Retractable rotor-type Mars manned spacecraft overall device and deployment method thereof

Abstract

The present invention relates to a retractable rotor-type Mars manned aircraft overall device and a deployment method thereof, and belongs to the technical field of aerospace Mars rotor-type aircraft. With respect to the existing Mars aircraft overall configuration, there is still a lack of a retractable eight-axis sixteen-rotor Mars manned aircraft overall configuration. A retractable rotor-type Mars manned aircraft overall device and a deployment method thereof are provided, comprising a main frame, a seat, a landing gear, and a rotor assembly. The main frame is connected to the rotor assemblies arranged equidistantly in the circumference. A seat is provided in the middle of the main frame, and a landing gear is provided below the seat. The rotor assembly comprises forward blades, a motor, a rotor arm, and reverse blades. The forward blades and reverse blades are connected to the motor, and the coaxially arranged forward blades and reverse blades are connected to the main frame via the rotor arm. The present invention has a stable structure, simple operation, a small folded envelope size, can complete manned flight, and is of great significance to the overall configuration of multi-rotor Mars manned aircraft.

Description

Technical Field

[0001] The present invention relates to a retractable rotor-type manned Mars aircraft overall device and a deployment method thereof, belonging to the technical field of aerospace Mars rotor-type aircraft. Background Art

[0002] Because Mars and Earth share similarities in planetary characteristics, sunlight, and seasons, humanity is committed to exploring Mars to promote scientific and technological development, resource utilization, and the advancement of human civilization. Currently, Mars rovers, the mainstream exploration method, face significant challenges traversing complex terrain such as canyons, mountains, and steep slopes due to their inherent limitations in performance and design. This hinders rovers from conducting more extensive scientific research and resource exploration on the Martian surface. Compared to rovers, Mars spacecraft explore the Martian surface through aerial flight. Therefore, they are significantly less affected by the Martian terrain, enabling more comprehensive and efficient exploration of the Martian surface. Furthermore, the successful flight of the US Ingenuity Mars helicopter has demonstrated the feasibility of rotary-wing aircraft on Mars, paving the way for future manned missions to Mars. In the prior art, for example, publication number CN209225382U, titled "A Tilt-Rotor Manned Flying Chair," discloses a technical solution comprising a main frame within the backrest, connected to the sides of the canopy and the seat, with a front landing gear and two rear landing gears positioned beneath the seat. This advantageously allows the manned flying chair to achieve vertical lift, aerial maneuvers, and low-altitude flight. However, the main frame is connected to the canopy and seat at the edges, which increases the difficulty of analyzing the device's forces. This makes it more suitable for small or simple flying structures. Publication number CN110155313A, titled "A Multi-Rotor Manned Aircraft," discloses a technical solution comprising four power modules, secured at four right angles to the battery compartment. The power modules comprise a power assembly and an arm assembly, configured in an eight-axis, sixteen-propeller configuration. This advantageously allows the multi-rotor manned aircraft to have excellent mechanical properties, a long flight time, a large payload, and enhanced safety. However, when it is folded, the interference range of the rotating propellers at the same right angle is large, resulting in the space it occupies still being large when folded.

[0003] Therefore, it is urgent to propose a retractable rotor-type Mars manned spacecraft overall device and its deployment method to solve the above-mentioned technical problems. Summary of the Invention

[0004] To overcome the aforementioned technical deficiencies, the present invention aims to provide a retractable rotary-wing manned Mars spacecraft assembly and a method for deploying the same. A brief overview of the present invention is provided below to provide a basic understanding of certain aspects of the present invention. It should be understood that this overview is not an exhaustive overview of the present invention. It is not intended to identify key or important aspects of the present invention, nor is it intended to limit the scope of the present invention.

[0005] The technical solution of the present invention:

[0006] The overall device of a retractable rotor-type manned Mars spacecraft includes a main frame, seats, landing gear, and rotor assemblies. The main frame is connected to the rotor assemblies arranged equidistantly around the circumference. The seat is set in the middle of the main frame, and the landing gear is set below the seat.

[0007] The rotor assembly includes forward blades, a motor, a rotor arm and reverse blades. The forward blades and reverse blades are connected to the motor, and the coaxially arranged forward blades and reverse blades are connected to the main frame through the rotor arm.

[0008] Preferably: the rotor assembly also includes a motor connector and a motor driver, the motor connector is equipped with a motor driver, one end of the motor connector is connected to one end of the rotor arm, the other end of the motor connector is connected to two motors, the output end of one motor is connected to the forward blade, and the output end of the other motor is connected to the reverse blade.

[0009] Preferably: the rotor assembly also includes a propeller clamp, the four forward blades are circumferentially equidistantly connected by a propeller clamp to form a forward rotor, the four reverse blades are circumferentially equidistantly connected by another propeller clamp to form a reverse rotor, a propeller clamp on the axis of the forward rotor is connected to the output end of one motor, and another propeller clamp on the axis of the reverse rotor is connected to the output end of another motor, and two symmetrical propeller clamps are located on both sides of the motor connector.

[0010] Preferably, the number of the rotor assemblies is eight, and the eight groups of rotor assemblies are arranged in a circular array.

[0011] Preferably: it also includes a connecting frame and a display, the display and the connecting frame are respectively installed on both sides of the seat, the two ends of the connecting frame are respectively connected to the landing frame and the main frame, the upper part of the connecting frame has a bending part, and the display and the connecting frame are respectively arranged on both sides of the seat.

[0012] Preferably, an avionics unit is also included. The avionics unit is arranged on the lower side of the main frame. The avionics unit includes a shell, a processor, a scientific payload and a power supply. A power supply for power supply, a scientific payload for measuring data and a processor are arranged in the shell. The two sides of the shell are respectively connected to the main frame and the connecting frame. The processor is electrically connected to the motor driver and the display.

[0013] Preferably, a rotor arm folding and unfolding assembly is also included, and the rotor arm folding and unfolding assembly is used to realize the folding and unfolding of the rotor assembly.

[0014] Preferably: the rotor arm folding and unfolding assembly includes a clamping part, a positioning side plate, a rotating shaft, a locking spring, a positioning shaft, a fixed side plate and a flange, one side of the positioning side plate is bolted to the clamping part, the middle part of the positioning side plate is rotatably connected to the fixed side plate through the rotating shaft, the other side of the positioning side plate is processed with a groove, the fixed side plate is processed with a horizontal groove, the positioning shaft is slidably connected to the horizontal groove, the two ends of the locking spring are respectively connected to the rotating shaft and the positioning shaft, the positioning shaft is matched with the groove, the flange is connected to the fixed side plate, the flange is connected to the main frame, and the clamping part is connected to the other end of the rotor arm.

[0015] Preferably: the rotor arm folding and unfolding assembly also includes a connecting shaft, two clamping parts, the two clamping parts are arranged in parallel, the middle part of the clamping part has a mounting hole, the other end of the rotor arm is inserted into the mounting hole, and positioning side plates are respectively provided on both sides of the clamping part, the two positioning side plates are connected by a connecting shaft, the two fixed side plates are arranged on the inner side of the positioning side plates, the two ends of the positioning shaft are respectively connected to the horizontal groove of a fixed side plate, and the middle part of the positioning shaft is connected to the middle part of the rotating shaft through a locking spring.

[0016] A method for deploying a retractable rotor-type manned Mars spacecraft overall device, using the retractable rotor-type manned Mars spacecraft overall device, comprises the following steps:

[0017] When the device is in the folded state, the angles between the two adjacent rotor arms and the horizontal plane of the main frame are α and β respectively, and the positioning shaft is tightly attached to the positioning arc groove of the positioning side plate under the tension of the locking spring;

[0018] During the deployment of the device, the astronauts manually pull the positioning shaft out of the positioning arc groove and rotate the rotor assembly around the rotation axis; during this rotation process, the positioning shaft is always in close contact with the positioning side plate under the tension of the locking spring; when the rotor assembly rotates to coincide with the horizontal plane, the positioning shaft slides into the groove and is fixed, completing the deployment process.

[0019] The present invention has the following beneficial effects:

[0020] The present invention is simple to operate and can complete manned flight, and is of great significance to the overall configuration of a multi-rotor manned Mars aircraft.

[0021] The avionics unit, connection frame, and landing gear of the present invention are arranged in a manner in which the connection point is coaxial with the center of gravity, which not only reduces the occupied volume but also simplifies the design difficulty and improves the stability of the device.

[0022] The present invention is a manned aircraft for Mars, and the rotors are evenly arranged, thereby simplifying flight control, reducing the number of electronic components used, and being easy and reliable to use and easy to repair and maintain. The present invention is not only suitable for large-sized rotors, but also easy to control so that the volume when folded is small and the folded envelope size is small. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 1 This is a schematic diagram of the overall structure of a retractable rotor-type manned Mars spacecraft;

[0024] Figure 2 It is a schematic diagram of the structure of the rotor assembly;

[0025] Figure 3 1 is a schematic diagram of the rotor arm folding and unfolding assembly in a folded state;

[0026] Figure 4 1 is a schematic diagram of the rotor arm folding and unfolding assembly in an unfolded state;

[0027] Figure 5 This is a schematic diagram of the overall assembly of the retractable rotor-type manned Mars spacecraft in a folded state;

[0028] Figure 6 yes Figure 5 A magnified schematic diagram of point A in the middle;

[0029] Figure 7 This is a schematic diagram of the expanded state of the overall assembly of the retractable rotor-type Mars manned spacecraft.

[0030] In the figure: 1-main frame, 2-avionics unit, 3-connecting frame, 4-seat, 5-landing gear, 6-display, 7-astronaut position, 8-rotor assembly, 9-rotor arm folding assembly, 8-1-forward blade, 8-2-propeller clamp, 8-3-motor, 8-4-motor connector, 8-5-motor driver, 8-6-rotor arm, 8-7-reverse blade, 9-1-clamping part, 9-2-positioning side plate, 9-3-connecting shaft, 9-4-rotation shaft, 9-5-locking spring, 9-6-positioning shaft, 9-7-fixed side plate, 9-8-flange, 9-21-into groove, 9-22-positioning arc groove, 9-71-horizontal groove. DETAILED DESCRIPTION

[0031] To make the objectives, technical solutions, and advantages of the present invention more clearly apparent, the present invention is described below using specific embodiments shown in the accompanying drawings. However, it should be understood that these descriptions are merely illustrative and are not intended to limit the scope of the present invention. In addition, in the following description, descriptions of well-known structures and technologies are omitted to avoid unnecessary confusion of the concepts of the present invention.

[0032] Specific implementation method 1: Combination Figure 1-Figure 7This embodiment describes a retractable rotary-wing manned Mars spacecraft comprising a main frame 1, seats 4, landing gear 5, and rotor assemblies 8. The sides of the main frame 1 are connected to a plurality of circumferentially equidistantly arranged rotor assemblies 8. The seat 4 is disposed on the lower middle portion of the main frame 1, and the landing gear 5 is disposed below the seat 4. The three-legged landing gear 5 supports the entire device.

[0033] The rotor assembly 8 includes a forward blade 8-1, a motor 8-3, a rotor arm 8-6 and a reverse blade 8-7. A plurality of circumferentially equidistant forward blades 8-1 and reverse blades 8-7 are each connected to a motor 8-3. The coaxially arranged forward blades 8-1 and reverse blades 8-7 are connected to the main frame 1 through the rotor arm 8-6.

[0034] The rotor assembly 8 also includes a motor connector 8-4 and a motor driver 8-5. The motor driver 8-5 is installed on the motor connector 8-4. One end of the motor connector 8-4 is fixedly connected to one end of the rotor arm 8-6. The other end of the motor connector 8-4 is bolted to the housings of two symmetrically arranged motors 8-3. The output end of one motor 8-3 is connected to the forward blade 8-1, and the output end of the other motor 8-3 is connected to the reverse blade 8-7.

[0035] The rotor assembly 8 also includes a propeller clamp 8-2, and the four forward blades 8-1 are fixedly connected circumferentially and equidistantly by a propeller clamp 8-2 to form a forward rotor. The four reverse blades 8-7 are fixedly connected circumferentially and equidistantly by another propeller clamp 8-2 to form a reverse rotor. One propeller clamp 8-2 at the axis of the forward rotor is connected to the output end of one motor 8-3, and the other propeller clamp 8-2 at the axis of the reverse rotor is connected to the output end of another motor 8-3. Two symmetrical propeller clamps 8-2 are located on the upper and lower sides of the motor connector 8-4. The inclination directions of the forward blade 8-1 and the reverse blade 8-7 are opposite, and the steering directions of the forward rotor and the reverse rotor are opposite, providing upward lift for the device and offsetting the generated reverse torque.

[0036] There are eight groups of rotor assemblies 8, which are arranged in a circular array. The eight rotor assemblies 8 in the eight-axis sixteen-rotor manned aircraft are connected to the main frame 1 via rotor arm folding assemblies 9. These rotor arm folding assemblies 9 can work together to complete the deployment and retraction of the rotor assemblies 8, thereby realizing the overall folding of the aircraft.

[0037] The astronaut 7 is provided with a plurality of control panels, each of which is provided with a plurality of control panels, and a plurality of control panels. The astronaut 7 is provided with a plurality of control panels, each of which is provided with a plurality of control panels, and a plurality of control panels. The astronaut 7 is provided with a plurality of control panels, and a plurality of control panels, each of which is provided with a plurality of control panels. The astronaut 7 is provided with a plurality of control panels, and a plurality of control panels, each of which is provided with a plurality of control panels.

[0038] It also includes an avionics unit 2. The avionics unit 2 is disposed on the lower side of the main frame 1. The main frame 1 and the avionics unit 2 are coaxially arranged with their centers of gravity. The avionics unit 2 includes a housing, a processor, a scientific payload, and a power supply. The housing contains a power supply for power supply, a scientific payload for measuring data, and a processor. The upper and lower sides of the housing are fixedly connected to the main frame 1 and the connecting frame 3, respectively. The processor is electrically connected to the motor driver 8-5 and the display 6. The power supply adopts a nuclear power supply, which is used to power the motor 8-3, the motor driver 8-5, and the display 6.

[0039] It also includes a rotor arm folding and unfolding assembly 9, which is used to realize the folding and unfolding of the rotor assembly 8;

[0040] The rotor arm folding and unfolding assembly 9 includes a clamping member 9-1, a positioning side plate 9-2, a rotating shaft 9-4, a locking spring 9-5, a positioning shaft 9-6, a fixed side plate 9-7 and a flange 9-8. One side of the positioning side plate 9-2 is bolted to the clamping member 9-1, and the middle part of the positioning side plate 9-2 is rotatably connected to the fixed side plate 9-7 through the rotating shaft 9-4. A groove 9-21 is machined on the other end of the positioning side plate 9-2, and a rectangular horizontal groove 9-71 is machined on the fixed side plate 9-7. The positioning shaft 9-6 is arranged in the horizontal groove 9-71 and is connected to the horizontal groove 9-71. Sliding connection, the two ends of the locking spring 9-5 are fixedly connected to the rotating shaft 9-4 and the positioning shaft 9-6 respectively, the positioning shaft 9-6 is matched with the groove 9-21, the groove 9-21 is a U-shaped groove, the flange 9-8 is bolted to the fixed side plate 9-7, the flange 9-8 is fixedly connected to the main frame 1, and the clamping piece 9-1 is detachably connected to the other end of the rotor arm 8-6; in the horizontal groove of the fixed side plate 9-7, the positioning shaft 9-6 is provided with a pulling force by the locking spring 9-5 to move horizontally, and after the positioning shaft 9-6 enters the groove of the positioning side plate 9-2, the deployment and locking are completed;

[0041] The rotor arm folding assembly 9 also includes a connecting shaft 9-3, two clamping members 9-1, and the two clamping members 9-1 are arranged in parallel. The clamping member 9-1 includes a left clamping block and a right clamping block. The two clamping blocks are symmetrically arranged to form the clamping member 9-1. The middle part of the clamping member 9-1 has a mounting hole. The other end of the rotor arm 8-6 is inserted into the mounting hole and is clamped and fixed by the left clamping block and the right clamping block. Positioning side plates 9-2 are respectively provided on both sides of the clamping member 9-1. The two positioning side plates 9 -2 is fixedly connected symmetrically by a connecting shaft 9-3, two fixed side plates 9-7 are arranged on the inner side of the positioning side plate 9-2, both ends of the positioning shaft 9-6 are connected to the horizontal groove 9-71 of a fixed side plate 9-7, the middle part of the positioning shaft 9-6 is connected to the middle part of the rotating shaft 9-4 through a locking spring 9-5, and the other end of the positioning shaft 9-6 is also processed with a positioning arc groove 9-22 with an angle less than 90°. The positioning arc groove 9-22 is used to cooperate with the positioning shaft 9-6 for installation in the folded state;

[0042] The specific basic parameters of the overall configuration of a retractable eight-axis sixteen-rotor Mars manned spacecraft are shown in Table 1:

[0043] Table 1 Basic parameters of the device

[0044]

[0045]

[0046] The present invention proposes a retractable eight-axis, sixteen-rotor Mars manned aircraft overall configuration; this solution has a stable structure, simple operation, a small folded envelope size, can complete manned flight, and is of great significance to the overall configuration of multi-rotor Mars manned aircraft; the present invention is a manned aircraft for Mars, and the rotors are evenly arranged, thereby simplifying flight control, thereby reducing the number of electronic components used, and is easy and reliable to use, and easy to repair and maintain; the present invention is not only suitable for large-sized rotors, but also easy to control the volume when folded, and the folded envelope size is small.

[0047] Specific implementation method 2: Combination Figure 1-Figure 7 This embodiment describes a method for deploying a retractable rotor-type manned Mars spacecraft assembly. The retractable rotor-type manned Mars spacecraft assembly, hereinafter referred to as the assembly, comprises a main frame 1, seats 4, landing gear 5, and a rotor assembly 8. The sides of the main frame 1 are connected to a plurality of circumferentially equidistantly arranged rotor assemblies 8. The seat 4 is disposed on the lower middle portion of the main frame 1, and the landing gear 5 is disposed below the seat 4.

[0048] The rotor assembly 8 includes a forward blade 8-1, a motor 8-3, a rotor arm 8-6 and a reverse blade 8-7. The forward blade 8-1 and the reverse blade 8-7 are each connected to a motor 8-3. The coaxial forward blade 8-1 and the reverse blade 8-7 are connected to the main frame 1 through the rotor arm 8-6.

[0049] The rotor assembly 8 also includes a motor connector 8-4 and a motor driver 8-5. The motor driver 8-5 is installed on the motor connector 8-4. One end of the motor connector 8-4 is fixedly connected to one end of the rotor arm 8-6. The other end of the motor connector 8-4 is bolted to the housings of two symmetrically arranged motors 8-3. The output end of one motor 8-3 is connected to the forward blade 8-1, and the output end of the other motor 8-3 is connected to the reverse blade 8-7.

[0050] The rotor assembly 8 also includes a propeller clamp 8-2, and the four forward blades 8-1 are fixedly connected circumferentially and equidistantly by a propeller clamp 8-2 to form a forward rotor. The four reverse blades 8-7 are fixedly connected circumferentially and equidistantly by another propeller clamp 8-2 to form a reverse rotor. One propeller clamp 8-2 at the axis of the forward rotor is connected to the output end of one motor 8-3, and the other propeller clamp 8-2 at the axis of the reverse rotor is connected to the output end of another motor 8-3. Two symmetrical propeller clamps 8-2 are located on the upper and lower sides of the motor connector 8-4. The inclination directions of the forward blade 8-1 and the reverse blade 8-7 are opposite, and the rotation directions of the forward rotor and the reverse rotor are opposite.

[0051] There are eight groups of the rotor assemblies 8, and the eight groups of the rotor assemblies 8 are arranged in a circular array;

[0052] The main frame 1 is fixedly connected to the landing frame 5 and the middle part of the main frame 1. The upper part of the connecting frame 3 has a bent portion, which can provide sufficient space for the astronaut 7 on the seat 4. The connecting frame 3 is fixedly connected to the seat 4, and the display 6 is fixedly connected to the landing frame 5. The display 6 and the connecting frame 3 are respectively arranged on the front and rear sides of the seat 4.

[0053] The apparatus further includes an avionics unit 2. The avionics unit 2 is disposed on the lower side of the main frame 1. The main frame 1 and the avionics unit 2 are arranged coaxially with each other. The avionics unit 2 includes a housing, a processor, a scientific payload, and a power supply. The housing contains a power supply for power supply, a scientific payload for measuring data, and a processor. The upper and lower sides of the housing are fixedly connected to the main frame 1 and the connecting frame 3, respectively. The processor is electrically connected to the motor driver 8-5 and the display 6. The power supply uses a nuclear power source.

[0054] It also includes a rotor arm folding and unfolding assembly 9, which is used to realize the folding and unfolding of the rotor assembly 8;

[0055] The rotor arm folding assembly 9 includes a clamping member 9-1, a positioning side plate 9-2, a rotating shaft 9-4, a locking spring 9-5, a positioning shaft 9-6, a fixed side plate 9-7 and a flange 9-8. One side of the positioning side plate 9-2 is bolted to the clamping member 9-1, and the middle part of the positioning side plate 9-2 is rotatably connected to the fixed side plate 9-7 through the rotating shaft 9-4. A groove 9-21 is processed on the other side of the positioning side plate 9-2, and a rectangular horizontal Slot 9-71, the positioning shaft 9-6 is arranged in the horizontal slot 9-71 and is slidably connected to the horizontal slot 9-71, the two ends of the locking spring 9-5 are fixedly connected to the rotating shaft 9-4 and the positioning shaft 9-6 respectively, the positioning shaft 9-6 is matched with the groove 9-21, the groove 9-21 is a U-shaped groove, the flange 9-8 is bolted to the fixed side plate 9-7, the flange 9-8 is fixedly connected to the main frame 1, and the clamping piece 9-1 is detachably connected to the other end of the rotor arm 8-6;

[0056] The rotor arm folding assembly 9 also includes a connecting shaft 9-3, two clamping members 9-1, and the two clamping members 9-1 are arranged in parallel. The clamping member 9-1 includes a left clamping block and a right clamping block. The two clamping blocks are symmetrically arranged to form the clamping member 9-1. The middle part of the clamping member 9-1 has a mounting hole. The other end of the rotor arm 8-6 is inserted into the mounting hole and is clamped and fixed by the left clamping block and the right clamping block. Positioning side plates 9-2 are respectively provided on both sides of the clamping member 9-1. The two positioning side plates 9-2 is fixedly connected symmetrically by a connecting shaft 9-3, two fixed side plates 9-7 are arranged on the inner side of the positioning side plate 9-2, both ends of the positioning shaft 9-6 are connected to the horizontal groove 9-71 of a fixed side plate 9-7, the middle part of the positioning shaft 9-6 is connected to the middle part of the rotating shaft 9-4 through a locking spring 9-5, and the upper part of the positioning shaft 9-6 is also processed with a positioning arc groove 9-22 with an angle less than 90°. The positioning arc groove 9-22 is used to cooperate with the positioning shaft 9-6 when it is in the folded state;

[0057] A method for deploying a retractable rotor-type manned Mars spacecraft assembly comprises the following steps:

[0058] When the device is in the folded state, the angles between the planes of the two adjacent rotor arms 8-6 and the horizontal plane of the main frame 1 are α=90° and β=108° respectively, and the positioning shaft 9-6 is tightly attached to the positioning arc groove 9-22 of the positioning side plate 9-2 under the tension of the locking spring 9-5;

[0059] During the deployment of the device, astronaut 7 manually pulls the positioning shaft 9-6 out of the positioning arc groove 9-22 and rotates the rotor assembly 8 around the rotation axis 9-4; during this rotation process, the positioning shaft 9-6 is always in close contact with the side of the positioning side plate 9-2 under the tension of the locking spring 9-5; when the rotor assembly 8 rotates to coincide with the horizontal plane, the positioning shaft 9-6 slides into the groove 9-21 along the horizontal groove 9-71 and is fixed, completing the deployment process. The folding process can be performed in the opposite manner to the deployment process.

[0060] It should be noted that in the above embodiments, as long as the technical solutions are not contradictory, they can be permuted and combined. Those skilled in the art can exhaust all possibilities based on the mathematical knowledge of permutations and combinations. Therefore, the present invention will no longer describe the technical solutions after permutations and combinations one by one, but it should be understood that the technical solutions after permutations and combinations have been disclosed by the present invention.

[0061] The foregoing description is merely a preferred embodiment of the present invention and is not intended to limit the present invention. Those skilled in the art will readily appreciate that various modifications and variations of the present invention are possible. Any modifications, equivalent substitutions, or improvements made within the spirit and principles of the present invention are intended to be within the scope of protection of the present invention.

Claims

1. A retractable rotor-type manned Mars spacecraft system, characterized by: The invention comprises a main frame (1), a seat (4), a landing gear (5) and a rotor assembly (8), wherein the main frame (1) is connected to the rotor assembly (8) which is arranged equidistantly in the circumference, a seat (4) is provided in the middle of the main frame (1), and a landing gear (5) is provided below the seat (4); The rotor assembly (8) includes a forward blade (8-1), a motor (8-3), a rotor arm (8-6), and a reverse blade (8-7); the forward blade (8-1) and the reverse blade (8-7) are connected to the motor (8-3); and the coaxially arranged forward blade (8-1) and the reverse blade (8-7) are connected to the main frame (1) via the rotor arm (8-6); It also includes a rotor arm folding and unfolding assembly (9), which is used to realize the folding and unfolding of the rotor assembly (8); The rotor arm folding and unfolding assembly (9) comprises a clamping member (9-1), a positioning side plate (9-2), a rotating shaft (9-4), a locking spring (9-5), a positioning shaft (9-6), a fixed side plate (9-7) and a flange (9-8). One side of the positioning side plate (9-2) is connected to the clamping member (9-1), the middle of the positioning side plate (9-2) is connected to the fixed side plate (9-7) via the rotating shaft (9-4), and the other side of the positioning side plate (9-2) is processed with a groove (9-21). A horizontal groove (9-71) is machined on the fixed side plate (9-7), the positioning shaft (9-6) is slidably connected to the horizontal groove (9-71), the two ends of the locking spring (9-5) are respectively connected to the rotating shaft (9-4) and the positioning shaft (9-6), the positioning shaft (9-6) is matched with the groove (9-21), the flange (9-8) is connected to the fixed side plate (9-7), the flange (9-8) is connected to the main frame (1), and the clamping member (9-1) is connected to the other end of the rotor support arm (8-6); When the retractable rotor-type Mars manned spacecraft is in a folded state, the angles between the two adjacent rotor arms (8-6) and the horizontal plane of the main frame (1) are α and β respectively; The upper portion of the positioning shaft (9-6) is further processed with a positioning arc groove (9-22) having an angle less than 90°. The positioning arc groove (9-22) is used for matching installation with the positioning shaft (9-6) in a folded state.

2. The retractable rotor-type manned Mars spacecraft assembly according to claim 1, characterized in that: The rotor assembly (8) further comprises a motor connector (8-4) and a motor driver (8-5), wherein the motor driver (8-5) is mounted on the motor connector (8-4), one end of the motor connector (8-4) is connected to the rotor arm (8-6), and the other end of the motor connector (8-4) is connected to two motors (8-3), the output end of one motor (8-3) is connected to the forward blade (8-1), and the output end of the other motor (8-3) is connected to the reverse blade (8-7).

3. The retractable rotor-type manned Mars spacecraft assembly according to claim 2, characterized in that: The rotor assembly (8) further comprises a propeller clamp (8-2), wherein four forward blades (8-1) are circumferentially equidistantly connected via one propeller clamp (8-2) to form a forward rotor, and four reverse blades (8-7) are circumferentially equidistantly connected via another propeller clamp (8-2) to form a reverse rotor. One propeller clamp (8-2) on the axis of the forward rotor is connected to the output end of one motor (8-3), and another propeller clamp (8-2) on the axis of the reverse rotor is connected to the output end of another motor (8-3). Two symmetrical propeller clamps (8-2) are located on both sides of the motor connector (8-4).

4. The retractable rotor-type manned Mars spacecraft assembly according to claim 3 is characterized in that: The number of the rotor assemblies (8) is eight groups, and the eight groups of the rotor assemblies (8) are arranged in a circular array.

5. The retractable rotor-type manned Mars spacecraft overall device according to claim 1 or 2, characterized in that: The invention also includes a connecting frame (3) and a display (6), wherein the display (6) and the connecting frame (3) are respectively installed on both sides of the seat (4), and the two ends of the connecting frame (3) are respectively connected to the landing frame (5) and the main frame (1), and the upper part of the connecting frame (3) has a bent portion, and the display (6) and the connecting frame (3) are respectively arranged on both sides of the seat (4).

6. The retractable rotor-type manned Mars spacecraft assembly according to claim 5, characterized in that: The apparatus further comprises an avionics unit (2), which is provided on the lower side of the main frame (1). The avionics unit (2) comprises a housing, a processor, a scientific payload and a power supply. A power supply for power supply, a scientific payload for measuring data and a processor are provided in the housing. Both sides of the housing are respectively connected to the main frame (1) and the connecting frame (3). The processor is electrically connected to the motor driver (8-5) and the display (6).

7. The retractable rotor-type manned Mars spacecraft assembly according to claim 6, characterized in that: The rotor arm folding assembly (9) also includes a connecting shaft (9-3), two clamping members (9-1), the two clamping members (9-1) are arranged in parallel, the middle of the clamping member (9-1) has a mounting hole, the other end of the rotor support arm (8-6) is inserted into the mounting hole, and positioning side plates (9-2) are respectively provided on both sides of the clamping member (9-1), the two positioning side plates (9-2) are connected by the connecting shaft (9-3), the two fixed side plates (9-7) are arranged on the inner side of the positioning side plates (9-2), the two ends of the positioning shaft (9-6) are respectively connected to the horizontal groove (9-71) of a fixed side plate (9-7), and the middle of the positioning shaft (9-6) is connected to the middle of the rotating shaft (9-4) through a locking spring (9-5).

8. A method for deploying a retractable rotor-type manned Mars spacecraft assembly, characterized in that: The overall device of the retractable rotor-type manned Mars spacecraft according to any one of claims 1 to 7 comprises the following steps: During the deployment of the device, the astronaut (7) manually pulls the positioning shaft (9-6) out of the positioning arc groove (9-22) and rotates the rotor assembly (8) around the rotation axis (9-4); during this rotation process, the positioning shaft (9-6) is always in close contact with the positioning side plate (9-2) under the pulling force of the locking spring (9-5); when the rotor assembly (8) rotates to coincide with the horizontal plane, the positioning shaft (9-6) slides into the groove (9-21) and is fixed, completing the deployment process.

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