A rocket body protruding equipment protection mechanism and an operating method thereof
By introducing a servo motor-driven linear guide and a spiral lift into the rocket body protrusion protection mechanism, combined with multi-point displacement sensors, active automatic adjustment and passive adaptation in the XYZ three directions are achieved. This solves the problems of single adjustment method and safety hazards in the existing technology, and improves the automation and safety of rocket attitude control.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- LUDONG UNIVERSITY
- Filing Date
- 2026-03-23
- Publication Date
- 2026-08-04
AI Technical Summary
The existing rocket body protrusion protection structure cannot achieve active and automatic adjustment in the XYZ directions. The adjustment method is simplistic and lacks a feedback mechanism, which causes the rocket's attitude changes to exceed the passive adaptation range, posing a safety hazard.
It adopts a protection mechanism including a heat insulation cover, a passive spring module and an active adjustment module, combined with a servo motor driven linear guide rail and a screw lift, and equipped with multi-point displacement sensors to achieve active automatic adjustment in three XYZ directions, and switches to active adjustment through signal feedback in passive adaptation state.
It achieves active automatic adjustment of the rocket body protruding equipment in the XYZ three directions, reduces manual intervention, improves operational safety and automation, ensures the rocket's attitude remains stable during hoisting, transportation and erection, and has a dual-redundant safety closed-loop control.
Smart Images
Figure CN122237394B_ABST
Abstract
Description
Technical Field
[0001] This invention relates to the technical field of launch vehicles, and in particular to a protective mechanism for protruding equipment on a rocket body and its operating method. Background Technology
[0002] Currently, before launch preparation, rockets need to protect external protruding structures or electrical equipment that require protection. Due to errors during the rocket's hoisting onto the erector, the axial and radial positions of the protrusions that need protection often deviate from the design values. Therefore, the protective structure is usually required to be adjustable in either the axial or radial direction.
[0003] Therefore, after the structure actively adjusts to its position, it should be able to passively adapt to the rocket's attitude, as slight roll or displacement may occur during transport and erection. When entering passive adjustment and adaptation mode, to prevent the rocket's attitude change from exceeding the passive adaptation range, the structure must have a signal feedback function. When the displacement sensor detecting the position of the passive adjustment mechanism receives a signal, it feeds back to the active adjustment mechanism, promptly lowering the attitude to avoid damage to the rocket. After the rocket is erected to the launch position, the protective structure needs to retract to prevent interference between the structure and the rocket's ascent path.
[0004] For related technologies, please refer to the adjustment device for the final insulation air outlet with application number 202410354576.1.
[0005] Regarding the aforementioned technologies, most axial adjustments of the adjustment structures are only unidirectional, failing to meet the requirement of simultaneous automatic adjustment in the XYZ directions. Furthermore, most adjustment structures are manual, requiring on-site personnel for adjustment, which poses safety hazards, especially in the pre-launch state. In addition, the single adjustment method cannot achieve a balance between active adjustment and passive adaptation, and lacks a feedback mechanism, making it easy for the attitude to exceed the passive adaptation design value, causing damage to the rocket body. Vertical adjustment of the vent is mostly single passive, with limited adaptability. Therefore, there is an urgent need to develop and innovate a method for the rocket to achieve active and automatic XYZ three-axis adjustment in a horizontal state after being hoisted to the erector frame. This method uses displacement sensors to determine the structural positioning; once the structure is in position, the active adjustment mechanism locks, and the entire protective structure switches to a passive adaptive rocket attitude mode. Summary of the Invention
[0006] To address the shortcomings of existing technologies, this invention provides a rocket body protrusion protection mechanism and its operation method, which can actively adjust its position and passively adapt to the rocket body's rolling and linear displacement attitude.
[0007] The technical solution of the present invention to solve the above-mentioned technical problems is as follows:
[0008] A rocket body protrusion protection mechanism includes a thermal insulation cover and a control module. A passive spring module is provided below the thermal insulation cover, and a ball joint flange is provided between the thermal insulation cover and the passive spring module. The two ends of the ball joint flange are respectively connected to the thermal insulation cover and the passive spring module. An active adjustment module is provided below the passive spring module.
[0009] The active adjustment module includes an X-axis adjustment component, a Y-axis adjustment component, and a Z-axis adjustment component, which are stacked vertically.
[0010] Both the passive spring module and the active adjustment module are equipped with sensor components for signal feedback, and the sensor components are connected to the control module.
[0011] Furthermore, the side of the heat insulation cover away from the passive spring module is set with an arc surface, and the side of the heat insulation cover close to the arc surface is covered with a layer of heat insulation material.
[0012] Furthermore, the passive spring module includes a spring base and a spring body. The spring base is provided with a spring sleeve, the spring body is placed inside the spring sleeve, the spring sleeve is provided with a pre-tightening bolt, and the spring body is sleeved on the outside of the pre-tightening bolt.
[0013] Furthermore, the X-axis adjustment assembly includes an X-axis adjustment base, on which an X-axis linear guide and an X-axis servo motor are provided, and the X-axis servo motor drives the X-axis linear guide to move.
[0014] Furthermore, the Y-axis adjustment assembly includes a Y-axis adjustment base, on which a Y-axis linear guide and a Y-axis servo motor are provided, and the Y-axis servo motor drives the Y-axis linear guide to move.
[0015] Furthermore, the Z-axis adjustment assembly includes a Z-axis adjustment base, on which a Z-axis screw jack and a Z-axis servo motor are mounted, and the Z-axis servo motor drives the Z-axis screw jack to move.
[0016] Furthermore, the sensor assembly includes a passive displacement sensor, an X-axis displacement sensor, a Y-axis displacement sensor, and a Z-axis displacement sensor. The passive displacement sensor is placed in a passive spring module, the X-axis displacement sensor is placed in an X-axis adjustment assembly, the Y-axis displacement sensor is placed in a Y-axis adjustment assembly, and the Z-axis displacement sensor is placed in a Z-axis adjustment assembly. The passive displacement sensor, X-axis displacement sensor, Y-axis displacement sensor, and Z-axis displacement sensor are respectively connected to the control module.
[0017] A method for operating a rocket body protrusion protection mechanism includes the following steps:
[0018] When the rocket is in a horizontal position, the first step is to enter the active horizontal adjustment mode. The active adjustment module first automatically locates the position along the X and Y axes, and determines the positioning status through the sensor components, so that the overall position of the thermal insulation cover is aligned with the outer envelope of the rocket body.
[0019] The active adjustment module then automatically locates the Z-axis position, completing the extension of the thermal insulation cover in the Z-axis, so that the thermal insulation cover contacts the rocket body and reaches the preset attitude.
[0020] Once in position, the control module automatically switches to passive adaptation mode. The insulation cover achieves roll self-adaptation through the ball joint flange and relies on the passive spring module to absorb the small displacements of the rocket body during transportation and erection.
[0021] Furthermore, when the passive adaptation of the passive spring module approaches the allowable limit, the sensor assembly immediately feeds back a signal and triggers the control module to re-enter the active adjustment mode to correct the position of the active adjustment module.
[0022] Furthermore, before the rocket body transitions to the vertical pre-launch state, the Z-axis adjustment component automatically retracts its full stroke and locks mechanically to ensure no interference with the launch envelope, thus completing the entire usage process.
[0023] In summary, compared with the prior art, the beneficial effects of the above technical solution are:
[0024] 1. This application features a passively adaptive protective structure. It adapts to the rocket body's roll via a ball joint flange and to the linear displacement of the rocket body via a spring. In passive adaptation mode, a displacement sensor still detects the mechanism's position. When the sensor receives a signal indicating that the rocket body's attitude change exceeds the spring's travel range, the signal is fed back to the servo motor, switching to active adjustment mode to promptly lower the attitude and prevent damage to the rocket body. Furthermore, the protective structure can automatically retract before being erected and ready for launch. This structure provides pre-launch protection for structures requiring protection during the rocket's pre-launch preparation phase. To ensure it does not interfere with the rocket's launch path, the protective structure needs sufficient retraction stroke in the vertical pre-launch state. Verification shows that an axial position adjustment using a servo motor-driven linear guide rail, combined with the extension and retraction of a vertical spiral lift, can meet the requirements for active adjustment. In passive adjustment mode, the ball joint flange and spring can meet the requirements for passively adapting the rocket body's attitude.
[0025] 2. This application adopts a servo control system combined with multi-point displacement sensors to monitor the relative positional relationship between the rocket body and the protection mechanism in real time under active adjustment mode, and realize the automatic following and synchronous adjustment of the rocket body attitude by the protection mechanism under passive adaptive mode, which greatly reduces manual intervention and improves the degree of automation and operational safety.
[0026] 3. The servo motor-driven linear guide rail of this application, in conjunction with the screw jack and a high-precision displacement sensor, achieves accurate position detection. Sensor feedback forms a closed-loop control, enabling the actuator to have rapid response, precise positioning capabilities, and the ability to switch and adjust states in a timely manner. This ensures that the protective structure maintains stable and accurate attitude adjustment throughout the entire process of hoisting, transportation, and erection, and can be quickly adjusted according to the geometric dimensions of different rocket models and by adjusting the stroke of the protective mechanism.
[0027] 4. In the active adjustment mode, the sensor detects the deviation between the mechanism's attitude and the rocket body's envelope in real time, providing accurate data for active adjustment. In the passive adjustment mode, the displacement sensor monitors the deformation of the spring mechanism, ensuring that it remains within a safe range when passively absorbing minor rolls and displacements of the rocket body. Once the sensor detects an offset approaching a preset threshold, the system immediately switches to active adjustment mode via signal feedback to correct the position of the protection mechanism, forming a dual-redundant safety closed loop and improving the system's fault tolerance and backup capabilities.
[0028] 5. After the rocket in this application transitions to the vertical pre-launch state, the spiral lifting system automatically retracts under the continuous position monitoring of sensors until the sensors detect the fully retracted position and trigger the mechanical lock. This multi-sensor verification mechanism ensures that the protection mechanism is completely out of the launch envelope, avoiding any structural interference and meeting the stringent safety requirements of the launch area. Attached Figure Description
[0029] Figure 1 This is a schematic diagram of the overall structure of an embodiment of the present invention;
[0030] Figure 2 This is a side view of an embodiment of the present invention;
[0031] Figure 3 This is a schematic diagram of the active adjustment module in an embodiment of the present invention;
[0032] Figure 4 This is a side view of the passive spring module and the ball joint flange in an embodiment of the present invention;
[0033] Figure 5 This is a cross-sectional view of the passive spring module and the ball joint flange in an embodiment of the present invention.
[0034] Explanation of reference numerals in the attached figures:
[0035] 1. Insulation cover; 2. Ball joint flange; 3. Passive spring module; 31. Spring base; 32. Spring body; 33. Spring sleeve; 34. Preload bolt; 4. Active adjustment module; 41. Y-axis adjustment assembly; 411. Y-axis adjustment base; 412. Y-axis linear guide; 413. Y-axis servo motor; 42. X-axis adjustment assembly; 421. X-axis adjustment base; 422. X-axis linear guide; 423. X-axis servo motor; 43. Z-axis adjustment assembly; 431. Z-axis adjustment base; 432. Z-axis screw jack; 433. Z-axis servo motor; 5. Sensor assembly; 51. Passive displacement sensor; 52. X-axis displacement sensor; 53. Y-axis displacement sensor; 54. Z-axis displacement sensor. Detailed Implementation
[0036] The principles and features of the present invention are described below with reference to all the accompanying drawings. The examples given are only for explaining the present invention and are not intended to limit the scope of the present invention.
[0037] This invention discloses a rocket body protrusion protection mechanism and its operation method.
[0038] Reference Figures 1 to 5 As shown, a rocket body protrusion protection mechanism includes a thermal insulation cover 1 and a control module. A passive spring module 3 is provided below the thermal insulation cover 1. A ball joint flange 2 is provided between the thermal insulation cover 1 and the passive spring module 3. The two ends of the ball joint flange 2 are respectively connected to the thermal insulation cover 1 and the passive spring module 3. The ball joint flange 2 is connected to the thermal insulation cover 1 and adapts to the rolling attitude of the rocket body through the ball joint.
[0039] Below the passive spring module 3 is an active adjustment module 4, which includes an X-axis adjustment component 42, a Y-axis adjustment component 41, and a Z-axis adjustment component 43. The X-axis adjustment component 42, the Y-axis adjustment component 41, and the Z-axis adjustment component 43 are stacked vertically.
[0040] Both the passive spring module 3 and the active adjustment module 4 are equipped with sensor components 5 for signal feedback, and the sensor components 5 are connected to the control module.
[0041] The side of the thermal insulation cover 1 furthest from the passive spring module 3 is set with an arc surface, and the side of the thermal insulation cover 1 closest to the arc surface is covered with a layer of thermal insulation material. The thermal insulation cover 1 is the arc surface that is in direct contact with the rocket body, and is responsible for wrapping the geometric shape of the structure to be protected. A flexible thermal insulation material layer can be attached to the edge to prevent damage to the rocket body.
[0042] The passive spring module 3 includes a spring base 31 and a spring body 32. A spring sleeve 33 is provided on the spring base 31, and the spring body 32 is placed inside the spring sleeve 33. A preload bolt 34 is provided inside the spring sleeve 33, and the spring body 32 is sleeved on the outside of the preload bolt 34.
[0043] The bottom of the spring sleeve 33 and the spring base 31 are connected to the Y-axis adjustment assembly 41 to adapt to the Z-axis displacement of the rocket body during the passive adaptive phase.
[0044] The X-axis adjustment assembly 42 includes an X-axis adjustment base 421, on which an X-axis linear guide rail 422 and an X-axis servo motor 423 are provided. The X-axis servo motor 423 drives the X-axis linear guide rail 422 to move.
[0045] The Y-axis adjustment assembly 41 includes a Y-axis adjustment base 411, on which a Y-axis linear guide rail 412 and a Y-axis servo motor 413 are provided. The Y-axis servo motor 413 drives the Y-axis linear guide rail 412 to move.
[0046] In addition to their respective linear guides and servo motors, the X-axis adjustment assembly 42 and the Y-axis adjustment assembly 41 also include corresponding guide adjustment blocks and trapezoidal lead screws.
[0047] The Z-axis adjustment assembly 43 includes a Z-axis adjustment base 431, on which a Z-axis screw jack 432 and a Z-axis servo motor 433 are mounted. The Z-axis servo motor 433 drives the Z-axis screw jack 432. The Z-axis screw jack 432 radially adapts to hoisting errors. In the vertical position of the rocket, it can drive the structure to fully retract, realizing vertical adjustment during the active adjustment phase. After the passive adaptive structure fails, it retracts in time through signal feedback to prevent damage to the rocket body. After the rocket body is erected in place, it retracts vertically completely. In this embodiment, four Z-axis screw jacks 432 and four Z-axis servo motors 433 are provided.
[0048] In this embodiment, the Y-axis adjustment component 41 is connected to the passive spring module 3, the X-axis adjustment component 42 is placed below the Y-axis adjustment component 41, and the Z-axis adjustment component 43 is placed below the X-axis adjustment component 42, stacked sequentially. The bottom of the Y-axis adjustment base 411 is connected to the X-axis linear guide rail 422 to achieve active Y-axis adjustment. The bottom of the X-axis adjustment base 421 is connected to the Z-axis screw jack 432 through the X-axis linear guide rail 422, driving the mechanism to move in the X-axis direction. The Z-axis screw jack 432 uses a Z-axis servo motor 433 to drive the lifting and lowering of the Z-axis screw jack 432.
[0049] Sensor assembly 5 includes a passive displacement sensor 51, an X-axis displacement sensor 52, a Y-axis displacement sensor 53, and a Z-axis displacement sensor 54. Passive displacement sensor 51 is housed in passive spring module 3, X-axis displacement sensor 52 is housed in X-axis adjustment assembly 42, Y-axis displacement sensor 53 is housed in Y-axis adjustment assembly 41, and Z-axis displacement sensor 54 is housed in Z-axis adjustment assembly 43. Passive displacement sensor 51, X-axis displacement sensor 52, Y-axis displacement sensor 53, and Z-axis displacement sensor 54 are each connected to the control module. When sensor assembly 5 detects the adjusted position, it provides signal feedback.
[0050] The Z-axis screw jack 432 is mounted on the Z-axis adjusting base 431 and connected to the X-axis adjusting base 421 at its upper part. An X-axis linear guide 422 is mounted above the X-axis adjusting base 421, and a Y-axis adjusting base 411 is fixed to the upper part of the X-axis linear guide 422. The Y-axis linear guide 412 is connected to the spring base 31. A ball joint flange 2 is mounted above the passive spring module 3 and connected to the insulation cover 1 structure. Displacement sensors are installed in their respective axial adjustment directions.
[0051] The insulation cover 1 is made of aluminum. The X-axis adjusting base 421, Y-axis adjusting base 411, and Z-axis adjusting base 431 are all made of steel. The screw jack, linear guide rail, and their corresponding servo motors are selected from finished products based on the load conditions. The spring body 32 is made of piano wire, with a stroke of not less than 60mm and a stiffness of not more than 12N / mm. The ball joint flange 2 is selected with an adaptation range of not less than 5° and not more than 13°. If an air duct is installed, the air duct is connected to the insulation cover 1, and the air duct is made of steel and a combination of flexible hoses.
[0052] This application utilizes a servo motor to drive the linear guide rail in the X and Y axes during structural adjustment, automatically replacing manual adjustment for greater precision and reduced safety hazards. It also works in conjunction with a screw jack to actively adjust the structure along the Z axis. Sensors determine position; displacement sensors are installed in all three axes (X, Y, and Z) to confirm positioning. The Z-axis has a retractable stroke, achieved through a screw jack with a large retractable stroke and good adaptability. Passive adaptive adjustment is also included, providing a protective structure that adapts to roll via the ball joint flange 2 and vertical displacement via springs. Passive-active switching is achieved through signal feedback. In passive adaptive mode, the displacement sensor feedback signal determines the adaptive margin of the mechanism, allowing for timely passive-active switching and providing a safety backup mechanism.
[0053] Reference Figures 1 to 5 As shown, an operation method for a rocket body protrusion protection mechanism includes the following steps:
[0054] When the rocket is in a horizontal position, the first step is to enter the active horizontal adjustment mode. The active adjustment module 4 first automatically locates the position along the X and Y axes, and the sensor assembly 5 determines the positioning status, so that the overall position of the thermal insulation cover 1 is aligned with the outer envelope of the rocket body.
[0055] Subsequently, the active adjustment module 4 automatically locates the Z-axis position, completes the extension of the thermal insulation cover 1 in the Z-axis, and makes the thermal insulation cover 1 contact the rocket body and reach the preset attitude.
[0056] Once in position, the control module automatically switches to passive adaptation mode. The insulation cover 1 achieves roll adaptation through the ball joint flange 2 and relies on the passive spring module 3 to absorb the small displacement of the rocket body during transportation and erection.
[0057] When the passive adaptation of the passive spring module 3 approaches the allowable limit, the sensor component 5 immediately feeds back a signal and triggers the control module to re-enter the active adjustment mode and correct the position of the active adjustment module 4.
[0058] Before the rocket body is switched to the vertical pre-launch state, the Z-axis adjustment component 43 automatically performs full-stroke retraction and mechanical locking to ensure that it does not interfere with the launch envelope and completes the entire usage process.
[0059] The implementation principle of the rocket body protrusion protection mechanism and its operation method according to an embodiment of the present invention is as follows:
[0060] This application proposes a protection mechanism for the protruding structure of an arrow body driven by a servo motor, a linear guide rail, and a screw jack. This mechanism has the ability to switch to passive adaptation of the arrow body attitude after actively adjusting to the correct position. In the passive adaptation state, it has a signal feedback function to prevent the change in the arrow body attitude from exceeding the passive adaptation amount. It can switch to an active adjustment mode for the entire protection mechanism through signal feedback.
[0061] After the rocket is hoisted, the protective structure can be reliably extended and moved in a horizontal position. Furthermore, once the rocket body is in place, a passive adaptation mechanism effectively accommodates any minor rolls and displacements that may occur during transport and erection. This mechanism uses two servo motors-driven linear guides to automatically adjust the X and Y axis positions, while four other servo motors drive the Z-axis helical jack 432 structure to extend and retract along the Z-axis.
[0062] After the active adjustment mechanism completes its attitude adjustment, the mechanism adapts to the rocket body's roll via the insulation cover 1 connected by the ball joint flange 2, and adapts to the displacement during rocket body transportation and erection via the passive spring module 3. When the rocket is switched to the vertical pre-launch state, the Z-axis spiral elevator system can automatically complete the full stroke retraction and mechanical locking via servo motor control to ensure no interference with the rocket launch envelope.
[0063] This application features high automation, good positioning accuracy, adjustable stroke, a combination of active adjustment and passive adaptation, and a signal feedback function to prevent failure of the passive adaptation structure, as well as strong safety and reliability. It can meet the requirements of rapid operation and safe launch during the launch preparation phase.
[0064] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.
Claims
1. A protective mechanism for protruding equipment on a rocket body, comprising a thermal insulation cover (1) and a control module, characterized in that: A passive spring module (3) is provided below the heat insulation cover (1), and a ball joint flange (2) is provided between the heat insulation cover (1) and the passive spring module (3). The two ends of the ball joint flange (2) are respectively connected to the heat insulation cover (1) and the passive spring module (3). An active adjustment module (4) is provided below the passive spring module (3). The active adjustment module (4) includes an X-axis adjustment component (42), a Y-axis adjustment component (41), and a Z-axis adjustment component (43), which are stacked vertically. Both the passive spring module (3) and the active adjustment module (4) are equipped with sensor components (5) for signal feedback, and the sensor components (5) are connected to the control module. The sensor assembly (5) includes a passive displacement sensor (51), an X-axis displacement sensor (52), a Y-axis displacement sensor (53), and a Z-axis displacement sensor (54). The passive displacement sensor (51) is placed in the passive spring module (3), the X-axis displacement sensor (52) is placed in the X-axis adjustment assembly (42), the Y-axis displacement sensor (53) is placed in the Y-axis adjustment assembly (41), and the Z-axis displacement sensor (54) is placed in the Z-axis adjustment assembly (43). The passive displacement sensor (51), X-axis displacement sensor (52), Y-axis displacement sensor (53), and Z-axis displacement sensor (54) are respectively connected to the control module. When the passive adaptation of the passive spring module (3) approaches the allowable limit, the sensor assembly (5) immediately feeds back a signal and triggers the control module to re-enter the active adjustment mode and correct the position of the active adjustment module (4). Before the rocket body is switched to the vertical pre-launch state, the Z-axis adjustment component (43) automatically performs full-stroke retraction and mechanical locking to ensure that it does not interfere with the launch envelope and completes the entire usage process.
2. The rocket body protrusion protection mechanism according to claim 1, characterized in that: The side of the heat insulation cover (1) away from the passive spring module (3) is set in an arc shape, and the side of the heat insulation cover (1) near the arc shape is covered with a layer of heat insulation material.
3. The rocket body protrusion protection mechanism according to claim 1, characterized in that: The passive spring module (3) includes a spring base (31) and a spring body (32). A spring sleeve (33) is provided on the spring base (31). The spring body (32) is placed inside the spring sleeve (33). A pre-tightening bolt (34) is provided inside the spring sleeve (33). The spring body (32) is sleeved on the outside of the pre-tightening bolt (34).
4. The rocket body protrusion protection mechanism according to claim 1, characterized in that: The X-axis adjustment assembly (42) includes an X-axis adjustment base (421), on which an X-axis linear guide rail (422) and an X-axis servo motor (423) are provided. The X-axis servo motor (423) drives the X-axis linear guide rail (422) to move.
5. A rocket body protrusion protection mechanism according to claim 1, characterized in that: The Y-axis adjustment assembly (41) includes a Y-axis adjustment base (411), on which a Y-axis linear guide rail (412) and a Y-axis servo motor (413) are provided. The Y-axis servo motor (413) drives the Y-axis linear guide rail (412) to move.
6. The rocket body protrusion protection mechanism according to claim 1, characterized in that: The Z-axis adjustment assembly (43) includes a Z-axis adjustment base (431), on which a Z-axis screw jack (432) and a Z-axis servo motor (433) are provided. The Z-axis servo motor (433) drives the Z-axis screw jack (432) to move.
7. An operating method for a rocket body protrusion protection mechanism, based on the rocket body protrusion protection mechanism according to claim 1, characterized in that, Includes the following steps: When the rocket is in a horizontal state, the first active horizontal adjustment mode is performed. The active adjustment module (4) first automatically locates the X and Y axis positions and judges the positioning status through the sensor assembly (5) so that the overall position of the heat insulation cover (1) is aligned with the outer envelope of the rocket body. Subsequently, the active adjustment module (4) automatically locates the Z-axis position, completes the extension of the heat insulation cover (1) in the Z-axis, and makes the heat insulation cover (1) contact the rocket body and reach the preset attitude. After finally reaching its final position, the control module automatically switches to passive adaptation mode. The insulation cover (1) achieves roll adaptation through the ball joint flange (2) and relies on the passive spring module (3) to absorb the small displacement of the rocket body during transportation and erection.