阅读说明：本技术 一种适用于外星探测直升机的可折叠机身 (Collapsible fuselage suitable for foreign body surveys helicopter ) 是由 招启军 周旭 王博 张夏阳 杜思亮 赵国庆 于 2021-07-27 设计创作，主要内容包括：本发明公开一种适用于外星探测直升机的可折叠机身,包括中心件,所述中心件上端用于连接充气式旋翼系统,所述中心件下端用于连接任务装置及起落架；所述中心件侧壁均匀环设有四个能够折叠的支撑翼部件,所述支撑翼部件外侧固定连接有能够充气的涵道气囊。本发明使机身和桨叶均能够进行折叠,从而减少运输时所占用的空间。(The invention discloses a foldable fuselage suitable for a extraterrestrial exploration helicopter, which comprises a central piece, wherein the upper end of the central piece is used for connecting an inflatable rotor system, and the lower end of the central piece is used for connecting a task device and an undercarriage; four foldable supporting wing parts are uniformly and circularly arranged on the side wall of the central part, and the outer sides of the supporting wing parts are fixedly connected with an inflatable ducted air bag. The folding device enables the machine body and the blades to be folded, so that the space occupied during transportation is reduced.)

1. The utility model provides a collapsible fuselage suitable for helicopter is surveyed to extra terrestrial which characterized in that: the inflatable rotary wing system comprises a central piece, wherein the upper end of the central piece is used for connecting the inflatable rotary wing system, and the lower end of the central piece is used for connecting a task device and an undercarriage; four foldable supporting wing parts are uniformly and circularly arranged on the side wall of the central part, and the outer sides of the supporting wing parts are fixedly connected with an inflatable ducted air bag.

2. The collapsible fuselage adapted for a alien sounding helicopter according to claim 1, characterized in that: the side wall of the central part is uniformly provided with four horizontal sleeves, the four horizontal sleeves are arranged in the same plane in a cross manner, and one end of each horizontal sleeve, which is far away from the central part, is opened.

3. The collapsible fuselage adapted for a alien sounding helicopter according to claim 2, characterized in that: the support wing part comprises a first short shaft which is rotatably connected with the horizontal sleeve, one end of the first short shaft, which is far away from the horizontal sleeve, is fixedly connected with a short wing, one end of the short wing, which is far away from the horizontal sleeve, is hinged with a long wing through a folding hinge, one end of the long wing, which is far away from the short wing, is fixedly provided with a second short shaft, and the tail end of the second short shaft is fixedly connected with the side wall of the ducted air bag.

4. The collapsible fuselage adapted for a alien sounding helicopter according to claim 3, characterized in that: a pair of bearings is arranged in the horizontal sleeve, and the first short shaft is rotatably arranged in the horizontal sleeve through the bearings.

5. The collapsible fuselage adapted for a alien sounding helicopter according to claim 3, characterized in that: the first short shaft is sleeved with a thrust bearing, the thrust bearing is arranged at one end, far away from the central piece, of the horizontal sleeve, and a bearing cover plate is arranged on the outer side of the thrust bearing.

6. The collapsible fuselage adapted for a alien sounding helicopter according to claim 1, characterized in that: the ducted air bag is of an annular structure after being inflated and unfolded.

Technical Field

The invention relates to the technical field of extraterrestrial exploration helicopters, in particular to a foldable fuselage suitable for an extraterrestrial exploration helicopter.

Background

The helicopter has the capability of vertical flight, can fly in an environment of an extraterrestrial globe with unknown environment, and performs a detection task. However, the process from the earth to the planet needs to depend on a carrier rocket for transportation, so that the size of the planet helicopter needs to be reduced in the transportation process so as to be convenient to carry and transport; at present, the Mars helicopter in the United states, namely the intelligent aircraft, has the advantages that the flying is realized on the surface of the Mars, the coaxial double-rotor configuration is adopted to solve the problem of the reverse torque of the rotor, and the occupied space of the whole aircraft can be reduced by folding two pairs of rotors together; the coaxial helicopter that present machine intelligence number adopted, two upper and lower pairs of rotors counter-rotation balanced rotor reaction moment when producing lift through alternately overlapping in order to reduce occupation space, nevertheless paddle self can't realize folding, therefore paddle itself still occupies certain space.

Disclosure of Invention

The invention aims to provide a foldable fuselage suitable for a extraterrestrial exploration helicopter, which aims to solve the problems in the prior art and enable the fuselage and blades to be folded, so that the occupied space during transportation is reduced.

In order to achieve the purpose, the invention provides the following scheme:

the invention provides a foldable fuselage suitable for a extraterrestrial exploration helicopter, which comprises a central piece, wherein the upper end of the central piece is used for connecting an inflatable rotor system, the inflatable rotor system is only controlled to change the total distance, the whole helicopter flies up and down, and other task devices and undercarriage components can be connected below the central piece; the side wall of the central part is uniformly and circularly provided with four foldable supporting wing parts, the outer sides of the supporting wing parts are fixedly connected with ducted airbags capable of being inflated, the material of each ducted airbag is made of aluminum magnesium alloy which is thin enough, the shape of the ducted airbag is formed after the materials are inflated, and the ducted airbag is of a ducted structure with an inflatable shape and used for improving pneumatic efficiency and further improving effective load. The control mode of the traditional rotor wing is divided into two parts, the rotor wing only applies total distance control, and other control is realized by depending on the support wing part; the support wings can be folded, can compress the space of the machine body during transportation and can be unfolded after the outer planet falls.

Optionally, four horizontal sleeves are uniformly arranged on the side wall of the central part, the four horizontal sleeves are arranged in the same plane in a cross manner, and one end of each horizontal sleeve, which is far away from the central part, is opened.

Optionally, the support wing part includes a first short shaft rotationally connected to the horizontal sleeve, one end of the first short shaft, which is far away from the horizontal sleeve, is fixedly connected to a short wing, and a folding hinge is installed at an end of one end of the short wing, so as to connect the outer long wing, and the short wing is used as a control surface for controlling, and the short wing is controlled to further control the long wing, so as to realize control; one end of the short wing, which is far away from the horizontal sleeve, is hinged with a long wing through a folding hinge, and the aerodynamic force on the short wing of each group of long wings is changed through the change of the total distance, so that the whole aircraft is operated; and a second short shaft is fixedly arranged at one end of the long wing, which is far away from the short wing, and the tail end of the second short shaft is fixedly connected with the side wall of the ducted air bag.

Optionally, a pair of bearings is arranged in the horizontal sleeve, and is used for bearing bending moment and realizing rotation of the short shaft relative to the central piece; the first short shaft is rotatably arranged in the horizontal sleeve through the bearing, the bearing is a radial bearing, and the horizontal sleeve is sleeved on the first short shaft and used for separating a pair of radial bearings.

Optionally, a thrust bearing is sleeved on the first short shaft, the thrust bearing is arranged at one end, far away from the central component, of the horizontal sleeve, and a bearing cover plate is arranged on the outer side of the thrust bearing; the thrust bearing is used for providing axial force to ensure the connection assembly of the supporting wing parts.

Optionally, the ducted airbag is of a ring structure after being inflated and deployed.

The inflatable rotor wing system comprises inflatable blades, wherein before inflation, the rotor wing can be fully folded, and then inflated and unfolded after reaching a target position, so that the folding of the rotor wing part is realized. The inflatable duct is utilized to generate additional lift force, the aerodynamic performance of the rotor wing can be further exerted, the effect of the duct is combined, the helicopter can generate enough aerodynamic force to realize flight under the extraterrestrial environment, and after the air bag of the duct is inflated, the control surface of the support wing part is unfolded. On the one hand the aerodynamic performance is improved and on the other hand the inflated configuration reduces the weight of the structure, so that there is sufficient weight margin for carrying the detection device. In order to balance the counter torque generated by the rotor wing, the supporting wing parts of the supporting duct adopt airfoil profile design, the angle is controllable, the framework generates two groups of couple counter torque for balancing the rotor wing, the four control surfaces of the supporting wing parts are controlled, and the flight control of the whole aircraft can be realized.

Compared with the prior art, the invention has the following technical effects:

the invention adopts the inflatable rotor wing and the inflatable duct, and can greatly compress the space in the carrying process. Compared with the conventional rotor wing and the duct, the rotor wing and the duct adopting the inflatable type have lighter weight and higher effective load under the same lifting force condition. The wingtip part of the conventional rotor has differential pressure resistance and the interference of the tip vortex of the rotor, the efficiency is reduced to some extent, the pneumatic efficiency of the rotor tip position can be improved by adopting the duct design, and in addition, the duct can also provide partial additional lift force, so that the pneumatic efficiency of the whole aircraft is higher.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings without creative efforts.

FIG. 1 is a schematic illustration of a partially folded state of a support wing of a foldable fuselage of a alien sounding helicopter according to the present invention;

FIG. 2 is a schematic view of the foldable fuselage of the alien sounding helicopter of the present invention in an unfolded state;

FIG. 3 is a front view of a support wing portion of the present invention;

wherein 100 is a foldable fuselage suitable for the extraterrestrial exploration helicopter, 1 is a central piece, 2 is a central shaft, 3 is a ducted airbag, 4 is a horizontal sleeve, 5 is a first short shaft, 6 is a short wing, 7 is a folding hinge, 8 is a long wing, 9 is a second short shaft, 10 is a bearing, 11 is a thrust bearing, and 12 is a bearing cover plate.

Detailed Description

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

The invention aims to provide a foldable fuselage suitable for a extraterrestrial exploration helicopter, which aims to solve the problems in the prior art and enable the fuselage and blades to be folded, so that the occupied space during transportation is reduced.

In order to make the aforementioned objects, features and advantages of the present invention comprehensible, embodiments accompanied with figures are described in further detail below.

Referring to fig. 1 to 3, the present invention provides a foldable airframe 100 suitable for a extraterrestrial exploration helicopter, including a central member 1, wherein the upper end of the central member 1 is used for connecting an inflatable rotor system through a central shaft 2, the expanded appearance structure of the inflatable rotor system is the same as that of a conventional rotor structure, not shown in the figure, the operation of the inflatable rotor system only changes in total distance, so as to realize the up-and-down flight of the whole helicopter, and other mission devices and landing gear components can be connected below the central member 1; the side wall of the central part 1 is uniformly and circularly provided with four foldable supporting wing parts, the outer sides of the supporting wing parts are fixedly connected with ducted airbags 3 capable of being inflated, the ducted airbags 3 are of an annular structure after being inflated and unfolded, aluminum magnesium alloy which is thin enough is selected as the material of the ducted airbags 3, the ducted airbags form the shape of the ducted shape after being inflated, and the ducted airbags 3 are of a ducted structure with an inflatable shape and used for improving pneumatic efficiency and further improving effective load. The control mode of the traditional rotor wing is divided into two parts, the rotor wing only applies total distance control, and other control is realized by depending on the support wing part; the support wing parts can be folded, can compress the space of the machine body during transportation and can be unfolded after the outer planet falls.

Specifically, four horizontal sleeves 4 are uniformly arranged on the side wall of the central part 1, the four horizontal sleeves 4 are arranged in the same plane in a cross manner, and one end of each horizontal sleeve 4, which is far away from the central part 1, is opened. The support wing part comprises a first short shaft 5 which is rotationally connected with the horizontal sleeve 4, one end of the first short shaft 5, which is far away from the horizontal sleeve 4, is fixedly connected with a short wing 6, the end part of one end of the short wing 6 is provided with a folding hinge 7 so as to be connected with the outer long wing 8, the short wing 6 is used as a control surface for operation, and the short wing 6 is operated to further control the long wing 8 so as to realize operation; one end of the short wing 6, which is far away from the horizontal sleeve 4, is hinged with a long wing 8 through a folding hinge 7, and aerodynamic force on each group of the long wing 8 and the short wing 6 is changed through total distance change, so that the whole aircraft is operated; one end of the long wing 8 far away from the short wing 6 is fixedly provided with a second short shaft 9, and the tail end of the second short shaft 9 is fixedly connected with the side wall of the ducted air bag 3.

A pair of bearings 10 is arranged in the horizontal sleeve 4, is used for bearing bending moment and can realize the rotation of the first short shaft 5 relative to the central piece 1; the first short shaft 5 is rotatably arranged in the horizontal sleeve 4 through a bearing 10, the bearing 10 adopts a radial bearing, and the horizontal sleeve 4 is sleeved on the first short shaft 5 and used for separating a pair of radial bearings. A thrust bearing 11 is sleeved on the first short shaft 5, the thrust bearing 11 is arranged at one end, away from the central component 1, of the horizontal sleeve 4, and a bearing cover plate 12 is arranged on the outer side of the thrust bearing 11 and used for protecting the thrust bearing 11; the thrust bearing 11 is used to provide axial force to secure the attachment assembly of the buttress wing components.

In a folded state, the ducted air bag 3 is in an uninflated state, the support wing parts for supporting the ducted air bag are also in a folded state, and the blades and the like of the inflatable rotor wing system are also in an uninflated state, so that the volume is reduced; in the unfolding state, the ducted air bags 3 are inflated, the supporting wing parts are unfolded by combining the auxiliary mechanism, and the inflatable rotor wing system is installed on the central part 1 through the middle shaft and unfolded in an inflating mode. And the outer ducted air bags 3 are combined to generate additional lifting force so as to improve the pneumatic efficiency of the rotor wing. The inboard support wing components are manipulated by the application to balance the reactive torque of the rotor. The angles of the four supporting wing parts are adjusted to enable each supporting wing part to generate different forces, and therefore control over flight is achieved. Further preferably, a link mechanism may be installed between the short wing 6 and the folding hinge 7 to increase rigidity and maintain the unfolded shape.

In another embodiment, the primary premise of using a helicopter to fly on the outer planet is to have a gaseous medium, such as a spark, and to have an atmospheric environment, but the ground environment is unknown and does not have the conditions for using a fixed wing aircraft, so that the helicopter is a very good detection aircraft configuration. In order to solve the problem of counter-torque of a helicopter rotor, a tail rotor is usually adopted to provide a lateral force to realize balance. If a bypass type configuration is adopted, the local annular air supply power can be changed on the outer surface of the bypass in a lateral air injection mode to realize the balance of the reactive torque. Or the rotor wing is driven by a blade tip air injection mode, so that no reaction torque is generated. However, these methods involve a high energy consumption, which results in a shortening of the detection radius of the aircraft. If a coaxial rotor wing structure like an aircraft intelligence number is adopted, the reaction torque balance can be realized, the course is controllable, and if the rotor wing is further folded, the whole aircraft carrying space can be compressed due to the small fuselage.

In the description of the present invention, it should be noted that the terms "center", "top", "bottom", "left", "right", "vertical", "horizontal", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience of description and simplicity of description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed in a particular orientation, and be operated, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first" and "second" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.

The principle and the implementation mode of the invention are explained by applying a specific example, and the description of the embodiment is only used for helping to understand the method and the core idea of the invention; meanwhile, for a person skilled in the art, according to the idea of the present invention, the specific embodiments and the application range may be changed. In view of the above, the present disclosure should not be construed as limiting the invention.