Ground deployment apparatus and method for a mars vehicle

Abstract

The application relates to a ground deployment device and method of an aircraft, and belongs to the technical field of rotor-type Mars aircrafts. The deployment mode of the Mars aircraft is affected by the surrounding terrain, and the adaptability is low. The application comprises a top cover, a Mars aircraft, a pushing device and a lower envelope body, the top cover is connected with the lower envelope body, the top cover and the lower envelope body form an envelope body, the Mars aircraft and the pushing device are arranged in the envelope body, and the Mars aircraft is arranged on the upper portion of the pushing device. The aircraft of the application is deployed and taken off on a landing platform, the dependence on the terrain around the lander is not strong, the deployment applicability is stronger, and the aircraft is not limited by the terrain.

Description

TECHNICAL FIELD

[0001] The application relates to a ground deployment device and method of an aircraft, and belongs to the technical field of rotor-type Mars aircrafts. BACKGROUND

[0002] Mars, as the planet closest to the earth, has recently attracted much attention. In order to detect the origin of life and the development history of the planet, Mars sample return has become the main task of exploring Mars by various countries, and Mars aircraft exploration is more efficient and has a wider exploration range. Using a Mars aircraft to perform a Mars sample return task can collect scientific samples from a farther place.

[0003] Since the size envelope of the quad-rotor Mars aircraft does not meet the launch requirements, the quad-rotor Mars aircraft needs to be folded and unfolded, and the folded and unfolded aircraft needs to be able to withstand the overload caused during the launch process and can be released from the lander on Mars after landing and provide a take-off environment. When the existing Mars aircraft is deployed on the ground, the device needs to be moved from the landing to the surface of Mars as a whole, which causes the mechanical arm to bear a large load and increases the risk of mechanical arm failure. In the extremely harsh maintenance conditions on Mars, the influence and loss caused by the deployment of the aircraft are difficult to estimate. The deployment method is affected by the surrounding terrain, has low adaptability, and affects the deployment efficiency and quality of the aircraft.

[0004] Therefore, it is urgent to provide a ground deployment device and method of a Mars aircraft to solve the above technical problems. SUMMARY

[0005] The application provides a ground deployment device and method of a Mars aircraft to solve the above technical problems.

[0006] The technical scheme of the application is as follows:

[0007] A ground deployment device of a Mars aircraft comprises a top cover, a Mars aircraft, a pushing device and a lower envelope body, the top cover is connected with the lower envelope body, the top cover and the lower envelope body form an envelope body in which the Mars aircraft and the pushing device are arranged, and the Mars aircraft is arranged on the upper part of the pushing device.

[0008] Preferably: the top cover includes an upper cover plate, a side cover plate, an end cover hook, a fixed lock frame, a steel rubber, a rotating lock frame, a torsion spring and a top cover positioning ball head. The upper part of the side cover plate is connected to the upper cover plate through a torsion spring. The upper part of the side cover plate is provided with a rotating lock frame, the upper cover plate is provided with a fixed lock frame, the fixed lock frame is connected to the rotating lock frame, the vertical surface of the fixed lock frame is provided with steel rubber, the lower part of the side cover plate is provided with an end cover hook, and the upper cover plate is provided with a top cover positioning ball head.

[0009] Preferably, the upper cover plate is square, and four sides of the square upper cover plate are respectively provided with side cover plates.

[0010] Preferably: the lower envelope body includes an outer shell, a first locking plate, a second locking plate, a lower envelope body expander, a wire rope, a tensioning member, a wire rope positioning column, a smooth sleeve, a locking pin, a square sleeve and a spring, the first locking plate and the second locking plate clamp one end of the wire rope, a spring is provided between the first locking plate and the second locking plate, the second locking plate is connected to the lower envelope body expander, the lower envelope body expander is provided on the upper part of the first locking plate, a tensioning member is provided on the wire rope, the second locking plate is provided at the bottom of the outer shell, the side of the outer shell is provided with a square sleeve, a smooth sleeve and a wire rope positioning column, the locking pin is slidably connected to the smooth sleeve, the locking pin is connected to the square sleeve, the other end of the wire rope passes through the wire rope positioning column and is connected to the locking pin, the spring is between the smooth sleeve and the locking pin, and the end cover hook cooperates with the locking pin.

[0011] Preferably: the pushing device includes an aircraft expander, an aircraft positioning ball head, a pusher outer shell, a pusher inner shell, a screw, a slider, a pushing bracket, a fixed bracket and a motor. The pusher inner shell is slidingly connected to the pusher outer shell, the pusher inner shell is connected to the lower envelope, the output end of the motor is connected to the screw through a reducer, the screw is connected to the lower envelope through a fixed bracket, the screw is threadedly connected to the slider, the slider is connected to the pushing bracket, the pushing bracket is connected to the pusher outer shell, the upper end of the pusher outer shell is provided with an aircraft positioning ball head, the middle part of the upper end of the pusher outer shell is provided with an aircraft expander, the aircraft expander is connected to the Mars aircraft, the lower part of the Mars aircraft is cooperated with the aircraft positioning ball head, and the lower part of the Mars aircraft is cooperated with the top cover positioning ball head.

[0012] A ground deployment method for a Martian spacecraft, using a ground deployment device for the Martian spacecraft, comprises the following steps:

[0013] S1: Storage;

[0014] S2: Deployment.

[0015] Preferably: in S1, the Mars spacecraft is connected to the pushing device through an expander, the top cover positioning ball head of the top cover and the spacecraft positioning ball head of the pushing device continue to fix the spacecraft in the horizontal plane, adjust the tensioning piece, and lock the sliding pin to tighten the end cover hook.

[0016] Preferably: S2 comprises the following steps:

[0017] S2.1: separation of the top cover and the lower envelope;

[0018] S2.2: The Martian spacecraft moves out of the lower envelope by ascending.

[0019] Preferred: In S2.1, when the Mars spacecraft is deployed, the lower envelope expander breaks, causing the first locking plate and the second locking plate to separate, the wire rope loses tension, and under the action of the spring, the lock slide pin moves upward and separates from the end cover hook. Under the action of the torsion spring, the side cover plate folds upward and unfolds. After the top cover is fully unfolded, the top cover is moved away using a robotic arm.

[0020] Preferred: In S2.2, the motor is started, and the motor drives the lead screw to rotate through the first-stage reducer and the second-stage reducer, and the slider drives the pusher housing to move upward through the lifting bracket. The aircraft moves upward with the pusher housing, and the aircraft moves out of the lower envelope. The rotor arms and landing legs on the Mars aircraft are unfolded, and the aircraft expander is energized and ruptured. After unfolding, the aircraft rotor begins to rotate, and finally the aircraft flies away from the lander.

[0021] The present invention has the following beneficial effects:

[0022] 1. The aircraft of the present invention is deployed and takes off from a landing platform, which is not highly dependent on the terrain around the lander, and has greater deployment applicability and is not restricted by the terrain.

[0023] 2. The present invention has a pushing device that can push the Mars spacecraft upward to deploy the spacecraft. The lower envelope of the deployment device does not need to be deployed. The required deployment area is smaller than that of the ground deployment solution, and the compactness is high.

[0024] 3. During the deployment process of the present invention, it is only necessary to remove the top cover of the deployment device with a robotic arm. The load on the robotic arm is small, which greatly avoids the risk of mechanical arm failure and provides a guarantee for the smooth deployment of the Mars spacecraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Figure 1 is a perspective view of a ground deployment apparatus and method for a Mars spacecraft;

[0026] Figure 2 is a cross-sectional view of a ground deployment apparatus and method for a Mars spacecraft;

[0027] Figure 3 yes Figure 2 Enlarged view of point A in the middle;

[0028] Figure 4 It is a structural diagram of the top cover;

[0029] Figure 5 yes Figure 4 Schematic diagram of the structure at B in the middle;

[0030] Figure 6 yes Figure 4 Schematic diagram of the structure at C in the middle;

[0031] Figure 7 It is a structural diagram of the pushing device;

[0032] Figure 8 It is a schematic diagram of the structure of the lower envelope;

[0033] Figure 9 yes Figure 8 Enlarged view of point D in the middle;

[0034] Figure 10 This is a schematic diagram of the Mars spacecraft deployment process.

[0035] In the figure: 1-top cover, 2-Mars spacecraft, 3-pushing device, 4-lower envelope, 1-1-upper cover, 1-2-side cover, 1-3-end cover hook, 1-4-fixed lock frame, 1-5-steel rubber, 1-6-rotating lock frame, 1-7-torsion spring, 1-8-top cover positioning ball head, 3-1-spacecraft expansion device, 3-2-spacecraft positioning ball head, 3-3-pushing device shell, 3-4-pushing device Inner shell, 3-5-screw, 3-6-slider, 3-7-push-up bracket, 3-8-fixed bracket, 3-9-motor, 4-1-outer shell, 4-2-first locking plate, 4-3-second locking plate, 4-4-lower envelope expander, 4-5-wire rope, 4-6-tensioning piece, 4-7-wire rope positioning column, 4-8-sliding sleeve, 4-9-locking pin, 4-10-square sliding sleeve, 4-11-spring. DETAILED DESCRIPTION

[0036] 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.

[0037] Specific implementation method 1: Combination Figure 1-10This embodiment describes a ground deployment device for a Mars aircraft, comprising a top cover 1, a Mars aircraft 2, a pushing device 3 and a lower envelope 4. The top cover 1 and the lower envelope 4 are detachably connected. The Mars aircraft 2 and the pushing device 3 are arranged in the envelope formed by the top cover 1 and the lower envelope 4. The Mars aircraft 2 is arranged on the upper part of the pushing device 3. The lander 5 is provided with the lower envelope 4 and a robotic arm 6, and the robotic arm 6 cooperates with the top cover 1. The aircraft of the present invention is deployed and taken off on a landing platform, and is not highly dependent on the terrain around the lander. The deployment is more adaptable and is not restricted by the terrain.

[0038] Specific implementation method 2: Combination Figure 1-10 This embodiment describes a ground deployment device for a Mars aircraft. The top cover 1 includes an upper cover plate 1-1, a side cover plate 1-2, an end cover hook 1-3, a fixed lock frame 1-4, a steel rubber 1-5, a rotating lock frame 1-6, a torsion spring 1-7, and a top cover positioning ball head 1-8. The upper part of the side cover plate 1-2 is connected to the upper cover plate 1-1 through the torsion spring 1-7, and the upper part of the side cover plate 1-2 is connected to the upper cover plate 1-1 through the first rotating shaft. A torsion spring 1-7 is mounted on the rotating shaft. The two ends of the torsion spring 1-7 are respectively pressed against the side cover 1-2 and the upper cover 1-1. A rotating lock frame 1-6 is fixedly arranged on the upper part of the side cover 1-2. A fixed lock frame 1-4 is fixedly arranged on the edge of the upper cover 1-1. The fixed lock frame 1-4 is connected to the rotating lock frame 1-6 through the second rotating shaft. The vertical surface of the fixed lock frame 1-4 is provided with a steel rubber 1-5. The first rotating shaft and the second rotating shaft are coaxially arranged. The end of the rotating lock frame 1-6 A sliding through hole is provided on the top, a spring is provided in the sliding hole, and limit blocks are provided at both ends of the first spring. A limit hole is provided on the side of the fixed lock frame 1-4. When the rotating lock frame 1-6 rotates 90°, the rotating lock frame 1-6 is parallel to the vertical plane of the fixed lock frame 1-4, and the rotating lock frame 1-6 contacts the steel rubber 1-5. The elastic force of the first spring compressed by the side of the fixed lock frame 1-4 is released, pushing the limit block out of the sliding hole and inserting into the limit hole to achieve positioning. A handle is provided on the upper part of the top cover 1, and the robotic arm moves the top cover by grabbing the handle. The lower part of the side cover plate 1-2 is provided with an end cover hook 1-3, and the upper cover plate 1-1 is provided with four top cover positioning ball heads 1-8 arranged equidistantly in the circumference; during the deployment process of the present invention, it is only necessary to use the robotic arm to remove the top cover of the deployment device. The load on the robotic arm is small, which greatly avoids the risk of failure of the robotic arm and provides a guarantee for the smooth deployment of the Mars spacecraft.

[0039] Specific implementation method three: Combination Figure 1-10 The present embodiment is described as a ground deployment device for a Mars aircraft. The upper cover plate 1-1 is a square, and the four sides of the square upper cover plate 1-1 are respectively provided with side cover plates 1-2.

[0040] Specific implementation method four: Combination Figure 1-10 This embodiment describes a ground deployment device for a Mars aircraft. The lower envelope 4 includes a shell 4-1, a first locking piece 4-2, a second locking piece 4-3, a lower envelope expander 4-4, a wire rope 4-5, a tensioner 4-6, a wire rope positioning column 4-7, a circular sleeve 4-8, a lock pin 4-9, a square sleeve 4-10 and a spring 4-11. The first locking piece 4-2 and the second locking piece 4-3 hold one end of the wire rope 4-5. Clamping, a compressed spring 4-11 is provided between the first locking piece 4-2 and the second locking piece 4-3, the second locking piece 4-3 is connected to the lower envelope expander 4-4 by bolts, the lower envelope expander 4-4 is provided on the upper part of the first locking piece 4-2 and presses the first locking piece 4-2, a tensioning member 4-6 is provided on the wire rope 4-5, the second locking piece 4-3 is fixedly provided at the bottom center of the square shell 4-1, and the four sides of the shell 4-1 are each provided with From top to bottom, a square sliding sleeve 4-10, a circular sliding sleeve 4-8 and several wire rope positioning columns 4-7 are arranged in sequence. The upper and lower ends of the lock sliding pin 4-9 are respectively provided with a square sliding rod and a circular sliding rod. The bottom surface of the lock sliding pin 4-9 is processed with an inclined surface corresponding to the end cover hook 1-3. The circular sliding rod of the lock sliding pin 4-9 is slidably connected to the circular sliding sleeve 4-8. The square sliding rod of the lock sliding pin 4-9 is connected to the square sliding sleeve 4-10. The other end of the wire rope 4-5 slides The circular slide rod passing through the wire rope positioning column 4-7 is connected to the lock slide pin 4-9. The circular slide rod of the lock slide pin 4-9 is provided with a spring 4-11. The two ends of the spring 4-11 are pressed tightly between the circular sleeve 4-8 and the lock slide pin 4-9. An opening is provided between the circular sleeve 4-8 and the square sleeve 4-10. The end cover hook 1-3 extends through the opening and cooperates with the lock slide pin 4-9. The middle part of the end cover hook 1-3 is provided with a notch for avoiding the circular slide rod.

[0041] Specific implementation method five: Combination Figure 1-10This embodiment describes a ground deployment device for a Mars aircraft. The pushing device 3 includes an aircraft expansion device 3-1, an aircraft positioning ball head 3-2, a pusher outer shell 3-3, a pusher inner shell 3-4, a screw 3-5, a slider 3-6, a lifting bracket 3-7, a fixed bracket 3-8 and a motor 3-9. The outer side of the pusher inner shell 3-4 is slidably connected to the pusher outer shell 3-3, the pusher inner shell 3-4 is fixedly connected to the lower envelope 4, and the pusher inner shell 3- 4 is fixedly connected to the motor 3-9, the output end of the motor 3-9 is connected to the screw 3-5 through the reducer, the screw 3-5 is fixedly connected to the lower envelope 4 through the fixed bracket 3-8, a bearing seat is provided on the fixed bracket 3-8, the end of the screw 3-5 is connected to the bearing seat, the slider 3-6 is a nut, and the side of the push-up bracket 3-7 is processed with a vertical sliding mouth. The upper end of the fixed bracket 3-8 passes through the sliding mouth and is connected to the screw 3-5 through the bearing seat, which plays a role in limiting the rotation of the push-up bracket 3-7 The lead screw 3-5 is a ball screw, which is threadedly connected to the slider 3-6. The slider 3-6 is fixedly connected to the lower part of the lifting bracket 3-7. The upper part of the lifting bracket 3-7 is fixedly connected to the pusher housing 3-3. The output end of the motor 3-9 is connected to the secondary reducer 3-11 through the primary reducer 3-10. The output end of the secondary reducer 3-11 is connected to the lead screw 3-5. The upper end surface of the pusher housing 3-3 is provided with four aircraft positioning ball heads 3-2 arranged equidistantly in the circumference. An aircraft expander 3-1 is provided in the middle of the upper end of the pusher shell 3-3, the aircraft expander 3-1 is connected to the Mars aircraft 2, the lower part of the Mars aircraft 2 is matched with the aircraft positioning ball head 3-2, and the lower part of the Mars aircraft 2 is matched with the top cover positioning ball head 1-8; the present invention has a pushing device, which can push the Mars aircraft upward to unfold the aircraft, and the lower envelope of the deployment device does not need to be unfolded. The required deployment area is smaller than the ground deployment scheme and is highly compact.

[0042] Specific implementation method six: combination Figure 1-10 This embodiment describes a ground deployment method for a Mars aircraft, which uses the ground deployment device for a Mars aircraft, and includes the following steps:

[0043] S1: Storage;

[0044] S2: Deployment.

[0045] Specific implementation method seven: combination Figure 1-10The present embodiment is described. This embodiment is a method for ground deployment of a Mars spacecraft. In S1, the Mars spacecraft 2 in the folded and unfolded state is fixedly connected to the pushing device 3 by the expander 3-1. The top cover positioning ball head 1-8 of the top cover 1 and the spacecraft positioning ball head of the pushing device 3 continue to fix the spacecraft in the horizontal plane to prevent the Mars spacecraft 2 from shaking left and right. The tensioning member 4-6 is adjusted, and the locking slide pin 4-9 presses the end cover hook 1-3 and fixes the end cover hook 1-3 to each other, so that the Mars spacecraft is further compressed and fixed inside the overall envelope, so that it can withstand the overload and vibration generated during the launch process. The present invention can enable the spacecraft to resist the overload and vibration generated during the launch process in the folded and unfolded state, and safely and reliably release the Mars spacecraft after landing on the ground of Mars, and provide a flight environment for the Mars spacecraft.

[0046] Specific implementation method eight: combination Figure 1-10 This embodiment describes a ground deployment method for a Mars spacecraft. S2 includes the following steps:

[0047] S2.1: The top cover 1 is separated from the lower envelope 4;

[0048] S2.2: The Mars spacecraft 2 moves out of the lower envelope 4 by ascending.

[0049] Specific implementation method nine: combination Figure 1-10 The present embodiment is described. The present embodiment is a ground deployment method for a Mars spacecraft. In S2.1, when the Mars spacecraft 2 is deployed, the lower envelope expander 4-4 starts to be energized, the expander breaks, and the first locking piece 4-2 and the second locking piece 4-3 are separated. The steel wire rope 4-5 loses tension, and under the action of the spring 4-11, the lock slide pin 4-9 moves upward and separates from the end cover hook 1-3. Under the action of the torsion spring 1-7, the side cover plate 1-2 is folded upward and unfolded, and the rotating lock frame 1-6 is connected to the side cover plate 1-2. The fixed lock frame 1-4 controls the folding angle of the rotating lock frame 1-6 (the angle between the upper cover plate and the side cover plate) within 90°-180°, and the fixed lock frame is equipped with a steel rubber 1-5 to reduce the impact caused by the folding process of the side plate. After the top cover 1 is fully unfolded, the robotic arm 6 is used to move the top cover 1 away.

[0050] Specific implementation method ten: Combination Figure 1-10The present embodiment is described. The present embodiment is a ground deployment method for a Mars spacecraft. In S2.2, the motor 3-9 is started. The motor 3-9 drives the screw 3-5 to rotate through the first-stage reducer 3-10 and the second-stage reducer 3-11. Since the ball screw 3-5 is fixed by the fixed bracket 3-8, the slider 3-6 drives the pusher housing 3-3 to move upward through the lifting bracket 3-7. The spacecraft 2 moves upward together with the pusher housing 3-3. The spacecraft 2 moves out from the lower envelope 4. The rotor arms and landing legs on the Mars spacecraft 2 are unfolded by the first torsion spring. The spacecraft expander 3-1 is energized and expanded. After unfolding, the spacecraft rotor begins to rotate, and finally the spacecraft flies away from the lander 5.

[0051] 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.

[0052] 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 ground deployment device for a Mars spacecraft, characterized by: The invention comprises a top cover (1), a Mars spacecraft (2), a pushing device (3) and a lower envelope (4), wherein the top cover (1) is connected to the lower envelope (4), the Mars spacecraft (2) and the pushing device (3) are arranged in the envelope formed by the top cover (1) and the lower envelope (4), and the Mars spacecraft (2) is arranged on the upper part of the pushing device (3); The top cover (1) comprises an upper cover plate (1-1), a side cover plate (1-2), an end cover hook (1-3), a fixed lock frame (1-4), a steel rubber (1-5), a rotating lock frame (1-6), a torsion spring (1-7) and a top cover positioning ball head (1-8); the upper portion of the side cover plate (1-2) is connected to the upper cover plate (1-1) via the torsion spring (1-7); the upper portion of the side cover plate (1-2) is provided with a rotating lock frame (1-6); the upper cover plate (1-1) is provided with a fixed lock frame (1-4); the fixed lock frame (1-4) is connected to the rotating lock frame (1-6); the vertical surface of the fixed lock frame (1-4) is provided with a steel rubber (1-5); the lower portion of the side cover plate (1-2) is provided with an end cover hook (1-3); and the upper cover plate (1-1) is provided with a top cover positioning ball head (1-8); The lower envelope (4) comprises a housing (4-1), a first locking piece (4-2), a second locking piece (4-3), a lower envelope expander (4-4), a steel wire rope (4-5), a tensioning member (4-6), a steel wire rope positioning column (4-7), a circular sliding sleeve (4-8), a locking slide pin (4-9), a square sliding sleeve (4-10) and a spring (4-11). The first locking piece (4-2) and the second locking piece (4-3) clamp one end of the steel wire rope (4-5). A spring (4-11) is provided between the first locking piece (4-2) and the second locking piece (4-3). The second locking piece (4-3) is connected to the lower envelope expander (4-4). The lower envelope expander (4-4) is provided on the first locking piece. A tensioning member (4-6) is provided on the upper part of the plate (4-2) and the steel wire rope (4-5); a second locking plate (4-3) is provided on the bottom of the housing (4-1); a square sliding sleeve (4-10), a circular sliding sleeve (4-8) and a steel wire rope positioning column (4-7) are provided on the side of the housing (4-1); a locking sliding pin (4-9) is slidably connected to the circular sliding sleeve (4-8); the locking sliding pin (4-9) is connected to the square sliding sleeve (4-10); the other end of the steel wire rope (4-5) passes through the steel wire rope positioning column (4-7) and is connected to the locking sliding pin (4-9); a spring (4-11) is between the circular sliding sleeve (4-8) and the locking sliding pin (4-9); and an end cover hook (1-3) is matched with the locking sliding pin (4-9).

2. The ground deployment device for a Martian aircraft according to claim 1, characterized in that: The upper cover plate (1-1) is square, and four sides of the square upper cover plate (1-1) are respectively provided with side cover plates (1-2).

3. The ground deployment device for a Martian aircraft according to claim 2, characterized in that: The pushing device (3) comprises an aircraft expansion breaker (3-1), an aircraft positioning ball head (3-2), a pusher outer shell (3-3), a pusher inner shell (3-4), a lead screw (3-5), a slider (3-6), a lifting bracket (3-7), a fixed bracket (3-8) and a motor (3-9). The pusher inner shell (3-4) is slidably connected to the pusher outer shell (3-3). The pusher inner shell (3-4) is connected to the lower envelope (4). The output end of the motor (3-9) is connected to the lead screw (3-5) through a reducer. The lead screw (3-5) is connected to the lower envelope (4) through the fixed bracket (3-8). The lead screw (3-5) is threadedly connected to the slider (3-6), the slider (3-6) is connected to the lifting bracket (3-7), the lifting bracket (3-7) is connected to the pusher housing (3-3), the upper end of the pusher housing (3-3) is provided with an aircraft positioning ball head (3-2), the middle part of the upper end of the pusher housing (3-3) is provided with an aircraft expansion breaker (3-1), the aircraft expansion breaker (3-1) is connected to the Mars aircraft (2), the lower part of the Mars aircraft (2) is matched with the aircraft positioning ball head (3-2), and the lower part of the Mars aircraft (2) is matched with the top cover positioning ball head (1-8).

4. A method for ground deployment of a Mars spacecraft, characterized by: A ground deployment device for a Martian aircraft according to any one of claims 1 to 3 comprises the following steps: S1: Storage; In S1, the Mars spacecraft (2) and the pushing device (3) are connected via the expansion breaker (3-1), the top cover positioning ball head (1-8) of the top cover (1) and the spacecraft positioning ball head of the pushing device (3) continue to fix the spacecraft in the horizontal plane, the tensioning member (4-6) is adjusted, and the locking slide pin (4-9) presses the end cover hook (1-3); S2: deployment; S2 includes the following steps: S2.1: The top cover (1) separates from the lower envelope (4); S2.2: The Martian spacecraft (2) moves out of the lower envelope (4) by ascending.

5. The ground deployment method of a Mars spacecraft according to claim 4, characterized in that: In S2.1, when the Mars spacecraft (2) is deployed, the lower envelope expander (4-4) expands and breaks, causing the first locking piece (4-2) and the second locking piece (4-3) to separate, and the wire rope (4-5) loses tension. Under the action of the spring (4-11), the lock slide pin (4-9) moves upward and separates from the end cover hook (1-3). Under the action of the torsion spring (1-7), the side cover (1-2) folds upward and unfolds. After the top cover (1) is fully unfolded, the top cover (1) is removed.

6. The ground deployment method of a Mars spacecraft according to claim 4, characterized in that: In S2.2, the motor (3-9) is started, and the motor (3-9) drives the lead screw (3-5) to rotate through the first-stage speed reducer (3-10) and the second-stage speed reducer (3-11), and the slider (3-6) drives the pusher housing (3-3) to move upward through the lifting bracket (3-7). The aircraft (2) moves upward along with the pusher housing (3-3), and the aircraft (2) moves out from the lower envelope (4). The rotor arms and landing legs on the Mars aircraft (2) are unfolded, and the aircraft expander (3-1) is energized and expanded. After unfolding, the aircraft rotor begins to rotate, and finally the aircraft flies away from the lander (5).

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