Conventional and detonation dual-mode spontaneous combustion propellant space engine

Abstract

The invention provides a conventional and detonation dual-mode spontaneous combustion propellant space engine, and belongs to the technical field of spacecraft propulsion systems. The conventional and detonation dual-mode spontaneous combustion propellant space engine comprises a propellant control valve, an engine head, an engine body and an external excitation device. The propellant control valve, the engine head part and the engine body part are connected in sequence, and the external excitation device is embedded into the outer wall of the engine body part; according to the invention, by adopting an external excitation mode, the space engine in a detonation mode is realized; by means of a selective excitation mode, the space engine capable of selecting a conventional mode and a detonation mode is achieved. The detonation combustion is applied to the spontaneous combustion propellant space engine, the upper limit of the combustion efficiency of the space engine of a constant-pressure thermodynamic cycle is broken through, and the combustion efficiency is further improved on the original basis.

Description

Technical Field

[0001] This invention belongs to the field of spacecraft propulsion system technology, specifically relating to a space engine with conventional and detonation dual-mode self-ignition propellants. Background Technology

[0002] High-performance space engines are crucial for the competitiveness and capability of future national defense equipment. To achieve the goal of becoming a space power, there is an urgent need for space engines with more advanced performance indicators. Considering factors such as thrust, specific impulse, on-orbit conditions, and operating temperature, self-igniting propellants are generally used as both fuel and oxidizer for high-performance space engines. For engines using the self-igniting propellant MMH / NTO, a 1% increase in combustion efficiency can improve the engine's vacuum specific impulse by approximately 3 seconds, extending the on-orbit time of high-value apogee satellites by 7-8 months. Therefore, there remains an urgent need for higher-performance space engines using self-igniting propellants.

[0003] Space engines using isobaric thermodynamic cycles have reached near-maximum combustion efficiency (approximately 96-98%). A fundamental shift in principle is needed, altering the combustion mode and transforming the thermodynamic cycle of the space engine to fundamentally improve its performance. Detonation combustion possesses self-pressurization characteristics and inherently offers high performance advantages. Slow combustion wave velocities are on the order of 1 to 10 m / s, while detonation wave velocities are on the order of 1000 to 3000 m / s. Space engines employing this method can achieve near-isovolute thermodynamic cycle efficiency, improving upon isobaric cycles by 10% to 15%, potentially breaking through the theoretical performance ceiling of existing space engines.

[0004] Currently, the relevant existing technologies include: A knock combustion chamber module and a knock combustion chamber (Patent document CN115342381A) are disclosed. This patent document discloses a knock combustion chamber module and a knock combustion chamber, which adopts a multi-annular slit combustion chamber. The knock combustion chamber is composed of multiple knock combustion chamber modules and is used in conjunction with an ignition assembly. Due to the presence of walls, the space utilization rate of the multi-annular slit combustion chamber is lower than that of the empty cylindrical combustion chamber. Moreover, because the contact area between the wall and the flame is larger, the heat dissipation intensity is higher than that of the empty cylindrical combustion chamber. Considering only heat loss, the engine combustion efficiency is lower than that of the empty cylindrical combustion chamber. Summary of the Invention

[0005] To address the shortcomings of existing technologies, the purpose of this invention is to provide a space engine with both conventional and detonation dual-mode self-ignition propellants.

[0006] The conventional and detonation dual-mode self-ignition propellant space engine provided by the present invention is characterized by comprising: a propellant control valve, an engine head, an engine body, and an external excitation device; The propellant control valve, engine head, and engine body are connected in sequence, and the external excitation device is embedded in the outer wall of the engine body.

[0007] Preferably, the propellant control valve is used to simultaneously control the oxidizer and fuel, and can be opened and closed simultaneously; The engine head achieves uniform atomization and mixing of the propellant, which includes an oxidant and fuel; The engine body includes a combustion chamber, a throat, and an expansion section. The sidewall of the combustion chamber is provided with radial excitation holes and tangential excitation holes. The throat is the narrowed portion between the combustion chamber and the expansion section of the engine body.

[0008] Preferably, a controllable intensity excitation is injected into the combustion chamber through radial excitation holes and tangential excitation holes that are connected to the external excitation device.

[0009] Preferably, the engine body can achieve stable combustion and detonation combustion of oxidizer and fuel in the combustion chamber, and accelerate the ejection of combustion products through the throat and expansion section; The combustion chamber has a cylindrical structure, and external excitation is input into the combustion chamber through radial and tangential holes along the cross-section of the combustion chamber. The radial excitation hole axis is perpendicular to the engine thrust axis; The angle between the axis of the tangential excitation hole and the combustion chamber wall is... ; The external excitation is generated by an external excitation device, which can quantitatively generate the required excitation intensity.

[0010] Preferably, the external excitation device generates a self-sustaining knock wave in the combustion chamber through radial excitation holes and tangential excitation holes, and the excitation intensity generated by the external excitation device is more than three times that of the combustion chamber pressure.

[0011] Preferably, the engine has two operating modes: a normal mode and a knock mode, which can be selected according to actual needs. In the normal mode, no external excitation is applied.

[0012] Preferably, the conventional mode is a slow-burning propellant that generates steady-state thrust; the detonation mode is a slow-burning to detonation combustion triggered by external excitation within 0.1 to 2 seconds after ignition, which then generates steady-state thrust.

[0013] Preferably, the combustion efficiency in the conventional mode is 90% to 95%, and the combustion efficiency in the detonation mode is 1.05 to 1.1 times that in the conventional mode.

[0014] Preferably, the triggering sequence of the detonation mode is as follows: t=0s: The propellant control valve opens, and propellant is filled; t=0.1s: Stable slow combustion is formed, and the combustion chamber pressure is established to more than 95% of the rated pressure; t=0.2s: External excitation injection, excitation pulse width <1ms, excitation pressure >6MPa; t=0.21s: The pressure peak monitoring sensor obtains the characteristic signal of the detonation wave. The pressure peak is 3.26MPa. Based on the time difference of the pressure peak, the propagation speed can be calculated to be approximately 2045m / s.

[0015] A conventional and detonation dual-mode self-ignition propellant space engine operating system, implemented using the conventional and detonation dual-mode self-ignition propellant space engine provided by the present invention, includes: Module M1: Conventional module, corresponding to the conventional mode of the engine; Module M2: Knock module, corresponding to the engine knock mode; The module M1 includes: Module M11: Propellant control valve opens; Module M12: Propellant is well atomized through the engine head; Module M13: Combustion occurs within the engine compartment, generating stable thrust; The module M2 includes: Module M22: The propellant is well atomized at the engine head, burns inside the engine body, and generates stable thrust; Module M22: An external excitation device generates a self-sustaining knock wave in the combustion chamber through radial and tangential excitation holes; Module M23: Within 0.1 to 2 seconds of engine ignition, an external excitation device generates an excitation intensity of more than three times the combustion chamber pressure, changing the combustion mode in the combustion chamber from slow combustion to detonation, and finally detonation combustion in the engine body to form stable thrust.

[0016] Compared with the prior art, the present invention has the following beneficial effects: 1. This invention applies detonation combustion to a space engine with self-igniting propellant. It adopts a hollow cylindrical combustion chamber to make full use of the structural space and realizes a space engine with detonation mode by using external excitation. It breaks through the upper limit of combustion efficiency of space engines with constant pressure thermodynamic cycle and achieves a further improvement in combustion efficiency (5% to 10%) on the original basis (90% to 95%).

[0017] 2. This invention realizes a space engine in detonation mode by using external excitation.

[0018] 3. This invention achieves a space engine with selectable conventional and detonation modes through selective excitation; 4. The detonation mode of this invention has higher combustion efficiency, thus the thrust is higher than that of the conventional mode, which can meet the requirements of two-stage variable thrust. Attached Figure Description

[0019] Other features, objects, and advantages of the present invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings: Figure 1 This is a schematic diagram of the overall structure of the present invention; Figure 2 This is a schematic diagram of the radial structure of the present invention; Figure 3 This is a schematic diagram of the axial distribution of the engine and external excitation structure of the present invention.

[0020] The diagram shows: Detailed Implementation

[0021] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the protection scope of the present invention.

[0022] like Figures 1 to 3 As shown, this embodiment of the invention provides a space engine with conventional and detonation dual-mode self-ignition propellant, including: a propellant control valve 1, an engine head 2, an engine body 3, and an external excitation device 4; the propellant control valve 1, the engine head 2, and the engine body 3 are connected in sequence, and the external excitation device 4 is embedded in the outer wall of the engine body 3; The propellant control valve 1 synchronously controls the on / off state of the oxidizer and fuel. Specifically, the propellant control valve 1 is used to simultaneously control the oxidizer and fuel, and can be opened and closed simultaneously. The engine head 2 achieves uniform atomization and mixing of the propellant, which includes an oxidant and fuel; The engine body 3 includes: a combustion chamber 31, a throat 32, and an expansion section 33. The sidewall of the combustion chamber 31 is provided with a radial excitation hole 34 and a tangential excitation hole 35. The throat 32 is the narrowed portion between the combustion chamber 31 and the expansion section 33 of the engine body 3. The external excitation device 4 injects controllable intensity excitation into the combustion chamber through the radial excitation hole 34 and the tangential excitation hole 35, which are connected to the external excitation device 4. Furthermore, the engine body 3 can achieve stable combustion and detonation combustion of oxidizer and fuel within the combustion chamber 31, and accelerate the ejection of combustion products through the throat 32 and the expansion section 33; the combustion chamber 31 has a cylindrical structure, and external excitation is input into the combustion chamber 31 through radial holes 34 and tangential holes 35 along the cross-section of the combustion chamber 31; the axis of the radial excitation hole 34 is perpendicular to the engine thrust axis; the angle between the axis of the tangential excitation hole 35 and the wall of the combustion chamber 31 is... The radial excitation hole 34 is perpendicular to the engine thrust axis; the external excitation is generated by the external excitation device 4, which can quantitatively generate the required excitation intensity; specifically, the external excitation device 4 generates a self-sustaining knock wave in the combustion chamber 31 through the radial excitation hole 34 and the tangential excitation hole 35, and the excitation intensity generated by the external excitation device 4 should be more than three times the pressure of the combustion chamber 31.

[0023] The engine has two operating modes: normal mode and knock mode, which can be selected according to actual needs. In normal mode, no external excitation is applied. In the conventional mode, the propellant undergoes slow combustion to generate steady-state thrust; in the detonation mode, the slow combustion is triggered by external excitation to transition to detonation combustion within 0.1 to 2 seconds after ignition, after which steady-state thrust is generated. Furthermore, the combustion efficiency in the conventional mode is 90% to 95%, and the combustion efficiency in the detonation mode is 1.05 to 1.1 times that in the conventional mode. Furthermore, the triggering sequence of the detonation mode is as follows: t=0s: Propellant control valve 1 opens, propellant filling begins; t=0.1s: Stable slow combustion is formed, and the pressure in combustion chamber 31 is established to more than 95% of the rated pressure; t=0.2s: External excitation injection, excitation pulse width <1ms, excitation pressure >6MPa; t=0.21s: The pressure peak monitoring sensor obtains the characteristic signal of the detonation wave. The pressure peak is 3.26MPa. Based on the time difference of the pressure peak, the propagation speed can be calculated to be approximately 2045m / s.

[0024] This invention also provides a working system for a space engine using a dual-mode (conventional and detonation) self-igniting propellant, implemented using the dual-mode (conventional and detonation) self-igniting propellant space engine provided by this invention, comprising: Module M1: Conventional module, corresponding to the conventional mode of the engine; Module M2: Knock module, corresponding to the engine knock mode; The module M1 includes: Module M11: Propellant control valve 1 is open; Module M12: The propellant is well atomized through the engine head 2; Module M13: Combustion occurs within engine body 3, generating stable thrust; The module M2 includes: Module M22: The propellant is well atomized through the engine head 2, and burns in the engine body 3 to generate stable thrust; Module M22: The external excitation device 4 generates a self-sustaining knock wave in the combustion chamber 31 through the radial excitation hole 34 and the tangential excitation hole 34; Module M23: Within 0.1 to 2 seconds of engine ignition, the external excitation device 4 generates an excitation intensity of more than three times the combustion chamber pressure, changing the combustion mode in the combustion chamber 31 from slow combustion to detonation, and finally detonation combustion in the engine body 3 to form stable thrust.

[0025] In summary, this invention provides a space engine with dual modes of conventional and detonation self-igniting propellant, comprising: a propellant control valve 1, an engine head 2, an engine body 3, and an external excitation device 4; the propellant control valve 1, engine head 2, and engine body 3 are connected sequentially, and the external excitation device 4 is embedded in the outer wall of the engine body 3; this invention achieves a space engine with detonation mode by employing external excitation; it achieves a space engine with selectable conventional and detonation modes by selective excitation; and by applying detonation combustion to a space engine with self-igniting propellant, it breaks through the upper limit of combustion efficiency of a space engine with constant pressure thermodynamic cycle, achieving a further improvement in combustion efficiency (5% to 10%) on the original basis (90% to 95%).

[0026] In the description of this application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application.

[0027] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. A space engine with conventional and detonation dual-mode self-ignition propellant, characterized in that, include: Propellant control valve (1), engine head (2), engine body (3), external excitation device (4); The propellant control valve (1), engine head (2), and engine body (3) are connected in sequence, and the external excitation device (4) is embedded in the outer wall of the engine body (3).

2. The space engine with conventional and detonation dual-mode auto-ignition propellant as described in claim 1, characterized in that, The propellant control valve (1) is used to simultaneously control the oxidizer and fuel, and can be opened and closed simultaneously. The engine head (2) achieves uniform atomization and mixing of the propellant, which includes an oxidant and fuel; The engine body (3) includes: a combustion chamber (31), a throat (32), and an expansion section (33). The side wall of the combustion chamber (31) is provided with a radial excitation hole (34) and a tangential excitation hole (35). The throat (32) is the narrowed part between the combustion chamber (31) and the expansion section (33) of the engine body (3).

3. The space engine with conventional and detonation dual-mode self-ignition propellant as described in claim 2, characterized in that, Controllable intensity excitation is injected into the combustion chamber through the radial excitation hole (34) and the tangential excitation hole (35) connected to the external excitation device (4).

4. The space engine with conventional and detonation dual-mode auto-ignition propellant as described in claim 2, characterized in that, The engine body (3) can achieve stable combustion and detonation of oxidizer and fuel in the combustion chamber (31), and accelerate the ejection of combustion products through the throat (32) and expansion section (33); The combustion chamber (31) is a cylindrical structure, and the radial hole (34) and tangential hole (35) along the cross section of the combustion chamber (31) input external excitation into the combustion chamber (31); The axis of the radial excitation hole (34) is perpendicular to the engine thrust axis; The angle between the axis of the tangential excitation hole (35) and the wall of the combustion chamber (31) is... ; The external stimulus is generated by the external stimulus device (4), which can quantitatively generate the required stimulus intensity.

5. The space engine with conventional and detonation dual-mode auto-ignition propellant as described in claim 4, characterized in that, The external excitation device (4) generates a self-sustaining detonation wave in the combustion chamber (31) through the radial excitation hole (34) and the tangential excitation hole (35). The excitation intensity generated by the external excitation device (4) is more than three times the pressure of the combustion chamber (31).

6. The space engine with conventional and detonation dual-mode auto-ignition propellant as described in claim 1, characterized in that, The engine has two operating modes: normal mode and knock mode, which can be selected according to actual needs. In normal mode, no external excitation is applied.

7. The space engine with conventional and detonation dual-mode auto-ignition propellant as described in claim 6, characterized in that, The conventional mode generates steady-state thrust through slow combustion of the propellant; the detonation mode generates steady-state thrust by triggering slow combustion to detonation combustion through external excitation within 0.1 to 2 seconds after ignition.

8. The space engine with conventional and detonation dual-mode auto-ignition propellant according to claim 6, characterized in that, The combustion efficiency is 90% to 95% in the conventional mode and 1.05 to 1.1 times that in the detonation mode.

9. The space engine with conventional and detonation dual-mode auto-ignition propellant according to claim 6, characterized in that, The trigger sequence for the detonation mode is as follows: t=0s: Propellant control valve (1) opens, propellant is filled; t=0.1s: Stable slow combustion is formed, and the pressure in the combustion chamber (31) is established to more than 95% of the rated pressure; t=0.2s: External excitation injection, excitation pulse width <1ms, excitation pressure >6MPa; t=0.21s: The pressure peak monitoring sensor obtains the characteristic signal of the detonation wave. The pressure peak is 3.26MPa. Based on the time difference of the pressure peak, the propagation speed can be calculated to be approximately 2045m / s.

10. A conventional and detonation dual-mode self-ignition propellant space engine operating system, implemented using the conventional and detonation dual-mode self-ignition propellant space engine according to any one of claims 1 to 9, comprising: Module M1: The standard module corresponds to the engine's standard mode; Module M2: Knock module, corresponding to the engine knock mode; The module M1 includes: Module M11: Propellant control valve (1) is open; Module M12: The propellant is well atomized through the engine head (2); Module M13: Combustion occurs within the engine body (3) to generate stable thrust; The module M2 includes: Module M22: The propellant is well atomized through the engine head (2), burns in the engine body (3), and forms stable thrust; Module M22: An external excitation device (4) generates a self-sustaining detonation wave in the combustion chamber (31) through radial excitation holes (34) and tangential excitation holes (34); Module M23: Within 0.1 to 2 seconds after engine ignition, an excitation intensity of more than three times the combustion chamber pressure is generated by an external excitation device (4), which changes the combustion mode in the combustion chamber (31) from slow combustion to detonation, and finally detonation combustion in the engine body (3) to form stable thrust.

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