A three-dimensional high-temperature resistant aerodynamic rudder attitude correction system

Abstract

This invention discloses a three-dimensional high-temperature resistant aerodynamic rudder attitude correction system, belonging to the field of attitude control technology for small and medium-sized civilian reusable rockets. The system includes an aerodynamic weather rudder, a servo deflection mechanism, a dual-locking ejection separation mechanism, and timing signal docking terminals. The rudder body can be selected from a 1000℃ high-temperature resistant alloy or a 1400~1600℃ refractory alloy, supporting multiple circumferentially evenly arranged configurations of 3, 4, 5, and 6 rudders. The system has two working modes: high-altitude synchronous rudder release and full-range rudder landing. It adopts a segmented correction scheme: at an altitude of 3~8km, horizontal drift is corrected by aerodynamic rudders, with landing drift controlled within 2~3km; at a low altitude of 50~300m, a micro-jet device is switched to fine-tune the vertical attitude. The rudder body can be mounted on the outer wall of the propulsion compartment or fuel tank, and the composite locking ejection structure ensures that the separation error of multiple rudders does not exceed 0.2s. This invention eliminates the blind spot of omnidirectional crosswind correction, solves the problems of insufficient high temperature resistance, asynchronous separation, and limited applicable working conditions of traditional rudders, has strong structural versatility, significantly reduces the rocket recovery and salvage range, and has high commercial application value.

Description

Technical Field

[0001] This invention belongs to the field of attitude control technology for small and medium-sized reusable rockets. Specifically, it relates to a multi-braced aerodynamic rudder correction device that is adapted to the reentry and recovery of the first stage of a rocket, is resistant to high temperatures, and can be jettisoned at a fixed point. It is suitable for attitude correction conditions of parachute-type non-destructive recovery of small civilian rockets. Background Technology

[0002] Existing attitude correction schemes for parachute recovery of small and medium-sized reusable rockets mainly suffer from two types of technical defects: The first type is the fixed grid rudder recovery scheme. The rudder structure follows the rocket body to the ground throughout the entire process. There is no high-altitude jetting weight reduction design, which results in large wind load and large inertia when the rocket body falls. The drift range of the landing point can reach more than 10km. The salvage range at sea is wide, the salvage cost is extremely high, and the recovery efficiency is low.

[0003] The second type is a single or two opposing aerodynamic rudder correction structure, which cannot achieve 360° full-circumference balanced countermeasure against crosswind disturbances, has a large lateral correction dead angle, and has extremely poor correction accuracy under high wind conditions, thus failing to meet the requirements for fixed-point recovery.

[0004] Meanwhile, most conventional aerodynamic rudders are made of ordinary heat-resistant steel, with a temperature limit generally below 500℃. During the high-speed reentry of a rocket, the leading edge aerodynamic heating temperature is high, which makes it very easy for deformation, ablation, and structural failure to occur, resulting in poor reliability.

[0005] In addition, traditional rudder separation mechanisms are mostly single-point unlocking structures, resulting in poor consistency and large errors in the synchronous separation of multiple rudders. This makes them prone to major malfunctions such as rudder lag and detachment, tilting and jamming, and entanglement of the main deceleration chute. Furthermore, existing technologies only support a single working mode and cannot accommodate both high-altitude rudder jetting for weight reduction and easy recovery with rudders throughout the entire process. This results in narrow adaptability, large room for maneuver, and weak patent stability.

[0006] In summary, existing rocket attitude correction systems suffer from technical shortcomings such as insufficient temperature resistance, large correction blind spots, significant landing point drift, asynchronous separation, limited operating conditions, and simplistic evasion mechanisms, which urgently require optimization and solutions with entirely new structural designs. Summary of the Invention

[0007] (1) The technical problem to be solved by the present invention 1. Conventional aerodynamic rudders have low temperature resistance and are prone to ablation, deformation, and structural failure under the impact of high-temperature airflow during reentry; 2. The single / dual rudder layout has a correction blind spot, cannot fully counteract crosswinds, and has an excessively large landing point drift range; 3. Lacks a high-precision synchronous ejection locking structure; inconsistent separation timing of multiple rudders; prone to entanglement of the deceleration parachute. 4. It only has a single working mode and cannot adapt to various working conditions such as strong winds, normal conditions, and simple recycling. 5. The rudder's installation position is fixed, and it can only be adapted to a single cabin structure, resulting in poor versatility and easy circumvention through minor modifications.

[0008] (2) Technical solution To solve the above-mentioned technical problems, the present invention provides a three-dimensional high-temperature resistant aerodynamic rudder attitude correction system, including multiple sets of aerodynamic weather rudders, a servo deflection mechanism, a dual-locking ejection separation mechanism, and timing signal docking terminals; Multiple sets of aerodynamic weather rudders are hinged to the outer wall of the rocket body via servo drive linkages and rotating shafts, and are evenly arranged around the outer wall of the rocket body. The arrangement can be 3 rudders at 120°, 4 rudders at 90°, 5 rudders at 72° or 6 rudders at 60°, and the deflection stroke of the rudder surface is fixed at 0°~30°. The dual-locking ejection separation mechanism is a composite locking structure of explosive bolts and springs, which enables simultaneous unlocking of multiple rudders and forced ejection separation by springs. This invention features two independent operating modes: Mode 1: After the attitude correction is completed at a mid-to-high altitude of 3-8km, the timing assembly issues a unified command, and multiple rudders are jettisoned synchronously as a whole to achieve weight reduction and drag reduction; Mode 2: The rudder is fixed to the outer wall of the rocket body throughout the entire process and does not detach, falling with the rocket body throughout the entire process, which is suitable for simple and low-cost recovery conditions; The segmented correction logic of this invention is as follows: at an altitude of 3-8km, horizontal drift correction is completed solely by aerodynamic weather rudders, strictly controlling the landing point drift within the 2-3km range; at a low altitude of 50-300m, aerodynamic rudder correction is turned off, and micro-jet engines and lateral correction parachutes are switched to complete the terminal vertical attitude fine-tuning. The aerodynamic weather rudder has a hinged mounting position compatible with two structures: it can be installed on the outer wall of the propulsion compartment or the outer wall of the fuel tank, fully covering the two mainstream installation layouts.

[0009] Furthermore, this invention provides two levels of high-temperature resistant material options: a conventional 1000℃ high-temperature alloy suitable for civilian conventional recycling conditions, and a 1400~1600℃ refractory alloy suitable for high-speed reentry extreme high-temperature conditions, comprehensively covering high and low temperature application scenarios. Beneficial effects

[0010] 1. The multi-rudder is evenly distributed in the circumferential direction, with no correction dead angles. It can evenly counteract crosswind disturbances in all directions in 360°. Compared with traditional solutions, the landing point drift is reduced by more than 70%, which greatly reduces the salvage range and lowers the recovery cost. 2. The dual-stage high-temperature resistant material design covers the range from 1000℃ conventional high temperature to 1600℃ extreme reentry high temperature, completely solving the problem of rudder body ablation and deformation failure, and is suitable for all working conditions of reentry environment; 3. The dual locking + spring-forced ejection structure ensures extremely high synchronization of multi-rudder separation, eliminating major malfunctions such as rudder jamming, lag, and entanglement of the deceleration chute. 4. It can freely switch between two working modes, taking into account both high-end precision rudder jetting and weight reduction and low-end simple rudder landing, and is suitable for small and medium-sized civilian rockets of all tonnage. 5. The dual-hull compatible installation structure ensures that regardless of whether the opponent installs the rudder in the propulsion compartment or the fuel tank, it falls within the protection scope of this invention, completely blocking conventional evasion paths; 6. The high- and low-altitude segmented correction logic has a clear division of labor, controlling horizontal drift at high altitudes and vertical attitude at low altitudes, greatly improving recovery accuracy and making it highly adaptable to commercial applications. Attached Figure Description

[0011] Figure 1 This is a schematic diagram of the overall assembly structure of the system; Figure 2 A schematic diagram of the cross-sectional structure of a single lateral aerodynamic weather vane; Figure 3 A comparative diagram showing the circumferential arrangement of 3 120° and 4 90° rudders; Figure 4 A cross-sectional schematic diagram of the explosive bolt + spring double-locking ejection separation mechanism; Figure 5 This is an assembly diagram of an embodiment where an aerodynamic weather vane is installed on the outer wall of the fuel tank.

[0012] Explanation of component markings in each attached drawing: ① Servo-driven linkage; ②Aerodynamic weather rudder; ③ Shaft; ④ Central rotating shaft and double-locking ejection separation mechanism; ⑤ The rudder body is arranged circumferentially; ⑥ Propulsion module; ⑦Lock; ⑧ Fuel tank. Detailed Implementation

[0013] All embodiments are consistent with the core structure of this invention, with only routine adaptation and replacement of parameters, layout, installation position, and materials, all of which fall within the protection scope of this invention.

[0014] Example 1 (Preferred conventional operating conditions: 3 rudders, propulsion compartment installation, 1000℃ alloy, high-altitude jettison) Three aerodynamic weather rudders ② are evenly and circumferentially hinged along the outer wall of the propulsion compartment ⑥ at 120°. The rudder body is made of a 1000℃ high-temperature resistant alloy base material; ① servo drive linkage and ③ rotating shaft cooperate to drive the rudder surface to deflect precisely from 0° to 30°. When the first stage of the rocket re-enters and descends to an altitude range of 3-8km, the system activates attitude correction, using multi-rudder coordinated deflection to counteract the lateral crosswind and control the horizontal drift of the rocket body to 2-3km. After the high-altitude correction is completed, the whole machine timing controller outputs a unified unlocking signal, the ⑦ latch of the ④ double-lock ejection separation mechanism is unlocked synchronously, the spring forces the ejection of the three rudders, the separation error of the multiple rudders is ≤0.12s, and the synchronous ejection and weight reduction are achieved. Descending to a low altitude of less than 300m, the aerodynamic rudder correction is turned off, and the micro-jet engine is switched to fine-tune the vertical attitude, completing a precise recovery.

[0015] Example 2 (Simplified recovery scenario: 4 rudders, fuel tank installed, landing with rudders throughout) Four ② pneumatic weather rudders are evenly distributed at 90° on the outer wall of the ⑧ fuel tank and are made of 1000℃ high temperature resistant alloy; In the 3-8km altitude range, horizontal drift correction is completed by the coordinated action of four rudders. After the correction is completed, the ejection mechanism is not triggered, and the rudders remain fixed and follow the rocket body as it falls. The main deceleration parachute bears the additional wind load on the control body, and the micro-jet engine starts at a low altitude of 50~300m to offset the residual wind disturbance, making it suitable for ultra-small, low-cost civilian rocket recovery scenarios.

[0016] Example 3 (Multi-specification rudder layout adaptation: universal solution for 5-rudder and 6-rudder configurations) Depending on the rocket body diameter and wind load requirements, a structure with 5 72° or 6 60° circumferentially evenly arranged components can be selected. The deflection stroke of the control surface remains unchanged at 0°~30°. The segmented correction logic, dual locking ejection structure, and dual working modes are fully reused. The landing point drift can still be stably controlled within 2~3km, which is an equivalent replacement embodiment.

[0017] Example 4 (High-Temperature Upgrade Extreme Working Conditions: Refractory Alloy Scheme at 1400~1600℃) Replace the ② aerodynamic weather vane with a niobium-based refractory alloy substrate, which can withstand the high temperature of high-speed reentry aerodynamics at 1400~1600℃ for a short time. The remaining servo drive structure, shaft hinge structure, double locking ejection mechanism, high and low altitude segmented correction timing, and dual mounting position structure remain completely unchanged; It is adapted to extreme high-temperature recovery conditions such as no front-mounted reverse thrust deceleration, large dive angle, and high-speed reentry, achieving full coverage of high and low temperature scenarios.

Claims

1. A three-dimensional high-temperature resistant aerodynamic rudder attitude correction system, characterized in that: The system includes multiple sets of aerodynamic weather vanes ②, a servo deflection mechanism, a dual-locking ejection separation mechanism ④, and timing signal docking terminals. The aerodynamic weather vanes ② are hinged to the outer wall of the rocket body via servo drive linkages ① and rotating shafts ③, and are evenly arranged circumferentially along the outer wall. The arrangement can be 3 at 120°, 4 at 90°, 5 at 72°, or 6 at 60°, with a fixed deflection stroke of 0°~30°. The dual-locking ejection separation mechanism ④ is a composite locking structure of explosive bolts and springs ⑦, and the synchronous separation error of the multiple sets of aerodynamic weather vanes ② is ≤0.2s. The system has two operating modes. In the first mode, after attitude correction at mid-to-high altitudes of 3-8 km, the aerodynamic weather vane ② is jettisoned synchronously. In the second mode, the aerodynamic weather vane ② remains fixed to the outer wall of the rocket body throughout the flight and is not jettisoned. Horizontal drift is corrected only in the 3-8 km range using the aerodynamic weather vane ②, with the landing drift range controlled at 2-3 km. At low altitudes of 50-300 m, the microjet engine and lateral attitude correction parachute are switched to complete the terminal vertical attitude correction. The aerodynamic weather vane ② can be hinged and installed on either the outer wall of the propulsion compartment ⑥ or the outer wall of the fuel tank ⑧.

2. The three-dimensional high-temperature resistant aerodynamic rudder attitude correction system according to claim 1, characterized in that: The aerodynamic weather vane ② is made of a first-class high-temperature resistant alloy base material, which can withstand the high temperature of rocket reentry aerodynamics of 1000℃ and is compatible with conventional civilian recovery rockets.

3. The three-dimensional high-temperature resistant aerodynamic rudder attitude correction system according to claim 1, characterized in that: The aerodynamic weather vane ② is made of a secondary refractory high-temperature alloy substrate, which can withstand short-term aerodynamic high temperature of 1400~1600℃ and is suitable for high-speed reentry vehicles without deceleration.

4. The three-dimensional high-temperature resistant aerodynamic rudder attitude correction system according to claim 1, characterized in that: The servo drive linkage ①, in conjunction with the rotating shaft ③, drives the aerodynamic weather vane ② to achieve reciprocating deflection adjustment from 0° to 30°.

5. The three-dimensional high-temperature resistant aerodynamic rudder attitude correction system according to claim 1, characterized in that: The dual-locking ejection separation mechanism ④ has multiple sets of synchronous spring ejection components built in, and the synchronous separation error of all aerodynamic weather vanes is controlled within 0.2s.

6. The three-dimensional high-temperature resistant aerodynamic rudder attitude correction system according to claim 1, characterized in that: The aerodynamic weather rudder consists of three evenly arranged 120° circumferential rudders, which are installed as a whole on the outer wall of the propulsion cabin and jettisoned after being corrected at high altitude.

7. The three-dimensional high-temperature resistant aerodynamic rudder attitude correction system according to claim 1, characterized in that: The aerodynamic weather vane consists of four evenly arranged 90° circumferential rudders, which are installed on the outer wall of the fuel tank and are recovered after landing without being jettisoned.

8. The three-dimensional high-temperature resistant aerodynamic rudder attitude correction system according to claim 1, characterized in that: In the altitude range of 3km to 8km, the aerodynamic weather rudder is used to counteract the crosswinds, and the landing point drift is controlled within the range of 2km to 3km.

9. The three-dimensional high-temperature resistant aerodynamic rudder attitude correction system according to claim 1, characterized in that: At low altitudes of 50m to 300m, the aerodynamic weather rudder is cut off for correction, and the micro-jet engine is switched to complete the fine adjustment of the rocket's vertical attitude.

10. The three-dimensional high-temperature resistant aerodynamic rudder attitude correction system according to claim 1, characterized in that: A combination of five 72° or six 60° circumferentially evenly arranged aerodynamic weather vanes can be selected, with the deflection stroke remaining constant at 0°~30°.

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