A locking and releasing device for a rotor-type Mars aircraft on a Mars rover

Abstract

The present invention discloses a locking and releasing device for a rotor-type Mars aircraft on a Mars rover, which includes a Mars rover, a debris shield assembly, a tail locking assembly, a rotor-type Mars aircraft, a middle locking member, and a head locking assembly. The debris shield assembly includes a debris shield, a cylindrical compression spring, an electric push rod I, a debris shield locking member, and a fixed pin I. The present invention belongs to the field of aerospace rotor-type Mars aircraft, and specifically refers to a locking and releasing device for a rotor-type Mars aircraft on a Mars rover, aiming to solve the problems of stability and reliability during the locking and releasing process between the rotor-type Mars aircraft and the Mars rover.

Description

Technical Field

[0001] The present invention belongs to the field of aerospace rotor-type Mars aircraft, and specifically refers to a locking and releasing device for a rotor-type Mars aircraft on a Mars rover. Background Art

[0002] Affected by the complex terrain of Mars, the field of vision of Mars rovers is limited in short-distance exploration work. Mars aircraft can use their aerial advantages to obtain richer Mars intelligence. Therefore, many scientists believe that Mars aircraft are important vehicles for Mars exploration missions and can cooperate with Mars rovers to carry out exploration work. At the same time, the thin atmosphere existing on the Mars surface provides great possibilities for rotor flight. Coaxial dual-rotor Mars aircraft have the advantages of a compact structure and high lift-drag efficiency, and have become an ideal configuration for Mars aircraft deployed on Mars rovers.

[0003] Due to the limited internal space of the launch vehicle, the overall structural dimensions of the Mars rover and the rotor-type Mars aircraft it transports cannot be too large. The rotor-type Mars aircraft needs to be simply folded and then locked and fixed at an appropriate position on the Mars rover. The locking and releasing device for the rotor-type Mars aircraft on the Mars rover is of great significance for reducing the rocket transportation cost, improving the locking and releasing stability and accuracy, etc. Summary of the Invention

[0004] In order to solve the above problems, the present invention provides a locking and releasing device for a rotor-type Mars aircraft on a Mars rover to solve the problems of stability and reliability in the locking and releasing process between the rotor-type Mars aircraft and the Mars rover.

[0005] In order to achieve the above functions, the technical solution adopted by the present invention is as follows: A locking and releasing device for a rotor-type Mars aircraft on a Mars rover, including a Mars rover, a debris shield assembly, a tail locking assembly, a rotor-type Mars aircraft, a middle locking member, and a head locking assembly. The debris shield assembly includes a debris shield, a cylindrical compression spring, an electric push rod I, a debris shield locking member, and a fixed pin I.

[0006] Further, the tail locking assembly includes a tail fixing member, a tail electromagnetic locking member, a cylindrical torsion spring I, and a fixed pin II.

[0007] Further, the rotor-type Mars aircraft includes a bottom module, a lower rotor module, and an upper rotor module. The bottom module of the rotor-type Mars aircraft includes an electric control box fixing member, a support leg locking member, a cylindrical torsion spring II, a fixed pin III, a fixed pin IV, a micro leaf spring, a support leg, and an electric control box.

[0008] Furthermore, the head locking assembly includes a head fixing member, a fixing pin five, a cylindrical torsion spring three, a motor, a motor support base, a head electromagnetic locking member, a cylindrical torsion spring four, a fixing pin six, a fixing pin seven, an electric push rod two, a fixing pin eight, a support leg restraint one, a fixing pin nine, and a support leg restraint two.

[0009] Furthermore, the bottom surface of the Mars rover is provided with fixing holes, a debris shield assembly, a tail locking assembly, and a middle locking member. The head fixing member is connected to the bottom fixing holes on the bottom surface by bolts.

[0010] Furthermore, the debris shield in the debris shield assembly is connected to the debris shield locking member by three fixing pins one. The top of the debris shield locking member is evenly distributed with three spherical protrusions, which are connected to the groove on the bottom surface of the Mars rover. The middle part of the debris shield locking member is hollow, and an electric push rod one and a cylindrical compression spring are locked inside. The electric push rod one is used to disengage the lock with the bottom surface of the Mars rover, and the cylindrical compression spring is used to provide elastic force for release.

[0011] Furthermore, in the tail locking assembly, the tail fixing member is connected to the tail electromagnetic locking member by two fixing pins two. The hollow structure of the tail fixing member's ring contacts the circular protrusion structure at the bottom of the bottom module of the rotor-type Mars aircraft. The tail electromagnetic locking member is provided with a cylindrical torsion spring one to provide elastic force for lifting and releasing.

[0012] Furthermore, the rotor-type Mars aircraft includes a bottom module, a lower rotor module, and an upper rotor module. The electronic control box fixing member is connected to the bottom module by bolts. The support leg locking member is connected to the left support leg and the right support leg through cooperation, and is connected to the electronic control box fixing member by a fixing pin three. The micro leaf spring is always in a compressed state, providing pressure for the fixing pin four, providing power for the movement of the fixing pin four in the groove, and making the fixing pin four always contact the outer contour of the electronic control box fixing member. The cylindrical torsion spring two is used to provide power for the support leg locking member to rotate around the fixing pin three.

[0013] Furthermore, the middle locking member is in surface contact with the surface of the parts inside the lower rotor module of the rotor-type Mars aircraft.

[0014] Furthermore, in the head locking assembly, the head fixing member is connected to the head electromagnetic locking member through the fixing pin five. The cylindrical torsion spring three and the motor are used to provide power for the overall rotation of the rotor-type Mars aircraft. The motor support is connected to the bottom surface of the Mars rover. The circular hollow structure of the head electromagnetic locking member contacts the circular ring-shaped convex structure at the head of the rotor module on the rotor-type Mars aircraft. The head electromagnetic locking member is connected to the support leg restraint member two through the fixing pin six. The cylindrical torsion spring four is used to provide power for the upward lifting of the support leg restraint member two. The locking end of the electric push rod two is connected to the support leg restraint member two through the fixing pin seven. The movable end of the electric push rod two is connected to the leg restraint member one through the fixing pin eight to provide power for the link mechanism. The leg restraint member one is connected to the support leg restraint member two through the fixing pin nine.

[0015] The beneficial effects achieved by the present invention with the above structure are as follows: A locking and releasing device for a rotor-type Mars aircraft on a Mars rover proposed by the present invention can effectively ensure the reliability of locking and the stability of releasing, and improve the reliability and stability of locking and releasing between the rotor-type Mars aircraft and the Mars rover. Brief Description of the Drawings

[0016] Figure 1 Schematic diagram of the relative position relationship between the whole of the present invention and the Mars rover;

[0017] Figure 2 Schematic diagram of the overall three-dimensional structure;

[0018] Figure 3 Schematic diagram of the three-dimensional structure of the debris cover assembly;

[0019] Figure 4 Schematic diagram of the three-dimensional structure of the debris cover locking assembly;

[0020] Figure 5 Cross-sectional view of the structure of the debris cover locking assembly;

[0021] Figure 6 Schematic diagram of the three-dimensional structure of the tail locking assembly;

[0022] Figure 7 Schematic diagram of the three-dimensional structure of the support leg locking structure;

[0023] Figure 8 Schematic diagram of the three-dimensional structure of the head locking assembly;

[0024] Figure 9 Schematic diagram of the three-dimensional state of the relative position of the support legs and the initial position of the device;

[0025] Figure 10 Schematic diagram of the released state of the tail locking assembly;

[0026] Figure 11Three-dimensional schematic diagram of the release state of the intermediate locking part;

[0027] Figure 12 Three-dimensional schematic diagram of the state where the rotary-wing Mars aircraft rotates to the final release position;

[0028] Figure 13 Three-dimensional schematic diagram of the release state of the support leg;

[0029] Figure 14 Three-dimensional schematic diagram of the final release state.

[0030] Among them, 1. Mars rover, 2. Debris cover assembly, 3. Tail locking assembly, 4. Rotary-wing Mars aircraft, 5. Intermediate locking part, 6. Head locking assembly, 2-1. Debris cover, 2-2. Cylindrical compression spring, 2-3. Electric push rod 1, 2-4. Debris cover locking part, 2-5. Fixed pin shaft 1, 3-1. Tail fixing part, 3-2. Tail electromagnetic locking part, 3-3. Cylindrical torsion spring 1, 3-4. Fixed pin shaft 2, 4-1. Electric control box fixing part, 4-2. Support leg locking part, 4-3. Cylindrical torsion spring 2, 4-4. Fixed pin shaft 3, 4-5. Fixed pin shaft 4, 4-6. Micro leaf spring, 4-7. Support leg, 6-1. Head fixing part, 6-2. Fixed pin shaft 5, 6-3. Cylindrical torsion spring 3, 6-4. Motor, 6-5. Motor support seat, 6-6. Head electromagnetic locking part, 6-7. Cylindrical torsion spring 4, 6-8. Fixed pin shaft 6, 6-9. Fixed pin shaft 7, 6-10. Electric push rod 2, 6-11. Fixed pin shaft 8, 6-12. Support leg restraint 1, 6-13. Fixed pin shaft 9, 6-14. Support leg restraint 2. Detailed implementation manners

[0031] The technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are part of the embodiments of the present invention, rather than all of them. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts shall fall within the protection scope of the present invention.

[0032] In the description of the present invention, it should be noted that the orientation or positional relationship indicated by the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. is based on the orientation or positional relationship shown in the accompanying drawings. It is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation of the present invention. In addition, the terms "first", "second", and "third" are only used for descriptive purposes and cannot be understood as indicating or implying relative importance. The present invention will be further described in detail below with reference to the accompanying drawings.

[0033] Please refer to Figures 1 - 9. A locking and releasing device for a rotor - type Mars aircraft on a Mars rover according to the present invention includes a Mars rover 1, a debris shield assembly 2, a tail locking assembly 3, a rotor - type Mars aircraft 4, a middle locking member 5, and a head locking assembly 6. The bottom surface of the Mars rover 1 is provided with fixing holes, and the debris shield assembly 2, the tail locking assembly 3, the middle locking member 5, and the head fixing member 6 are connected to the bottom fixing holes to complete the locking.

[0034] The debris shield assembly 2 includes a debris shield 2 - 1. The debris shield 2 - 1 is connected to a debris shield locking member 2 - 4 through three fixing pin shafts 2 - 5. The top of the debris shield locking member 2 - 4 is evenly distributed with three spherical protrusions, which are connected to the groove on the bottom surface of the Mars rover 1. Two identical assemblies are used to lock the debris shield assembly 2 and the Mars rover 1. The middle part of the debris shield locking member 2 - 4 is hollow, and an electric push rod 2 - 3 is locked inside. When the inner rod of the electric push rod 2 - 3 extends, the debris shield locking member 2 - 4 is disengaged from the Mars rover 1. At the same time, a cylindrical compression spring 2 - 2 provides elastic force to achieve release. The Mars rover 1 moves to ensure that there are no sundries in the space below.

[0035] The tail locking assembly 3 includes a tail fixing member 3 - 1 connected to the ground of the Mars rover 1. The tail fixing member 3 - 1 is connected to a tail electromagnetic locking member 3 - 2 through two fixing pin shafts 3 - 4. The hollow structure of the ring of the tail fixing member 3 - 2 contacts the circular - ring - shaped protrusion structure at the bottom of the bottom module of the rotor - type Mars aircraft 4, and locking is achieved through electromagnetic force. After power - off, the electromagnetic force disappears, and the tail electromagnetic locking member 3 - 2 is lifted to the left by the elastic force of a cylindrical torsion spring 3 - 3 to achieve release.

[0036] The rotor - type Mars aircraft 4 includes a bottom module, a lower rotor module, and an upper rotor module. An electric control box fixing member 4 - 1 is connected to the bottom module through bolts. A support leg locking member 4 - 2 is connected to the left support leg 4 - 7 and the right support leg 4 - 8 through cooperation, and is connected to the electric control box fixing member 4 - 1 through a fixing pin shaft 4 - 4. The left support leg 4 - 7 is restricted by the bottom surface of the Mars rover 1, and the right support leg 4 - 8 is restricted by a support leg restraint member 6 - 12 and a support leg restraint member 6 - 14 to achieve a folded and locked state.

[0037] The middle locking member 5 is in surface contact with the surface of the parts inside the lower rotor module of the rotor - type Mars aircraft 4, and locking of the rotor - type Mars aircraft 4 is achieved through electromagnetic force. After power - off, the electromagnetic force disappears to achieve release. The hollow structure of the ring of the head electromagnetic locking member 6 - 6 contacts the circular - ring - shaped protrusion structure at the head of the upper rotor module of the rotor - type Mars aircraft 4, and locking is achieved through electromagnetic force. The rotor - type Mars aircraft 4 and the head locking assembly 6 temporarily become an integral body, and the integral body rotates a certain angle around a fixing pin shaft 5 - 2 under the action of gravity and the elastic force of a cylindrical torsion spring 6 - 3.

[0038] After the middle locking member 5 is released, the left support leg 4-7 is no longer restricted. Under the elastic force of the cylindrical torsion spring two 4-3, the support leg locking member 4-2 rotates around the fixed pin three 4-4. During the rotation, the micro leaf spring 4-6 is in a compressed state and is mechanically restricted by the groove of the support leg locking member 4-2. The fixed pin four 4-5 can only move within the groove and always contacts the outer contour of the electronic control box fixing member 4-1. When it rotates to the groove position of the electronic control box fixing member 4-1, the micro leaf spring 4-6 pushes the fixed pin four 4-5 into the groove and, under the elastic force, realizes locking to complete the positioning of the support leg 4-7.

[0039] During specific use, the hollow circular structure of the head electromagnetic locking member 6-6 in the head locking assembly 6 contacts the circular convex structure at the head of the rotor module on the rotor-type Mars aircraft 4, and locking is achieved through electromagnetic force. The rotor-type Mars aircraft 4 and the head locking assembly 6 temporarily become an integral body. Under the action of gravity and the elastic force of the cylindrical torsion spring three 6-3, after rotating a certain angle around the fixed pin five 6-2, the motor 6-4 needs to provide torque to continue rotating to the specified position. Subsequently, the inner rod of the electric push rod 6-9 extends to drive the support leg restraint member one 6-12 to rotate around the fixed pin nine 6-13, realizing the release of the right support leg 4-8. The positioning principle is the same as that described for the left support leg 4-7. The fixed pin seven 6-9, the electric push rod two 6-10, the fixed pin eight 6-11, the support leg restraint member one 6-12, the fixed pin nine 6-13, the support leg restraint member two 6-14, as a whole, lift upward around the fixed pin six 6-8 under the elastic force of the cylindrical torsion spring four 6-7 to achieve release. Subsequently, the head electromagnetic locking member 6-6 is powered off, the electromagnetic force disappears, and the rotor-type Mars aircraft 4 is released under the action of gravity to complete the locking and release between the rotor-type Mars aircraft and the Mars vehicle.

[0040] Please refer to Figures 9 - 14 , which shows different position states of the locking and releasing device for the rotor-type Mars aircraft on the Mars vehicle during operation.

[0041] Compared with the prior art, the advantage of the present invention is that it can effectively ensure the reliability of locking and the stability of release, and improve the reliable stability of the locking and release between the rotor-type Mars aircraft and the Mars vehicle.

[0042] The above describes the present invention and its implementation manners. This description is not restrictive. What is shown in the drawings is only one of the implementation manners of the present invention, and the actual structure is not limited thereto. Generally speaking, if those of ordinary skill in the art are inspired by it and, without departing from the purpose of the present invention creation, design structurally similar ways and embodiments to this technical solution without creative efforts, they should all fall within the protection scope of the present invention.

Claims

1. A locking and releasing device for a rotor-type Mars aircraft on a Mars rover, characterized in that: It includes a Mars rover (1), a debris cover assembly (2), a tail locking assembly (3), a rotor-type Mars aircraft (4), a middle locking part (5), and a head locking assembly (6); the tail locking assembly (3) includes a tail fixing part (3-1), a tail electromagnetic locking part (3-2), a cylindrical torsion spring one (3-3), and a fixed pin shaft two (3-4). In the tail locking assembly (3), the tail fixing part (3-1) is connected to the tail electromagnetic locking part (3-2) through two fixed pin shafts two (3-4). The hollow circular structure of the tail fixing part (3-1) contacts the circular convex structure at the bottom of the bottom module of the rotor-type Mars aircraft (4). The tail electromagnetic locking part (3-2) is provided with a cylindrical torsion spring one (3-3) to provide the elastic force for lifting and releasing; the rotor-type Mars aircraft (4) includes a bottom module, a lower rotor module, and an upper rotor module; the bottom module of the rotor-type Mars aircraft (4) includes an electric control box fixing part (4-1), a support leg locking part (4-2), a cylindrical torsion spring two (4-3), a fixed pin shaft three (4-4), a fixed pin shaft four (4-5), a micro leaf spring (4-6), a left support leg (4-7), a right support leg (4-8), and an electric control box; the head locking assembly (6) includes a head fixing part (6-1), a fixed pin shaft five (6-2), a cylindrical torsion spring three (6-3), a motor (6-4), a motor support seat (6-5), a head electromagnetic locking part (6-6), a cylindrical torsion spring four (6-7), a fixed pin shaft six (6-8), a fixed pin shaft seven (6-9), an electric push rod two (6-10), a fixed pin shaft eight (6-11), a support leg restraint one (6-12), a fixed pin shaft nine (6-13), and a support leg restraint two (6-14). In the head locking assembly (6), the head fixing part (6-1) is connected to the head electromagnetic locking part (6-6) through the fixed pin shaft five (6-2). The cylindrical torsion spring three (6-3) and the motor (6-4) are used to provide power for the overall rotation of the rotor-type Mars aircraft (4). The motor support seat (6-5) is connected to the bottom surface of the Mars rover (1). The hollow circular structure of the head electromagnetic locking part (6-6) contacts the circular convex structure at the head of the upper rotor module of the rotor-type Mars aircraft (4). The head electromagnetic locking part (6-6) is connected to the support leg restraint two (6-14) through the fixed pin shaft six (6-8). The cylindrical torsion spring four (6-7) is used to provide power for the upward lifting of the support leg restraint two (6-14). The locking end of the electric push rod two (6-10) is connected to the support leg restraint two (6-14) through the fixed pin shaft seven (6-9), and its movable end is connected to the leg restraint one (6-12) through the fixed pin shaft eight (6-11). The leg restraint one (6-12) is connected to the support leg restraint two (6-14) through the fixed pin shaft nine (6-13).

2. The locking and releasing device for a rotor-type Mars aircraft on a Mars rover according to claim 1, characterized in that: The bottom surface of the described rover (1) is provided with fixing holes, a debris shield assembly (2), a tail locking assembly (3), and a middle locking member (5). The head locking assembly (6) is connected to the bottom fixing holes with bolts.

3. A locking and releasing device for a rotary-wing Mars aircraft on a Mars rover according to claim 2, characterized in that: The described debris shield assembly (2) includes a debris shield (2-1), a cylindrical compression spring (2-2), an electric push rod I (2-3), a debris shield locking member (2-4), and a fixing pin I (2-5).

4. A locking and releasing device for a rotor-type Mars aircraft on a Mars rover according to claim 3, characterized in that: The debris shield (2-1) in the described debris shield assembly (2) is connected to the debris shield locking member (2-4) through three fixing pins I (2-5). The top of the debris shield locking member (2-4) is evenly distributed with three spherical protrusions, which are connected to the groove on the bottom surface of the rover (1). The middle part of the debris shield locking member (2-4) is hollow and internally locks an electric push rod I (2-3) and a cylindrical compression spring (2-2).

5. A locking and releasing device for a rotary-wing Mars aircraft on a Mars rover according to claim 4, characterized in that: The described rotary-wing Mars aircraft (4) includes a bottom module, a lower rotary-wing module, and an upper rotary-wing module. The electric control box fixing member (4-1) is connected to the bottom module with bolts. The support leg locking member (4-2) is connected to the left support leg (4-7) and the right support leg (4-8) through cooperation, and is connected to the electric control box fixing member (4-1) through a fixing pin III (4-4). The micro leaf spring (4-6) is always in a compressed state. The cylindrical torsion spring II (4-3) is used to provide power for the support leg locking member (4-2) to rotate around the fixing pin III (4-4).

6. A locking and releasing device for a rotor-type Mars aircraft on a Mars rover according to claim 5, characterized in that: The middle locking member (5) is in surface contact with the surface of the parts inside the lower rotary-wing module of the rotary-wing Mars aircraft (4).

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