different combustion cylinders, wherein the engine according to this invention can better avoid the effect of structural wear, effectively enhance the sealing performance between combustion chambers and abate gas leakage between cylinders, wherein the designed profile and sealing means can enlarge the design error margin for engines, abate the processing difficulty of engines, and effectively decrease the production costs of engines.

Abstract: An oblong-shaped rotor engine with improved high sealing performance includes an upper end cover, a lower end cover, a rotor, three combustion chambers, three isolation zones, a fuel spray ignition unit, a sealing pin row and an eccentric driving shaft, a sealing pin row, which seals the transition zone between different combustion cylinders, wherein the engine according to this invention can better avoid the effect of structural wear, effectively enhance the sealing performance between combustion chambers and abate gas leakage between cylinders, wherein the designed profile and sealing means can enlarge the design error margin for engines, abate the processing difficulty of engines, and effectively decrease the production costs of engines.