A nozzle position adjusting mechanism for simulating interaction of engine plume of a deep space probe with regolith

Abstract

The application discloses a nozzle position adjusting mechanism for simulating the interaction between the engine plume of a deep space probe and asteroid soil, and belongs to the technical field of deep space probe ground simulation tests. The nozzle position adjusting mechanism comprises a structural frame, an asteroid soil box which is fixed below the structural frame and is used for containing simulated asteroid soil, a nozzle which is installed at the end of a motion mechanism and serves as a driven component, a cylinder A which is used for driving the nozzle to move in a vertical direction to simulate the descending process of the probe, a cylinder B which is used for driving the nozzle to move in a horizontal direction to simulate the translation process of the probe, and a rotary cylinder which is used for driving the nozzle to swing back and forth around a horizontal axis to simulate the attitude swing of the probe. The application can realize the influence of multi-factor coupling on the erosion depth of the asteroid soil, the erosion symmetry and the attitude interference torque of the probe.

Description

Technical Field

[0001] This invention belongs to the field of deep space exploration ground simulation test technology, and in particular relates to a nozzle position adjustment mechanism for simulating the interaction between the engine plume of a deep space probe and the stellar soil. Background Technology

[0002] During the landing process of a deep space probe, the high-speed plume generated by its engine impacts the surface of the celestial body, causing erosion of the stellar soil, dust, and asymmetric reaction forces, directly affecting landing safety and the probe's attitude stability. To conduct relevant experimental research on the ground, it is necessary to simulate the multi-degree-of-freedom motion of the nozzle during the landing process.

[0003] However, existing plume-spherical soil interaction simulation devices have relatively simple nozzle movement modes, mostly only able to achieve simple vertical rise and fall, making it difficult to realistically reproduce the complex movements such as lateral drift and attitude swing that accompany the probe during actual landing. This makes it impossible to fully examine the combined effects of multiple factors such as vertical descent speed, horizontal movement speed, swing angle and frequency on the depth of spherical soil erosion, erosion symmetry and probe attitude disturbance torque, thus limiting the engineering guidance value of the experimental results. Summary of the Invention

[0004] To address the shortcomings of existing technologies, this invention provides a nozzle position adjustment mechanism that simulates the interaction between the plume of a deep space probe engine and stellar soil, thus solving the aforementioned problems.

[0005] To achieve the above objectives, the present invention provides the following technical solution: a nozzle position adjustment mechanism for simulating the interaction between the engine plume of a deep space probe and stellar soil, comprising: a structural frame; a stellar soil box, fixed below the structural frame for holding simulated stellar soil; a nozzle, installed at the end of the motion mechanism and serving as a driven component; cylinder A for driving the nozzle to move vertically to simulate the descent of the probe; cylinder B for driving the nozzle to move horizontally to simulate the translation of the probe; and a rotary cylinder for driving the nozzle to reciprocate around a horizontal axis to simulate the attitude swing of the probe.

[0006] A further technical solution: The experimental device can simulate the ratio of nozzle height above ground to nozzle radius. The range is 0~90.

[0007] Further technical solution: The total vertical descent stroke of the nozzle The vertical descent stroke is changed by cylinder A. It is used to adjust the range of plume height.

[0008] Further technical solution: The nozzle descends a certain distance per second The nozzle's descent distance per second is adjusted via cylinder A. It is used to influence the depth of plume erosion and the height of dust.

[0009] Further technical solution: The total horizontal movement stroke of the nozzle The stroke of the horizontal movement of the nozzle is adjusted by cylinder B, which is used to affect the erosion range of the plume on the star soil and its attitude stability.

[0010] Further technical solution: The nozzle moves horizontally a distance per second The horizontal movement distance of the nozzle per second is adjusted by cylinder B. It is used to affect the ground contact speed and the disturbance torque.

[0011] Further technical solution: the nozzle swing angle The nozzle swing angle is changed by rotating the cylinder. It is used to influence the asymmetry of plume erosion of the star soil and the disturbance torque.

[0012] A further technical solution: The nozzle executes a composite trajectory including at least one of the following motions: descent, translation, and oscillation, according to set parameters. such as vertical motion ; Horizontal movement ; Swinging motion ; Indicates the vertical descent speed. Indicates horizontal movement speed. Indicates the amplitude of the swing. Indicates the oscillation frequency. Indicates the initial height. Indicates the initial horizontal position.

[0013] Beneficial effects This invention provides a nozzle position adjustment mechanism that simulates the interaction between the plume of a deep space probe engine and stellar regolith, and has the following advantages compared with the prior art: 1. Strong multi-degree-of-freedom motion simulation capability: The mechanism can independently control the nozzle to perform vertical descent, horizontal translation, and reciprocating oscillation around the vertical axis, realistically reproducing the complex motion trajectory of a deep space probe during landing and achieving comprehensive simulation of multi-degree-of-freedom motion processes. 2. Motion trajectory: A comprehensive simulation of multi-degree-of-freedom motion processes is achieved, with a wide range of adjustable motion parameters and strong adaptability: the total vertical descent stroke can reach 450mm, the total horizontal movement stroke can reach 1100mm, the swing angle is not less than ±10°, and both the descent speed and horizontal movement speed can be adjusted within the range of 0~300mm / s. Taking China's Tianwen-1 Mars probe as a reference, its focus is on the height-to-radius ratio (…). Erosion begins to appear around 26, and this organization can achieve [further action]. =0~90 full range simulation, and related speed indicators ( The rate of change far exceeds the requirements of actual missions, and the parameter range fully covers and surpasses the key state points of concern during the descent process, adapting to the test requirements of various detector models.

[0014] 3. Supports systematic research on parameter influence patterns: Based on its wide-range and high-precision motion adjustment capabilities, it can easily perform benchmark static tests, single-factor tests, and multi-factor combined test matrices. For example, by systematically changing the vertical descent speed, horizontal movement speed, swing amplitude, and swing frequency, it can comprehensively reveal the influence patterns of each motion parameter individually and in combination on the depth of erosion, dust height, erosion asymmetry, and probe attitude disturbance torque, providing crucial experimental basis for the design of lander engine thrust control strategies and attitude control algorithms. Attached Figure Description

[0015] Figure 1 This is a three-dimensional structural diagram of the present invention.

[0016] Figure 2 This is a partial structural diagram of the present invention.

[0017] Figure 3 For the present invention Figure 2 An enlarged schematic diagram of structure A in the image.

[0018] Figure reference numerals: Structural frame 101, nozzle 201, cylinder A 207, cylinder B 208, star soil box 209, rotary cylinder 302. Detailed Implementation

[0019] To make the objectives, technical solutions, and advantages of this invention clearer, the invention will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative and not intended to limit the invention.

[0020] The specific implementation of the present invention will be described in detail below with reference to specific embodiments.

[0021] Please see Figures 1-3The present invention provides a nozzle position adjustment mechanism for simulating the interaction between the plume of a deep space probe engine and star soil, comprising a structural frame 101. The star soil box 209 is fixed below the structural frame 101 and is used to hold simulated star soil; The nozzle 201 is installed at the end of the rotary cylinder 302 and serves as the driven component; An air path system, connected to the nozzle 201, is used to supply gas with adjustable pressure to the nozzle 201 to form a simulated plume; A vertical motion module is used to drive the nozzle 201 to move in the vertical direction to simulate the descent process of the detector; A horizontal motion module is used to drive the nozzle 201 to move in the horizontal direction to simulate the translation process of the detector. The oscillation module is used to drive the nozzle 201 to oscillate back and forth around a horizontal axis to simulate the swaying of the probe's attitude.

[0022] Specifically, the vertical motion module includes a cylinder A207, and an air tank 206 is fixedly connected to a slider that slides back and forth in the vertical direction on the cylinder A207. By activating the cylinder A207, the vertical stroke of the nozzle 201 is changed, thereby adjusting the plume height range and providing a basis for studying the influence on erosion depth and dust height. By changing the vertical speed of the nozzle 201, the descent rate is adjusted, thereby providing a basis for studying the influence on ground contact speed and attitude stability.

[0023] The horizontal motion module includes cylinder B208, and cylinder A207 is fixedly connected to a slider that reciprocates in the horizontal direction on the star soil box 209. By activating cylinder B208, the stroke of nozzle 201 in the horizontal direction is changed, simulating the horizontal displacement of a deep space probe engine, thereby affecting the erosion range and attitude stability, and changing the speed of nozzle 201 in the horizontal direction, thus providing a basis for studying the simulated horizontal ground contact speed and its influence on ground contact speed and disturbance torque. The swing module includes a rotary cylinder 302, which is fixedly connected to the lower surface of cylinder A207. The solenoid valve 202 is fixedly installed on the output shaft of the rotary cylinder 302 and is used to drive the solenoid valve 202 to swing back and forth. By starting the rotary cylinder 302, the swing angle of the nozzle 201 is changed, thereby adjusting the spray angle of the nozzle 201 onto the star soil in the star soil box 209, thus affecting the erosion asymmetry and interference torque.

[0024] As a preferred option, the motion parameters of this test apparatus have a wide design range. For example, the total vertical descent stroke of nozzle 201 The nozzle descends a distance of 201 meters per second. Total horizontal travel of nozzle 201 The nozzle moves horizontally a distance of 201 meters per second. Nozzle 201 swing angle Nozzle 201 exit radius Taking China's Tianwen-1 Mars probe as an example, and referring to the numerical calculation results in the literature, when When the ratio of nozzle height to nozzle radius is approximately 26, the erosive effect of the engine plume on the Martian surface begins to appear. This experimental setup can achieve The simulation of the descent process shows that even if the nozzle radius Re is later expanded to 10mm, the state point corresponding to H / Re=45 can still be simulated, indicating that the current design parameters can fully cover the height range of interest during the descent process. Furthermore, according to publicly available reports, the Tianwen-1 Mars probe descended a distance of [distance] per second before landing. The maximum achievable descent distance per second of this device It can completely simulate the dynamic descent process; In addition, this experimental device can achieve a total horizontal movement of 1100 mm, a maximum horizontal movement distance of 300 mm per second, and a swing angle of more than ±10°. Coupled with the aforementioned descent process, it can comprehensively simulate the multi-degree-of-freedom motion process of a deep space probe during landing.

[0025] This invention also provides a test method using the above-mentioned test apparatus, comprising the following steps: setting a vertical descent speed. Horizontal movement speed x, swing amplitude and oscillation frequency The motion parameters are set; the gas path system is activated, allowing the high-pressure gas to reach the set pressure after secondary decompression and form a high-speed plume from the nozzle 201; simultaneously, the vertical motion module, horizontal motion module, and oscillation module drive the nozzle 201 to execute a composite trajectory including at least one of the following motions: descent, translation, and oscillation, according to the set parameters: such as vertical motion ; Horizontal movement ; Swinging motion ; Indicates the vertical descent speed. Indicates horizontal movement speed. Indicates the amplitude of the swing. Indicates the oscillation frequency. Indicates the initial height. Indicates the initial horizontal position.

[0026] The core design parameters of the experimental device of this invention are as follows: Total vertical descent stroke of nozzle 201 Nozzle 201 descends a distance per second Total horizontal travel of nozzle 201 Nozzle 201 horizontal movement distance per second Nozzle 201 swing angle Nozzle 201 Exit Radius In the above implementation method, taking China's Tianwen-1 Mars probe as an example, and referring to the numerical calculation results in the literature, when When the ratio of nozzle height to nozzle radius is approximately 26, the erosive effect of the engine plume on the Martian surface begins to appear. This experimental setup can achieve The descent process can be simulated, and even if the nozzle radius Re expands to 10 mm in the later stages, it can still be simulated. The state point corresponding to =45 indicates that the current design parameters can fully cover the height segment of interest during the descent process; Furthermore, according to publicly available reports, the Tianwen-1 Mars probe descended a distance of [distance] per second before landing. The maximum achievable descent distance per second of this device It can completely simulate the dynamic descent process; In addition, this experimental device can achieve a total horizontal movement of 1100 mm, a maximum horizontal movement distance of 300 mm per second, and a swing angle greater than ±10°. Coupled with the aforementioned descent process, it can comprehensively simulate the multi-degree-of-freedom motion process of a deep space probe during landing. Furthermore, it can utilize single-factor or two-factor combination experimental matrices (such as vertical descent speed) to simulate this motion. Use values ​​of 0.05, 0.15, and 0.30 m / s for horizontal movement speed. Use values ​​of 0, 0.05, and 0.10 m / s; oscillation amplitude Choose 0°, 5°, and 10°; oscillation frequency By taking values ​​of 0.2, 0.5, and 1.0 Hz, the influence of various motion parameters on the depth of stellar soil erosion, dust height, erosion asymmetry, and the disturbance torque of the detector attitude can be systematically studied. Trial matrix: 1. Standard Static Test parameter( , , θ0, Once set, it remains unchanged during the experiment.

[0027] 2. Single-factor experiment Only one parameter changes, while the others remain fixed values ​​(which can be set). 1 series: change, =0, θ0=0°, =0Hz 2. series: change, =0.1m / s, θ0=0°, =0Hz 3. θ0 series: θ0 variation, =0.1m / s, =0, =0Hz 4. series: change, =0.1m / s, =0, θ0=10° Total: 3 x 4 = 12 groups 3. Two-factor combination experiment Pairing up: 1. and Combinations (3×3=9 groups, θ0=0°, =0Hz) 2. Combined with θ0 (3×3=9 groups, =0, =0Hz) 3. and Combinations (3×3=9 groups) =0, θ0=10°) 4. Combined with θ0 (3×3=9 groups, =0.1m / s, =0.5Hz) 5. and Combinations (3×3=9 groups) =0.1m / s, θ0=10°) 6. θ0 and Combinations (3×3=9 groups) =0, =0) Total: 9 x 6 = 54 groups.

[0028] It should be noted that, in this document, relational terms such as "first" and "second" are used only to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such process, method, article, or apparatus.

[0029] The term "fixed connection" as used in this application refers to a connection in which parts or components are fixed without any relative movement. This includes both detachable and non-detachable connections. (1) Detachable connection: The parts are fixed together by screws, splines, wedges, etc. This type of connection can be disassembled during maintenance without damaging the parts, but the specifications of the connecting parts used must be correct (such as the length of bolts, keys, wedges) and properly tightened; (2) Non-removable connection: mainly refers to welding, riveting and tenon joints, etc. Since forging, sawing or oxygen cutting is required for disassembly during maintenance or replacement, the parts generally cannot be reused. At the same time, attention should be paid to process quality, technical inspection and remedial measures (such as correction, polishing, etc.) when connecting.

[0030] The sliding connection referred to in this application means that the component can slide along a linear trajectory, and the hinge referred to in this application means that the component can rotate along an axially constrained direction; in some cases, the sliding connection and hinge referred to in this application can also be damped, so that the component has the ability to maintain in the desired position.

[0031] Although embodiments of the invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A nozzle position adjustment mechanism for simulating the interaction between a deep space probe engine plume and stellar soil, characterized in that, include; Structural framework (101); The star soil box (209) is fixed below the structural frame (101) and is used to hold simulated star soil; The nozzle (201) is installed at the end of the motion mechanism (101) and serves as the driven component; Cylinder A (207) is used to drive the nozzle (201) to move in the vertical direction to simulate the descent process of the detector; Cylinder B (208) is used to drive the nozzle (201) to move in the horizontal direction to simulate the translation process of the detector; A rotary cylinder (302) is used to drive the nozzle (201) to reciprocate around a horizontal axis to simulate the attitude swing of the detector.

2. The nozzle position adjustment mechanism for simulating the interaction between the engine plume of a deep space probe and stellar soil as described in claim 1, characterized in that, The experimental setup can simulate the ratio of the nozzle (201) height above the ground to the nozzle (201) radius. The range is 0~90.

3. The nozzle position adjustment mechanism for simulating the interaction between the engine plume of a deep space probe and stellar soil as described in claim 1, characterized in that, The nozzle (201) vertically descends a total of... The vertical descent stroke is changed by cylinder A (207). It is used to adjust the range of plume height.

4. The nozzle position adjustment mechanism for simulating the interaction between the engine plume of a deep space probe and stellar soil as described in claim 1, characterized in that, The nozzle (201) descends a distance per second The distance the nozzle (201) descends per second is adjusted by cylinder A (207). It is used to influence the depth of plume erosion and the height of dust.

5. The nozzle position adjustment mechanism for simulating the interaction between the engine plume of a deep space probe and stellar soil according to claim 1, characterized in that, The total horizontal movement stroke of the nozzle (201) The stroke of the horizontal movement of the nozzle (201) is adjusted by the cylinder B (208) to affect the erosion range of the plume on the star soil and the attitude stability.

6. The nozzle position adjustment mechanism for simulating the interaction between the engine plume of a deep space probe and stellar soil according to claim 1, characterized in that, The nozzle (201) moves horizontally a distance per second The horizontal movement distance of the nozzle (201) per second is adjusted by cylinder B (208). It is used to affect the ground contact speed and the disturbance torque.

7. The nozzle position adjustment mechanism for simulating the interaction between the engine plume of a deep space probe and stellar soil according to claim 1, characterized in that, The nozzle (201) swing angle The swing angle of the nozzle (201) is changed by rotating the cylinder (302). It is used to influence the asymmetry of plume erosion of the star soil and the disturbance torque.

8. The nozzle position adjustment mechanism for simulating the interaction between the engine plume of a deep space probe and stellar soil according to claim 1, characterized in that, The nozzle (201) executes a composite trajectory including at least one of the following motions: descent, translation, and oscillation, according to set parameters: such as vertical motion ; Horizontal movement ; Swinging motion ; Indicates the vertical descent speed. Indicates horizontal movement speed. Indicates the amplitude of the swing. Indicates the oscillation frequency. Indicates the initial height. Indicates the initial horizontal position.

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