Knocking vector propulsion scheme based on multi-unit combination
By adopting a multi-unit combination in the knock engine, the working state of the unit body is adjusted to obtain additional control torque, which solves the problem of traditional vector nozzles affecting the performance of the engine and realizes the vector propulsion effect in the knock engine.
Patent Information
- Application Number
- CN202510524336.6
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-04-24
- Publication Date
- 2025-06-13
AI Technical Summary
In traditional aerospace engines, vector nozzles have complex problems affecting engine performance and control strategies, and there is a lack of effective vector propulsion schemes in pulsed knock engines and rotary knock engines.
By adopting a combination of multiple units in the pulsed knock engine and the rotary knock engine, the multiple units are arranged in an axial or central symmetrical manner, and by closing or adjusting the working state of individual units, additional control torque is obtained to achieve vector propulsion.
Without introducing vector nozzles, the vector propulsion function of the engine is realized, avoiding the performance impact and control complexity brought by vector nozzles, and improving space utilization and maneuverability.
Smart Images
Figure CN120140061A_ABST
Abstract
Description
Technical Field
[0001] The present invention relates to the fields of detonation propulsion and vector propulsion, and specifically to a detonation vector propulsion scheme based on the combination of multiple unit bodies. Background Art
[0002] A detonation engine is a new type of engine that uses detonation combustion to generate thrust, including different forms such as pulse detonation engines and rotating detonation engines. Detonation combustion has potential advantages such as fast heat release, small entropy increase, and high thermal cycle efficiency, and has become one of the research hotspots in the field of aerospace power.
[0003] As an indispensable key technology for advanced aircraft, the core principle of vector propulsion is to use additional control torques to adjust the attitude of the aircraft, which helps to reduce the takeoff and landing roll distance and improve maneuverability and flexibility.
[0004] Traditional aerospace engines usually generate vector thrust by installing vector nozzles, but vector nozzles have disadvantages such as affecting engine performance and complex control strategies. For pulse detonation engines and rotating detonation engines, both have the advantages of simple structure and flexible design, which are convenient for integrating into a power device with vector propulsion function by means of the combination of multiple unit bodies, and obtaining the overall vector propulsion effect by regulating the working state of individual unit bodies. Therefore, the present invention proposes a detonation vector propulsion scheme based on the combination of multiple unit bodies, enabling the detonation engine to have vector propulsion function without introducing vector nozzles, avoiding the negative impacts caused by installing vector nozzles, improving space utilization rate, and having important significance for the practical application of detonation engines. Summary of the Invention
[0005] Technical Problems to be Solved
[0006] Aiming at the problems that the vector nozzle, as a traditional vector propulsion device of the engine, affects engine performance and has complex control strategies, the present invention proposes a detonation vector propulsion scheme based on the combination of multiple unit bodies, and obtains the overall vector propulsion effect by regulating the working state of individual unit bodies. The present invention can be applied to fields such as detonation propulsion.
[0007] In order to achieve the above object, the technical solution adopted by the present invention is as follows:
[0008] A detonation vector propulsion scheme based on the combination of multiple unit bodies, including a vector propulsion scheme based on the combination of pulse detonation engine unit bodies, a vector propulsion scheme based on the combination of rotating detonation engine unit bodies, and a vector propulsion scheme based on the hybrid combination of pulse detonation engine unit bodies and rotating detonation engine unit bodies.
[0009] The vector propulsion scheme based on the combination of pulse detonation engine units includes multiple pulse detonation engine units. The multiple pulse detonation engine units are arranged in axial symmetry or central symmetry. During the process of all pulse detonation engine units working in the same state, additional control torque is obtained by shutting down individual pulse detonation engine units or changing the supply conditions of individual pulse detonation engine units, so as to achieve vector propulsion.
[0010] The vector propulsion scheme based on the combination of rotating detonation engine units includes multiple rotating detonation engine units. The multiple rotating detonation engine units are arranged in axial symmetry or central symmetry. During the process of all rotating detonation engine units working in the same state, additional control torque is obtained by shutting down individual rotating detonation engine units or changing the supply conditions of individual rotating detonation engine units, so as to achieve vector propulsion.
[0011] The vector propulsion scheme based on the hybrid combination of pulse detonation engine units and rotating detonation engine units includes a rotating detonation engine unit and multiple pulse detonation engine units. The combustion chamber channel configuration of the rotating detonation engine unit is in axial symmetry or central symmetry structure. The rotating detonation engine unit does not participate in the generation of vector thrust and only maintains the axial thrust required by the aircraft. The multiple pulse detonation engine units are arranged in axial symmetry or central symmetry, and their axis of symmetry or center of symmetry coincides with the axis of symmetry or center of symmetry of the combustion chamber channel configuration of the rotating detonation engine unit. During the process of all pulse detonation engine units working in the same state, additional control torque is obtained by shutting down individual pulse detonation engine units or changing the supply conditions of individual pulse detonation engine units, so as to achieve vector propulsion.
[0012] Beneficial effects:
[0013] By adopting a detonation vector propulsion scheme based on the combination of multiple units proposed by the present invention, additional control torque is obtained by regulating the working state of individual units, so as to achieve the vector propulsion effect. Thus, vector thrust can be generated without introducing a vector nozzle that has disadvantages such as affecting the internal flow field of the engine and complex control strategies. The present invention can be applied to fields such as detonation vector propulsion. Description of the drawings
[0014] Figure 1 It is an axonometric view of the vector propulsion scheme based on the combination of pulse detonation engine units in a detonation vector propulsion scheme based on the combination of multiple units of the present invention;
[0015] Figure 2 It is a schematic diagram of the vector propulsion scheme based on the combination of pulse detonation engine units in a detonation vector propulsion scheme based on the combination of multiple units of the present invention;
[0016] Figure 3 Schematic diagram of other ways of arranging unit bodies in the vector propulsion scheme based on the combination of pulse detonation engine unit bodies in a detonation vector propulsion scheme based on the combination of multiple unit bodies according to the present invention;
[0017] Figure 4 Axonometric view of the vector propulsion scheme based on the combination of rotating detonation engine unit bodies in a detonation vector propulsion scheme based on the combination of multiple unit bodies according to the present invention;
[0018] Figure 5 Schematic diagram of the vector propulsion scheme based on the combination of rotating detonation engine unit bodies in a detonation vector propulsion scheme based on the combination of multiple unit bodies according to the present invention;
[0019] Figure 6 Schematic diagram of other ways of arranging unit bodies in the vector propulsion scheme based on the combination of rotating detonation engine unit bodies in a detonation vector propulsion scheme based on the combination of multiple unit bodies according to the present invention;
[0020] Figure 7 Axonometric view of the vector propulsion scheme based on the hybrid combination of pulse detonation engine unit bodies and rotating detonation engine unit bodies in a detonation vector propulsion scheme based on the combination of multiple unit bodies according to the present invention;
[0021] Figure 8 Schematic diagram of the vector propulsion scheme based on the hybrid combination of pulse detonation engine unit bodies and rotating detonation engine unit bodies in a detonation vector propulsion scheme based on the combination of multiple unit bodies according to the present invention;
[0022] Figure 9 Schematic diagram of other ways of arranging unit bodies in the vector propulsion scheme based on the hybrid combination of pulse detonation engine unit bodies and rotating detonation engine unit bodies in a detonation vector propulsion scheme based on the combination of multiple unit bodies according to the present invention.
[0023] Wherein, 1-a to 1-h are pulse detonation engine unit bodies, 2-a to 2-f are rotating detonation engine unit bodies, 11 is the head injection structure of the pulse detonation engine unit body, 111 is the oxidant inlet of the pulse detonation engine unit body, 112 is the fuel inlet of the pulse detonation engine unit body, 12 is the combustion chamber of the pulse detonation engine unit body, 13 is the tail nozzle of the pulse detonation engine unit body, 21 is the head injection structure of the rotating detonation engine unit body, 211 is the oxidant inlet of the rotating detonation engine unit body, 212 is the fuel inlet of the rotating detonation engine unit body, 22 is the combustion chamber of the rotating detonation engine unit body, 221 is the outer ring of the combustion chamber of the rotating detonation engine unit body, 222 is the inner ring of the combustion chamber of the rotating detonation engine unit body, 23 is the tail nozzle of the rotating detonation engine unit body, 231 is the outer ring of the tail nozzle of the rotating detonation engine unit body, and 232 is the inner ring of the tail nozzle of the rotating detonation engine unit body. Detailed implementation manners
[0024] The present invention will be further described below in conjunction with the accompanying drawings and specific implementation processes.
[0025] Refer to Figure 1 、 Figure 4 and Figure 7 A detonation vector propulsion scheme based on multi-unit combination includes a vector propulsion scheme based on the combination of pulse detonation engine units, a vector propulsion scheme based on the combination of rotating detonation engine units, and a vector propulsion scheme based on the hybrid combination of pulse detonation engine units and rotating detonation engine units. Among them, for the vector propulsion scheme based on the combination of pulse detonation engine units and the vector propulsion scheme based on the combination of rotating detonation engine units, the pulse detonation engine units 1-a to 1-g or the rotating detonation engine units 2-a to 2-d are all arranged axially symmetrically or centrally symmetrically. By closing individual units or changing the supply conditions of individual units, an overall vector propulsion effect can be obtained; for the vector propulsion scheme based on the hybrid combination of pulse detonation engine units and rotating detonation engine units, the combustion chamber channel configuration of the rotating detonation engine unit 2-a is axially symmetric or centrally symmetric, and does not participate in the generation of vector thrust, but only maintains the axial thrust required by the aircraft. The pulse detonation engine units 1-a and 1-b are arranged axially symmetrically or centrally symmetrically, and their axes of symmetry or centers of symmetry coincide with the axis of symmetry or center of symmetry of the combustion chamber channel configuration of the rotating detonation engine unit 2-a. By closing individual pulse detonation engine units or changing the supply conditions of individual pulse detonation engine units, an overall vector propulsion effect can be obtained.
[0026] Embodiment 1:
[0027] Refer to Figure 1 and Figure 2 In a vector propulsion scheme based on the combination of pulse detonation engine units in a detonation vector propulsion scheme based on multi-unit combination, the pulse detonation engine units 1-a to 1-g are arranged centrally symmetrically. Under the condition that all pulse detonation engine units are in the same working state, by closing the pulse detonation engine units 1-a and 1-b or synchronously increasing the oxidizer / fuel supply rate of the pulse detonation engine units 1-f and 1-g, an overall upward vector propulsion effect can be obtained.
[0028] Refer to Figure 3 Other ways of arranging unit bodies in a vector propulsion scheme based on the combination of pulse detonation engine units in a detonation vector propulsion scheme based on multi-unit combination include but are not limited to Figure 3 shown in (a) to (c) in
[0029] Embodiment 2:
[0030] See Figure 4 and Figure 5 , in a detonation vector propulsion scheme based on the combination of multiple units, a vector propulsion scheme based on the combination of rotating detonation engine units. The rotating detonation engine units 2-a to 2-d are arranged in central symmetry. Under the condition that all rotating detonation engine units are in the same working state, by closing the rotating detonation engine unit 2-b or increasing the oxidizer / fuel supply rate of the rotating detonation engine unit 2-c, a vector propulsion effect to the left as a whole can be obtained.
[0031] See Figure 6 , in a detonation vector propulsion scheme based on the combination of multiple units, other ways of arranging the units in the vector propulsion scheme based on the combination of rotating detonation engine units include but are not limited to Figure 6 as shown in (a) to (c) in
[0032] Example 3:
[0033] See Figure 7 and Figure 8 , in a detonation vector propulsion scheme based on the combination of multiple units, a vector propulsion scheme based on the hybrid combination of pulse detonation engine units and rotating detonation engine units. The combustion chamber channel configuration of the rotating detonation engine unit 2-a is an axisymmetric structure, which does not participate in the generation of vector thrust and only maintains the axial thrust required by the aircraft. The pulse detonation engine units 1-a and 1-b are arranged in axial symmetry, and the symmetry axes of the two coincide with the symmetry axis of the combustion chamber channel configuration of the rotating detonation engine unit. Under the condition that all pulse detonation engine units are in the same working state, by increasing the oxidizer / fuel supply rate of the pulse detonation engine unit 1-a or decreasing the oxidizer / fuel supply rate of the pulse detonation engine unit 1-b, a vector propulsion effect to the right as a whole can be obtained.
[0034] See Figure 9 , in a detonation vector propulsion scheme based on the combination of multiple units, other ways of arranging the units in the vector propulsion scheme based on the hybrid combination of pulse detonation engine units and rotating detonation engine units include but are not limited to Figure 9 as shown in (a) to (c) in
[0035] The specific embodiments of the present invention have been described in detail above in combination with the accompanying drawings and the specific implementation process. However, the present invention is not limited to the above embodiments. Without departing from the basic principles of the present invention, those skilled in the art can make various adjustments and optimizations to the above methods.
Claims
1. A detonation vector propulsion scheme based on a combination of multiple units, including a vector propulsion scheme based on a combination of pulse detonation engine units, a vector propulsion scheme based on a combination of rotating detonation engine units, and a vector propulsion scheme based on a mixed combination of pulse detonation engine units and rotating detonation engine units. When the device arranged under this scheme is working, the vector propulsion effect is achieved by changing the working state of individual engine units.
2. The vector propulsion scheme based on the pulse detonation engine unit combination according to claim 1 is characterized in that: It comprises a plurality of pulse detonation engine units; the plurality of pulse detonation engine units are arranged in an axisymmetric or center-symmetrical manner, and when all the pulse detonation engine units are working in the same state, additional control torque is obtained by shutting down individual pulse detonation engine units or changing the supply conditions of individual pulse detonation engine units to achieve vector propulsion.
3. The vector propulsion scheme based on the combination of rotating detonation engine units according to claim 1 is characterized in that: It comprises a plurality of rotating detonation engine units; the plurality of rotating detonation engine units are arranged in an axisymmetric or center-symmetrical manner, and when all rotating detonation engine units are working in the same state, additional control torque is obtained by shutting down individual rotating detonation engine units or changing supply conditions of individual rotating detonation engine units to achieve vector propulsion.
4. The vector propulsion scheme based on the hybrid combination of a pulse detonation engine unit and a rotating detonation engine unit according to claim 1 is characterized in that: It comprises a rotating detonation engine unit body and a plurality of pulse detonation engine unit bodies; the combustion chamber channel configuration of the rotating detonation engine unit body is an axisymmetric or center-symmetrical structure, the rotating detonation engine unit body does not participate in the generation of vector thrust, and only maintains the axial thrust required by the aircraft; the plurality of pulse detonation engine unit bodies are arranged axisymmetric or center-symmetrically, and their symmetry axes or symmetry centers coincide with the symmetry axes or symmetry centers of the combustion chamber channel configuration of the rotating detonation engine unit bodies; in the process of all pulse detonation engine unit bodies working in the same state, by closing individual pulse detonation engine unit bodies or changing the supply conditions of individual pulse detonation engine unit bodies, additional control torque is obtained to achieve vector propulsion.