Innovative Design of a Modular Mars Probe Satellite
By: Wu Jiawei, Zhou Yu, Jiang Yihang
This article is sourced from“Invention and Innovation” August 2023 High School Edition
Our school is the first “Future Talent Training Base for Aerospace” in Chongqing, offering courses such as “Design and Manufacturing of Launch Vehicle Structures” and “Exploration and Production of Functional Simulated Satellites”.
Through our studies, we learned that Mars exploration missions are currently a research hotspot in the aerospace field, aiming to lay the foundation for the next phase of Mars base construction. After class, our teacher asked us to try designing a Mars base. While researching, we found that transforming the Martian environment and constructing a base on Mars is a long and arduous process.
We thought of the method used in field scientific research—before entering the deep mountains for investigation, we should first build a forward base at the foot of the mountain to meet the needs of material supply and long-term monitoring.
During the exploration process, we discovered that Phobos could serve as a “natural space station” for Mars, facilitating the construction of the Mars base. Additionally, Phobos has high strategic significance and scientific research value, and several countries have begun related research. The exploration of Phobos will be the second most important aerospace task after Mars exploration.
Wu Jiawei is mainly responsible for the design and application of the satellite’s main structure, functional design, and paper writing. Zhou Yu is mainly responsible for 3D structure design and printing, system programming, and system debugging. Jiang Yihang is mainly responsible for structure design and drawing, circuit connections, and structure assembly.
(1) Terrain and Landform Imaging
Comprehensively acquire terrain and landform data, detect open and flat terrain, analyze the distribution of impact craters, and consider factors such as energy supply, foundation pits, observation stations, and living environments to provide references for site selection for the base. By identifying foundation pit images, determine coordinate locations to customize the optical navigation system for the subsequent construction of Phobos.
(2) Gravitational Field Measurement
Design orbits to ensure a high success rate for spacecraft landing and escape.
(3) Other Tasks
Such as detecting the environment of Phobos, measuring atmospheric conditions, illumination, radiation, and the distribution of internal rocks and ice layers, etc.
To collect gravitational field, terrain, and landform data from Phobos, we designed a separable “multi-satellite” structure for the Phobos probe satellite, using a multi-satellite combination to enter a stable quasi-satellite orbit around Phobos, which then separates into individual cube satellites. Through the optical imaging module and gravitational gradient instrument carried on this platform, comprehensive detection of Phobos will be conducted, establishing a self-organizing communication network among single satellites for task allocation and monitoring.
We named the designed satellite “Spark One”; the overall system composition of the satellite is shown in Figure 1.
Figure 1: Schematic Diagram of the Satellite’s Overall System Composition
Before the satellite is launched, different cube satellite units are selected for assembly according to different mission objectives, with cube satellite unit 1 serving as the main body of the satellite, capable of conducting communication between the satellite and the ground (in addition, it also has long-term orbital maneuvering capability). Other cube satellites serve as payload units, each carrying different mission payloads, such as high-definition visible light cameras, gravitational gradient instruments, and AI intelligent processing platforms. They are connected together through an automatic separation mechanism before separation, and automatically separate upon reaching the mission orbit. After separation, a self-organizing network is established among the satellite units for online task planning and data sharing.
Taking the dual-satellite combination as an example, the “Spark One” satellite is divided into optical imaging cube satellite units and gravitational gradient detection cube satellite units. Each cube satellite unit structure adopts the international standard 1U (10 cm x 10 cm x 10 cm) cube satellite frame as the structural system, and the layout of various devices in the cube satellite unit is fixedly connected to the satellite structure by stacking. The structure of the “Spark One” satellite and the three-dimensional layout of the internal devices are shown in Figure 2.
Figure 2: Three-Dimensional Diagram of the Structure of the “Spark One” Satellite and Layout of Internal Devices
(1) Design of Physical Model
The physical model includes the overall design of the satellite structure and the design of the satellite electronic system. The overall structure of the satellite includes the overall design of the 1U cube satellite unit and the design of the separable connection device.
The exterior of the single satellite adopts a deployable solar panel to increase the satellite’s power generation capacity. Solar sensors are set on the X, Y, and Z planes of the satellite to provide attitude information. The “Spark One” satellite is equipped with multiple lithium-ion batteries, working in conjunction with solar panels to ensure stable power supply. The satellite’s electronic system mainly includes gravitational data collection based on STM32 microcontroller and image recognition system based on Raspberry Pi.
The physical model adopts a dual-satellite combination unit, where one cube satellite unit collects gravitational data and detects atmospheric dust, while the other cube satellite unit collects and analyzes images. In terms of ground simulation system payload, the optical imaging satellite is equipped with temperature sensors and high-resolution cameras, while the gravitational gradient detection satellite is equipped with gravitational gradient instruments and dust detection sensors.
Figure 3: Construction and Assembly of the “Spark One” Satellite Structure
(2) Design of Satellite Circuit
The satellite physical system mainly consists of three layers: data acquisition layer, data processing layer, and result display layer. The data acquisition layer includes gravitational sensors, temperature sensors, dust detection sensors, and high-definition camera modules. The data processing layer includes processors based on STM32 F103 chips and image processing modules based on Raspberry Pi. The result display layer uses OLED displays.
(3) Design of Satellite Separation Structure
Considering that the optical imaging satellite and gravitational gradient detection satellite need to perform tasks in different orbits, we designed a simple mechanical structure for separating small satellites. This structure includes a response device, mechanical transmission device, and ejection release device, with advantages such as low cost, simple structure, stable operation, and small separation impact force. This separation device enhances the satellite’s expandability, facilitating the implementation of parallel multi-task detection plans.
Figure 4: Mechanical Structure and Physical Model of Satellite Separation
(4) AI Image Recognition
Using high-definition cameras to capture raw images, these raw images include visual image information and infrared image information of the surface of Phobos within the detector’s field of view. Based on the processed images, features of the surface of Phobos can be extracted through analysis of foundation pits and contours.
During the validation experiment, there was a lack of real-time images of Phobos, so we designed the satellite’s image recognition system as an offline system, meaning it cannot capture images of Phobos in real-time. Therefore, the shooting process is omitted, and photos of Phobos are used for overall contour and surface foundation pit feature recognition.
Figure 5: Steps of Image Recognition
Using the same processing method to identify foundation pits and mark basic coordinates. However, there were errors between the experimental results and expectations, and further optimization of the program will continue.
(5) Gravitational Data Collection
Using a six-axis gyroscope to simulate the construction of a gravitational gradient instrument, measuring acceleration in three axes, simulating the measurement of satellite gravitational acceleration through the Z-axis.
Figure 6: Testing of the Simulated Gravitational Gradient Instrument
The MCU controller reads the serial data from the gyroscope module JY61, which includes the acceleration data in three axes. The gyroscope module is placed with the Z-axis facing up on a stationary table, and the read acceleration data in three axes is consistent with the predicted results.
(6) Other Tasks
In the simulation experiment, through visual programming, the “Spark One” satellite achieved dust detection, temperature detection, and display. Through assembly and programming debugging, the “Spark One” satellite basically meets the design requirements.
We propose a multi-task parallel Phobos probe system design, which is expected to achieve preliminary detection tasks for sustainable development of Mars exploration. The modular structure can promote scientific discoveries in Mars exploration and drive the development of deep space exploration technology and modular spacecraft design technology.
The “Spark One” satellite still has considerable room for improvement, and we will make the following improvements in the future: integrate artificial intelligence and deep learning to optimize image recognition algorithms; improve the separation device to achieve free adjustment of separation and assembly; and conduct research and analysis on the thermal control system to ensure the satellite can function normally in the Martian environment. (Guiding Teachers: Tian Zhen, Long Cheng)
General Secretary Xi Jinping pointed out that “Exploring the vast universe, developing the aerospace industry, and building a strong aerospace nation is our unremitting pursuit of the aerospace dream.” The separation-type Phobos probe satellite designed by students Wu Jiawei, Zhou Yu, and Jiang Yihang is an innovative practical work involving the aerospace professional field. The emergence of this work mainly reflects: first, the effective implementation of the school’s characteristic science and technology project—”Future Talent Training Base for Aerospace” and courses such as “Design and Manufacturing of Launch Vehicle Structures” and “Exploration and Production of Functional Simulated Satellites” is commendable. Second, the teacher guided students to explore practical projects on “Mars environmental transformation and base construction,” focusing on the exploration of approaches and methods for aerospace talent cultivation, demonstrating pioneering spirit and leading the cultivation of top talents in related fields. Third, it showcases the students’ learning and application abilities in aerospace-related knowledge and technology.
The report of the 20th National Congress of the Communist Party pointed out: “The starry sky is vast, exploration is endless, and only through continuous innovation can the Chinese nation better move towards the future.” We believe that the three students will grow into outstanding aerospace talents needed by the country and the people in the school’s characteristic science and technology field. (Expert Reviewer: Tan Di’ao, First Expert of the Expert Consultation Work Committee of the China Invention Association, President of the Invention Education Branch of the China Invention Association, Special Teacher of Science and Technology Innovation Education, Expert in the National Training Program for Teachers of the Ministry of Education.)
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Source:“Invention and Innovation” August 2023 High School Edition
Edited by: Qin Yinyin, Xia Yanhui
Reviewed by: Qin Yinyin
Final Review: Li Baichun