Carrier rocket booster landing area range control system

Abstract

The invention discloses a carrier rocket booster landing area range control system which is characterized in that the carrier rocket booster landing area range control system comprises a carrier rocket booster, a strake wing assembly and a grid rudder subsystem, the strake wing assembly comprises strake wings symmetrically installed on the two sides of the booster, and the strake wings are used for improving the transverse and longitudinal gliding capacity of the booster; the grid rudder subsystem comprises a plurality of grid rudders which are installed close to the tail end face around the axis of a booster at a fixed angle, the grid rudders can be folded, unfolded, locked and rotated by being attached to the outer surface of the booster, and the grid rudders arranged away from the core level are unfolded and locked before the carrier rocket takes off and the booster is separated. Other grid rudders are folded and unfolded after the booster is separated; and after the booster enters the atmosphere again, all the grid rudders carry out control in a coordinated mode, and the booster is guided to fall to a designated falling area. The gliding ability of the booster can be improved, the landing point precision of the booster is improved, the landing area range of the booster is reduced, and the landing area potential safety hazard caused by uncontrolled flight after the booster is separated in the past is greatly reduced.

Description

Technical Field

[0001] This invention relates to a launch vehicle booster control system, and more particularly to a launch vehicle booster impact area control system. Background Technology

[0003] Currently, with the increasing thrust requirements of my country's new generation of launch vehicles, the number of rocket launches with attached boosters is rising, exacerbating the safety risks in the landing area due to the uncertainty of booster debris dispersion. Furthermore, the lack of positioning devices leads to prolonged debris search and loss-of-control times, posing significant challenges to local governments and military units. Therefore, there is an urgent need for rapid and efficient technical solutions to the landing area safety problem. At present, there are no systems or methods in China specifically for booster landing area control. The aspects described in this article address these challenges. Summary of the Invention

[0004] To overcome the shortcomings of existing technologies, this invention provides a launch vehicle booster landing area range control system with leading-edge slat structure and grid fins. Based on the existing bundled launch vehicle, the system makes limited adaptive modifications to the bundled boosters. Without affecting launch safety and mission safety, it achieves low cost and high reliability in reducing the booster's landing area range and controlling the landing point position.

[0005] The technical solution of this invention is: A launch vehicle booster impact area control system is characterized by comprising a launch vehicle booster, a strake wing assembly, and a grid fin subsystem. The booster is mounted around the launch vehicle core stage and has a frontal face and a tail face opposite to the frontal face; the tail face is used to mount the propulsion system. The strake wing assembly includes strakes symmetrically mounted on both sides of the booster to improve the booster's lateral and longitudinal gliding capabilities. The grid fin subsystem includes multiple grid fins mounted at a fixed angle around the booster axis near the tail face, capable of retracting, deploying, locking, and rotating against the outer surface of the booster. After the booster separates from the launch vehicle core stage, the booster's heading, pitch, and roll attitudes are controlled independently by rotating different grid fins. During operation, the grid fins located away from the core stage participate in booster directional control, deploying and locking before booster separation from launch vehicle liftoff for stability enhancement during the ascent phase. Other grid fins retract and deploy after booster separation to achieve attitude stabilization. Leading strakes increase lift-to-drag ratio and improve booster lateral and longitudinal gliding capabilities. After booster re-entry, all grid fins coordinate to guide the booster to its designated landing area. Furthermore, it further includes a controller that controls the grid rudder to deploy, retract, and rotate by sending command signals.

[0006] Furthermore, the leading edge slats are symmetrically arranged along the booster axis on the outer surface of the booster cylindrical section, and are in the form of slender plates; the multiple grid rudders are distributed around the booster axis.

[0007] Furthermore, the grid rudder has at least three units, and their arrangement angles are set as required.

[0008] Furthermore, a single grid rudder is placed far from the core stage and directly opposite the core stage to participate in booster heading control; a pair of grid rudders are placed close to the core stage and symmetrically to participate in booster pitch and roll control. The three grid rudders are evenly distributed along the circumference and spaced 120° apart.

[0009] Furthermore, the grid of the single-grid rudder is a specific airfoil, and the airflow over its surface provides aerodynamic force. By changing the angle of attack, aerodynamic force and torque in different directions can be obtained. The rotation state includes state one, state two and state three. State one is the unrotated state. The single-grid rudder rotates counterclockwise to state two or clockwise to state three to provide yaw torque.

[0010] Furthermore, the rotation states of the pair of grid rudders include a first state, a second state, and a third state. The first state is an unrotated state. The pair of grid rudders simultaneously rotate counterclockwise from the first state to the second state, or clockwise to the third state, providing pitch torque. When the pair of grid rudders rotate in opposite directions, they provide roll torque.

[0011] Furthermore, once the booster reaches an altitude of 70 kilometers above the ground, it enters the atmosphere. The single-grid rudder begins yaw control, while the pair of grid rudders begins pitch and roll control, bringing the booster to a stable attitude. After the booster's attitude stabilizes, the onboard guidance system sends guidance commands, which drive the control surfaces of the single-grid rudder and the pair of grid rudders to guide the booster toward the target landing area.

[0012] The advantages of this invention compared to the prior art are: The launch vehicle landing area reduction control system described in this invention is a novel application combining leading-edge extensions (LES) and grid fins. The LES improves the lift-to-drag ratio during unpowered gliding of the booster, contributing to increased lateral glide capability; the grid fins offer high control efficiency and low control hinge torque. Compared to existing landing area control technologies, this invention can efficiently reduce the control range of the landing area and utilize high lift to guide the booster to a safer debris landing location, further mitigating potential safety risks to the booster.

[0013] Furthermore, the booster landing area control system described in this invention can be widely applied to boosters with diameters of 2 meters and 3.35 meters in my country, and can also be improved and applied to boosters of other diameters. It is also an important support for verifying the technology of reusable boosters. Attached Figure Description

[0014] Figure 1 of (a) Figure 1 (b) and Figure 1 (c) shows a front view, a side view and a top view of a typical launch vehicle booster with a leading-edge wing and grid fin structure according to an embodiment of the present invention; Figure 2 (a) is a schematic diagram of the grid fins of a launch vehicle booster in an embodiment of the present invention. Figure 2 (b) is a schematic diagram of the single grid fin 202 deploying and the pair of grid fins 203 retracting at the start of launch; Figure 2 (c) and Figure 2 (d) shows the rotation states of single-grid rudders 202 and 203, respectively; Figure 3 This is a state in an embodiment of the present invention where a launch vehicle booster is strapped to the core stage; Figure 4 This is a flight profile of a launch vehicle booster landing area range control system according to an embodiment of the present invention. Detailed Implementation

[0015] To provide a clearer and more detailed description of the present invention, it will be further described below with reference to the accompanying drawings.

[0016] This invention provides a system for significantly reducing the impact area of ​​a launch vehicle booster, comprising a leading-edge extension wing structure, grid fins, and related systems. Specifically, the launch vehicle booster impact area control system of this invention includes a launch vehicle booster, a leading-edge extension wing assembly, and a grid fin subsystem. The leading-edge extension wing assembly includes leading-edge extensions symmetrically mounted on both sides of the booster to improve the booster's lateral and longitudinal gliding capabilities. The grid fin subsystem includes multiple grid fins mounted at a fixed angle around the booster axis at the tail end, which can be retracted, deployed, locked, and rotated against the outer surface of the booster. After the booster separates from the launch vehicle core stage, the booster's heading, pitch, and roll attitudes are controlled independently by rotating different grid fins.

[0017] In one embodiment, the booster is mounted around the core stage of the launch vehicle and has a frontal end face and a tail end face opposite to the frontal end face. The tail end face is used to mount the propulsion system. The leading-edge extensions are symmetrically arranged along the booster axis on the outer surface of the booster section and are elongated. The multiple grid fins are distributed around the booster axis and can be retracted and deployed to fit the section.

[0018] In one embodiment, there are two leading-edge extensions symmetrically arranged on the booster section. There are three grid fins arranged around the booster axis, with the arrangement angle set as required. The grid fins are installed near the tail end face, fitting snugly against the section, and can be independently retracted, deployed, and rotated around the mounting axis.

[0019] The launch vehicle booster impact area control system of the present invention can be equipped with a controller that controls the deployment, retraction, and rotation of the grid fins by sending command signals. The controller is located inside the bottom section of the booster.

[0020] In one implementation, a grid rudder is arranged far from the core stage and directly opposite the core stage to participate in booster heading control; two grid rudders are arranged symmetrically close to the core stage to participate in booster pitch and roll control. The three grid rudders are evenly distributed along the circumference and spaced 120° apart.

[0021] An embodiment of the present invention provides a method for controlling the landing area of ​​a booster, comprising leading-edge extensions that increase lift during booster unpowered gliding, and a grid fin subsystem for controlling the booster's attitude; when the booster is launched while strapped to the core stage, the inner grid fins near the core stage retract, while the outer grid fins deploy, without affecting the launch mission of the main launch vehicle; after the booster separates, it performs controlled unpowered gliding using the additional lift provided by the leading-edge extensions, with all grid fins deployed to participate in the control, and the airflow passing through the grid fin surfaces generating control force and torque to precisely guide the booster to the intended landing area.

[0022] In one embodiment, the launch vehicle booster landing area control method of the present invention includes: from launch vehicle liftoff to booster separation, one grid fin away from the core stage is deployed and locked for flight stabilization during the ascent phase; after booster separation, the remaining two grid fins are retracted and deployed to complete attitude stabilization control; leading-edge extensions are used to increase the lift-to-drag ratio and improve the booster's lateral and longitudinal gliding capabilities; after the booster re-enters the atmosphere at an altitude of 70 km, the three grid fins coordinate to guide the booster to the designated landing area.

[0023] Figure 1 The main structure of the launch vehicle booster body, leading-edge slats, and grid fins was showcased. Figure 1 (a) is a front view of the launch vehicle booster 100. Figure 1 (b) is Figure 1 The side view of the booster shown in (a) Figure 1 (c) is Figure 1 The top view of the booster shown in (a). Figure 1As shown, the booster 100 has a top windward end face 101 and an opposite bottom tail end face 102, with the booster's propulsion system 103 mounted near the tail end face 102. In this embodiment, the booster 100 includes a pair of leading-edge extensions 201 mounted on the cylindrical section. After the booster separates from the core stage, it glides unpowered up the windward end face 101. The leading-edge extensions 201 can be used to improve the booster's aerodynamic stability and increase its aerodynamic lift-to-drag ratio.

[0024] A single grid rudder 202 and a pair of symmetrically arranged grid rudders 203 are distributed circumferentially near the tail end face 102.

[0025] Grid fins also play a role in improving aerodynamic stability, such as Figure 1 As shown in (c), the single grid fin 202 is used for the booster's heading control, while a pair of grid fins 203 are used for the booster's pitch and roll control. The single grid fin 202 is located on the side opposite to the rocket core stage, and the three grid fins are evenly distributed circumferentially, spaced 120° apart. The number and arrangement of the leading-edge extension fins 201 and grid fins described in this embodiment are only one application mode, and other easily conceivable variations should also be included in this invention. For example, the leading-edge extension fin can be a flat fixed wing surface or a extendable wing surface, and the grid fins can be arranged in a "T" shape with three grid fins or in a "+" shape with four grid fins, depending mainly on the structural layout space and control force requirements.

[0026] In one embodiment, the leading edge wing 201 is fixed to the booster section; the single grid rudder 202 and a pair of grid rudders 203 can be retracted and deployed. Figure 2 (a) is a front view of the booster grid fins all retracted. Figure 2 (b) is a side view showing the single grid fin 202 deployed and the pair of grid fins 203 retracted. This configuration is applicable when the booster is attached to the launch vehicle core stage. From rocket liftoff to booster separation, the single grid fin 202 reliably deploys to enhance flight stability during the ascent phase; the pair of grid fins 203 on both sides retract without causing structural interference, and the grid fin surfaces fit snugly against the cylinder to reduce the impact on the overall aerodynamic characteristics of the booster and launch vehicle. Figure 3 A front view of the booster assembled with the rocket core stage 010 during rocket launch preparation, showing the single grid fin 202 deployed and a pair of grid fins 203 retracted.

[0027] Figure 2(c) shows the rotating state of the single-grid rudder 202, while state 202B is the non-rotating state. The grid of the rudder is a specific airfoil, and the airflow over its surface can provide aerodynamic forces. Different aerodynamic forces and moments in different directions can be obtained by changing the angle of attack. The single-grid rudder 202 can rotate counterclockwise from state 202B to state 202A, or clockwise to state 302C, providing yaw moment.

[0028] Figure 2 (d) shows the rotational states of a pair of grid rudders 203. The first state 203B is the unrotated state. The pair of grid rudders can simultaneously rotate counterclockwise from the first state 203B to the second state 203A, or clockwise to the third state 203C, providing pitch torque. When the pair of grid rudders 203 rotate in opposite directions, they can provide roll torque.

[0029] Figure 4 A flight profile of the launch vehicle booster is shown. Figure 4 As shown, multiple time points are illustrated, including time point 301 to time point 313 (the thirteenth time point). The boosters and their control systems were launched with the launch vehicle from... Figure 4 Between the first time point 301 and the second time point 302, at this time Figure 2 The single grid rudder 202 shown is deployed and locked, while the pair of grid rudders 203 are retracted and not controlled. Only the single grid rudder 202 provides aerodynamic stabilization.

[0030] After the second time point 302, the launch vehicle core stage separates from the booster. After separation, due to inertia, the booster engages in unpowered flight, and its altitude continues to rise, as shown in the third time point 303 in the figure. Subsequently, it enters the high-altitude jettison phase at the fourth time point 304, at which time a pair of grid fins 203 deploy, ready to participate in control.

[0031] When the booster reaches an altitude of 70 kilometers above the ground, Figure 4 At time 305 (the fifth time point), the booster re-enters the atmosphere. The single-grid rudder 202 initiates yaw control, while the pair of grid rudders 203 initiates pitch and roll control, bringing the booster to a stable attitude. After the booster's attitude stabilizes, at time 306 (the sixth time point), the onboard guidance system sends guidance commands. Based on these commands, the single-grid rudder 202 and the pair of grid rudders 203 are driven to guide the booster to land at the target area at time 307 (the seventh time point) and time 308 (the eighth time point). The landing point at time 308 (the eighth time point) is a controlled landing point. If no guidance is provided, the booster will land at time 309 (the ninth time point) and time 310 (the tenth time point), which is an uncontrolled landing point.

[0032] After the launch vehicle core stage separated from the boosters, the launch vehicle core stage separated from the satellite fairing at time 311 (11 o'clock). Then, at time 312 (12 o'clock), the first and second stages of the rocket separated, and at time 313 (13 o'clock), the satellite separated from the rocket, completing the satellite's entry into orbit.

[0033] Through the above process, the landing point of the booster can be controlled within a small range.

[0034] In summary, the launch vehicle landing zone control system presented in this invention is a new technology that combines leading-edge extensions (LES) with grid fins. The LES improves the lift-to-drag ratio during unpowered gliding of the booster, contributing to increased lateral glide capability; the grid fins offer high control efficiency and low control hinge torque. Compared to existing landing zone control technologies, this invention can efficiently reduce the control range of the landing zone and utilize high lift to control the booster towards a safer debris landing point, further mitigating potential safety risks to the booster.

[0035] Furthermore, the booster landing area control system described in this invention can be widely applied to boosters with diameters of 2 meters and 3.35 meters in my country, and can also be improved and applied to boosters of other diameters. It is also an important support for verifying the technology of reusable boosters.

[0036] This invention can improve the gliding capability of boosters, increase the accuracy of booster landing points, reduce the range of booster landing areas, and greatly reduce the safety hazards of landing areas caused by uncontrolled flight after booster separation in the past.

[0037] The above description is only the best specific embodiment of the present invention, but the protection scope of the present invention is not limited thereto. Any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in the present invention should be within the protection scope of the present invention.

[0038] The contents not described in detail in this specification are common knowledge to those skilled in the art.

Claims

1. A launch vehicle booster landing area range control system, characterized in that, It includes a launch vehicle booster, a strake wing assembly, and a grid fin subsystem. The booster is mounted around the launch vehicle core stage and has a frontal face and a tail face opposite the frontal face; the tail face is used to mount the propulsion system. The strake wing assembly includes strakes symmetrically mounted on both sides of the booster to improve its lateral and longitudinal gliding capabilities. The grid fin subsystem includes multiple grid fins mounted at a fixed angle around the booster axis near the tail face. These fins can retract, deploy, lock, and rotate against the outer surface of the booster. After the booster separates from the launch vehicle core stage, the booster's heading, pitch, and roll attitude can be controlled independently by rotating the different grid fins. During operation, the grid fins located away from the core stage participate in booster heading control and are locked in place from launch vehicle liftoff to booster separation for flight stabilization during the ascent phase. Other grid fins are retracted and deployed after booster separation to complete attitude stabilization control. Leading slats are used to increase lift-to-drag ratio and improve booster lateral and longitudinal gliding capabilities. After booster re-entry into the atmosphere, all grid fins coordinate to carry out control and guide the booster to the designated landing area.

2. The launch vehicle booster landing area control system according to claim 1, characterized in that, It further includes a controller that controls the grid rudder to deploy, retract, and rotate by sending command signals.

3. The launch vehicle booster landing area control system according to claim 1, characterized in that, The leading edge wing is symmetrically arranged on the outer surface of the booster cylindrical section along the booster axis, and is in the form of a slender plate; the multiple grid rudders are distributed around the booster axis.

4. The launch vehicle booster landing area control system according to claim 1, characterized in that, The grid rudder has at least three units, and the arrangement angle is set as required.

5. The launch vehicle booster landing area control system according to claim 1, characterized in that, A single grid rudder is positioned away from the core stage and directly opposite it to participate in booster heading control; a pair of grid rudders are positioned symmetrically close to the core stage to participate in booster pitch and roll control. The three grid rudders are evenly distributed along the circumference and spaced 120° apart.

6. The launch vehicle booster landing area control system according to claim 5, characterized in that, The single-grid rudder has a specific airfoil grid. Airflow over its surface provides aerodynamic force. By changing the angle of attack, aerodynamic force and torque in different directions can be obtained. The rotation states include state one, state two, and state three. State one is the unrotated state. The single-grid rudder rotates counterclockwise to state two or clockwise to state three to provide yaw torque.

7. The launch vehicle booster landing area control system according to claim 5, characterized in that, The rotation states of the pair of grid rudders include a first state, a second state, and a third state. The first state is an unrotated state. The pair of grid rudders simultaneously rotate from the first state counterclockwise to the second state, or clockwise to the third state, providing pitch torque. When the pair of grid rudders rotate in opposite directions, they provide roll torque.

8. The launch vehicle booster landing area control system according to claim 5, characterized in that, Once the booster reaches an altitude of 70 kilometers above the ground, it enters the atmosphere. The single-grid rudder begins yaw control, while the pair of grid rudders begin pitch and roll control to bring the booster to a stable attitude. After the booster's attitude stabilizes, the onboard guidance system sends guidance commands, which drive the control surfaces of the single-grid rudder and the pair of grid rudders to guide the booster toward the target landing area.

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