A propulsion and attitude adjustment device for aircraft in a space cabin

Abstract

The present invention belongs to the field of aircraft control technology, and specifically relates to a propulsion and attitude adjustment device for aircraft in a space capsule. The propulsion and attitude adjustment device for aircraft in a space capsule in the present invention includes a body and a first adjustment mechanism, and the first adjustment component and the second adjustment component both include a suction and discharge fluid component and a main body. A fluid flow channel is provided in the main body, and the fluid flow channel has a first flow channel opening and a second flow channel opening. The suction and discharge fluid component is provided at the first flow channel opening, and the body can be rotated or displaced along the first axis direction of the body under the action of the suction and discharge of the suction and discharge fluid component. By using the propulsion and attitude adjustment device for aircraft in a space capsule in the present technical solution, a pushing operation can be realized, and a rotation operation along the first direction can also be realized. Under the synergistic effect, the torque can be balanced, thereby achieving the purpose of rotating or displacing the body along the first direction.

Description

Technical Field

[0001] The present invention belongs to the technical field of aircraft control, and in particular relates to an aircraft propulsion and attitude adjustment device in a space cabin. Background Art

[0002] At present, the method for balancing the fan counter-torque of propeller aircraft is mainly symmetrical arrangement. Coaxial counter-propellers achieve axial propulsion along the propeller axis by balancing the counter-torque of two fans. The two fans are installed on the same flow channel, and a certain safety distance is maintained between the two propellers, which increases the length of the main shaft. In order to achieve attitude adjustment, coaxial counter-propellers need to add a complex variable propeller mechanism or a dual-motor coupling mechanism, which increases the complexity of the overall mechanism. Tail rotor balancing requires the installation of a tail rotor at the tail of the fuselage to balance the counter-torque generated by the rotation of the main propeller. In order to reduce the power consumption of the tail rotor to balance the rotation of the fuselage, a long tail is used to increase the distance between the tail rotor and the main propeller, but this results in an excessively long tail, reduced safety, and an increase in the fuselage length to balance the torque. While these devices solve the problem of counteracting counter-torque, they also require targeted design of the fuselage, which significantly increases the complexity and cost of the system structure. Summary of the Invention

[0003] The purpose of the present invention is to at least solve the problems of complex structure and low reliability of existing fan aircraft. This purpose is achieved through the following technical solutions:

[0004] A first aspect of the present invention provides a flight propulsion and attitude adjustment device for an aircraft in a space station, comprising:

[0005] body;

[0006] The first regulating mechanism comprises a first regulating component and a second regulating component connected to opposite sides of the body along a first direction, the first regulating component and the second regulating component both comprising a suction and discharge fluid component and a main body, a fluid flow channel being provided in the main body, the fluid flow channel having a first flow channel opening and a second flow channel opening, the first flow channel opening being provided along the first direction and facing away from the side of the body, the second flow channel opening being provided in a direction perpendicular to the first direction, the suction and discharge fluid component being provided at the first flow channel opening, the body being able to rotate or displace along the first axial direction of the body under the action of the suction and discharge of the suction and discharge fluid component, and the first axial direction being provided parallel to the first direction.

[0007] By using the space capsule aircraft propulsion and attitude adjustment device in the technical solution, a combined structure of an aircraft body and a first adjustment mechanism is adopted. The first adjustment mechanism includes a first adjustment component and a second adjustment component. The first adjustment component and the second adjustment component are respectively connected to opposite sides of the aircraft body, and can achieve torque balance or superposition by applying force to the aircraft body, thereby achieving displacement or rotation of the aircraft body along the first direction. Among them, the first adjustment component and the second adjustment component both include a fluid suction and discharge component and a main body. A fluid flow channel is provided in the main body. The fluid suction and discharge component is provided at the first flow channel opening of the fluid flow channel. It can inhale air from the second flow channel opening and exhaust air from the first flow channel opening, thereby achieving a pushing operation. It can also inhale air from the first flow channel opening and exhaust air from the second flow channel opening, thereby achieving a rotation operation along the first direction. Therefore, under the coordinated action of the fluid suction and discharge components of the first adjustment component and the second adjustment component, the torque can be balanced, thereby achieving the purpose of rotating or displacing the aircraft body along the first direction. The space capsule aircraft propulsion and attitude adjustment device of the present invention has a simple structure and is easy to assemble and disassemble. It only needs to connect the two adjustment components on both sides of the aircraft body to achieve rotation or displacement along the first direction, thereby improving reliability.

[0008] In addition, the spacecraft propulsion and attitude adjustment device in the space capsule according to the present invention may also have the following additional technical features:

[0009] In some embodiments of the present invention, the fluid flow channel includes a first fluid flow channel portion and a second fluid flow channel portion, one end of the first fluid flow channel portion is connected to the outside world through the first flow channel opening, one end of the second fluid flow channel portion is connected to the other end of the first fluid flow channel portion, and the other end of the second fluid flow channel portion is connected to the outside world through the second flow channel opening.

[0010] In some embodiments of the present invention, the second fluid flow channel portion also includes a first straight fluid flow channel portion and a second straight fluid flow channel portion that are connected to each other, wherein one end of the first straight fluid flow channel portion away from the second straight fluid flow channel portion is connected to the first fluid flow channel, and one end of the second straight fluid flow channel portion away from the first straight fluid flow channel portion is connected to the outside world through the second flow channel opening, and the second straight fluid flow channel portion is arranged close to the circumferential edge of the main body.

[0011] In some embodiments of the present invention, there are two second fluid flow channel portions, the two second fluid flow channel portions are symmetrical about the center line of the first fluid flow channel portion, and there are two second flow channel openings, each second fluid flow channel portion corresponds to one second flow channel opening, and the two second flow channel openings are oriented in opposite directions.

[0012] In some embodiments of the present invention, there are four second fluid flow channel portions, and the four second fluid flow channel portions are arranged at intervals along the circumference of the first fluid flow channel portion. Any two of the four second fluid flow channel portions are symmetrical about the center line of the first fluid flow channel. There are four second flow channel openings, and each second fluid flow channel portion corresponds to one second flow channel opening. The second flow channel openings corresponding to any two of the four second fluid flow channel portions are in opposite directions.

[0013] In some embodiments of the present invention, the orthographic projection of the fluid flow channel of the first regulating component on the preset plane along the first direction coincides with the orthographic projection of the fluid flow channel of the second regulating component on the preset plane.

[0014] In some embodiments of the present invention, the fluid suction and exhaust assembly includes a fan and a driving member, and the driving member is connected to the fan to drive the fan to rotate.

[0015] In some embodiments of the present invention, the center line of the first flow channel opening is arranged to coincide with the axis of the machine body.

[0016] In some embodiments of the present invention, the aircraft propulsion and attitude adjustment device in the space cabin also includes a second adjustment mechanism, which is connected to the opposite sides of the body along the second direction. The body can rotate or displace along the second axis direction of the body under the adjustment of the second adjustment mechanism, and the second axis direction is set parallel to the second direction.

[0017] In some embodiments of the present invention, the aircraft propulsion and attitude adjustment device in the space cabin also includes a third adjustment mechanism, which is connected to the opposite sides of the body along the third direction. The body can rotate or displace along the third axis direction of the body under the adjustment of the third adjustment mechanism. The third axis direction is set parallel to the third direction, and the first direction, the second direction and the third direction are perpendicular to each other. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Various other advantages and benefits will become apparent to those skilled in the art upon reading the detailed description of the preferred embodiment below. The accompanying drawings are for illustration purposes only and are not to be considered as limiting the present invention. The same reference numerals are used throughout the accompanying drawings to denote the same components. In the accompanying drawings:

[0019] Figure 1 The overall structural diagram of the propulsion and attitude adjustment device for an aircraft in a space capsule according to an embodiment of the present invention is schematically shown;

[0020] Figure 2 for Figure 1 A schematic diagram of the structure of the aircraft propulsion and attitude adjustment device in the mid-space cabin from another perspective;

[0021] Figure 3 for Figure 2 Schematic diagram of the cross-sectional structure in the AA direction;

[0022] Figure 4 for Figure 1 A schematic structural diagram of a first embodiment of the main body of the first adjustment assembly of the aircraft propulsion and attitude adjustment device in the mid-space cabin;

[0023] Figure 5 for Figure 1 A schematic structural diagram of a second embodiment of the main body of the first adjustment assembly of the aircraft propulsion and attitude adjustment device in the mid-space cabin;

[0024] Figure 6 for Figure 1 A schematic structural diagram of a first embodiment of the main body of the second adjustment assembly of the aircraft propulsion and attitude adjustment device in the mid-space cabin;

[0025] Figure 7 for Figure 1 A schematic structural diagram of a second embodiment of the main body of the second adjustment component of the aircraft propulsion and attitude adjustment device in the mid-space cabin.

[0026] The reference numerals in the accompanying drawings represent the following:

[0027] 10. Body;

[0028] 21. First regulating component; 22. Second regulating component; 23. Main body; 231. First flow channel opening; 232. Second flow channel opening; 233. First fluid flow channel portion; 234. Second fluid flow channel portion; 2341. First linear fluid flow channel portion; 2342. Second linear fluid flow channel portion; 241. Fan. DETAILED DESCRIPTION

[0029] Exemplary embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. Although exemplary embodiments of the present disclosure are shown in the accompanying drawings, it should be understood that the present disclosure can be implemented in various forms and should not be limited by the embodiments described herein. Rather, these embodiments are provided to enable a more thorough understanding of the present disclosure and to fully convey the scope of the present disclosure to those skilled in the art.

[0030] It should be understood that the terms used herein are for the purpose of describing specific example embodiments only and are not intended to be limiting. Unless the context clearly indicates otherwise, the singular forms "one", "an" and "said" as used herein may also be meant to include plural forms. The terms "comprise", "include", "contain" and "have" are inclusive and therefore specify the presence of stated features, steps, operations, elements and / or parts, but do not exclude the presence or addition of one or more other features, steps, operations, elements, parts, and / or combinations thereof. The method steps, processes, and operations described herein are not to be construed as necessarily requiring them to be performed in the specific order described or illustrated, unless the order of execution is clearly indicated. It should also be understood that additional or alternative steps may be used.

[0031] Although the terms first, second, third, etc. can be used in the text to describe multiple elements, components, regions, layers and / or sections, these elements, components, regions, layers and / or sections should not be limited by these terms. These terms can only be used to distinguish an element, component, region, layer or section from another region, layer or section. Unless the context clearly indicates otherwise, terms such as "first", "second" and other numerical terms do not imply order or sequence when used in the text. Therefore, the first element, component, region, layer or section discussed below can be referred to as the second element, component, region, layer or section without departing from the teaching of the example embodiments.

[0032] For ease of description, spatially relative terms may be used herein to describe the relationship of one element or feature relative to another element or feature as shown in the figures, such as "inside," "outside," "inside," "outside," "below," "beneath," "above," and the like. Such spatially relative terms are intended to include different orientations of the device in use or operation in addition to the orientation depicted in the figures. For example, if the device in the figures is flipped, an element described as "below" or "below" another element or feature would then be oriented as "above" or "above" another element or feature. Thus, the example term "below" can include both above and below orientations. The device may be otherwise oriented (rotated 90 degrees or in other orientations) and the spatially relative descriptors used herein are interpreted accordingly.

[0033] At present, the methods for balancing the fan anti-torque of fan aircraft mainly include coaxial counter-propeller, tail rotor balance and rudder balance.

[0034] Coaxial counter-propellers utilize two fans mounted on the same flow path, maintaining a safe distance between them. The fans balance the counter-torque, achieving axial propulsion along the propeller axis. However, this increases mechanical complexity and main shaft length, requiring a dedicated, independent flow path between the two propellers, which increases the aircraft's length. To achieve attitude adjustment, a variable-pitch mechanism or dual-motor coupling is required, resulting in a highly complex and complex structure.

[0035] Tail rotor balancing requires the installation of a tail rotor at the rear of the aircraft to balance the counter-torque generated by the rotation of the main rotor. To reduce the power consumption of the tail rotor to balance the aircraft's rotation, a long tail is used to increase the distance between the tail rotor and the main rotor. However, this results in an excessively long tail, which reduces safety, and the aircraft length is increased to balance the torque.

[0036] For single-fan aircraft and underwater equipment, corresponding control surfaces need to be designed to balance the torque imbalance caused by the fan rotation. Therefore, targeted design is required to achieve normal propulsion and attitude adjustment of the aircraft, which increases the size, complexity and use cost of the overall structure.

[0037] Figure 1 The overall structural diagram of the aircraft propulsion and attitude adjustment device in a space capsule according to an embodiment of the present invention is schematically shown. Figure 2 for Figure 1 A schematic diagram of the structure of the aircraft propulsion and attitude adjustment device in the space cabin from another perspective. Figure 1 and 2 As shown, the present invention provides a propulsion and attitude adjustment device for an aircraft in a space capsule. The propulsion and attitude adjustment device for an aircraft in a space capsule in the present invention includes a body 10 and a first adjustment mechanism, wherein the first adjustment mechanism includes a first adjustment component 21 and a second adjustment component 22 connected to opposite sides of the body 10 along a first direction. The first adjustment component 21 and the second adjustment component 22 each include a fluid suction and discharge component and a main body 23. The main body 23 is provided with a fluid flow channel, and the fluid flow channel has a first flow channel opening 231 and a second flow channel opening 232. The first flow channel opening 231 is arranged along the first direction and faces away from the body 10, and the second flow channel opening 232 is arranged in a direction perpendicular to the first direction. The fluid suction and discharge component is arranged at the first flow channel opening 231. The body 10 can rotate or displace along a first axial direction of the body 10 under the action of the suction and discharge of air by the fluid suction and discharge component, and the first axial direction is arranged parallel to the first direction.

[0038] By using the aircraft propulsion and attitude adjustment device in the space cabin of the present technical solution, a combined structure of the body 10 and the first adjustment mechanism is adopted. The first adjustment mechanism includes a first adjustment component 21 and a second adjustment component 22. The first adjustment component 21 and the second adjustment component 22 are respectively connected to the opposite sides of the body 10, and can achieve torque balance or superposition when applying force to the body 10, thereby achieving displacement or rotation of the body 10 along the first direction. Among them, the first adjustment component 21 and the second adjustment component 22 both include a fluid suction and discharge component and a main body 23. A fluid flow channel is provided in the main body 23, and the fluid suction and discharge component is provided at the first flow channel opening 231 of the fluid flow channel. Air can be sucked in by the second flow channel opening 232 and exhausted by the first flow channel opening 231, thereby realizing a pushing operation. Air can also be sucked in by the first flow channel opening 231 and exhausted by the second flow channel opening 232, thereby realizing a rotation operation along the first direction. Therefore, under the coordinated action of the suction and exhaust fluid components of the first adjustment component 21 and the second adjustment component 22, the torque can be balanced, thereby achieving the purpose of rotating or displacing the body 10 along the first direction. The aircraft propulsion and attitude adjustment device in the space cabin of the present invention has a simple structure and is easy to disassemble and assemble. It only needs to connect two adjustment components on both sides of the body 10 to realize rotation or displacement along the first direction, thereby improving reliability.

[0039] In some embodiments of the present invention, Figure 3 As shown, the fluid flow path includes a first fluid flow path portion 233 and a second fluid flow path portion 234. One end of the first fluid flow path portion 233 communicates with the outside world via a first flow path opening 231. One end of the second fluid flow path portion 234 communicates with the other end of the first fluid flow path portion 233, and the other end of the second fluid flow path portion 234 communicates with the outside world via a second flow path opening 232. The fluid suction and discharge assembly is located at the first flow path opening of the first fluid flow path portion 233. In this embodiment, the first fluid flow path portion 233 is located in the middle of the main body 23 and is used to accommodate the fluid suction and discharge assembly. The fluid suction and discharge assembly can perform suction or exhaust operations due to its own characteristics. When the suction operation is performed, the suction and exhaust fluid component can suck in air from the first flow channel opening 231 and discharge the air from the second flow channel opening 232 through the fluid flow channel. Since the direction of the second flow channel opening 232 is perpendicular to the first flow channel opening 231, a torque can be applied to the main body 23 along the first direction. At the same time, the main body 23 is connected to the body 10, which can enable the body 10 to rotate along the first direction.

[0040] Specifically, when performing exhaust operation, the suction and exhaust fluid component can inhale air from the second flow channel 232 and discharge the air from the first flow channel 231 through the fluid flow channel. Since the direction of the first flow channel 231 is the same as the first direction, it can drive the main body 23 and the body 10 connected to the main body 23 to move along the first direction.

[0041] Specifically, in this embodiment, the first adjustment assembly 21 and the second adjustment assembly 22 are used in conjunction with each other, that is, when the suction and discharge components of the first adjustment assembly 21 and the second adjustment assembly 22 are simultaneously inhaling or exhausting air, they can drive the body 10 to rotate in the first direction. When one of the suction and discharge components of the first adjustment assembly 21 and the second adjustment assembly 22 is inhaling air and the other is in exhausting air, the body 10 can be displaced in the first direction.

[0042] In some embodiments of the present invention, Figure 3 As shown, the second fluid flow channel portion 234 also includes a first linear fluid flow channel portion 2341 and a second linear fluid flow channel portion 2342 that are interconnected. The end of the first linear fluid flow channel portion 2341 away from the second linear fluid flow channel portion 2342 is connected to the first fluid flow channel, and the end of the second linear fluid flow channel portion 2342 away from the first linear fluid flow channel portion 2341 is connected to the outside through the second flow channel opening 232. The second linear fluid flow channel portion 2342 is disposed near the circumferential edge of the main body 23. In this embodiment, the second fluid flow channel portion 234 also includes a first linear fluid flow channel portion 2341 and a second linear fluid flow channel portion 2342, which are disposed at an angle, preferably perpendicularly, and the second linear fluid flow channel portion 2342 is disposed near the edge of the main body 23. This ensures that the second linear fluid flow channel portion 2342 deviates from the bisector of the main body 23. Consequently, when exhaust is exhausted through the second flow channel opening 232, the airflow at the edge of the main body 23 is reacted, ultimately achieving rotation of the main body 23.

[0043] Specifically, in this embodiment, the main body 23 is a cube, and the second main line fluid flow channel portion is parallel to the edge of one side of the cube, which can better ensure that the reaction force of the airflow applies force to one corner of the cube and realize the rotation of the main body 23 and the body 10 connected to it.

[0044] In some embodiments of the present invention, Figure 4 and 6As shown, two second fluid flow channel portions 234 are provided, and the two second fluid flow channel portions 234 are centrosymmetrical about the centerline of the first fluid flow channel portion 233. Two second flow channel openings 232 are provided, and each second fluid flow channel portion 234 corresponds to a second flow channel opening 232, and the two second flow channel openings 232 face opposite directions. In this embodiment, two second fluid flow channel portions 234 and two air outlets are provided, and the two second fluid flow channel portions 234 are centrosymmetrical about the centerline of the first fluid flow channel portion 233. This ensures that during the suction and discharge operation, the suction and discharge fluid assembly applies airflow reaction force to two opposing corners of the main body 23, thereby better ensuring that the main body 23 rotates in the first direction without displacement in the second or third directions (the second, first, and third directions are perpendicular to each other), thereby improving reliability.

[0045] In some embodiments of the present invention, Figure 5 and 7 As shown, there are four second fluid flow channel portions 234, which are spaced apart circumferentially around the first fluid flow channel portion 233. Any two of the four second fluid flow channel portions 234 are symmetrical about the centerline of the first fluid flow channel. There are four second flow channel openings 232, with each second fluid flow channel portion 234 corresponding to a second flow channel opening 232. The second flow channel openings 232 corresponding to any two of the four second fluid flow channel portions 234 face opposite directions. In this embodiment, the above arrangement ensures that the suction and discharge fluid assembly applies airflow reaction forces to the four opposing corners of the main body 23 during suction operation, thereby better ensuring rotation of the main body 23 in the first direction without causing displacement in the second or third directions (the second, first, and third directions are perpendicular to each other), thereby improving reliability. In the present invention, a combination structure of four second fluid flow channel portions 234 and four second flow channel openings 232 is preferred, which can better ensure the adjustment of the posture of the body 10.

[0046] In some embodiments of the present invention, the orthographic projection of the fluid flow path of the first regulating assembly 21 along the first direction on the preset plane coincides with the orthographic projection of the fluid flow path of the second regulating assembly 22 on the preset plane. In this embodiment, the fluid flow path structures of the first regulating assembly 21 and the second regulating assembly 22 are identical, differing in that the second flow path opening 232 of the first regulating assembly 21 is located on the side of the main body 23 of the first regulating assembly 21 away from the housing 10, while the second flow path opening 232 of the second regulating assembly 22 is located on the side of the main body 23 of the second regulating assembly 22 away from the housing 10. That is, the second flow path opening 232 of the first regulating assembly 21 and the second flow path opening 232 of the second regulating assembly 22 are both located away from the housing 10, facilitating the coordinated suction and exhaust operations of the first regulating assembly 21 and the second regulating assembly 22.

[0047] In some embodiments of the present invention, the fluid suction and exhaust component includes a fan 241 and a driving member, which is connected to the fan 241 and is used to drive the fan 241 to rotate. In this embodiment, the fan 241 can also be replaced by a propeller. During the rotation, the propeller continuously stirs the air, forcing the air to rotate along the direction of the propeller's rotation. At the same time, the air will inevitably give the propeller and the main body 23 connected to the propeller a torque in the opposite direction. This torque is called the reaction torque of the propeller. This means that when the fan 241 or propeller performs an exhaust operation, it will directly force the main body 23 connected to it to rotate. If this fan 241 performs an intake operation, it will cause the main body 23 to rotate in the opposite direction to the exhaust operation. The driving member in this embodiment is a motor.

[0048] In some embodiments of the present invention, the centerline of the first flow channel 231 is arranged to coincide with the axis of the body 10. In this embodiment, this arrangement ensures that when the first flow channel 231 is in exhaust operation, it propels the main body 23 and the body 10 connected to the main body 23 to the center position, ensuring the accuracy of displacement along the first direction and improving reliability.

[0049] In some embodiments of the present invention, the propulsion and attitude adjustment device for the aircraft in the space capsule further includes a second adjustment mechanism, the second adjustment mechanism being connected to opposite sides of the body along the second direction, and the body being capable of rotating or displacing along the second axis of the body under the adjustment of the second adjustment mechanism, wherein the second axis is parallel to the second direction. In this embodiment, the second adjustment mechanism has the same structure as the first adjustment mechanism and also includes two adjustment components, respectively connected to opposite sides of the body 10 along the second direction, and both adjustment components include a fluid suction and discharge component and a main body 23, wherein the main body 23 is provided with a fluid flow channel, the fluid flow channel having a third air port and a fourth air port, the third air port being arranged along the second direction and facing away from the body, and the fourth air port being arranged in a direction perpendicular to the second direction, the fluid suction and discharge component being arranged at the third air port, and the body being capable of rotating or displacing along the second axis of the body under the action of the suction and discharge of air by the fluid suction and discharge component, wherein the second axis is parallel to the second direction.

[0050] Specifically, the combined use of the first adjustment mechanism and the second adjustment mechanism can ensure that the body 10 can be adjusted in four degrees of freedom, further improving the posture adjustment capability of the body 10.

[0051] In some embodiments of the present invention, the propulsion and attitude adjustment device for the aircraft in the space capsule further includes a third adjustment mechanism, the third adjustment mechanism being connected to opposite sides of the body along the third direction, the body being able to rotate or displace along a third axis of the body under the adjustment of the third adjustment mechanism, the third axis being parallel to the third direction, and the first direction, the second direction, and the third direction being perpendicular to each other. In this embodiment, the third adjustment mechanism has the same structure as the first adjustment mechanism, and also includes two adjustment components, respectively connected to opposite sides of the body 10 along the third direction, and both adjustment components include a suction and discharge fluid component and a main body 23, the main body 23 being provided with a fluid flow channel, the fluid flow channel having a fifth air port and a sixth air port, the fifth air port being arranged along the third direction and facing away from the body, the sixth air port being arranged in a direction perpendicular to the third direction, the suction and discharge fluid component being arranged at the fifth air port, the body being able to rotate or displace along the third axis of the body under the action of the suction and discharge of air by the suction and discharge fluid component, the third axis being parallel to the third direction.

[0052] Specifically, the combined use of the first adjustment mechanism, the second adjustment mechanism, and the third adjustment mechanism can ensure that the body 10 can be adjusted in six degrees of freedom, further improving the posture adjustment capability of the body 10.

[0053] Furthermore, the operating principle of the spacecraft propulsion and attitude adjustment device in the space capsule of the present invention is as follows (this principle takes the fluid flow path including a first fluid flow path portion 233 and two second fluid flow path portions 234 as an example):

[0054] When the fan 241 of the first adjustment assembly 21 is performing an intake operation and the fan 241 of the second adjustment assembly 22 is performing an exhaust operation, air is taken in by the first flow channel 231 of the first adjustment assembly 21, and exhausted by the two second flow channel 232 of the first adjustment assembly 21. Due to the relative action of the airflow discharged from the second flow channel 232, the main body 23 of the first adjustment assembly 21 and the housing 10 are subjected to a positive torque. At the same time, the fan 241 of the second adjustment assembly 22, during the exhaust operation, directly exerts a reverse torque on the main body 23 and the housing 10, i.e., a torque in the opposite direction to that of the first adjustment assembly 21. This causes the torques generated between the first adjustment assembly 21 and the second adjustment assembly 22 to cancel each other out. At the same time, due to the intake of air by the fan 241 of the first adjustment assembly 21 and the exhaust of air by the fan 241 of the second adjustment assembly 22, the housing 10 is subjected to a positive displacement operation along the first direction, without any rotation operation.

[0055] When the fan 241 of the first adjustment component 21 performs an exhaust operation and the fan 241 of the second adjustment component 22 performs an intake operation, the principle is the same as above and will not be repeated here. In this case, the torque between the first adjustment component 21 and the second adjustment component 22 of the body 10 will also be offset. However, since the fan 241 of the first adjustment component 21 exhausts air and the fan 241 of the second adjustment component 22 inhales air, the body 10 will perform a reverse displacement operation along the first direction and no rotation operation will occur.

[0056] When the fan 241 of the first regulating assembly 21 and the fan 241 of the second regulating assembly 22 are both operating to draw air, the propulsive force in the first direction is offset by the fact that both regulating assemblies are operating to draw air. At the same time, air is drawn in by the first flow channel opening 231 of the first regulating assembly 21 and exhausted by the two second flow channel openings 232 of the first regulating assembly 21. Due to the relative action of the airflows discharged from the second flow channel openings 232, the main body 23 of the first regulating assembly 21 and the housing 10 have a positive torque. At the same time, when the fan 241 of the second regulating assembly 22 is operating to draw air, air is also drawn in by the first flow channel opening 231 of the second regulating assembly 22 and exhausted by the two second flow channel openings 232 of the second regulating assembly 22. Due to the relative action of the airflows discharged from the second flow channel openings 232, the main body 23 of the second regulating assembly 22 and the housing 10 have a positive torque. The superposition of the positive torque between the first adjustment component 21 and the second adjustment component 22 can further drive the body 10 to perform a positive rotation operation along the first direction, and there is no displacement along the first direction during this process.

[0057] When the fan 241 of the first adjustment component 21 and the fan 241 of the second adjustment component 22 are both performing exhaust operations, the principle is the same as above and will not be repeated here. In this case, negative torque will be generated between the first adjustment component 21 and the second adjustment component 22 of the body 10, and under the superposition of the two negative torques, the body 10 can be further driven to perform a negative rotation operation along the first direction, and the propulsion force along the first direction in this process will be offset because both adjustment components are performing exhaust operations, so there is no displacement along the first direction.

[0058] Furthermore, the flight control mechanism of the present invention can provide both thrust and the torque required for attitude adjustment along a first direction. This mechanism includes a first adjustment assembly 21 and a second adjustment assembly 22, which are mounted on the same axis of the aircraft 10 to achieve propulsion and attitude adjustment of the aircraft 10 along that axis. This mechanism does not rely on the specific design of the objects being propelled and attitude adjusted, and does not require a safety distance. It can be symmetrically mounted anywhere on the exterior of the aircraft 10 to achieve propulsion at that location and attitude adjustment along that axis.

[0059] Specifically, the flight adjustment mechanism of the present invention does not require a targeted design of the body 10, and does not require a reserved flow channel in the body 10. It occupies a small space and is easy to install. If omnidirectional movement is required, it is only necessary to install three sets of corresponding adjustment components in three directions (first direction, second direction and third direction) to achieve six-degree-of-freedom movement. The mechanism can generate corresponding two-directional torque and unidirectional thrust through the forward and reverse rotation of the driving member in the mechanism. In addition, under preferred circumstances, the mechanism only requires one motor and 2n second fluid flow channel parts 234 to complete, with a simple structure and high reliability. The torque size can be actively adjusted by the driving force of the driving member and the speed of the fan 241.

[0060] The above description is merely a preferred embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any changes or substitutions that can be easily conceived by a person skilled in the art within the technical scope disclosed in the present invention should be included in the scope of protection of the present invention. Therefore, the scope of protection of the present invention should be based on the scope of protection of the claims.

Claims

1. A propulsion and attitude adjustment device for an aircraft in a space capsule. The propulsion and attitude adjustment device for an aircraft in a space capsule is characterized by: include: body; a first regulating mechanism, the first regulating mechanism comprising a first regulating assembly and a second regulating assembly connected to opposite sides of the body along a first direction, the first regulating assembly and the second regulating assembly both comprising a fluid suction and discharge assembly and a main body, a fluid flow channel being provided in the main body, the fluid flow channel comprising a first flow channel opening and a second flow channel opening, the first flow channel opening being provided along the first direction and facing away from the body, the second flow channel opening being provided in a direction perpendicular to the first direction, the fluid suction and discharge assembly being provided at the first flow channel opening, the body being capable of rotating or displacing along a first axial direction of the body under the action of suction and discharge of air by the fluid suction and discharge assembly, the first axial direction being provided parallel to the first direction; The fluid flow channel includes a first fluid flow channel portion and a second fluid flow channel portion, one end of the first fluid flow channel portion is connected to the outside through the first flow channel opening, one end of the second fluid flow channel portion is connected to the other end of the first fluid flow channel portion, and the other end of the second fluid flow channel portion is connected to the outside through the second flow channel opening; The second fluid flow channel portion also includes a first straight fluid flow channel portion and a second straight fluid flow channel portion that are connected to each other. One end of the first straight fluid flow channel portion away from the second straight fluid flow channel portion is connected to the first fluid flow channel, and one end of the second straight fluid flow channel portion away from the first straight fluid flow channel portion is connected to the outside world through the second flow channel opening. The second straight fluid flow channel portion is arranged close to the circumferential edge of the main body.

2. The spacecraft propulsion and attitude adjustment device according to claim 1, characterized in that: There are two second fluid flow channel portions, and the two second fluid flow channel portions are symmetrical about the center line of the first fluid flow channel portion. There are two second flow channel openings, and each second fluid flow channel portion corresponds to one second flow channel opening, and the two second flow channel openings are oriented in opposite directions.

3. The propulsion and attitude adjustment device for an aircraft in a space capsule according to claim 1, characterized in that: There are four second fluid flow channel portions, and the four second fluid flow channel portions are arranged at intervals along the circumference of the first fluid flow channel portion. Any two of the four second fluid flow channel portions are symmetrical about the center line of the first fluid flow channel. There are four second flow channel openings, and each second fluid flow channel portion corresponds to one second flow channel opening. The second flow channel openings corresponding to any two of the four second fluid flow channel portions are in opposite directions.

4. The propulsion and attitude adjustment device for an aircraft in a space capsule according to claim 1, characterized in that: The orthographic projection of the fluid flow channel of the first regulating component on the preset plane along the first direction coincides with the orthographic projection of the fluid flow channel of the second regulating component on the preset plane.

5. The propulsion and attitude adjustment device for an aircraft in a space capsule according to claim 1, characterized in that: The fluid suction and exhaust assembly includes a fan and a driving member, wherein the driving member is connected to the fan and is used to drive the fan to rotate.

6. The propulsion and attitude adjustment device for an aircraft in a space capsule according to claim 1, characterized in that: The center line of the first flow channel opening is arranged to coincide with the axis of the machine body.

7. The propulsion and attitude adjustment device for an aircraft in a space capsule according to claim 1, characterized in that: The aircraft propulsion and attitude adjustment device in the space cabin also includes a second adjustment mechanism, which is connected to the opposite sides of the body along the second direction. The body can rotate or displace along the second axis direction of the body under the adjustment of the second adjustment mechanism, and the second axis direction is arranged parallel to the second direction.

8. The propulsion and attitude adjustment device for an aircraft in a space capsule according to claim 7, characterized in that: The aircraft propulsion and attitude adjustment device in the space capsule also includes a third adjustment mechanism, which is connected to the opposite sides of the body along the third direction. The body can rotate or displace along the third axis direction of the body under the adjustment of the third adjustment mechanism. The third axis direction is arranged parallel to the third direction, and the first direction, the second direction and the third direction are perpendicular to each other.

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