Coaxial mars helicopter and locking release device

Abstract

The application relates to a coaxial Mars helicopter and locking and releasing device. The application aims to solve the problems of poor stability and reliability in the locking and releasing process between the coaxial Mars helicopter and the lander. The application comprises a coaxial Mars helicopter, a pyrotechnic clamp plate assembly, a column assembly, a horizontal clamping platform and a landing device; the column assembly and the horizontal clamping assembly are fixedly installed on the landing device, the coaxial Mars helicopter is set upside down in the column assembly, the top of the coaxial Mars helicopter is connected with the horizontal clamping platform, and the coaxial Mars helicopter is connected with the column assembly through the pyrotechnic clamp plate assembly. The application belongs to the technical field of aerospace vehicles.

Description

Technical Field

[0001] This invention relates to a Mars helicopter and a locking and releasing device, belonging to the field of spacecraft technology. Background Technology

[0002] Due to the complex and unknown environment of Mars, Mars rovers face many limitations in exploration missions, while Mars helicopters can leverage aerial superiority to gather richer Martian intelligence. Many research institutions have begun studying the integration of Mars helicopters and rovers for exploration. Among various aircraft types, the coaxial Mars helicopter is characterized by its small size, light weight, and portability, making it suitable for Mars exploration missions.

[0003] Storing the helicopter on the lander for launch reduces the rocket's transport volume. Due to the presence of overweight and vibration during rocket launch, restraining the helicopter within the rocket's transport space is crucial. After the probe reaches the Martian surface, the helicopter will be unlocked, released, and deployed. Successfully completing deployment and other preparatory tasks is a key step in the exploration mission, significantly improving its efficiency and accelerating interstellar exploration. Summary of the Invention

[0004] To address the problem of poor stability and reliability during the locking and releasing process between a coaxial Mars helicopter and a lander, this invention proposes a coaxial Mars helicopter and a locking and releasing device.

[0005] The technical solution adopted by the present invention to solve the above problems is as follows: The present invention includes a coaxial Mars helicopter, a pyrotechnic clamping plate assembly, a column assembly, a horizontal clamping platform, and a landing device; the column assembly and the horizontal clamping assembly are fixedly installed on the landing device, the coaxial Mars helicopter is inverted and installed inside the column assembly, the top of the coaxial Mars helicopter is connected to the horizontal clamping platform, and the coaxial Mars helicopter is connected to the column assembly through the pyrotechnic clamping plate assembly.

[0006] Furthermore, the coaxial Mars helicopter includes a solar panel, rotor blades, a central fixed main shaft, a fuselage, and a motor; the motor is fixedly installed inside the fuselage, the lower end of the central fixed main shaft is coaxially fixedly connected to the motor shaft of the motor, the rotor blades are coaxially fixedly mounted on the central fixed main shaft, and the solar panel is installed at the top of the central fixed main shaft.

[0007] Furthermore, the coaxial Mars helicopter also includes four landing leg hinges, four landing legs, four restraint tubes, and four wheel sets; the four landing legs are evenly distributed around the fuselage, the upper end of the landing leg is connected to the fuselage through the landing leg hinge, a wheel set is installed at the lower end of the landing leg, and a restraint tube is installed on the upper part of the landing leg.

[0008] Furthermore, the pyrotechnic clamp assembly includes a pyrotechnic component, a clamp, two first spiral springs, and a rotating shaft; the pyrotechnic component is fixed to one end of the clamp, the rotating shaft is fixed to the other end of the clamp, and the axis of the rotating shaft is perpendicular to the center line of the clamp along its length direction; the two first spiral springs are respectively fitted onto both ends of the rotating shaft.

[0009] Furthermore, the column assembly includes four track columns and two column beams; the four track columns are arranged vertically in a rectangular shape, and the two column beams are arranged side by side in parallel. The two ends of the column beams are fixedly connected to the two adjacent track columns. The center line of the column beams along the length direction is perpendicular to the center line of the track columns along the length direction. The coaxial Mars helicopter is inverted and arranged between the four track columns.

[0010] Furthermore, the horizontal clamping assembly includes two clamping constraint blocks, two connecting rods, a rotating disk, a second spiral spring, and a pyrotechnic assembly; the two connecting rods are symmetrically arranged in a straight line on both sides of the rotating disk, with the end of the connecting rod closer to the rotating disk connected to the rotating disk via the second spiral spring, and the end of the connecting rod further away from the rotating disk fixedly connected to the lower end of the clamping constraint block; the rotating disk is connected to the top of the coaxial Mars helicopter via the pyrotechnic assembly.

[0011] Furthermore, the landing equipment includes a lander and a robotic arm; the robotic arm is mounted on the upper surface of the lander.

[0012] The beneficial effects of this invention are: the locking and releasing mechanism of the coaxial Mars helicopter proposed in this invention can be applied to the deployment in the combined exploration mission of lander and spacecraft, which can effectively ensure the reliability of locking and the stability of releasing, improve the reliability and stability of locking and releasing of rotor Mars helicopter and lander, and is of great significance for improving the efficiency of Mars exploration mission and accelerating galactic exploration. Attached Figure Description

[0013] Figure 1 This is a schematic diagram of the overall structure of the present invention;

[0014] Figure 2 This is a schematic diagram of a coaxial Mars helicopter structure;

[0015] Figure 3 This is a three-dimensional schematic diagram of the fire-resistant clamp assembly structure;

[0016] Figure 4 This is a three-dimensional schematic diagram of the column structure;

[0017] Figure 5 This is a three-dimensional schematic diagram of the horizontal clamping platform structure;

[0018] Figure 6 This is a three-dimensional schematic diagram of the landing equipment structure. Detailed Implementation

[0019] Specific implementation method one: Combining Figure 1 This embodiment describes a coaxial Mars helicopter and locking / releasing device, comprising a coaxial Mars helicopter 1, a pyrotechnic clamping plate assembly 2, a column assembly 3, a horizontal clamping platform 4, and a landing device 5. The column assembly 3 and the horizontal clamping assembly 4 are fixedly installed on the landing device 5. The coaxial Mars helicopter 1 is inverted and installed inside the column assembly 3. The top of the coaxial Mars helicopter 1 is connected to the horizontal clamping platform 4. The coaxial Mars helicopter 1 is connected to the column assembly 3 through the pyrotechnic clamping plate assembly 2.

[0020] Specific Implementation Method Two: Combining Figure 2 This embodiment describes a coaxial Mars helicopter 1 with a locking and releasing device. The coaxial Mars helicopter 1 includes a solar panel 1-1, rotor blades 1-2, a central fixed main shaft 1-3, a fuselage, and a motor. The motor is fixedly installed inside the fuselage. The lower end of the central fixed main shaft 1-3 is coaxially and fixedly connected to the motor shaft of the motor. The rotor blades 1-2 are coaxially and fixedly mounted on the central fixed main shaft 1-3. The solar panel 1-1 is installed at the top of the central fixed main shaft 1-3.

[0021] The geometric center of the solar panel 1-1 is provided with a connection position for the pyrotechnic component 4-5, and the solar panel 1-1 is connected to the movable component 4-5. The rotor blade 1-2 consists of an upper rotor system and a lower rotor system. The upper rotor system consists of two rotor blades, and the lower rotor system consists of two rotor blades. The rotor blade 1-2 is a non-swaying hinge.

[0022] The other components and connections are the same as in Specific Implementation Method 1.

[0023] Specific implementation method three: Combining Figure 2 This embodiment describes a coaxial Mars helicopter 1 with a locking and releasing device, which further includes four landing leg hinges 1-4, four landing legs 1-5, four restraint tubes 1-6, and four wheel sets 1-7. The four landing legs 1-5 are evenly distributed around the fuselage. The upper end of the landing leg 1-5 is connected to the fuselage through the landing leg hinges 1-4, a wheel set 1-7 is installed at the lower end of the landing leg 1-5, and a restraint tube 1-6 is installed on the upper part of the landing leg 1-5.

[0024] Initially positioned upwards, landing legs 1-5 are rotated downwards via landing leg hinges 1-4 under the action of a spiral spring. When rotated to the target angle, the ratchet mechanism inside the hinge locks the angle. The restraint tube 1-6 is located in the upper middle section of landing legs 1-5 facing the fuselage, and the wheel assembly 1-7 is located at the end of landing legs 1-5.

[0025] The other components and connections are the same as in Specific Implementation Method 2.

[0026] Specific implementation method four: Combination Figure 3 This embodiment describes a coaxial Mars helicopter and a locking and releasing device pyrotechnic clamp assembly 2, which includes a pyrotechnic component 2-1, a clamp 2-2, two first spiral springs 2-3, and a rotating shaft 2-4. The pyrotechnic component 2-1 is fixed to one end of the clamp 2-2, and the rotating shaft 2-4 is fixed to the other end of the clamp 2-2. The axis of the rotating shaft 2-4 is perpendicular to the center line of the clamp 2-2 along its length. The two first spiral springs 2-3 are respectively fitted onto both ends of the rotating shaft 2-4.

[0027] In the pyrotechnic clamp assembly 2, the pyrotechnic assembly 2-1 is connected to the central area of ​​the solar panel 1-1 and can be disconnected by pyrotechnic action; the rotating shaft 2-4 is installed on the wall of the lander 4-1, and there are spiral springs 2-3 on both sides of the root of the clamp 2-2 to provide the clamp with the power to rotate around the rotating shaft 2-4.

[0028] The other components and connections are the same as in Specific Implementation Method 1.

[0029] Specific Implementation Method Five: Combining Figure 4 This embodiment describes a coaxial Mars helicopter and locking release device. The column assembly 3 includes four track columns 3-1 and two column beams 3-2. The four track columns 3-1 are arranged vertically in a rectangular shape, and the two column beams 3-2 are arranged side by side in parallel. The two ends of the column beams 3-2 are fixedly connected to the two adjacent track columns 3-1. The center line of the column beams 3-2 along the length direction is perpendicular to the center line of the track columns 3-1 along the length direction. The coaxial Mars helicopter 1 is arranged upside down between the four track columns 3-1.

[0030] In the column assembly 3, there is a vertical slide that is adapted to the restraint tube 1-6; when the helicopter ascends, the restraint tube 1-6 moves along the geometric path of the slide, and the landing leg 1-5 flips downward along the landing leg hinge 1-4.

[0031] The other components and connections are the same as in Specific Implementation Method 1.

[0032] Specific Implementation Method Six: Combination Figure 5This embodiment describes a horizontal clamping assembly 4 for a coaxial Mars helicopter and locking release device, comprising two clamping constraint blocks 4-1, two connecting rods 4-2, a rotating disk 4-3, a second spiral spring 4-4, and a pyrotechnic assembly 4-5. The two connecting rods 4-2 are symmetrically arranged in a straight line on both sides of the rotating disk 4-3. The end of the connecting rod 4-2 near the rotating disk 4-3 is connected to the rotating disk 4-3 via the second spiral spring 4-4, and the end of the connecting rod 4-2 away from the rotating disk 4-3 is fixedly connected to the lower end of the clamping constraint block 4-1. The rotating disk 4-3 is connected to the top of the coaxial Mars helicopter 1 via the pyrotechnic assembly 4-5.

[0033] The second spiral spring 4-4 ​​is in a compressed state in the rotating disk 4-3. The pyrotechnic assembly 4-5 locks the rotating disk 4-3. The connecting rod 4-2 is connected to the bottom end of the clamping constraint block 4-1 via a rotating pin. The upper end of the clamping constraint block 4-1 has a groove adapted to the shape of the blade end to constrain the blade. After receiving the working signal, the pyrotechnic assembly 4-5 unlocks the rotating disk 4-3. Under the natural recovery of power of the second spiral spring 4-4, the rotating disk 4-3 rotates and, through the connecting rod 4-2, disengages the clamping constraint block 4-1 from the rotor blade 1-2.

[0034] The other components and connections are the same as in Specific Implementation Method 1.

[0035] Specific implementation method seven: Combination Figure 6 This embodiment describes a coaxial Mars helicopter and locking release device landing device 5, which includes a lander 5-1 and a robotic arm 5-2; the robotic arm 5-2 is mounted on the upper surface of the lander 5-1.

[0036] The lander 5-1 has vertical walls for mounting the pyrotechnic components 2-1. The robotic arm 5-2 is located outside the horizontal clamping platform 4 and has 5 segments and 6 degrees of freedom. It is used to lift the helicopter out of the column 3 when the helicopter is deployed.

[0037] The other components and connections are the same as in Specific Implementation Method 1.

[0038] The above description is merely a preferred embodiment of the present invention and is not intended to limit the present invention in any way. Although the present invention has been disclosed above with reference to preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art can make some modifications or alterations to the above-disclosed technical content to create equivalent embodiments without departing from the scope of the present invention. Any simple modifications, equivalent substitutions, and improvements made to the above embodiments without departing from the scope of the present invention, based on the technical essence of the present invention and within the spirit and principles of the present invention, shall still fall within the protection scope of the present invention.

Claims

1. A coaxial Mars helicopter and a locking and releasing device, characterized in that: The coaxial Mars helicopter and locking release device include a coaxial Mars helicopter (1), a pyrotechnic clamp assembly (2), a column assembly (3), a horizontal clamping assembly (4), and a landing device (5); the column assembly (3) and the horizontal clamping assembly (4) are fixedly installed on the landing device (5), the coaxial Mars helicopter (1) is inverted and installed inside the column assembly (3), the top of the coaxial Mars helicopter (1) is connected to the horizontal clamping assembly (4), and the coaxial Mars helicopter (1) is connected to the column assembly (3) through the pyrotechnic clamp assembly (2); The column assembly (3) includes four track columns (3-1) and two column beams (3-2); the four track columns (3-1) are arranged vertically in a rectangular shape, and the two column beams (3-2) are arranged side by side in parallel. The two ends of the column beams (3-2) are fixedly connected to the two adjacent track columns (3-1). The center line of the column beams (3-2) along the length direction is perpendicular to the center line of the track columns (3-1) along the length direction. The coaxial Mars helicopter (1) is arranged upside down between the four track columns (3-1). The horizontal clamping assembly (4) includes two clamping constraint blocks (4-1), two connecting rods (4-2), a rotating disk (4-3), a second spiral spring (4-4), and a pyrotechnic assembly (4-5). The two connecting rods (4-2) are symmetrically arranged in a straight line on both sides of the rotating disk (4-3). The end of the connecting rod (4-2) near the rotating disk (4-3) is connected to the rotating disk (4-3) through the second spiral spring (4-4), and the end of the connecting rod (4-2) away from the rotating disk (4-3) is fixedly connected to the lower end of the clamping constraint block (4-1). The rotating disk (4-3) is connected to the top of the coaxial Mars helicopter (1) through the pyrotechnic assembly (4-5).

2. The coaxial Mars helicopter and locking / releasing device according to claim 1, characterized in that: The coaxial Mars helicopter (1) includes a solar panel (1-1), rotor blades (1-2), a central fixed main shaft (1-3), a fuselage, and a motor; the motor is fixedly installed inside the fuselage, the lower end of the central fixed main shaft (1-3) is coaxially fixedly connected to the motor shaft of the motor, the rotor blades (1-2) are coaxially fixedly mounted on the central fixed main shaft (1-3), and the solar panel (1-1) is installed at the top of the central fixed main shaft (1-3).

3. The coaxial Mars helicopter and locking / releasing device according to claim 2, characterized in that: The coaxial Mars helicopter (1) also includes four landing leg hinges (1-4), four landing legs (1-5), four restraint tubes (1-6), and four wheel sets (1-7); the four landing legs (1-5) are evenly distributed around the fuselage, the upper end of the landing leg (1-5) is connected to the fuselage through the landing leg hinge (1-4), a wheel set (1-7) is installed at the lower end of the landing leg (1-5), and a restraint tube (1-6) is installed on the upper part of the landing leg (1-5).

4. The coaxial Mars helicopter and locking / releasing device according to claim 1, characterized in that: The pyrotechnic clamp assembly (2) includes a pyrotechnic component (2-1), a clamp (2-2), two first spiral springs (2-3), and a rotating shaft (2-4). The pyrotechnic component (2-1) is fixed at one end of the clamp (2-2), and the rotating shaft (2-4) is fixed at the other end of the clamp (2-2). The axis of the rotating shaft (2-4) is perpendicular to the center line of the clamp (2-2) along its length. The two first spiral springs (2-3) are respectively fitted on both ends of the rotating shaft (2-4).

5. The coaxial Mars helicopter and locking / releasing device according to claim 1, characterized in that: The landing equipment (5) includes a lander (5-1) and a robotic arm (5-2); the robotic arm (5-2) is mounted on the upper surface of the lander (5-1).

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