CN119412246A - Liquid rocket engine and liquid rocket - Google Patents
Liquid rocket engine and liquid rocket Download PDFInfo
- Publication number
- CN119412246A CN119412246A CN202411478474.7A CN202411478474A CN119412246A CN 119412246 A CN119412246 A CN 119412246A CN 202411478474 A CN202411478474 A CN 202411478474A CN 119412246 A CN119412246 A CN 119412246A
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- Prior art keywords
- gear
- gas
- reactive
- liquid rocket
- rocket engine
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/44—Feeding propellants
- F02K9/46—Feeding propellants using pumps
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/60—Constructional parts; Details not otherwise provided for
- F02K9/62—Combustion or thrust chambers
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/80—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)
Abstract
The invention provides a liquid rocket engine and a liquid rocket, and relates to the technical field of rocket engine equipment. The turbine pump comprises a fuel pump, an oxidant pump and a turbine, wherein an outlet of the fuel pump and an outlet of the oxidant pump are respectively communicated with a thrust chamber and a gas generator, the gas generator is provided with a first gas passage connected with the turbine and a second gas passage used for communicating with the outside atmosphere, a gas regulating valve is arranged on the second gas passage, a reactive stepping motor is connected with a valve core of the gas regulating valve through a transmission mechanism, and a controller is electrically connected with the reactive stepping motor and is used for sending pulse signals to the reactive stepping motor at a set control frequency and controlling the power-on time sequence of the reactive stepping motor so as to drive the reactive stepping motor to rotate positively and reversely and regulate the opening of the gas regulating valve. The thrust adjusting process only relates to a gas adjusting valve, the reliability is high, and a reaction type stepping motor is adopted, so that a larger output torque can be generated under a smaller current, and the required power is smaller.
Description
Technical Field
The invention relates to the technical field of rocket engine equipment, in particular to a liquid rocket engine and a liquid rocket.
Background
The main power device of the carrier rocket generally adopts a liquid rocket engine. Because the liquid rocket engine has complex composition and large development difficulty, the factors such as reliability and the like are considered, and the liquid rocket engine is generally designed into fixed thrust. As the demand for recovery and re-use of the launch vehicle deepens, thrust regulation becomes a requisite capability of the liquid rocket engine.
In the liquid rocket engine adopting the gas generator circulation mode at present, the quantity of regulating valves can be more, the weight of the engine is increased, the control process of a plurality of flow regulating valves is complex, and the overall reliability can be reduced. In addition, the current regulating valve is regulated by adopting a permanent magnet motor, and when the opening degree of a valve core of the regulating valve needs to be changed, the permanent magnet motor needs to overcome the internal magnetic field force by larger current, so that the position of a rotor is changed, and the power consumption is larger.
Disclosure of Invention
The invention provides a liquid rocket engine and a liquid rocket, which are used for solving the defects that in the prior art, the liquid rocket engine is large in number of regulating valves which are required to be arranged for realizing thrust regulation, complex in control, low in reliability and large in power consumption of a motor in the regulating process of the regulating valves.
In a first aspect, the invention provides a liquid rocket engine, comprising a thrust chamber, a gas generator, a turbine pump, a gas regulating valve, a controller and a reactive stepping motor;
The turbine pump comprises a fuel pump, an oxidant pump and a turbine, and an outlet of the fuel pump and an outlet of the oxidant pump are respectively communicated with the thrust chamber and the gas generator;
the gas generator is provided with a first gas passage and a second gas passage, the first gas passage is connected with the turbine, the second gas passage is used for communicating with the external atmosphere, and the gas regulating valve is arranged on the second gas passage;
The reactive stepping motor is connected with a valve core of the gas regulating valve through a transmission mechanism, the controller is electrically connected with the reactive stepping motor, and the controller is configured to send pulse signals to the reactive stepping motor at a set control frequency and control the energizing time sequence of the reactive stepping motor so as to drive the reactive stepping motor to rotate forwards or reversely and regulate the opening of the gas regulating valve.
According to the liquid rocket engine, the transmission mechanism comprises a first gear, a second gear and a rack, the second gear is identical to the first gear in structure, the first gear is rigidly connected with an output shaft of the reactive stepping motor, the second gear is connected to the side face of the first gear through a torsion spring, the torsion spring is used for enabling second teeth of the second gear and first teeth of the first gear to be arranged in a staggered mode along the circumferential direction, the rack is meshed with the first gear and the second gear respectively, and the end portion of the rack is connected with the valve core.
According to the liquid rocket engine provided by the invention, the transmission mechanism further comprises a limiting device, wherein the limiting device is arranged on one side of the second gear, which is opposite to the first gear, and is used for limiting the axial direction of the second gear;
And/or, the transmission mechanism further comprises a linear displacement sensor electrically connected with the controller, and the linear displacement sensor is connected with the valve core or the rack and used for detecting the valve core opening of the gas regulating valve.
According to the liquid rocket engine provided by the invention, the output shaft of the reactive stepping motor is connected with the first gear through the reduction gear pair, the reduction gear pair is arranged in the reactive stepping motor, and the reduction ratio of the reduction gear pair is 20:1-40:1.
According to the liquid rocket engine provided by the invention, the set control frequency of the controller is 500-800 Hz, and the power-on time sequence of the reactive stepping motor is four-phase four-beat.
According to the liquid rocket engine provided by the invention, the fuel pump, the oxidant pump and the turbine are coaxially arranged;
and/or the turbine is an impulse turbine.
According to the liquid rocket engine provided by the invention, the fuel pump is communicated with the gas generator and the thrust chamber through the first tee pipe;
and/or the oxidant pump is communicated with the gas generator and the thrust chamber through a second tee pipe.
According to the liquid rocket engine provided by the invention, the liquid rocket engine further comprises the exhaust spray pipe, wherein the exhaust spray pipe is respectively connected with the outlet of the second fuel gas passage and the fuel gas output end of the turbine pump, and the pipe diameter of the exhaust spray pipe is firstly reduced and then increased along the flow direction of fluid.
According to the liquid rocket engine provided by the invention, the outlet of the second gas passage is connected with the first exhaust spray pipe, the pipe diameter of the first exhaust spray pipe is firstly reduced and then increased along the flow direction of the fluid, and/or the gas output end of the turbine pump is provided with the second exhaust spray pipe, and the pipe diameter of the second exhaust spray pipe is firstly reduced and then increased along the flow direction of the fluid.
In a second aspect, the present invention also provides a liquid rocket comprising an rocket body and the liquid rocket engine according to the first aspect, wherein the liquid rocket engine is mounted on the rocket body.
The liquid rocket engine and the liquid rocket provided by the invention have the advantages that the second gas passage is additionally arranged at the downstream of the gas generator, the gas regulating valve is arranged on the second gas passage, the controller controls the valve core opening of the gas regulating valve through the transmission mechanism by controlling the reactive stepping motor, so that the gas flow entering the turbine pump is controlled, the power of the turbine pump is regulated, the thrust regulation is realized, only one gas regulating valve is involved in the thrust regulation process, compared with the traditional liquid rocket engine, the setting number of the regulating valves is reduced, the complexity of the engine is reduced, the manufacturing cost is reduced, the coupling among the regulating valves is not involved in the regulation process, the complex decoupling control logic is not required, the control is simple, and the reliability is high. The reactive stepping motor is adopted, so that larger output torque can be generated under smaller current, the required power is smaller, and the generated heat is less. In addition, the rotor of the reactive stepping motor has no magnetism, and when the motor changes the current running state, only the moment of inertia of the motor rotor is needed to be overcome, and the magnetic force is not needed to be overcome, so that the motor is ensured to still maintain larger output torque margin at the moment of starting and stopping, and the control reliability is improved.
Drawings
In order to more clearly illustrate the invention or the technical solutions of the prior art, the following description will briefly explain the drawings used in the embodiments or the description of the prior art, and it is obvious that the drawings in the following description are some embodiments of the invention, and other drawings can be obtained according to the drawings without inventive effort for a person skilled in the art.
Fig. 1 is a schematic structural diagram of a liquid rocket engine provided by the invention.
Fig. 2 is a schematic diagram of a partial structure of a liquid rocket engine provided by the invention.
Fig. 3 is a schematic diagram of gear connection of the transmission mechanism provided by the invention.
Fig. 4 is a schematic diagram of the transmission engagement of the first gear, the second gear and the rack provided by the invention.
Reference numerals:
1. Thrust chamber, 2, gas generator, 21, first gas passage, 22, second gas passage, 3, oxidant pump, 4, fuel pump, 5, turbine, 6, gas regulating valve, 7, reactive stepper motor, 71, first electric connector, 72, second electric connector, 81, first gear, 810, first tooth, 811, first tooth surface, 82, second gear, 820, second tooth, 821, second tooth surface, 9, torsion spring, 10, rack.
Detailed Description
For the purpose of making the objects, technical solutions and advantages of the present invention more apparent, the technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings, and it is apparent that the described embodiments are some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
The features of the invention "first", "second" and the like in the description and in the claims may be used for the explicit or implicit inclusion of one or more such features. In the description of the present invention, unless otherwise indicated, the meaning of "a plurality" is two or more. Furthermore, in the description and claims, "and/or" means at least one of the connected objects, and the character "/", generally means that the associated object is an "or" relationship.
In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings are merely for convenience in describing the present invention and simplifying the description, and do not indicate or imply that the device or element being referred to must have a specific orientation, be configured and operated in a specific orientation, and therefore should not be construed as limiting the present invention.
In the description of the present invention, unless explicitly stated or limited otherwise, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected, mechanically connected, electrically connected, directly connected, indirectly connected via an intermediate medium, or in communication between two elements. The specific meaning of the above terms in the present invention will be understood in specific cases by those of ordinary skill in the art.
In the related art, the thrust adjustment modes are different according to the different circulation modes of the variable thrust liquid rocket engine. The circulation mode of the variable thrust liquid rocket engine mainly relates to the circulation, expansion circulation and afterburning circulation of a gas generator, and the variable thrust liquid rocket engine of the three circulation modes is used for adjusting the engine thrust by adjusting the power of a turbine pump. Wherein the afterburning cycle maintains the mixing ratio by adjusting the flow into the thrust chamber. The expansion cycle achieves stabilization of the mixing ratio of the thrust chamber by adjusting the rotational speed of the turbo pump. The fuel gas generator circulates and adjusts the flow of the propellant entering the fuel gas generator to change the flow of the propellant of the thrust chamber, thereby realizing thrust adjustment.
In the prior variable thrust liquid rocket engine adopting a gas generator circulation mode, an oxidant pipeline and a fuel pipeline which enter the gas generator are provided with regulating valves, the two regulating valves synchronously act to realize the control of the gas flow of the gas generator, and meanwhile, the oxidant pipeline or the fuel pipeline of a thrust chamber is provided with a regulating valve to adjust the combustion mixing ratio of the thrust chamber. The whole scheme needs to set up three governing valves, and governing valve quantity is more, can increase engine weight, and the action process of three governing valves is coupled each other moreover, and control is complicated, and whole reliability also can reduce.
The liquid rocket engine of the present invention is described below with reference to FIGS. 1-4.
The invention provides a liquid rocket engine, which is shown in fig. 1 and comprises a thrust chamber 1, a gas generator 2, a turbine pump, a gas regulating valve 6, a controller and a reactive stepping motor 7. Both the thrust chamber 1 and the gas generator 2 are in communication with a turbo pump.
The turbine pump comprises a fuel pump 4, an oxidant pump 3 and a turbine 5, the gas generator 2 is connected with the turbine 5, and the outlet of the fuel pump 4 and the outlet of the oxidant pump 3 are respectively communicated with the thrust chamber 1 and the gas generator 2. The fuel pump 4 supplies high-pressure fuel to the thrust chamber 1 and the gas generator 2, respectively, and the oxidant pump 3 supplies high-pressure oxidant to the thrust chamber 1 and the gas generator 2, respectively. After the liquid rocket engine is started, the outlet of the fuel pump 4 is always in communication with the thrust chamber 1, that is, a regulating valve is not provided in the connection path between the fuel pump 4 and the thrust chamber 1. Similarly, after the liquid rocket engine is started, the outlet of the oxidizer pump 3 is always in communication with the thrust chamber 1, the outlet of the fuel pump 4 and the gas generator 2, and the outlet of the oxidizer pump 3 and the gas generator 2.
The reaction type stepping motor 7 is connected with a valve core of the gas regulating valve 8 through a transmission mechanism, and the controller is electrically connected with the reaction type stepping motor 7. The controller is configured to phase-react the stepper motor 7 at a set control frequency and to control the energization timing of the reactive stepper motor 7 to drive the reactive stepper motor 7 to rotate forward or reverse. The reaction type stepping motor 7 is connected with the transmission mechanism and is used for driving the transmission mechanism to adjust the opening of the valve core, specifically, the moment of the reaction type stepping motor 7 can be transmitted to the valve core of the gas regulating valve 8 through the transmission mechanism, so that the valve core of the gas regulating valve 8 is pushed to move, and the opening of the valve core is adjusted.
The controller is electrically connected with the reactive stepper motor 7, and is configured to send pulse signals to the reactive stepper motor 7 at a set control frequency, so that the running steps of the reactive stepper motor 7 can be accurately controlled. Wherein the control frequency refers to the number of pulses sent to the motor within 1 s. For example, a control frequency of 500Hz indicates a number of 500 pulses sent to the motor within 1 s. And the controller controls the power-on time sequence of the reactive stepping motor 7, drives the reactive stepping motor 7 to rotate forward or reversely, and realizes the accurate adjustment of the opening of the valve core of the gas regulating valve 8, thereby accurately realizing the purpose of increasing or decreasing the thrust of the rocket engine. The controller may be integrated in the central controller of the liquid rocket for sending control instructions to the reactive stepper motor 7.
The propellant combination formed by the fuel and the oxidant is a two-component propellant such as liquid oxygen methane, liquid oxygen kerosene, liquid oxygen alcohol, and unsymmetrical dimethylhydrazine dinitrogen tetroxide. The gas generator 2 has a first gas passage 21 and a second gas passage 22, and the first gas passage 21 is connected to the turbo pump to push the turbo pump to operate and then to discharge the gas into the atmosphere. The second gas passage 22 is for communicating with the outside atmosphere, and the gas regulating valve 6 is mounted to the second gas passage 22.
After being pressurized by an oxidant pump 3, part of the oxidant in the oxidant storage tank enters the thrust chamber 1 to be combusted with fuel entering the thrust chamber 1 to generate thrust, and the rest part of the oxidant enters the gas generated by combustion of the gas generator 2 to drive a turbine 5 and then is discharged to the atmosphere. After being pressurized by a fuel pump 4, part of fuel in the fuel storage tank enters the thrust chamber 1 to be combusted with the entering oxidant, and the rest part enters the gas generator 2 to be combusted with the oxidant to generate gas to drive a turbine 5. The gas generator 2 provides dynamic supercharging power for the turbine 5 through the first gas passage 21, the second gas passage 22 is arranged in parallel with the first gas passage 21, the gas regulating valve 6 is arranged on the second gas passage 22, the gas flow of the first gas passage 21 is controlled by controlling the opening degree of the gas regulating valve 6, and then the power of the turbine pump is controlled, so that the thrust is regulated.
The controller controls the reaction type stepping motor 7, and the valve core of the gas regulating valve 8 is driven to move through the transmission mechanism, so that the valve core of the gas regulating valve 8 can be kept at a specified position, and the gas quantity entering the first gas passage 21 in the gas generator 2 can be accurately regulated. The process of controlling the fuel gas regulating valve 8 by the reactive stepping motor 7 is open-loop control, so that the phenomenon that the motor shakes back and forth near a steady-state position due to closed-loop control in the related art is avoided, on one hand, the output torque of the motor is ensured not to be attenuated, the control reliability is improved, and on the other hand, the stability of the output power control of the liquid rocket engine is ensured, and the condition that the opening of a valve core is negligent or small is avoided.
Specifically, the valve core opening of the gas regulating valve 6 can be regulated by controlling the reactive stepping motor 7 through the controller according to the regulation requirement of the thrust, the throttle capability of the engine is not limited by the injection pressure drop of the gas generator 2 any more, but by the combustion injection pressure drop of the thrust chamber 1, and the thrust regulation range is improved on the premise of less sacrificing the engine performance. The controller controls the reactive stepping motor 7 to enable the valve core of the gas regulating valve 6 to be completely closed, the gas generator 2 drives the turbine pump to operate at maximum power, the whole liquid rocket engine provides maximum thrust, the valve core opening of the gas regulating valve 6 is gradually increased along with the operation of the reactive stepping motor 7, the gas quantity entering the turbine pump is reduced, the thrust of the liquid rocket engine is gradually decreased, and the controller controls the reactive stepping motor 7 to enable the valve core opening of the gas regulating valve 6 to be maximum, the gas generator 2 drives the turbine 5 to operate at minimum power, and the whole liquid rocket engine provides minimum thrust.
In the thrust regulation process, the controller controls the reactive stepping motor 7 to enable the equivalent flow area of the gas regulating valve 6 to change monotonically, and correspondingly, the thrust of the liquid rocket engine changes monotonically, so that the engine control difficulty is simplified, the closed-loop control of the engine can be realized only by proportional integral control, the whole regulation link is single, the control is simple, and the reliability is higher.
The liquid rocket engine provided by the embodiment of the invention is characterized in that the second gas passage 22 is additionally arranged at the downstream of the gas generator 2, the gas regulating valve 6 is arranged on the second gas passage 22, the controller controls the valve core opening of the gas regulating valve 6 through the transmission mechanism by controlling the reactive stepping motor 7, so that the gas flow entering the turbine pump is controlled, and the power of the turbine pump is regulated, thereby realizing thrust regulation, and compared with the traditional liquid rocket engine, the thrust regulation process only relates to one gas regulating valve 6, reduces the setting number of the regulating valves, reduces the complexity of the engine, is beneficial to reducing the manufacturing cost, does not relate to the coupling among the regulating valves in the regulation process, does not need to be provided with complex decoupling control logic, is simple to control and has high reliability. The reactive stepping motor 7 is adopted, so that larger output torque can be generated under smaller current, the required power is smaller, and the generated heat is less. In addition, the rotor of the reactive stepping motor 7 has no magnetism, and when the motor changes the current running state, only the moment of inertia of the motor rotor is needed to be overcome, and the magnetic force is not needed to be overcome, so that the motor is ensured to still maintain a larger output moment margin at the moment of starting and stopping, and the control reliability is improved.
As shown in fig. 2, 3 and 4, the transmission mechanism includes a first gear 81, a second gear 82, a torsion spring 9 and a rack 10. Wherein the first gear 81 is rigidly connected to the output shaft of the reactive stepper motor 7. The second gear 82 has the same structure as the first gear 81, the second gear 82 is relatively connected to the side surface of the first gear 81 through the torsion spring 9, and the torsion spring 9 is used for enabling the second teeth 820 of the second gear 82 to be staggered with the first teeth 810 of the first gear 81 along the circumferential direction. The rack 10 is engaged with the first gear 81 and the second gear 82, respectively, and an end of the rack 10 is connected to a spool of the gas regulating valve 8.
The controller sends a driving instruction to the reaction type stepping motor 7, the reaction type stepping motor 7 is driven to rotate, the first gear 81 is driven to rotate, the second gear 82 is driven to rotate through the torsion spring 9, namely, the first gear 81 and the second gear 82 rotate on the rack 10, so that the rack 10 moves linearly relatively, the valve core of the gas regulating valve 8 is driven to move linearly, and the valve core opening of the gas regulating valve 8 is regulated.
In the related art, a worm and gear transmission mechanism is generally adopted for transmission, gaps generally exist at the meshing positions of worm and gear transmission in machining, and gaps of parts in different batches are generally inconsistent, so that idle dead zones exist in forward and backward stroke movements, the hysteresis error is larger, and in the forward and backward stroke processes, the opening degree of a valve core is inconsistent under the same instruction, so that the adjustment precision of a system is reduced. Considering that errors exist in machining of a gear rack and a mechanical transmission mechanism, so that a larger or smaller gap exists in part matching, the double-gear transmission mechanism is used for transmission through matching of a double gear with a torsion spring 9 and the rack. Specifically, as shown in fig. 4, under the action of the torsion spring 9, opposite forces can be applied to the first gear 81 and the second gear 82, so that teeth on the first gear 81 and the second gear 82 are circumferentially staggered by a certain angle, the specific angle depends on the size of a machining gap, and when the first gear 81 and the second gear 82 rotate, the first tooth surface 811 of the first gear 81 and the second tooth surface 821 of the second gear 82 can be always in close contact with the rack 10, and the gap is eliminated, so that the ring stagnation error is eliminated. Therefore, when a phase synchronous number instruction is sent to the reactive stepping motor 7, the reactive stepping motor 7 can reach the same position no matter in forward rotation or reverse rotation, and the thrust adjustment precision requirement under open loop control is met.
According to the liquid rocket engine provided by the embodiment of the invention, the first gear 81 and the second gear 82 are connected through the torsion spring 9, and the first gear 81 and the second gear 82 are meshed with the rack 10, so that the rotation of the reactive stepping motor 7 is converted into the linear motion of the valve core of the gas regulating valve 8 through the meshing of the racks and the gears, and the reactive stepping motor 7 rotates for a certain angle according to a control instruction of the controller, so that the change of the opening of the valve core is converted, and the accurate regulation of the thrust of the liquid rocket engine is realized.
According to one embodiment of the invention, the pitch circle diameter of the first gear 81 and the second gear 82 is 20mm. It should be noted that, the pitch diameters of the first gear 81 and the second gear 82 may be adjusted according to actual requirements, and the pitch diameters of the first gear 81 and the second gear 82 are not specifically limited in the embodiments of the present invention.
In a specific embodiment, the transmission mechanism further includes a limiting device, where the limiting device is disposed on a side of the second gear 82 opposite to the first gear 81, and is used for limiting the axial direction of the second gear 82, so as to prevent the second gear 82 from falling off, improve transmission stability, and improve reliability of the system. The specific type of the limiting device is not particularly limited, and the limiting device can be designed according to practical use conditions, for example, the limiting device can adopt a retainer ring, a baffle plate and the like.
In a specific embodiment, the conventional mechanism further includes a linear displacement sensor for detecting the valve element opening of the gas regulating valve 6. The linear displacement sensor is connected with a valve core or a rack 10 of the gas regulating valve 8. The linear displacement sensor is electrically connected with the controller.
Specifically, the linear displacement sensor detects the moving distance of the valve core, and sends displacement data to the controller for processing to obtain the corresponding opening degree of the valve core. Under open loop control, the data of the linear displacement sensor is only used as a monitoring signal to monitor the valve core opening of the gas regulating valve 6, and the data do not participate in control and regulation. In other examples, the data collected by the linear displacement sensor participates in control, a feedback link is added, namely, the data of the linear displacement sensor is fed back to the controller, the controller repeatedly adjusts according to the deviation between the actual position and the target position of the valve core, and closed-loop control is realized, so that the diversity of system control is increased, the control mode is flexible, closed-loop control and open-loop control can be realized, and open-loop control is generally adopted.
Of course, the conventional mechanism may be provided with both the limiting device and the linear displacement sensor, and the respective setting modes thereof are as described above and will not be described again.
Optionally, the output shaft of the reactive stepper motor 7 is connected to the first gear 81 through a reduction gear pair, the reduction gear pair is built in the reactive stepper motor 7, and the reduction ratio of the reduction gear pair is 20:1-40:1, for example, the reduction ratio is 30:1. The output torque of the motor can be improved through the reduction gear pair, fine adjustment of the valve core of the gas regulating valve 8 can be realized, the thrust regulation resolution ratio of the liquid rocket engine can be improved, and the control precision can be improved.
Optionally, the controller sets the control frequency to 500-800 Hz, and the power-on time sequence of the reactive stepping motor 7 is four-phase four-beat. According to the invention, a four-phase four-beat control mode is adopted, and the set control frequency is 500-800 Hz, so that on one hand, the output torque of the motor is maximized at the moment, the reliability of the liquid rocket engine adjustment is ensured, and on the other hand, the step angle of the motor is reduced, and therefore, the resolution (the control precision of the opening degree of the finger valve) of the system is high enough.
Optionally, a liquid medium is stored in the reactive stepper motor 7 for conducting heat. Specifically, the liquid medium such as kerosene is filled in the reactive stepping motor 7, so that the heat conductivity can be improved, the heat dissipation effect of the reactive stepping motor 7 is better, and the reliability of the liquid rocket engine is improved.
The controller provides a constant current source for single-phase power supply of 500mA or double-phase power supply of 250mA for the reactive stepping motor 7, pulse signals are sent to the motor at a control frequency of 500Hz according to the requirement of a central controller of the liquid rocket, the motor runs one step every time one pulse signal is sent, the step angle is 0.5 DEG, and the forward rotation or the reverse rotation of the reactive stepping motor 7 is controlled by controlling the power supply time sequence of an internal coil winding of the reactive stepping motor 7, so that the aim of increasing or decreasing the thrust is fulfilled.
Referring to fig. 2, the reactive stepper motor 7 is provided with a first electrical connector 71 and a second electrical connector 72, and the controller is electrically connected to the reactive stepper motor 7 through the first electrical connector 71 and the second electrical connector 72 to realize communication. In actual use, the first electrical connector 71 and the second electrical connector 72 are usually used as the main control channels alternately, that is, assuming that the first electrical connector 71 is used as the main control channel in the first start, the second electrical connector 72 is used as the main control channel in the second start or test, so that the two electrical connectors can be ensured to keep the same use times basically, and the service life of the reactive stepper motor 7 is prolonged. In addition, when there is a failure in the controller communicating with the reactive stepper motor 7 through the first electrical connector 71, at this time, it is possible to switch to the second electrical connector 72 for communication, thereby improving reliability.
The reaction type stepping motor 7 is used as a core electric appliance component for thrust adjustment, is a direct executor of a controller instruction, receives a pulse signal of the controller, and opens or closes a valve core of the gas regulating valve 8 to a specified opening degree through the transmission of the first gear 81, the second gear 82 and the rack 10 at an operation rate of 2 ms/step according to the number of operation steps. For example, when the gear reference circle diameter is 20mm, the valve core corresponds to linear displacement of 0.0872mm and the total valve core travel of the gas regulating valve 8 is about 35mm, so that the maximum number of steps of operation of the reactive stepping motor 7 is about 401 steps, and the maximum rotation of the output shaft of the motor corresponds to about 200 degrees, and accordingly, mechanical stop structures such as limit stops can be arranged in a fan-shaped range of about 200 degrees in the motor, thereby ensuring the operation travel and improving the accuracy. It can be understood that the mechanical stop structure is arranged in the reaction type stepping motor 7, so that the output shaft of the reaction type stepping motor 7 can be circumferentially limited, for example, according to the actual use situation, the maximum circumferential rotation of the output shaft only needs 200 degrees, and then the mechanical stop structures can be respectively arranged at the positions of 0 degrees and 200 degrees. The cumulative calculation of the 7 steps of the reaction type stepping motor is started from the 0-degree position, the position where the motor automatically resets is fixed and automatically resets to the same position when the motor is electrified each time can be ensured by arranging the mechanical stop structure, and if the mechanical stop structure is not arranged, the circumferential direction of the output shaft can rotate by 360 degrees, so that the 0-step reference cannot be determined. Thus, the adjustment accuracy per run can be improved by the mechanical stop structure.
The reactive stepping motor 7 is adopted, only about ten watts of power is needed, on the premise that the control precision of the resolution is about 0.0872mm is met, the dynamic torque can reach 0.2 N.m, the static torque (namely the holding torque) can reach 0.3 N.m, and the larger load can be driven by smaller power, so that the reactive stepping motor 7 has one of the advantages. The reactive stepping motor 7 adopts open loop control, can be stabilized at the current position after running to the target position, prevents the reactive stepping motor 7 from shaking back and forth near the steady state position, causes the attenuation of output torque, and optimizes the working environment of the reactive stepping motor 7. In addition, since the rotor material of the reactive stepper motor 7 is a material easy to magnetize and has no magnetism, when the reactive stepper motor 7 changes the running state, the load to be overcome by the reactive stepper motor 7 is only the rotational inertia of the rotor, and a larger output torque margin can still be maintained in the starting and stopping processes of the motor.
In summary, the liquid rocket engine provided by the invention adopts the gas regulating valve 6 to regulate the thrust by one valve body, adopts the reactive stepping motor 7 and the transmission mechanism with the function of eliminating the hysteresis error in the thrust regulation process, and combines the set control frequency and the open loop control mode of the reactive stepping motor 7 to regulate the thrust of the liquid rocket engine, thereby playing a positive role in ensuring the running reliability of the motor and the accuracy and stability of the thrust regulation.
Wherein, the different running steps of the reactive stepping motor 7 correspond to different opening degrees of the gas regulating valve 6, and further correspond to different thrust forces. Therefore, the variable thrust parameters of the engine are calculated and calibrated before the rocket is delivered, and when the rocket is required to be subjected to variable thrust adjustment, the controller accurately sends corresponding instructions to the reactive stepping motor 7 according to the corresponding relation between the instructions calibrated in advance and the thrust, so that the engine can realize adjustment of different thrust.
Before the liquid rocket engine provided by the invention starts to work, the power-on program self-checking operation is performed except other preparation works. That is, in the no-load state, it is checked whether the full stroke operation of the reactive stepping motor 7 is normal and the reset operation is performed, and the start position is maintained at 0 steps, and at this time, the gas regulating valve 6 is in the closed state. When the engine receives an ignition instruction to start ignition, the valve core of the time sequence gas regulating valve 6 is required to be completely opened, the controller is installed and set to control the frequency to send a plurality of electric pulse signals to the reactive stepping motor 7, the reactive stepping motor 7 operates for a plurality of steps, and the valve core is completely opened within a certain time. In the running process of the engine, the controller sends pulse instructions of corresponding steps to the reactive stepping motor 7 according to the thrust regulation requirement, and the reactive stepping motor 7 runs corresponding steps according to the set running speed, so that the opening of the valve core is increased or decreased. After the reactive stepping motor 7 executes the pulse command sent by the controller, the pulse command is stabilized at a designated position and kept still, so that the stability of the working condition of the engine is ensured.
The turbo pump is a coaxial turbo pump or a non-coaxial turbo pump. For example, the turbine 5, the fuel pump 4, and the coolant pump 3 are mounted on the same shaft, are coaxially provided, and operate at the same rotational speed, and the turbine 5 is disposed on one side of both the fuel pump 4 and the coolant pump 3 or in the middle of the fuel pump 4 and the coolant pump 3. The fuel pump 4 and the oxidant pump 3 may share one turbine 5, or one turbine 5 may be provided separately. Specifically, the turbine 5 drives the oxidant pump 3 and the fuel pump 4 through one or more reduction gear boxes, or the turbine 5 is directly connected to the oxidant pump 3 and the fuel pump 4.
During the thrust adjustment process, various parameters of the liquid rocket engine can be changed. Taking a coaxial turbine pump as an example, the pressure after the pump is in direct proportion to the square of the rotating speed, the inlet pressures of the thrust chamber 1 and the gas generator 2 are changed in proportion, and the flow resistance of the flow paths of the two combustion assemblies of the thrust chamber 1 and the gas generator 2 are in proportion to the square of the flow. The mixing ratio of the propellant entering the thrust chamber 1 and the gas generator 2 can thus be maintained unchanged. The actual adjustment is affected by interference factors, and the mixing ratio of the two combustion components of the thrust chamber 1 and the gas generator 2 is slightly deviated, but the deviation is within the allowable range.
Wherein the turbine 5 is an impulse turbine. The turbine pressure ratio of the impulse turbine 5 is relatively large, and conditions are created for adding the second gas passage 22 and providing the gas regulating valve 6 on the second gas passage 22. In addition, the liquid rocket engine does not need to independently increase the flow resistance of each flow path of the system, and can correspondingly reduce the design power of the turbine pump, thereby improving the performance of the engine.
Optionally, the gas regulating valve 6 does not require the tightness of the valve in a locking state, so that the design difficulty is reduced. The possible gas leakage caused by the gas regulating valve 6 can be compensated for by engine adjustment calculations.
The oxidant pump 3 and the fuel pump 4 may be single stage pumps or multistage pumps. For example, the fuel pump 4 and the oxidizer pump 3 are each a single stage pump or are each a multistage pump. The turbine 5 is a single stage turbine. For example, the turbine 5 is a homopolar impulse turbine or a two-stage or multi-stage impulse turbine.
As shown in fig. 1, the fuel pump 4 communicates with the gas generator 2 and the thrust chamber 1 through a first tee. Specifically, the first tee pipe is an inlet pipe and an outlet pipe. The input branch pipe of the first three-way pipe is communicated with the output end of the fuel pump 4, the first output pipe of the first three-way pipe is communicated with the fuel inlet of the thrust chamber 1, and the second output pipe of the first three-way pipe is communicated with the fuel inlet of the gas generator 2. By providing a first tee, the piping arrangement between the fuel pump 4 and the gasifier 2 and the thrust chamber 1 is simplified.
Similarly, the oxidant pump 3 communicates with the gasifier 2 and the thrust chamber 1 via a second tee. Specifically, the second tee pipe is an inlet pipe and an outlet pipe. The input branch pipe of the second three-way pipe is communicated with the output end of the oxidant pump 3, the first output pipe of the second three-way pipe is communicated with the oxidant inlet of the thrust chamber 1, and the second output pipe of the second three-way pipe is communicated with the oxidant inlet of the gas generator 2. By providing a second tee, the piping arrangement between the oxidant pump 3 and the gasifier 2 and the thrust chamber 1 is simplified.
In one embodiment, the liquid rocket engine further includes an exhaust nozzle connected to the outlet of the second gas passage 22 and the gas output of the turbo pump, respectively. Wherein the pipe diameter of the exhaust nozzle is firstly reduced and then increased along the flow direction of the fluid.
The fuel gas discharged through the second fuel gas passage 22 and the fuel gas discharged from the worm wheel pump are recycled through the exhaust nozzle before being discharged into the atmosphere, so that the two fuel gas passages share one exhaust nozzle, and the structure is simplified. As the pipe diameter of the exhaust spray pipe is contracted and then increased, when the air flow flows in the first exhaust spray pipe, the air flow is accelerated through the contraction area and then the expansion area, and the thrust is provided for the engine by means of the exhaust air flow.
Specifically, the exhaust nozzle is a Laval pipe, and comprises a first connecting section and a second connecting section, wherein the large-diameter end of the first connecting section is connected with the outlet of the second fuel gas passage 22, and the small-diameter end of the first connecting section is connected with the small-diameter end of the second connecting section. Optionally, the cross sections of the first connecting section and the second connecting section are circular or square.
Optionally, the outlet of the second gas passage 22 is connected to a first exhaust nozzle, the pipe diameter of which decreases and increases along the flow direction of the fluid, and/or the gas output end of the turbine pump is provided with a second exhaust nozzle, the pipe diameter of which decreases and increases along the flow direction of the fluid. The second exhaust nozzle and the first exhaust nozzle may have the same structure and are both Laval tubes.
When the first exhaust nozzle is connected to only the outlet of the second gas passage 22, the gas discharged from the second gas passage 22 is recycled through the first exhaust nozzle before being discharged to the atmosphere. Under the condition that only the gas output end of the turbine pump is provided with the second exhaust nozzle, the gas exhausted by the turbine pump is recycled through the second exhaust nozzle before being exhausted into the atmosphere. In the case where the first exhaust nozzle is connected to the outlet of the second gas passage 22 and the second exhaust nozzle is provided at the gas output end of the turbo pump, the two exhaust nozzles are arranged in parallel to recycle the gas.
The embodiment of the invention also provides a liquid rocket which comprises a rocket body and the liquid rocket engine, wherein the liquid rocket engine is arranged on the rocket body. Wherein the liquid rocket is a single-stage rocket or a multi-stage rocket.
It should be noted that the above-mentioned embodiments are merely for illustrating the technical solution of the present invention, and not for limiting the same, and although the present invention has been described in detail with reference to the above-mentioned embodiments, it should be understood by those skilled in the art that the technical solution described in the above-mentioned embodiments may be modified or some technical features may be equivalently replaced, and these modifications or substitutions do not make the essence of the corresponding technical solution deviate from the spirit and scope of the technical solution of the embodiments of the present invention.
Claims (10)
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| CN202411478474.7A CN119412246A (en) | 2024-10-22 | 2024-10-22 | Liquid rocket engine and liquid rocket |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2484285C1 (en) * | 2011-12-29 | 2013-06-10 | Николай Борисович Болотин | Oxygen-hydrogen liquid-propellant engine |
| CN109915280A (en) * | 2019-03-14 | 2019-06-21 | 北京星际荣耀空间科技有限公司 | A kind of electronic variable thrust rocket engine and the rocket with it |
| CN214741725U (en) * | 2021-05-12 | 2021-11-16 | 北京星际荣耀空间科技股份有限公司 | Open type variable thrust rocket engine and rocket |
| CN115596572A (en) * | 2022-10-28 | 2023-01-13 | 北京星河动力装备科技有限公司（Cn） | Liquid rocket, liquid rocket engine propellant mixing ratio adjustment system and method |
| CN118564370A (en) * | 2024-07-31 | 2024-08-30 | 北京星河动力装备科技有限公司 | Liquid rocket engine and liquid rocket |
-
2024
- 2024-10-22 CN CN202411478474.7A patent/CN119412246A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2484285C1 (en) * | 2011-12-29 | 2013-06-10 | Николай Борисович Болотин | Oxygen-hydrogen liquid-propellant engine |
| CN109915280A (en) * | 2019-03-14 | 2019-06-21 | 北京星际荣耀空间科技有限公司 | A kind of electronic variable thrust rocket engine and the rocket with it |
| CN214741725U (en) * | 2021-05-12 | 2021-11-16 | 北京星际荣耀空间科技股份有限公司 | Open type variable thrust rocket engine and rocket |
| CN115596572A (en) * | 2022-10-28 | 2023-01-13 | 北京星河动力装备科技有限公司（Cn） | Liquid rocket, liquid rocket engine propellant mixing ratio adjustment system and method |
| CN118564370A (en) * | 2024-07-31 | 2024-08-30 | 北京星河动力装备科技有限公司 | Liquid rocket engine and liquid rocket |
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