35 results about "Rocket-based combined cycle" patented technology

The invention discloses structural design of an inlet isolation segment of a rocket-based-combined-cycle engine. Under the restraint that the minimal section of the inlet isolation segment is located in a throat segment, the sectional area of an effective circulation area of the isolation segment is improved, so that the sectional area of the inlet throat segment is increased to be equal to the sectional area of an intake of a combustion chamber, effective circulation area equal-sectional-area circulation is achieved on an inlet rocket supporting plate segment, and an equal straight segment behind the inlet rocket supporting plate segment is improved into a contraction segment so as to be matched with the section of the intake of the combustion chamber. It is ensured that the minimal section area of the inlet isolation segment is located in the throat segment. By means of the inlet isolation segment, the start mach number of an inlet is lowered, and the flow coefficients of the inlet in an injection mode and a ramjet mode and other performance parameters are increased. The design of the inlet isolation segment of the rocket-based-combined-cycle engine is high in development performance, the inlet isolation segment is designed according to different sectional sizes of the intake of the combustion chamber, the work range of the inlet can be effectively expanded, and the overall performance of the engine can be improved.

The invention discloses a variable-structure exhaust nozzle of a rocket based combined cycle engine. An inner flow field of the exhaust nozzle is in an overexpansion state under an injection modality, the inner flow field of the exhaust nozzle is in an under-expansion state under an under-combustion / super-combustion state, an upper cover plate is driven by a motor, and suction slotted holes in a rear body of an aircraft is made to be in an opened or closed state. The suction slotted holes in the upper wall face of the a spray pipe are opened when the engine works at a non-design point, the suction slotted holes in the wall face of the spray pipe are closed when the engine works at a design point, the work performance of the spray pipe under the injection modality is improved, and meanwhile it is guaranteed that the work performance of the spray pipe under the under-combustion / super-combustion modality is not reduced. The variable-structure exhaust nozzle is strong in expandability, and the suction slotted holes with different section areas can be designed according to the actual geometric structures, the work envelope curve and the work performance needs of the exhaust nozzle. The suction slotted holes are distributed according to the actual structural size of the exhaust nozzle, and the work performance of the exhaust nozzle under the non-design point is improved.

The invention discloses a variable structure combustion chamber of a rocket-based-combined-cycle engine. The variable structure combustion chamber is composed of a drive system, a back pressure cavity and a combustion chamber body. The drive system is located at the upper portion of the back pressure cavity. The back pressure cavity is fixed to the portion above variable sections of the combustion chamber body and forms an integral structure with the combustion chamber body. A combustion chamber fixed section is sequentially connected with variable sections of the combustion chamber body. The variable sections are connected through cooperation of ball head hinge convex faces and ball head hinge concave faces. Two sets of hydraulic drive mechanisms drive the first variable section and the third variable section of the combustion chamber body through drive rods and connecting rods. Axial sealing grooves of the variable sections are filled with graphite strips so as to isolate high-temperature fuel gas in the combustion chamber body, and sealing is guaranteed. According to the variable structure combustion chamber, stable transition among different modes is achieved through grade adjustment. In the injection mode and the subsonic combustion mode, the variable sections of the combustion chamber body are adjusted by a hydraulic drive mechanism to generate different divergence angles and throat heights, so that the combustion chamber body is in the optimal work state, and the thrusting force and specific impulse performance of the combustion chamber body are obviously improved.

The invention discloses a rocket-based combined cycle ejector mode performance test engine. A main rocket combustor is fixed in the front of a secondary combustor; intake ducts are mounted above and below the main rocket combustor respectively; intake ends of the intake ducts are fixed in the rear of the main rocket combustor through support lugs; the rear ends of the intake ducts are connected with the secondary combustor through an intake duct flange and a second combustor flange; the secondary combustor is in a divergent straight structure; the main rocket combustor is fitly connected with the secondary combustor; a flue of a nozzle divergent segment gradually changes from round to square. The main rocket combustor is charged through the combination of seven-pointed star shape and inner holes by close-to-wall pouring; after ignition, the flow of gas in a main rocket is kept basically unchanged; variation pattern of the rocket-based combined cycle ejector mode performance along with flight Mach number and height is verified; the basis is provided for passage design. The rocket-based combined cycle ejector mode performance test engine is simple in structure and convenient to maintain, and the influence of gas composition upon engine performance and trajectory climb can be extensively researched.