CN112722334A - Carrier rocket and rocket sublevel recovery control method - Google Patents
Carrier rocket and rocket sublevel recovery control method Download PDFInfo
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- CN112722334A CN112722334A CN202110190455.4A CN202110190455A CN112722334A CN 112722334 A CN112722334 A CN 112722334A CN 202110190455 A CN202110190455 A CN 202110190455A CN 112722334 A CN112722334 A CN 112722334A
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- B—PERFORMING OPERATIONS; TRANSPORTING
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- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
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Abstract
The embodiment of the application provides a carrier rocket and a rocket sublevel recovery control method. In the rocket substage of the launch vehicle provided by the embodiment of the application, the fuel consumption of the second engine is less than that of the first engine during the operation process per unit time because the maximum thrust of the second engine is less than that of the first engine. Therefore, in the process of the return section of the rocket sublevel, the control device controls the second engine positioned at the second end of the rocket body and the grid rudder close to the first end of the rocket body to adjust the real-time posture of the rocket sublevel, so that the fuel consumption can be reduced in the process of recovering the rocket sublevel.
Description
Technical Field
The application relates to the technical field of aircrafts, in particular to a carrier rocket and a rocket sublevel recovery control method.
Background
With the development of aerospace technology, the number of the carrier rockets launched every year in the world is more and more, and the corresponding capital investment is also more and more, so how to reduce the launch cost of the carrier rockets, and effectively recovering the rocket sublevels is the current key research direction. At present, the rocket substage in the carrier rocket is only provided with an engine for pushing the carrier rocket body to fly, and the engine is a variable-thrust engine with large thrust depth so as to push the carrier rocket body to enter a preset flying orbit. Therefore, during the rocket substage recovery process, the posture adjustment of the rocket substage can be completed only by the engine.
However, in the process of adjusting the posture of the rocket substage, the power required by the rocket substage is far less than the thrust for pushing the carrier rocket body, and at the moment, the posture of the rocket substage is adjusted by continuously depending on the power generated by the variable thrust engine with large thrust depth, so that the fuel consumption is large.
Disclosure of Invention
The application provides a carrier rocket and a rocket sublevel recovery control method aiming at the defects of the existing mode, and is used for solving the technical problem that the fuel consumption is large in the rocket sublevel recovery process in the prior art.
In a first aspect, embodiments of the present application provide a launch vehicle, the launch vehicle including a rocket substage, the rocket substage including:
an arrow body;
the first engine is positioned at the first end of the rocket body and used for pushing the carrier rocket body to fly in the takeoff section;
the second engine is positioned at a second end, opposite to the first end, of the arrow body, and the maximum thrust of the second engine is smaller than that of the first engine;
at least two grid rudders which are arranged along the circumferential direction outside the peripheral wall of the arrow body and are close to the first end;
and a control device electrically connected with the second engine and the grid rudder and used for controlling the second engine and/or the grid rudder in the return section of the rocket substage.
Optionally, the rocket substage further comprises: the environment information acquisition device is used for acquiring real-time operation parameters of the rocket sublevel;
and the control device is in communication connection with the environmental information acquisition device and is used for controlling the second engine and/or the grid rudder at the return section of the rocket sublevel according to the real-time operation parameters so as to adjust the real-time attitude of the rocket sublevel.
Optionally, the first engine is in communication with the control device;
the control device is used for controlling the second engine and the grid rudder to adjust the real-time posture of the rocket sublevel, enabling the second end of the rocket body to face the ground and controlling the first engine to stall when determining that the rocket sublevel is separated from the carrier rocket body according to the real-time operation parameters; after the second end of the rocket body is directed to the ground, the second motor and the grid rudder are controlled so that the descending speed of the rocket stage is less than the preset speed.
Optionally, in a radial plane of the arrow body, the grid rudders are symmetrically arranged about the radial direction of the arrow body;
the control device is also used for controlling the grid rudder to be unfolded when the rocket sublevel is separated from the carrier rocket body; and controlling the deflection angle of the grid rudder in real time in the process of adjusting the real-time posture of the rocket sublevel and enabling the second end of the rocket body to face the ground.
Optionally, the rocket sub-stage further comprises a supporting and damping device, which is located at the second end of the rocket body and is telescopically arranged inside the rocket body;
and the control device is used for controlling the support of the supporting damping device to extend out of the interior of the rocket body and expand when determining that the distance between the rocket sublevel and the ground is less than the preset distance according to the real-time operation parameters.
In a second aspect, the present embodiment provides a method for controlling recovery of a rocket substage in a launch vehicle according to the first aspect, including:
controlling a second engine and/or a grid rudder of the rocket sublevel at a return section of the rocket sublevel according to the real-time operation parameters of the rocket sublevel so as to adjust the real-time attitude of the rocket sublevel; the first engine and the grid rudder are positioned at the first end of the rocket body of the rocket stage; the second motor is located at the second end of the arrow body, and the maximum thrust of the second motor is smaller than the maximum thrust of the first motor.
Optionally, controlling a second motor and/or a grid rudder of the rocket substage at a return section of the rocket substage to adjust a real-time attitude of the rocket substage according to real-time operating parameters of the rocket substage, comprising:
when the rocket substage is determined to be separated from the carrier rocket body according to the real-time operation parameters, controlling a second engine and a grid rudder to adjust the real-time posture of the rocket substage, enabling the second end of the rocket body to face the ground, and controlling the first engine to stop; after the second end of the rocket body is directed to the ground, the second motor and the grid rudder are controlled so that the descending speed of the rocket stage is less than the preset speed.
Optionally, when it is determined that the rocket substage is separated from the carrier rocket body according to the real-time operation parameters, controlling the second engine and the grid rudder to adjust the real-time attitude of the rocket substage so that the second end of the rocket body faces the ground includes:
controlling the grid rudder to expand when the rocket sublevel is separated from the carrier rocket body according to the real-time operation parameters;
and in the process of adjusting the real-time posture of the rocket sublevel and enabling the second end of the rocket body to face the ground, controlling the deflection angle of the grid rudder in real time according to the real-time operation parameters.
Optionally, after controlling the second engine and the grid rudder to make the descent speed of the rocket substage less than the preset speed, the method further comprises:
and controlling the support of the supporting and damping device to extend out of the interior of the rocket body and expand when the distance between the rocket sublevel and the ground is determined to be smaller than the preset distance according to the real-time operation parameters.
Optionally, before controlling the second engine and/or the grid rudder of the rocket substage in the return section of the rocket substage to adjust the real-time attitude of the rocket substage according to the real-time operation parameters of the rocket substage, the method further includes:
and controlling the grid rudder to be in a storage state before the rocket substage is separated from the carrier rocket body according to the real-time operation parameters, wherein the grid rudder in the storage state is parallel to the outer side of the peripheral wall of the rocket body.
The beneficial technical effects brought by the technical scheme provided by the embodiment of the application comprise:
in the rocket substage of the launch vehicle provided by the embodiment of the application, the fuel consumption of the second engine is less than that of the first engine during the operation process per unit time because the maximum thrust of the second engine is less than that of the first engine. Therefore, in the process of the return section of the rocket sublevel, the control device controls the second engine positioned at the second end of the rocket body and the grid rudder close to the first end of the rocket body to adjust the real-time posture of the rocket sublevel, so that the fuel consumption can be reduced in the process of recovering the rocket sublevel.
Additional aspects and advantages of the present application will be set forth in part in the description which follows and, in part, will be obvious from the description, or may be learned by practice of the present application.
Drawings
The foregoing and/or additional aspects and advantages of the present application will become apparent and readily appreciated from the following description of the embodiments, taken in conjunction with the accompanying drawings of which:
fig. 1 is a schematic structural diagram of a rocket substage provided in an embodiment of the present application;
FIG. 2 is a schematic diagram of a rocket stage structure according to an embodiment of the present disclosure;
fig. 3 is a schematic expansion flow chart of a rocket-stage recovery control method according to an embodiment of the present application.
Description of reference numerals:
10-arrow body;
20-a first engine;
30-a second engine;
40-grid rudder;
50-a control device;
60-an environmental information acquisition device;
70-supporting a shock-absorbing device; 71-bracket.
Detailed Description
Reference will now be made in detail to the present application, examples of which are illustrated in the accompanying drawings, wherein like reference numerals refer to the same or similar parts or parts having the same or similar functions throughout. In addition, if a detailed description of the known art is not necessary for illustrating the features of the present application, it is omitted. The embodiments described below with reference to the drawings are exemplary only for the purpose of explaining the present application and are not to be construed as limiting the present application.
It will be understood by those within the art that, unless otherwise defined, all terms (including technical and scientific terms) used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this application belongs. It will be further understood that terms, such as those defined in commonly used dictionaries, should be interpreted as having a meaning that is consistent with their meaning in the context of the prior art and will not be interpreted in an idealized or overly formal sense unless expressly so defined herein.
As used herein, the singular forms "a", "an", "the" and "the" are intended to include the plural forms as well, unless the context clearly indicates otherwise. It will be further understood that the terms "comprises" and/or "comprising," when used in this specification, specify the presence of stated features, integers, steps, operations, elements, and/or components, but do not preclude the presence or addition of one or more other features, integers, steps, operations, elements, components, and/or groups thereof. As used herein, the term "and/or" includes all or any element and all combinations of one or more of the associated listed items.
The terms referred to in this application will first be introduced and explained:
rocket substages refer to the structural components of a multi-stage launch vehicle used to propel a payload into a predetermined trajectory and thrown away after a single stage of operation is completed.
At present, the existing carrier rocket is often a multi-stage carrier rocket and comprises a plurality of rocket substages, and each rocket substage is provided with a rocket body structure and a power device. The whole carrier rocket is pushed to accelerate to fly after the first substage of the multistage carrier rocket is ignited, the first rocket substage is separated from the whole carrier rocket after the first rocket substage is ignited, the carrier rocket is continuously pushed to fly after the second rocket substage is ignited, the rest is done in sequence until the effective load is accelerated to a preset speed and sent to a preset orbit, and the separated rocket substage can fall into a designated rocket debris falling area in the ground.
The invention of the application researches and discovers that the rocket substage in the current carrier rocket is only provided with an engine for pushing the carrier rocket body to fly, and the engine is mostly a variable-thrust engine with large thrust depth so as to push the carrier rocket body to enter a preset flying orbit. Therefore, during the rocket substage recovery process, the posture adjustment of the rocket substage can be completed only by the engine.
However, after the rocket substage is separated from the carrier rocket body, the residual fuel carried by the rocket substage is greatly reduced, so that the weight of the rocket substage is greatly reduced, the inertia of the rocket substage is reduced, and in the process of adjusting the posture of the rocket substage by using the high-thrust depth variable-thrust engine, the posture adjustment precision is low, so that the landing precision of the rocket substage is low easily, and the recovery success rate of the rocket substage is low.
Moreover, the fuel consumption of the variable-thrust engine with high thrust depth is higher, and more residual fuel needs to be carried by the rocket substage, so that the weight of the carrier rocket is increased, and the thrust for launching the carrier rocket is increased.
The rocket sublevel, the recovery control method thereof and the carrier rocket aim to solve the technical problems in the prior art.
The following describes the technical solutions of the present application and how to solve the above technical problems with specific embodiments.
The embodiment of the application provides a carrier rocket which comprises a rocket substage, wherein the structural schematic diagram of the rocket substage is shown in figure 1, and the structural framework schematic diagram of the rocket substage is shown in figure 2. The rocket substage comprises: an arrow body 10; a first engine 20, located at the first end of the rocket body 10, for propelling the carrier rocket body to fly in the takeoff section; a second motor 30 located at a second end of the arrow body 10 opposite to the first end, and a maximum thrust of the second motor 30 is smaller than a maximum thrust of the first motor 20; at least two grid rudders 40 arranged along the circumferential direction outside the peripheral wall of the arrow body 10 and close to the first end; and a control device 50 electrically connected to the second motor 30 and the grid rudder 40 for controlling the second motor 30 and/or the grid rudder 40 at a return stage of the rocket stage.
In the rocket substage provided in the embodiment of the present application, since the maximum thrust of the second engine 30 is smaller than the maximum thrust of the first engine 20, the fuel consumption of the second engine 30 is smaller than the fuel consumption of the first engine 10 during the operation per unit time. Thus, during the return section of the rocket substage, the second motor 20 located at the second end of the rocket body 10 and the grid rudder 40 located near the first end of the rocket body 10 are controlled by the control device 50 to adjust the real-time attitude of the rocket substage, thereby enabling to reduce the fuel consumption during the recovery of the rocket substage.
It should be noted that in the embodiments of the present application, the rocket substage is specifically the first rocket substage of the launch vehicle. The takeoff phase refers to the process of launching the launch vehicle from launch to the point where the predetermined flight trajectory is reached. In the takeoff section of the carrier rocket, the first engine 20 pushes the carrier rocket to fly to a preset flying orbit, after the sub-stage of the rocket is separated from the carrier rocket body, the first engine 20 stops working after flameout, the second engine 30 and the grid rudder 40 are controlled by the control device 40 to adjust the real-time posture of the sub-stage of the rocket, so that the sub-stage of the rocket enters the atmosphere according to the preset recovery orbit, and finally the soft landing of the sub-stage of the rocket is realized.
In the embodiment of the present application, the first engine 20 is a variable thrust engine having a large thrust depth, and the second engine 30 is a variable thrust engine having a small thrust depth. The control precision of the variable-thrust engine with small thrust depth is higher than that of the variable-thrust engine with large thrust depth.
Compared with the prior art that the attitude of the rocket substage is adjusted by relying on the first engine 20 with higher maximum thrust, the rocket substage provided by the embodiment of the application adjusts and controls the real-time attitude of the rocket substage through the mutual matching of the second engine 30 with lower maximum thrust and the grid rudder 40, so that the fuel consumption can be reduced in the rocket substage recovery process.
Those skilled in the art have found, through evaluation, that when the first engine 20 is a variable thrust engine with a large thrust depth, in the rocket sublevel recovery process, the rocket sublevel needs to carry at least 50 tons of fuel to meet the fuel requirement of rocket sublevel recovery; in contrast, with the second engine 30 with low thrust and variable thrust, the rocket substage only needs to carry 10 tons of fuel during the rocket substage recovery process, so as to meet the fuel requirement of rocket substage recovery. Therefore, the rocket substage provided by the embodiment of the application can greatly reduce the requirement of recovered fuel and can greatly reduce the fuel carried by the rocket substage.
Moreover, the thrust generated by the second engine 30 is matched with the mass of the rocket sublevel, so that the control precision of the second engine 30 is improved, the posture adjustment precision of the rocket sublevel can be improved through the mutual matching of the second engine 30 and the grid rudder 40, the landing precision of the rocket sublevel can be further improved, and the recovery success rate of the rocket sublevel can be improved.
In one embodiment of the present application, the rocket substage further comprises an environmental information collecting device 60 for collecting real-time operating parameters of the rocket substage; the control device 50 is in communication with the environmental information gathering device 60 for controlling the second motor 30 and/or the grid rudder 40 in the return section of the rocket substage in accordance with the real-time operating parameters to adjust the real-time attitude of the rocket substage.
In the embodiment of the present application, the environmental information collecting device 60 collects the real-time operating parameters of the rocket sublevel, and the control device 50 can determine the real-time operating state of the rocket itself according to the real-time operating parameters of the rocket sublevel, so that the control device 50 can control the second engine 30 and/or the grid rudder 40 at the return section of the rocket sublevel, thereby adjusting the real-time attitude of the rocket sublevel.
It should be noted that, in the embodiment of the present application, the real-time operation parameters of the rocket substage include real-time trajectory information of the rocket substage, remaining amount of fuel in the rocket substage, and air flow strength information in the atmosphere where the rocket substage is located.
In one embodiment of the present application, the first engine 20 is communicatively coupled to the control device 50; the control device 50 is used for controlling the second engine 30 and the grid rudder 40 to adjust the posture of the rocket sublevel when determining that the rocket sublevel is separated from the carrier rocket body according to the real-time operation parameters, so that the second end of the rocket body 10 in the rocket sublevel faces the ground, and controlling the first engine 20 to extinguish; after the second end of the rocket body 10 is directed toward the ground, the second motor 30 and the grid rudder 40 are controlled so that the descent speed of the rocket stage is less than a preset speed.
Optionally, when the rocket substage is separated from the carrier rocket body, the control device 50 determines that the rocket substage is separated from the carrier rocket body according to the real-time operation parameters sent by the environmental information collection device 60, at this time, the control device 50 sends a control signal to the first engine 20 to control the first engine 20 to shut down, so that the first engine 20 stops working. The control device 50 sends a control signal to the second engine 30 and the grid rudder 40, and the second engine 30 and the grid rudder 40 adjust the corresponding working state according to the control signal to adjust the posture of the rocket sublevel, so that the second end of the rocket body 10 in the rocket sublevel faces the ground to realize the soft landing of the rocket sublevel.
It should be noted that the first engine 20 may be controlled to be turned off by another control device, or a control program may be stored in a storage unit of the first engine 20 in advance, and the control unit of the first engine 20 may control the first engine 20 to be turned off by operating the control program.
Optionally, the second motor 30 comprises a nozzle, and the nozzle of the second motor 30 faces away from the first end, so that after the second end of the rocket body 10 faces the ground in the rocket stage, the thrust generated by the second motor 30 can slow down the descending speed of the rocket stage, and optionally, in order to ensure the stability during descending of the rocket stage, as shown in fig. 1, the axis of the second motor 30 is coincident with the axis D of the rocket body 10.
After determining that the second end of the rocket body 10 faces the ground according to the real-time operation parameters sent by the environmental information acquisition device 60, the control device 50 controls the second engine 30 and the grid rudder 40 to adjust the real-time posture of the rocket sub-stage, so that the second end keeps the real-time posture facing the ground, and the descent speed of the rocket sub-stage is smaller than the preset speed. In the process, the descending speed of the rocket sublevel is reduced through the second engine 30 and the grid rudder 40, the impact force of the rocket sublevel on the ground can be reduced, the rocket body 10 of the rocket sublevel is prevented from being violently expanded with the ground, the soft landing of the rocket sublevel can be realized, and the recovery success rate of the rocket sublevel can be improved.
In the embodiment of the present application, the thrust generated by the second engine 30 can slow down the descent speed of the rocket substage, that is, the thrust generated by the second engine 30 only needs to resist the descent trend of the rocket substage. In the embodiment of the present application, the second motor 30 is a variable thrust motor with a small thrust depth, and the control device 50 may control the more appropriate thrust generated by the second motor 30 to slow down the descent speed of the rocket stage. Compared with the prior art which only depends on the first engine 20 to slow down the descent speed of the rocket substage, the second engine 30 consumes less fuel, so that fuel can be saved.
Moreover, with the reduction of the fuel required in the rocket substage recovery process, the fuel carried by the carrier rocket is reduced when the carrier rocket is launched, so that the load of the carrier rocket can be reduced.
In one embodiment of the present application, the grid rudder 40 comprises at least two grid rudders 40, the grid rudders 40 are arranged along the circumference of the arrow body 10, and on the radial plane of the arrow body 10, the grid rudders 40 are symmetrically arranged with respect to the radial direction of the arrow body 10.
In the embodiment of the present application, the rocket substage is provided with two grid rudders 40, and those skilled in the art can set a suitable number of grid rudders 40 according to actual requirements. Before the rocket substage is separated from the launch vehicle body, the grid rudder 40 is in a retracted state, i.e., the grid rudder 40 is parallel to the outer side of the peripheral wall of the rocket body 10.
The control device 50 is also used for controlling the grid rudder 40 to be unfolded when the rocket substage is separated from the carrier rocket body; and controlling the deflection angle of the grid rudder 40 in real time in the process of adjusting the real-time attitude of the rocket sub-stage so that the second end of the rocket body 10 faces the ground.
In the embodiment of the application, when the control device 50 determines that the rocket sublevel is separated from the carrier rocket body according to the real-time operation parameters sent by the environmental information acquisition device 60, the control device controls the grid rudder 40 to be unfolded, so that the grid rudder 40 is perpendicular to the outer side of the peripheral wall of the rocket body 10. As shown in fig. 1, the grid rudder 40 is in a deployed state.
The control device 50 also controls the deflection angle of the grid rudder 40 in real time in the process of adjusting the real-time attitude of the rocket sub-stage so that the second end of the rocket body 10 faces the ground, so that the second end maintains the real-time attitude of the rocket sub-stage, and the attitude of the rocket sub-stage is prevented from deflecting.
Optionally, the control device 50 calculates a deflection angle required by the grid rudder 40 at the next moment in real time according to the real-time operation parameters sent by the environment information collecting device 60, and controls the grid rudder 40 to rotate according to the required deflection angle, so as to adjust the deflection angle of the grid rudder 40 in real time. Therefore, in the return section of the rocket sublevel, the control device 50 can calculate the deflection angle required by the grid rudder 40 at the next moment in real time according to the current environmental information of the rocket sublevel, so that the attitude adjustment precision of the rocket sublevel can be improved, the landing precision of the rocket sublevel can be improved, and the recovery success rate of the rocket sublevel can be improved.
Furthermore, the descent speed of the rocket substage can be reduced by controlling the deflection angle of the grid rudder 40 during the rocket substage recovery process.
In one embodiment of the present application, the rocket stage further includes a support dampening device 70 located at the second end of the rocket body 10 and telescopically disposed within the rocket body 10. In the embodiment of the application, by arranging the supporting and damping device 70, the rocket sublevel can absorb the buffered energy and stabilize the rocket body 10 through the supporting and damping device 70 in the landing process of the rocket sublevel, so that the rocket sublevel can land vertically and safely and stably.
In the embodiment of the present application, when the control device 50 determines that the distance between the rocket stage and the ground is smaller than the preset distance according to the real-time operation parameters sent by the environmental information acquisition device 60, the support 71 for supporting the damping device 70 is controlled to extend and expand from the interior of the rocket body 10. The buffered energy is absorbed by the bracket 71 and the rocket body 10 is stabilized, so that the rocket stage safely and stably vertically lands.
It should be noted that the mount 71 supporting the shock absorbing device 70 is telescopically provided inside the rocket body 10 before the rocket substage lands to avoid affecting the flight of the launch vehicle and the attitude adjustment process of the rocket substage.
Based on the same inventive concept, the embodiment of the application provides a recovery control method for rocket substages in a carrier rocket, which is provided by the embodiments and comprises the following steps:
controlling a second engine 30 and/or a grid rudder 40 of the rocket sublevel at a return section of the rocket sublevel according to real-time operation parameters of the rocket sublevel to adjust a real-time attitude of the rocket sublevel; the first engine 20 and the grid rudder 40 are located at a first end of the rocket body 10 of the rocket stage; the second motor 30 is located at the second end of the arrow body 10, and the maximum thrust of the second motor 30 is smaller than the maximum thrust of the first motor 20.
Optionally, the control device 50 controls the second engine 30 and/or the grid rudder 40 at the rocket sublevel in the return section of the rocket sublevel according to the real-time operation parameters of the rocket sublevel sent by the environmental information acquisition device 60 to adjust the real-time attitude of the rocket sublevel; the first engine 20 and the grid rudder 40 are located at a first end of the rocket body 10 of the rocket stage; a second motor 30 is located at a second end of the arrow body 10.
In an embodiment of the present application, a rocket-stage recovery control deployment method is provided, a flow diagram of the method is shown in fig. 3, and the method includes the following steps S301 to S303:
s301, when the rocket substages are separated from the carrier rocket body according to the real-time operation parameters, controlling the second engine 30 and the grid rudder 40 to adjust the real-time posture of the rocket substages, enabling the second end of the rocket body 10 to face the ground, and controlling the first engine 20 to stop working.
Optionally, when determining that the rocket substage is separated from the carrier rocket body according to the real-time operation parameters of the rocket substage sent by the environmental information acquisition device 60, the control device 50 sends a control signal to the second engine 30 and the grid rudder 40, controls the second engine 30 and the grid rudder 40 to adjust the real-time attitude of the rocket substage, so that the second end of the rocket body 10 faces the ground, and adjusts the real-time attitude of the rocket substage, so that the second end of the rocket body 10 maintains the real-time attitude of the rocket substage facing the ground. The control device 50 sends a control signal to the first engine 20 to control the first engine 20 to be turned off, so that the first engine 20 stops operating.
S302, after the second end of the rocket body 10 faces the ground, the second motor 30 and the grid rudder 40 are controlled so that the descent speed of the rocket stage is less than a preset speed.
Alternatively, after the second end of the rocket body 10 faces the ground, the control device 50 sends a control signal to the second engine 30 and the grid rudder 40, and the descent speed of the rocket substage is slowed down by controlling the thrust generated by the second engine 30 and by controlling the deflection angle of the grid rudder 40, so that the descent speed of the rocket substage is less than the preset speed, and the safe landing of the rocket substage can be ensured.
And S303, controlling the support 71 supporting the damping device 70 to extend out of the interior of the rocket body 10 and expand when the distance between the rocket sublevel and the ground is determined to be smaller than the preset distance according to the real-time operation parameters.
Optionally, when the control device 50 determines that the distance between the rocket substage and the ground is less than the preset distance according to the real-time operation parameters of the rocket substage sent by the environmental information acquisition device 60, the bracket 71 supporting the damping device 70 is controlled to extend out of the interior of the rocket body 10 and expand. The support 71 is made of elastic materials, or the support 71 is made of hydraulic shock-absorbing rods, so that the support can play a role in buffering and shock absorption in the rocket stage landing process.
In an embodiment of the application, the step S301 specifically includes:
the control device 50 controls the grid rudder 40 of the grid rudder 40 to be unfolded when determining that the rocket sublevel is separated from the carrier rocket body according to the real-time operation parameters of the rocket sublevel sent by the environment information acquisition device 60. In the present embodiment, the grid rudder 40 includes at least two grid rudders 40.
In the process of adjusting the real-time posture of the rocket sublevel to enable the second end of the rocket body 10 to face the ground, the control device 50 controls the deflection angle of the grid rudder 40 in real time according to the real-time operation parameters of the rocket sublevel sent by the environment information acquisition device 60.
In one embodiment of the present application, before controlling the second motor 30 and/or the grid rudder 40 of the rocket substage at the return section of the rocket substage to adjust the real-time attitude of the rocket substage according to the real-time operation parameters of the rocket substage, further comprises:
the control device 50 determines that the grid rudder 40 is in the storage state before the rocket substages are separated from the carrier rocket body according to the real-time operation parameters of the rocket substages sent by the environmental information acquisition device 60, and the grid rudder 40 in the storage state is parallel to the outer side of the peripheral wall of the rocket body 10.
By applying the embodiment of the application, at least the following beneficial effects can be realized:
in the rocket substage of the launch vehicle provided in the embodiment of the present application, since the maximum thrust of the second engine 30 is smaller than the maximum thrust of the first engine 20, the fuel consumption of the second engine 30 is smaller than the fuel consumption of the first engine 20 during the operation per unit time. Therefore, during the return section of the rocket substage, the control device 50 controls the second engine 20 located at the second end of the rocket body 10 and the grid rudder 40 close to the first end of the rocket body 10 to adjust the real-time posture of the rocket substage, and compared with the prior art that the posture of the rocket substage is adjusted by the first engine 20, the rocket substage provided by the embodiment of the application can reduce the fuel consumption during the rocket substage recovery process.
Moreover, in the return section process of the rocket sublevel of the carrier rocket provided by the embodiment of the application, the real-time attitude of the rocket sublevel is adjusted and controlled together through the mutual matching of the second engine 30 and the grid rudder 40, so that the attitude adjustment precision of the rocket sublevel can be improved, the landing precision of the rocket sublevel can be further improved, and the recovery success rate of the rocket sublevel can be improved.
Those of skill in the art will appreciate that the various operations, methods, steps in the processes, acts, or solutions discussed in this application can be interchanged, modified, combined, or eliminated. Further, other steps, measures, or schemes in various operations, methods, or flows that have been discussed in this application can be alternated, altered, rearranged, broken down, combined, or deleted. Further, steps, measures, schemes in the prior art having various operations, methods, procedures disclosed in the present application may also be alternated, modified, rearranged, decomposed, combined, or deleted.
In the description of the present application, it is to be understood that the terms "center", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience in describing the present application and simplifying the description, but do not indicate or imply that the referred device or element must have a particular orientation, be constructed in a particular orientation, and be operated, and thus should not be construed as limiting the present application.
The terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of the present application, "a plurality" means two or more unless otherwise specified.
In the description of the present application, it is to be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present application can be understood in a specific case by those of ordinary skill in the art.
In the description herein, particular features, structures, materials, or characteristics may be combined in any suitable manner in any one or more embodiments or examples.
The foregoing is only a partial embodiment of the present application, and it should be noted that, for those skilled in the art, several modifications and decorations can be made without departing from the principle of the present application, and these modifications and decorations should also be regarded as the protection scope of the present application.
Claims (10)
1. A launch vehicle comprising a rocket substage, wherein the rocket substage comprises:
an arrow body;
the first engine is positioned at the first end of the rocket body and used for pushing the carrier rocket body to fly in a takeoff section;
a second motor located at a second end of the arrow body opposite the first end, the second motor having a maximum thrust force less than a maximum thrust force of the first motor;
at least two grid rudders arranged along the circumferential direction outside the peripheral wall of the arrow body and close to the first end;
a control device electrically connected to the second motor and the grid rudder for controlling the second motor and/or the grid rudder at a return section of the rocket substage.
2. A launch vehicle according to claim 1, characterised in that it further comprises: the environment information acquisition device is used for acquiring real-time operation parameters of the rocket sublevel;
and the control device is in communication connection with the environmental information acquisition device and is used for controlling the second engine and/or the grid rudder at the return section of the rocket sublevel according to the real-time operation parameters so as to adjust the real-time attitude of the rocket sublevel.
3. A launch vehicle according to claim 2, characterised in that said first engine is communicatively connected to said control device;
the control device is used for controlling the second engine and the grid rudder to adjust the real-time posture of the rocket sublevel, enabling the second end of the rocket body to face the ground and controlling the first engine to stall when the rocket sublevel is determined to be separated from the carrier rocket body according to the real-time operation parameters; after the second end of the rocket body is directed toward the ground, controlling the second engine and the grid rudder so that the descent speed of the rocket substage is less than a preset speed.
4. A launch vehicle according to claim 2, characterised in that, in the radial plane of the arrow body, the grid rudders are arranged symmetrically with respect to the radial direction of the arrow body;
the control device is also used for controlling the grid rudder to be unfolded when the rocket substage is separated from the carrier rocket body; and controlling the deflection angle of the grid rudder in real time in the process of adjusting the real-time posture of the rocket sublevel to enable the second end of the rocket body to face the ground.
5. A launch vehicle according to claim 2, further comprising a support shock absorber located at said second end of said rocket body and telescopically disposed within said rocket body;
and the control device is used for controlling the support of the supporting and damping device to extend out of the interior of the rocket body and expand when the control device determines that the distance between the rocket sublevel and the ground is smaller than a preset distance according to the real-time operation parameters.
6. A method of controlling recovery of a secondary stage of a rocket in a launch vehicle according to any one of claims 2 to 5, comprising:
controlling a second engine and/or a grid rudder of the rocket sublevel at a return section of the rocket sublevel according to the real-time operation parameters of the rocket sublevel so as to adjust the real-time attitude of the rocket sublevel; the first engine and grid rudder are located at a first end of a rocket body of the rocket stage; the second motor is located at the second end of the arrow body, and the maximum thrust of the second motor is less than the maximum thrust of the first motor.
7. The recovery control method of claim 6, wherein controlling a second motor and/or a grid rudder of the rocket substage at a return section of the rocket substage to adjust a real-time attitude of the rocket substage according to real-time operating parameters of the rocket substage comprises:
when the rocket substage is determined to be separated from the carrier rocket body according to the real-time operation parameters, controlling the second engine and the grid rudder to adjust the real-time posture of the rocket substage, enabling the second end of the rocket body to face the ground, and controlling the first engine to stall; after the second end of the rocket body is directed toward the ground, controlling the second engine and the grid rudder so that the descent speed of the rocket substage is less than a preset speed.
8. The recovery control method of claim 7, wherein said controlling the second engine and the grid rudder to adjust the real-time attitude of the rocket substage such that the second end of the rocket body is directed toward the ground when it is determined that the rocket substage is separated from the launch vehicle body based on the real-time operating parameters comprises:
controlling the grid rudder to be unfolded when the rocket substage is determined to be separated from the carrier rocket body according to the real-time operation parameters;
and controlling the deflection angle of the grid rudder in real time according to the real-time operation parameters in the process of adjusting the real-time posture of the rocket sublevel and enabling the second end of the rocket body to face the ground.
9. The recovery control method according to claim 8, wherein after the controlling the second engine and the grid rudder so that the descent speed of the rocket substage is less than a preset speed, further comprising:
and controlling a support for supporting a damping device to extend out of the rocket body and expand when the distance between the rocket sublevel and the ground is determined to be smaller than a preset distance according to the real-time operation parameters.
10. The recovery control method of claim 6, further comprising, before controlling a second motor and/or a grid rudder of the rocket substage at a return section of the rocket substage to adjust a real-time attitude of the rocket substage according to real-time operating parameters of the rocket substage:
and controlling the grid rudder to be in a storage state before determining that the rocket substage is separated from the carrier rocket body according to the real-time operation parameters, wherein the grid rudder in the storage state is parallel to the outer side of the peripheral wall of the rocket body.
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| CN112722334B (en) | 2022-05-17 |
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