Propulsion device, mars vehicle deployment device and method employing the same

Abstract

The application relates to a propelling device, a Mars aircraft deployment device and a method, and belongs to the technical field of rotor-type Mars aircrafts. The application aims to provide a Mars aircraft propelling device and deployment device which can guarantee that the aircraft can bear the overload caused in the launching process and can be released from the lander after landing on Mars and provided with a take-off environment. The propelling device comprises two first-order fixed rods arranged in parallel in the horizontal direction, two second-order propelling rods correspondingly slidably arranged in the two first-order fixed rods in the length direction, two third-order propelling rods correspondingly slidably arranged in the two second-order propelling rods in the length direction, and a transmission assembly. Through the propelling device, the aircraft in the folded state and an outer envelope body used for limiting the aircraft are pushed out of the lander, so that the aircraft can be fully unfolded and taken off. The technical problem of aircraft storage and unfolding after launching and landing in the prior art is effectively solved.

Description

Technical Field

[0001] This invention relates to a propulsion device, a Mars spacecraft deployment device and method using the propulsion device, and belongs to the technical field of rotorcraft Mars spacecraft. Background Technology

[0002] Mars, as the closest planet to Earth, has recently attracted much attention. To explore the origins of life and the evolutionary history of planets, Mars sample return has become a major mission for various countries exploring Mars. Mars spacecraft-based exploration methods offer higher efficiency and a wider detection range. Using Mars spacecraft to perform sample return missions allows for the collection of scientifically valuable samples from distant locations.

[0003] Since the size envelope of the quadcopter Mars spacecraft does not meet the launch requirements, the quadcopter Mars spacecraft needs to be folded and unfolded. During the release and takeoff process, the blades of the unfolded spacecraft need to be fully deployed. Therefore, there is an urgent need for a spacecraft propulsion and deployment device that can ensure that the spacecraft can withstand the overload caused during the launch process and can be released by the lander after landing on Mars and provide a takeoff environment. Summary of the Invention

[0004] The present invention aims to solve the above-mentioned technical problems and provides a propulsion device, a Mars spacecraft deployment device and method using the propulsion device.

[0005] The technical solution adopted by the present invention to solve the above-mentioned technical problems is as follows:

[0006] A propulsion device includes two first-order fixed rods arranged horizontally in parallel, two second-order propulsion rods correspondingly slidably inserted into the two first-order fixed rods along the length direction, two third-order propulsion rods correspondingly slidably inserted into the two second-order propulsion rods along the length direction, and a transmission assembly. The transmission assembly includes a drive rope, a winding wheel, a first pulley, a second pulley, and a third pulley. The winding wheel is rotatably mounted on a lander and its rotation is controlled by a winding motor. The first pulley is rotatably mounted on the front part of the first-order fixed rod, the second pulley is rotatably mounted on the rear part of the second-order propulsion rod, and the third pulley is rotatably mounted on the front end of the second-order propulsion rod. The drive rope is sequentially wound around the first to third pulleys, with one end of the drive rope wound around the winding wheel and the other end fixedly clamped to the rear part of the third-order propulsion plate. Each first-order fixed rod has several support legs fixedly mounted at its bottom end.

[0007] Furthermore, a fixed bracket is provided between the two first-order fixed rods. The bottom end of the fixed bracket is fixed to the lander, and the top end of the fixed bracket is fixed to the bottom of the outer envelope through an unlocking expansion joint.

[0008] Furthermore, sliding wheels are respectively provided between the second-order push rod and the first-order fixed rod, and between the third-order push rod and the second-order push rod.

[0009] Furthermore, the upper part of the first-order fixed rod and the upper part of the second-order push rod are provided with channels along their length direction, and the channels are connected to the internal space of the first-order fixed rod or the second-order push rod.

[0010] Furthermore, the first pulley is rotatably mounted on the first-stage fixed rod via the first pulley mounting component, the second pulley is rotatably mounted on the rear of the second-stage push rod via the second pulley mounting component, and the third pulley is rotatably mounted on the front end of the second-stage push rod via the third pulley mounting component. Each first-stage fixed rod has a through hole vertically opened on its front bottom surface, and the upper part of the first pulley is located inside the through hole.

[0011] Furthermore, a limit block is fixedly installed on the rear bottom end face of the third-stage push rod, and the limit block's extension limit position is limited by the third pulley mounting component.

[0012] Furthermore, the two first-order fixed rods are fixedly connected by several crossbeams.

[0013] Furthermore, the two winding wheels are arranged side by side and fixedly connected by a connecting shaft. The two winding wheels are rotatably mounted on the top of the lander via two motor support frames. The winding motor is fixedly mounted on one of the motor support frames and its output shaft is fixedly connected to the connecting shaft.

[0014] A Mars spacecraft deployment device employing the aforementioned propulsion system includes a lander, a robotic arm, a propulsion system, and an outer enclosure. Several support legs of the robotic arm and propulsion system are fixedly mounted on the top of the lander. The outer enclosure is fixedly mounted on two third-order propulsion rods. When not deployed, the spacecraft is folded and installed within the outer enclosure. The outer enclosure includes a shell assembly and a locking assembly for controlling the opening and closing of the shell assembly. The shell assembly includes a cubically arranged top cover, bottom plate, and four side baffles. A spacecraft support frame is fixedly mounted inside the shell assembly, with the spacecraft fuselage located at the top of the support frame and the top cover. Between them, and through several positioning ball heads at the top of the aircraft support frame to achieve horizontal limitation, the upper and lower parts of the aircraft support frame are respectively distributed with four first limiting members and four second limiting members along their circumference. The upper, middle and lower inner walls of each side baffle are respectively fixed with third limiting members, fourth limiting members and fifth limiting members. In the closed state of the shell assembly, the four wing motors of the aircraft are correspondingly clamped between the second limiting members and the fifth limiting members, the propeller blades are correspondingly clamped between the first limiting members and the fourth limiting members, and the solar panel on the top of the aircraft is clamped between the four third limiting members.

[0015] A deployment method using the aforementioned Mars spacecraft deployment device includes the following steps:

[0016] Step 1: When the aircraft is deployed, the outer envelope separates from the lander, the propulsion system activates, and the outer envelope and the aircraft inside it extend out of the lander.

[0017] Step 2: The robotic arm presses down on the top of the outer envelope, and the envelope expansion device in the locking assembly expands and breaks, causing the four side baffles to flip outward and open, thereby releasing the outer constraint on the aircraft.

[0018] Step 3: Control the robotic arm to remove the top cover of the outer envelope, and the aircraft will fly away from the lander, completing the flight deployment of the aircraft.

[0019] Compared with the prior art, the present invention has the following advantages:

[0020] The propulsion device of this invention has a simple structure and safe and reliable operation. It pushes the folded-out spacecraft and its external enclosure (used for spacecraft restraint) out of the lander, facilitating the full deployment and takeoff of the spacecraft. This effectively solves the technical problem of spacecraft storage and deployment after launch and landing in existing Mars spacecraft technologies.

[0021] By using various limiting components inside the outer enclosure, the aircraft's wing motors, propellers, and solar panels are pressed together, ensuring that the aircraft can resist structural damage caused by vibration during launch and landing.

[0022] By using various limiting components inside the outer enclosure, the aircraft's wing motors, propellers, and solar panels are pressed together, ensuring that the aircraft can resist structural damage caused by vibration during launch and landing. Attached Figure Description

[0023] Figure 1 This is a schematic diagram of the first three-dimensional structure of the propulsion device;

[0024] Figure 2 for Figure 1 Enlarged cross-sectional view at point A;

[0025] Figure 3 for Figure 1 Enlarged cross-sectional view at point B;

[0026] Figure 4 This is a schematic diagram of the second three-dimensional structure of the propulsion device;

[0027] Figure 5 for Figure 4 Enlarged schematic diagram of point P;

[0028] Figure 6 for Figure 4 A magnified diagram of point N;

[0029] Figure 7 for Figure 4 A schematic diagram showing the installation positions of the first and second pulleys in the indicated direction;

[0030] Figure 8 This is a schematic diagram of the maximum extension position of the third-order push rod; (the second-order push rod is not shown, so as to clearly show the limiting component at the rear end of the third-order push rod).

[0031] Figure 9 A three-dimensional structural diagram of the deployment device when the aircraft is not deployed;

[0032] Figure 10 A three-dimensional structural diagram of the deployment device with the propulsion unit extended when deployed for an aircraft;

[0033] Figure 11 A three-dimensional structural diagram of the deployment device with the propulsion unit fully extended from the lander and the outer envelope deployed when deployed for the aircraft;

[0034] Figure 12 A three-dimensional structural diagram of the deployment device in the takeoff state of an aircraft;

[0035] Figure 13 This is a schematic diagram of the unfolded structure of the outer envelope;

[0036] Figure 14 A schematic diagram of the three-dimensional structure of the outer envelope in half-section view;

[0037] Figure 15 for Figure 14 Enlarged view of point C;

[0038] Figure 16 for Figure 14 Enlarged schematic diagram of the main section at point D.

[0039] In the picture:

[0040] 100. Propulsion device;

[0041] 1. First-stage fixed rod; 1-1. Through hole; 2. Second-stage push rod; 3. Third-stage push rod; 4-1. Drive rope; 4-2. Winding wheel; 4-3. First pulley; 4-4. Second pulley; 4-5. Third pulley; 4-6. First pulley mounting bracket; 4-7. Second pulley mounting bracket; 4-8. Third pulley mounting bracket; 4-10. Motor support frame; 4-11. Winded motor;

[0042] 101. Lander;

[0043] 102. Robotic arm;

[0044] 103. Envelope;

[0045] 12-1 Top cover; 12-2 Bottom plate; 12-3 Side baffle; 13-1 Envelope expansion joint; 13-2 Upper locking plate; 13-3 Lower locking plate; 13-4 Steel rope; 13-5 Locking pin; 13-6 Square sliding sleeve; 13-7 Round sliding sleeve; 13-8 Unlocking spring; 13-9 Expansion joint spring; 13-10 Tensioning element; 13-11 Coil spring; 14 Aircraft support frame; 15 Positioning ball head; 16 First limiting element; 17 Second limiting element; 18 Third limiting element; 19 Fourth limiting element; 20 Fifth limiting element. Detailed Implementation

[0046] Combination Figures 1 to 16 The technical solutions in the embodiments of the present invention are clearly and completely described. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0047] It should be noted that the descriptions of "left," "right," "left side," "right side," "upper part," "lower part," "top," and "bottom" in this invention are defined based on the orientation or positional relationships shown in the accompanying drawings. They are merely for the convenience of describing the invention and for simplifying the description, and do not indicate or imply that the described structure must be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on the invention. In the description of this invention, "a plurality of" means two or more, unless otherwise explicitly specified.

[0048] In the description of this invention, unless otherwise expressly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal communication between two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0049] Specific implementation method one: Combining Figures 1-14This embodiment describes a propulsion device, comprising two first-order fixed rods 1 arranged horizontally in parallel, two second-order propulsion rods 2 correspondingly slidably inserted into the two first-order fixed rods 1 along the length direction, two third-order propulsion rods 3 correspondingly slidably inserted into the two second-order propulsion rods 2 along the length direction, and a transmission assembly. The transmission assembly includes a drive rope 4-1, a winding wheel 4-2, a first pulley 4-3, a second pulley 4-4, and a third pulley 4-5. The winding wheel 4-2 is rotatably mounted on the lander 101. The rotation is controlled by a winding motor 4-11. The first pulley 4-3 is rotatably installed at the front of the first-stage fixed rod 1, the second pulley 4-4 is rotatably installed at the rear of the second-stage push rod 2, and the third pulley 4-5 is rotatably installed at the front end of the second-stage push rod 2. The drive rope 4-1 is sequentially wound on the first to third pulleys 4-5, with one end of the drive rope 4-1 wound on the winding wheel 4-2 and the other end fixedly clamped to the rear of the third-stage push plate. Several support legs 5 are fixedly installed at the bottom of each first-stage fixed rod 1.

[0050] In this invention, the front of the propulsion device is the direction in which the propulsion device extends, and the rear is the direction in which it retracts.

[0051] Two first-order fixed rods 1 are fixed to the top of the lander 101 by several support legs 5, and the outer envelope 103 is fixed to two third-order thrust rods 3.

[0052] There are two sets of transmission components, which respectively control the extension of the second-order push rod 2 and the third-order push rod 3 on the same side.

[0053] The propulsion process of the propulsion device 100 is achieved by tightening the drive rope 4-1 through the winding wheel 4-2. Specifically, the winding motor 4-11 drives the winding wheel 4-2 to rotate counterclockwise, which in turn drives the first pulley 4-3 to rotate counterclockwise through the drive rope 4-1, thereby driving the second pulley 4-4 to rotate clockwise. At the same time, the second pulley 4-4 and the second-stage push rod fixed to the second pulley 4-4 are pulled forward. When the second-stage push rod 2 moves to its limit position, the drive rope 4-1 continues to drive the third pulley 4-5 to rotate counterclockwise, thereby pulling the third-stage push rod 3 forward. When the third-stage push rod 3 moves to its limit position, the winding motor 4-11 stops rotating, and the propulsion of the propulsion device 100 is completed.

[0054] The propulsion device 100 extends, driving the outer envelope 103 on the third-stage propulsion rod 3 to extend out of the lander 101, thereby extending the aircraft 104 inside the outer envelope 103 out of the lander 101.

[0055] The propulsion device of the present invention has a simple structure and safe and reliable operation. Through the propulsion device, the spacecraft 104 in its folded state and its external enclosure 103 used for limiting the spacecraft 104 are pushed out of the lander 101, facilitating the deployment and flight of the spacecraft 104. This effectively solves the technical problem of storing and deploying the Mars spacecraft 104 after launch and landing in the prior art.

[0056] The drive rope 4-1 can be a steel wire rope.

[0057] A fixed support 6 is also provided between the two first-order fixed rods 1. The bottom end of the fixed support 6 is fixedly connected to the lander 101, and the top end of the fixed support 6 is fixedly connected to the bottom of the outer envelope 103 through an unlocking expansion joint 7. With this design, the outer envelope 103 and the lander 101 are connected by the fixed support 6. When the aircraft 104 is deployed, the unlocking expansion joint 7 is energized to cause the internal metal rod to break, thereby separating the outer envelope 103 from the fixed support 6, and thus separating the outer envelope 103 from the lander 101.

[0058] Sliding wheels 8 are respectively installed between the second-stage push rod 2 and the first-stage fixed rod 1, and between the third-stage push rod 3 and the second-stage push rod 2. This design facilitates the sliding of the second-stage push rod 2 within the first-stage fixed rod 1 and the sliding of the third-stage push rod 3 within the second-stage push rod 2. The specific positions of the sliding wheels 8 can be selected according to actual conditions; preferably, the sliding wheel 8 between the second-stage push rod 2 and the first-stage fixed rod 1 is rotatably installed at the rear end of the second-stage push rod 2. The sliding wheels 8 between the third-stage push rod 3 and the second-stage push rod 2 are rotatably installed at both the front and rear ends of the third-stage push rod 3.

[0059] Both the upper part of the first-order fixed rod 1 and the upper part of the second-order push rod 2 have channels along their length, and these channels communicate with the internal space of the corresponding first-order fixed rod 1 or second-order push rod 2. This design facilitates the fixed connection between the outer envelope 103 and the push device 100, allowing the third-order push rod 3 to slide smoothly along the push direction when the two are fixedly connected.

[0060] The first pulley 4-3 is rotatably mounted on the first-stage fixed rod 1 via the first pulley mounting piece 4-6. The second pulley 4-4 is rotatably mounted on the rear of the second-stage push rod 2 via the second pulley mounting piece 4-7. The third pulley 4-5 is rotatably mounted on the front end of the second-stage push rod 2 via the third pulley mounting piece 4-8. Each first-stage fixed rod 1 has a vertically oriented through hole 1-1 at its front bottom surface, with the upper part of the first pulley 4-3 located within the through hole 1-1. This design facilitates the passage of the drive rope 4-1 through the through hole 1-1. Simultaneously, the location of the upper part of the first pulley 4-3 within the through hole 1-1 allows for limiting the forward movement of the second pulley 4-4 to its extreme position, preventing excessive slippage of the second pulley 4-4 and thus preventing the second-stage push rod 2 from disengaging from the first-stage fixed rod 1.

[0061] A limiting block 10 is fixedly mounted on the rear bottom end face of the third-stage push rod 3. The extension limit position of the limiting block 10 is limited by the third pulley mounting part 4-8. With this design, when the third-stage push rod 3 extends to the limit position, the limiting block 10 is blocked by the third pulley mounting part 4-8, thereby limiting the extension limit position of the third-stage push rod 3.

[0062] Two first-order fixed rods 1 are fixedly connected by several crossbeams 11. This design, by setting several crossbeams 11, serves to reinforce the first-order fixed rods 1. The crossbeams 11 are arranged along the length of the first-order fixed rods 1.

[0063] Two winding wheels 4-2 are arranged side by side and fixedly connected by a connecting shaft. The two winding wheels 4-2 are rotatably mounted on the top of the lander 101 via two motor support frames 4-10. The winding motor 4-11 is fixedly mounted on one of the motor support frames 4-10, and its output shaft is fixedly connected to the connecting shaft. This design enables the synchronous rotation of the two winding wheels 4-2 through the connecting shaft, thereby ensuring the synchronous movement of the two second-order push rods and the synchronous movement of the two third-order push rods.

[0064] Specific Implementation Method Two: Combining Figures 1-16This embodiment describes a Mars spacecraft deployment device employing the aforementioned propulsion system, comprising a lander 101, a robotic arm 102, a propulsion system 100, and an outer enclosure 103. The robotic arm 102 and several support legs 5 of the propulsion system 100 are fixedly mounted on the top of the lander 101. The outer enclosure 103 is fixedly mounted on two third-order propulsion rods 3. When not deployed, the spacecraft 104 is folded and installed within the outer enclosure 103. The outer enclosure 103 includes a shell assembly and a locking assembly for controlling the opening and closing of the shell assembly. The shell assembly includes a cubically arranged top cover 12-1, a bottom plate 12-2, and four side baffles 12-3. A spacecraft support frame 14 is fixedly mounted inside the shell assembly. The fuselage of the spacecraft 104 is located within the flight... Between the top of the aircraft support frame 14 and the top cover 12-1, and through several positioning ball heads 15 at the top of the aircraft support frame 14, horizontal positioning is achieved. The upper and lower parts of the aircraft support frame 14 are respectively distributed with four first limiting members 16 and four second limiting members 17 along their circumference. The upper, middle and lower inner walls of each side baffle 12-3 are respectively fixed with third limiting members 18, fourth limiting members 19 and fifth limiting members 20. In the closed state of the shell assembly, the four wing motors of the aircraft 104 are correspondingly clamped between the second limiting members 17 and the fifth limiting members 20, the propeller blades are correspondingly clamped between the first limiting members 16 and the fourth limiting members 19, and the solar panel on the top of the aircraft 104 is clamped between the four third limiting members 18.

[0065] With this design, the propulsion device 100 is fixed to the lander 101 by the support leg 5. When deploying the aircraft 104, the top cover 12-1 of the outer envelope 103 is removed by the robotic arm 102.

[0066] The first limiting member 16 and the fourth limiting member 19 correspond to form the propeller limiting members of the aircraft 104;

[0067] The second limiting member 17 and the fifth limiting member 20 correspond to form the wing motor limiting members of the aircraft 104;

[0068] Four third limiting members 18 press the solar panels of the aircraft 104 together;

[0069] The limiting components inside the outer enclosure 103 press the wing motors, propellers and solar panels of the aircraft 104 together, ensuring that the aircraft 104 can resist structural damage caused by vibration during launch and during landing of the lander 101.

[0070] The locking assembly includes an envelope expansion joint 13-1, an upper locking plate 13-2, a lower locking plate 13-3, steel ropes 13-4, an upper locking plate 13-5, a square sliding sleeve 13-6, a round sliding sleeve 13-7, and an unlocking spring 13-8. The lower locking plate 13-3 is fixedly mounted in the middle of the base plate 12-2. There are four steel ropes 13-4, and one end of each steel rope 13-4 is clamped between the upper locking plate 13-2 and the lower locking plate 13-3. The envelope expansion joint 13-1 is pressed above the upper locking plate 13-2 and fixedly connected to the lower locking plate 13-3. An expansion joint spring 13-9 is vertically compressed between the upper locking plate 13-2 and the lower locking plate 13-3. Each steel rope 13-4 is equipped with a tensioning element 13-10. Four side baffles are also included. The upper part of the inner wall of 12-3 is fixedly equipped with square sliding sleeves 13-6 and round sliding sleeves 13-7 arranged vertically opposite each other. Each square sliding sleeve 13-6 and its corresponding round sliding sleeve 13-7 are provided with an upper locking piece 13-5. Each upper locking piece 13-5 is slidably inserted into the square sliding sleeve 13-6 and round sliding sleeve 13-7 through a square sliding rod fixed at its upper part and a round sliding rod fixed at its lower part. The lower surface of the top cover 12-1 is fixedly equipped with three top hooks. The bottom surface of the upper locking piece 13-5 is machined with a bevel that corresponds to the top hook. The unlocking spring 13-8 is fitted on the round sliding rod between the round sliding sleeve 13-7 and the upper locking piece 13-5. The other end of the steel rope 13-4 is fixedly connected to the bottom end of the corresponding round sliding rod.

[0071] An opening is provided between the round sliding sleeve 13-7 and the square sliding sleeve 13-6. The top hook enters through the opening and engages with the upper locking plate 13-5. A notch is provided in the middle of the top hook to avoid the round sliding rod. In the folded state of the aircraft 104, adjusting the tensioning member 13-10 causes the upper locking plate 13-5 to press the top hook and fix it to itself, thereby maintaining the fixed connection between the side baffle 12-3 and the top cover 12-1, and pressing the aircraft 104 tightly into the shell assembly. This allows the aircraft 104 to resist overload and vibration generated during launch in the folded state. When the aircraft 104 is deployed, the envelope expander 13-1 is energized, causing its internal metal rod to expand and break, which separates the upper locking plate 13-2 from the lower locking plate 13-3. The ball head of the steel cable 13-4 falls off, causing the steel cable 13-4 to lose tension. Under the action of the unlocking spring 13-8, the upper locking plate 13-5 moves upward and separates from the top hook. All side baffles 12-3 are unlocked from the top cover 12-1 and flip outward.

[0072] The four side baffles 12-3 are connected to the base plate 12-2 via rotating shafts, and each rotating shaft is equipped with a coil spring 13-11. The coil springs 13-11 facilitate the outward flipping action of each side baffle 12-3.

[0073] All limiting components are made of foam. The use of foam limiting components can effectively reduce the overall weight of the outer enclosure 103, while also protecting the wing motors, propellers, and solar panels, preventing structural damage during launch or landing of the lander 101.

[0074] Other components and connections are the same as in Specific Implementation Method 1.

[0075] Specific implementation method three: Combining Figures 1-16 This embodiment describes a deployment method using the aforementioned Mars spacecraft deployment device, comprising the following steps:

[0076] Step 1: When the aircraft is deployed, the outer envelope 103 separates from the lander 101, the propulsion device 100 is activated, and the outer envelope 103 and the aircraft 104 inside it extend out of the lander 101; by unlocking the expansion joint 7 and energizing it, the metal rod inside it breaks, thereby separating the outer envelope 103 from the fixed support 6, and thus separating the outer envelope 103 from the lander 101.

[0077] Step 2: The robotic arm 102 presses down on the top of the outer envelope 103. The envelope expansion device 13-1 in the locking assembly expands and breaks, causing the four side baffles 12-3 to flip outward and open, thereby releasing the outer constraint on the aircraft 104.

[0078] Step 3: Control the robotic arm 102 to remove the top cover 12-1 of the outer enclosure 103, and the aircraft 104 flies away from the lander 101, completing the flight deployment of the aircraft 104.

[0079] The deployment method described in this invention enables the spacecraft 104 to resist overload and vibration generated during launch in a folded state, and to safely and reliably release the Mars spacecraft after landing on the Martian surface, while also providing a flight environment for the Mars spacecraft.

[0080] Other components and connections are the same as in specific implementation method one or two.

[0081] The above description is only a preferred embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any equivalent substitutions or modifications made by those skilled in the art within the scope of the technology disclosed in the present invention, based on the technical solution and inventive concept of the present invention, should be covered within the scope of protection of the present invention.

Claims

1. A method of deploying a Mars vehicle deployment device, the method comprising: The deployment device includes a lander (101), a robotic arm (102), a propulsion device (100), and an outer enclosure (103). The propulsion device (100) includes two first-order fixed rods (1) arranged horizontally in parallel, two second-order propulsion rods (2) correspondingly slidably inserted into the two first-order fixed rods (1) along the length direction, two third-order propulsion rods (3) correspondingly slidably inserted into the two second-order propulsion rods (2) along the length direction, and a transmission assembly. The transmission assembly includes a drive rope (4-1), a winding wheel (4-2), a first pulley (4-3), a second pulley (4-4), and a third pulley (4-5). Wheel (4-2) is rotatably mounted on lander (101) and its rotation is controlled by wound motor (4-11). First pulley (4-3) is rotatably mounted on the front of first-stage fixed rod (1). Second pulley (4-4) is rotatably mounted on the rear of second-stage push rod (2). Third pulley (4-5) is rotatably mounted on the front end of second-stage push rod (2). Drive rope (4-1) is sequentially wound on first to third pulleys (4-5). One end of drive rope (4-1) is wound on wound wheel (4-2), and the other end is fixedly clamped to the rear of third-stage push plate. Several support legs (5) are fixedly mounted at the bottom of each first-stage fixed rod (1). Several support legs (5) of the robotic arm (102) and propulsion device (100) are fixedly mounted on the top of the lander (101). The outer enclosure (103) is fixedly mounted on two third-order propulsion rods (3). When the aircraft (104) is not deployed, it is folded and installed inside the outer enclosure (103). The outer enclosure (103) includes a shell assembly and a locking assembly for controlling the opening and closing of the shell assembly. The shell assembly includes a top cover (12-1), a bottom plate (12-2), and four side baffles (12-3) arranged in a cubic shape. An aircraft support frame (14) is fixedly mounted inside the shell assembly. The fuselage of the aircraft (104) is located between the top of the aircraft support frame (14) and the top cover (12-1), and is connected to the aircraft support frame (14). Several positioning ball heads (15) at the top achieve horizontal positioning. The upper and lower parts of the aircraft support frame (14) are respectively distributed with four first positioning members (16) and four second positioning members (17) along their circumference. The upper, middle and lower inner walls of each side baffle (12-3) are respectively fixed with third positioning members (18), fourth positioning members (19) and fifth positioning members (20). In the closed state of the shell assembly, the four wing motors of the aircraft (104) are respectively clamped between the second positioning members (17) and the fifth positioning members (20), and the propeller blades are respectively clamped between the first positioning members (16) and the fourth positioning members (19). The solar panel on the top of the aircraft (104) is clamped between the four third positioning members (18). The deployment method includes the following steps: Step 1: When the aircraft is deployed, the outer envelope (103) separates from the lander (101), the propulsion device (100) is activated, and the outer envelope (103) and the aircraft (104) inside it extend out of the lander (101); Step 2: The robotic arm (102) presses down on the top of the outer envelope (103), and the envelope expander (13-1) in the locking assembly expands and breaks, causing the four side baffles (12-3) to flip outward and open, thereby releasing the outer constraint on the aircraft (104). Step 3: Control the robotic arm (102) to remove the top cover (12-1) of the outer envelope (103), and the aircraft (104) flies away from the lander (101), completing the flight deployment of the aircraft (104).

2. The method of deploying a Mars vehicle deployment device of claim 1, wherein: A fixed bracket (6) is also provided between the two first-order fixed rods (1). The bottom end of the fixed bracket (6) is fixed to the lander (101), and the top end of the fixed bracket (6) is fixed to the bottom of the outer envelope (103) by an unlocking expansion joint (7).

3. The method of deploying a Mars vehicle deployment device according to claim 1 or 2, wherein: Sliding wheels (8) are respectively provided between the second-order push rod (2) and the first-order fixed rod (1) and between the third-order push rod (3) and the second-order push rod (2).

4. The method of deploying a Mars vehicle deployment device of claim 1, wherein: The upper part of the first-order fixed rod (1) and the upper part of the second-order push rod (2) are provided with channels along their length direction. The channels are connected to the internal space of the first-order fixed rod (1) or the second-order push rod (2).

5. The deployment method of the Mars spacecraft deployment device according to claim 1, characterized in that: The first pulley (4-3) is rotatably mounted on the first-stage fixed rod (1) via the first pulley mounting piece (4-6). The second pulley (4-4) is rotatably mounted on the rear of the second-stage push rod (2) via the second pulley mounting piece (4-7). The third pulley (4-5) is rotatably mounted on the front end of the second-stage push rod (2) via the third pulley mounting piece (4-8). Each first-stage fixed rod (1) has a through hole (1-1) vertically opened on the front bottom end face, and the upper part of the first pulley (4-3) is located in the through hole (1-1).

6. The deployment method of the Mars spacecraft deployment device according to claim 5, characterized in that: A limit block (10) is fixedly installed on the rear bottom end face of the third-stage push rod (3), and the extension limit position of the limit block (10) is limited by the third pulley mounting part (4-8).

7. The deployment method of the Mars spacecraft deployment device according to claim 1, characterized in that: Two first-order fixed rods (1) are fixedly connected by several crossbeams (11).

8. The deployment method of the Mars spacecraft deployment device according to claim 1, characterized in that: Two winding wheels (4-2) are arranged side by side and fixedly connected by a connecting shaft. The two winding wheels (4-2) are rotatably mounted on the top of the lander (101) via two motor support frames (4-10). The winding motor (4-11) is fixedly mounted on one of the motor support frames (4-10) and its output shaft is fixedly connected to the connecting shaft.

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