A locking and releasing device for a multi-rotor Mars aircraft

Abstract

The present invention provides a locking and releasing device for a multi-rotor Martian aircraft, comprising a cylindrical sealed box body, the box body comprising a top wall, side walls, and a bottom wall, the side walls being assembled from a plurality of side panels, the plurality of side panels being in end-to-end sealing contact along the circumference of the bottom wall, the side panels being rotatably connected to the bottom wall, a spiral spring being provided between the side panels and the bottom wall, the top wall being assembled from a plurality of top panels, the number of top panels corresponding to the number of side panels, the corresponding top panels being fixedly connected or integrally formed with the side panels, the top panels being provided with grooves, the plurality of grooves being connected to form a ring, a locking mechanism being provided within the ring, an aircraft base being provided within the box body, the aircraft base being fixedly provided to the bottom wall, and an aircraft restraint mechanism being fixedly provided on the inner wall of the box body. The present invention has a simple structure and is easy to use.

Description

Technical Field

[0001] The present invention relates to a locking and releasing device for a multi-rotor Mars aircraft, belonging to the technical field of space resource detection. Background Art

[0002] Mars has a thin atmosphere, less than 1% of Earth's density. This thin atmosphere makes the existence of Martian spacecraft possible. Humans have many ways to explore Mars, with rovers being the most common. However, if rovers were to work together with spacecraft, the results would be even better. The spacecraft could explore a wider area and guide the rover's direction to avoid obstacles. Existing multi-rotor Martian spacecraft are prone to collisions, moisture, and dust contamination during transportation from the surface to the Martian surface. Furthermore, the harsh Martian surface environment makes most unprotected multi-rotor Martian spacecraft unusable. Summary of the Invention

[0003] The purpose of the present invention is to provide a locking and releasing device for a multi-rotor Martian aircraft, which can constrain the folding structure of the multi-rotor Martian aircraft when it is stored or transported in space, and can be easily unfolded, unlocked, released and perform tasks when it arrives at the destination.

[0004] To achieve the above objectives, the present invention is implemented through the following technical solutions:

[0005] A multi-rotor Martian aircraft locking and releasing device comprises a cylindrical sealed box body, the box body comprises a top wall, a side wall and a bottom wall, the side wall is composed of a plurality of side panels, and the plurality of side panels are in sealing contact end to end along the circumference of the bottom wall, the side panels are rotatably connected to the bottom wall, a spiral spring is provided between the side panels and the bottom wall, the top wall is composed of a plurality of top panels, the number of the top panels corresponds one to one to the number of the side panels, the corresponding top panels and the side panels are fixedly connected or integrally formed, a groove is provided on the top panel, and the plurality of grooves are connected to form a ring, a locking mechanism is provided in the ring, an aircraft base is provided in the box body, the aircraft base is fixedly provided on the bottom wall, the aircraft base is used to place the Martian aircraft, and an aircraft restraint mechanism is fixedly provided on the inner wall of the box body.

[0006] Preferably, the locking mechanism is a wrapping belt, which restrains the multiple top plates together.

[0007] Preferably, pyrotechnic devices are connected to both sides of the wrapping belt.

[0008] Preferably, the aircraft base is located at the center of the bottom wall, and a gap is left between the aircraft base and the inner wall of the box.

[0009] Preferably, the aircraft constraint mechanism is groove-shaped, including a motor constraint groove, a wheel constraint groove and a blade constraint groove, and the motor constraint groove, the wheel constraint groove and the blade constraint groove are respectively adapted to the motor, wheels and blades of the Martian aircraft.

[0010] Preferably, the motor restraint groove and the wheel restraint groove are both fixedly arranged on the bottom wall.

[0011] Preferably, the blade restraint groove is fixed on the side wall.

[0012] Preferably, the number of the motor restraint grooves is several, and the several motor restraint grooves are evenly distributed on the bottom wall along the same circumference with the center of the bottom wall as the center.

[0013] Preferably, the number of the wheel restraining grooves is several, and the several wheel restraining grooves are evenly distributed on the bottom wall along the same circumference with the center of the bottom wall as the center.

[0014] Preferably, the blade restraining grooves are provided in a plurality of groups, and the blade restraining grooves in the plurality of groups are evenly distributed on the side wall along the same circumference.

[0015] Compared with the prior art, the present invention has the following beneficial effects:

[0016] 1. The present invention serves as a container for the multi-rotor Martian aircraft during storage and transportation, thereby making the multi-rotor Martian aircraft less susceptible to moisture and dust during storage and transportation, and protecting the aircraft's mechanical structure and internal circuits from damage caused by collisions.

[0017] 2. The present invention realizes the unlocking and release of the multi-rotor Mars aircraft on the surface of Mars through the arrangement of the spiral spring, the wrapping belt and the pyrotechnic device. The structure is simple and easy to deploy, which reduces the difficulty of controlling it on the surface of Mars.

[0018] 3. The present invention can be applied to Martian spacecraft with different numbers of rotors by adjusting the number of envelope side panels and the shape of the bottom panel. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 This is a schematic diagram of the three-dimensional structure of the first embodiment of the present invention when locked.

[0020] Figure 2 for Figure 1 Top view of an embodiment.

[0021] Figure 3 for Figure 1 Front view of an embodiment.

[0022] Figure 4 for Figure 2Section view along AA.

[0023] Figure 5 for Figure 3 Cross-sectional view along BB.

[0024] Figure 6 for Figure 1 Schematic diagram of the three-dimensional structure when the embodiment is released.

[0025] Figure 7 This is a schematic diagram of the three-dimensional structure of the second embodiment of the present invention when locked.

[0026] In the figure: 1. Wrapping belt; 2. Top plate; 3. Side plate; 4. Blade restraint groove; 5. Aircraft base; 6. Motor restraint groove; 7. Wheel restraint groove; 8. Bottom wall. DETAILED DESCRIPTION

[0027] Below, the present invention is further described with reference to the accompanying drawings:

[0028] In the description of the present invention, it should be noted that all directional indications (such as top, bottom, etc.) are based on the orientation or positional relationship shown in the accompanying drawings, which are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply 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 on the present invention; in addition, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be internal communication between two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0029] Example 1

[0030] like Figure 1-7As shown, the present invention discloses a locking and releasing device for a multi-rotor Martian aircraft. The device comprises a cylindrical sealed housing comprising a top wall, side walls, and a bottom wall. The side walls are formed by a plurality of side panels 3, which are arranged in end-to-end sealing contact along the circumference of the bottom wall 8. The side panels 3 are pivotally connected to the bottom wall 8, with a spiral spring disposed between the side panels 3 and the bottom wall 8. The top wall is formed by a plurality of top panels 2, with the number of top panels 2 corresponding to the number of side panels 3. The corresponding top panels 2 and side panels 3 are fixedly connected or integrally formed. Preferably, sealing strips are provided at the junctions between the side panels, the top panel, and the bottom wall to ensure good sealing of the locking and releasing device for a multi-rotor Martian aircraft. The top panel 2 is provided with a groove, which is connected to form a ring. A locking mechanism is disposed within the ring. The locking mechanism is a wrapping band 1, which binds the top panels 2 together to offset the elastic force generated by the spiral springs at the bottom of the side panels 3. The two sides of the bag belt 1 are connected by a pyrotechnic device (such as an explosive bolt). When the bag belt 1 reaches the surface of Mars, the pyrotechnic device can bounce the bag belt 1 open.

[0031] The box is provided with an aircraft base 5, which is fixed to the bottom wall 8 and fixedly connected to the bottom wall 8 (e.g., bolted). Preferably, the aircraft base 5 is located at the center of the bottom wall 8 and is a cylindrical body protruding into the interior of the box. It is conformable to the multi-rotor Martian aircraft and is used to place the Martian aircraft and bear the weight of the multi-rotor Martian aircraft, allowing for stable transportation and storage. A gap is left between the aircraft base 5 and the inner wall of the box to accommodate other aircraft structures.

[0032] An aircraft restraint mechanism is fixedly provided on the inner wall of the housing. The aircraft restraint mechanism is groove-shaped and includes a motor restraint groove 6, a wheel restraint groove 7, and a blade restraint groove 4. The motor restraint groove 6 is shaped to conform to the motor of the Martian aircraft, the wheel restraint groove 7 is shaped to conform to the wheel of the Martian aircraft, and the blade restraint groove 4 is shaped to conform to the blade of the Martian aircraft. The motor restraint groove 6 and the wheel restraint groove 7 are both fixedly connected (e.g., bonded) to the bottom wall 8. There are a plurality of motor restraint grooves 6, each of which is evenly distributed on the bottom wall 8 along a common circumference centered on the center of the bottom wall 8. There are a plurality of wheel restraint grooves 7, each of which is evenly distributed on the bottom wall 8 along a common circumference centered on the center of the bottom wall 8. The blade restraint groove 4 is fixedly connected (e.g., bonded) to the side wall. There are a plurality of groups of blade restraint grooves 4, each of which is evenly distributed on the side wall along a common circumference centered on a point on an axis passing through the center of the bottom wall 8. Used to constrain some easily movable components (including wheels, motors and blades) that make up the multi-rotor Mars aircraft to prevent them from moving during transportation.

[0033] Specifically, when the multi-rotor Martian aircraft is a quadrotor, the number of top panels 2 and side panels 3 is four. When the multi-rotor Martian aircraft's locking and release mechanism needs to be locked, the scroll spring contracts, and the bottom wall 8, top panel 2, and side panels 3 form a sealed box space to prevent moisture, dust, and possible collisions during storage and transportation. When the multi-rotor Martian aircraft's locking and release mechanism needs to be released, the scroll spring expands, and the corresponding top panel 2 and side panels 3 are pulled outward by the scroll spring, preferably at an angle of 90°. There are four motor restraint slots 6 and four wheel restraint slots 7, respectively. The motor restraint slots 6 are equidistant from the center of the bottom wall 8, with a 90° angle between each slot. Their shape conforms to the motor, preventing damage to the motor due to collision or vibration during transportation. The wheel restraint slots 7 are equidistant from the center of the bottom wall 8, with a 90° angle between each slot, preventing damage to the wheels due to collision or vibration during transportation. There are eight blade restraint slots 4 , with two blade restraint slots 4 forming a group. The blade tip is placed in the blade restraint slot 4 to prevent it from moving during transportation.

[0034] Example 2

[0035] like Figure 7As shown, when the multi-rotor Martian aircraft has six rotors, the number of side panels 3 and top panel 2 can be increased accordingly, and the shape of bottom wall 8 can be modified, so that the bottom wall 8 forms a box space with the side panels 3 and top panel 2. When the multi-rotor Martian aircraft has other numbers of rotors, the number of side panels 3 and top panel 2 and the shape of bottom wall 8 can be appropriately adjusted to meet the needs of aircraft with different numbers of rotors.

[0036] Working principle:

[0037] During the ground preparation process, the multi-rotor Mars aircraft is placed on the aircraft base and fixed, the motor is placed in the motor constraint groove position for constraint and fixation, the wheels are placed in the wheel constraint groove position for constraint and fixation, and the blade tips are placed in the blade constraint groove for constraint and fixation. After that, the side panels and the top panel are closed, the strap is installed in the ring formed by the grooves of the top panel, and after being fixed with a pyrotechnic device, the multi-rotor Mars aircraft locking and releasing device is locked, which serves as a container for storing the multi-rotor Mars aircraft during the process of transporting it from the ground to the surface of Mars. After arriving at the surface of Mars, the multi-rotor Mars aircraft locking and releasing device needs to be released. After the pyrotechnic device pops open the strap, the side panels and the top panel are pulled 90 degrees to the four sides by the spiral spring. At this time, the Mars multi-rotor aircraft body can directly unfold by itself and perform the Mars exploration mission. The structure is simple and easy to use.

[0038] In summary, the locking and releasing device for a multi-rotor Martian aircraft provided by the present invention should be finally explained as follows: the above description is merely a preferred embodiment of the present invention and is not intended to limit the present invention. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art can still modify the technical solutions described in the aforementioned embodiments or replace some of the technical features therein with equivalents. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principles of the present invention shall be included within the scope of protection of the present invention.

Claims

1. A locking and releasing device for a multi-rotor Mars aircraft, characterized in that The box body includes a columnar sealed box body, which includes a top wall, a side wall and a bottom wall, the side wall is composed of a plurality of side panels, and the plurality of side panels are in sealing contact end to end along the circumference of the bottom wall, the side panels are rotatably connected to the bottom wall, and a spiral spring is provided between the side panels and the bottom wall, the top wall is composed of a plurality of top panels, the number of the top panels corresponds one to one to the number of the side panels, the corresponding top panels and the side panels are fixedly connected or integrally formed, a groove is provided on the top panel, and the plurality of grooves are connected to form a ring, a locking mechanism is provided in the ring, an aircraft base is provided in the box body, the aircraft base is fixed on the bottom wall, the aircraft base is used to place a Martian aircraft, and an aircraft restraint mechanism is fixed on the inner wall of the box body.

2. The locking and releasing device for a multi-rotor Martian aircraft according to claim 1, characterized in that The locking mechanism is a wrapping belt, which binds the multiple top plates together.

3. The locking and releasing device for a multi-rotor Martian aircraft according to claim 2, characterized in that Both sides of the wrapping belt are connected with pyrotechnic devices.

4. The locking and releasing device for a multi-rotor Martian aircraft according to claim 1, characterized in that The aircraft base is located at the center of the bottom wall, and a gap is left between the aircraft base and the inner wall of the box.

5. The locking and releasing device for a multi-rotor Martian aircraft according to claim 1, characterized in that The aircraft constraint mechanism is groove-shaped, including a motor constraint groove, a wheel constraint groove and a blade constraint groove. The motor constraint groove, the wheel constraint groove and the blade constraint groove are respectively conformed to the motor, wheel and blade of the Martian aircraft.

6. The locking and releasing device for a multi-rotor Martian aircraft according to claim 5, characterized in that The motor restraint groove and the wheel restraint groove are both fixedly arranged on the bottom wall.

7. The locking and releasing device for a multi-rotor Martian aircraft according to claim 5, characterized in that The blade restraining groove is fixed on the side wall.

8. The locking and releasing device for a multi-rotor Martian aircraft according to claim 6, characterized in that The number of the motor restraint grooves is several, and the motor restraint grooves are evenly distributed on the bottom wall along the same circumference with the center of the bottom wall as the center.

9. The locking and releasing device for a multi-rotor Martian aircraft according to claim 6, characterized in that The number of the wheel restraining grooves is several, and the several wheel restraining grooves are evenly distributed on the bottom wall along the same circumference with the center of the bottom wall as the center.

10. The locking and releasing device for a multi-rotor Martian aircraft according to claim 7, characterized in that The blade restraining grooves are present in a plurality of groups, and the blade restraining grooves in the plurality of groups are evenly distributed on the side wall along the same circumference.

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