Folding and unfolding mechanism and sectional cabin of small variant aircraft

Abstract

The invention discloses a small variant aircraft folding and unfolding mechanism and a sectional type cabin in the technical field of small variant aircrafts, the sectional type cabin comprises a nose, a fixed wing cabin section, a battery electric control cabin section, a tail, a nose connecting section and a tail connecting section, and a rotor motor is fixedly installed in the nose; the folding and unfolding mechanism is fixedly installed in the fixed wing cabin section, the battery and the electric control system are fixedly installed in the battery electric control cabin, the empennage and the landing supporting mechanism are fixedly installed on the tail, the nose and the fixed wing cabin section are fixedly connected through the nose connecting section, and the tail and the battery electric control cabin section are fixedly connected through the tail connecting section. The battery is electrically connected with the rotor motors and the folding and unfolding mechanism through the electric control system, and the fixed wings are fixedly installed on the folding and unfolding mechanism. The folding and unfolding mechanism is compact in structure, high in space utilization rate and suitable for small variant aircrafts.

Description

Technical Field

[0001] The present invention relates to the technical field of small variable aircraft, and particularly to a folding and unfolding mechanism and a segmented cabin of a small variable aircraft. Background Technique

[0002] With the complication of flight missions of military and civilian aircraft, being able to fly across airspaces and wide speed ranges, having multi-mission adaptability and versatility, and achieving "one aircraft with multiple functions" has gradually become a new requirement for aircraft design. The performance space of aircraft with a fixed external layout is limited. Variable aircraft that can adaptively change their external shapes according to mission requirements and flight environments to achieve the best flight performance have become one of the important directions for the development of future aircraft, and have shown broad application prospects in military and civilian fields;

[0003] As a key aerodynamic component, the variable forms of wings have received the most extensive attention. For fixed-wing aircraft, the present invention designs a folding and unfolding mechanism for a small variable aircraft to achieve its folding and unfolding actions, making the folding and unfolding mechanism structure compact, solving the problem of space utilization rate, being suitable for use in small variable aircraft, and at the same time ensuring symmetrical folding and unfolding of both wings. Summary of the Invention

[0004] The purpose of the present invention is to provide a folding and unfolding mechanism and a segmented cabin of a small variable aircraft to solve the problems raised in the above background technique.

[0005] To achieve the above purpose, the present invention provides the following technical solution: A folding and unfolding mechanism and a segmented cabin of a small variable aircraft. The segmented cabin includes a nose, a fixed-wing cabin section, a battery and electronic control cabin section, a tail, as well as a nose connection section and a tail connection section. The rotor motor is fixedly installed in the nose, the folding and unfolding mechanism is fixedly installed in the fixed-wing cabin section, the battery and the electronic control system are fixedly installed in the battery and electronic control cabin, the tail wing and the landing support mechanism are fixedly installed on the tail. The nose and the fixed-wing cabin section are fixedly connected through the nose connection section, and the tail and the battery and electronic control cabin section are fixedly connected through the tail connection section. The battery is electrically connected to the rotor motor and the folding and unfolding mechanism through the electronic control system, and the fixed wing is fixedly installed on the folding and unfolding mechanism.

[0006] Furthermore, the folding and unfolding mechanism includes a control motor, a main transmission shaft, a main transmission gear, a reversing transmission shaft, a reversing transmission gear, a lever transmission shaft, a lever transmission gear, a folding and unfolding connecting rod, and a fixed support bearing. The control motor is fixedly installed inside the fixed wing cabin section. One end of the main transmission shaft is fixedly installed on the output shaft of the control motor through a flange, and the other end is slidably installed inside the fixed wing cabin section. A main transmission gear is fixedly installed on the main transmission shaft. One end of the reversing transmission shaft is fixedly installed inside the fixed wing cabin section, and a reversing transmission gear is slidably installed on the reversing transmission shaft. The lever transmission shaft is slidably installed inside the fixed wing cabin section through the fixed support bearing. A lever transmission gear is fixedly installed on the lever transmission shaft, and forks are respectively fixedly installed at both ends of the lever transmission shaft.

[0007] Furthermore, there are two lever transmission shafts, which are respectively installed on the left and right sides of the control motor. The main transmission gear meshes with the reversing transmission gear and one of the lever transmission gears respectively, and the other lever transmission gear meshes with the reversing transmission gear.

[0008] Furthermore, one end of the folding and unfolding connecting rod is provided with a fixed seat for connecting the fixed wing, and the other end is provided with a sliding groove.

[0009] Furthermore, there are two rotating shafts, which are respectively installed on the sides of the two lever transmission shafts away from the control motor. Both ends of the rotating shafts respectively pass through the middle of the folding and unfolding connecting rod and then are slidably installed inside the fixed wing cabin section. The sliding groove is installed in cooperation with the fork, and the fork can slide inside the sliding groove.

[0010] Furthermore, the fork adopts a Z-shaped structure. One end of it is fixedly connected to the lever transmission shaft, and a pulley is slidably installed at the other end. The pulley is slidably installed inside the sliding groove.

[0011] Furthermore, the main transmission gear, the reversing transmission gear, and the lever transmission gear have the same model.

[0012] Furthermore, after the two lever transmission shafts are installed, the axial directions of the forks on the two lever transmission shafts have different angles with respect to the same reference line. The angle on the side meshing with the main transmission gear is α, and the angle on the side meshing with the reversing transmission gear is β.

[0013] Furthermore, the two lever transmission shafts and the rotating shafts are horizontally arranged with respect to the interior of the cabin. The included angle between the axis connection line of the reversing transmission shaft and the meshing lever transmission shaft and the axis connection line of the two lever transmission shafts is θ. α and β should satisfy the following formula:

[0014]

[0015] In the formula: mod (the first parameter, the second parameter) represents the remainder of the first parameter divided by the second parameter; π is the circumference ratio; Z is the number of teeth of the gear; N is a non-negative integer; θ can be calculated according to the cosine theorem.

[0016] Compared with the prior art, the beneficial effects of the present invention are as follows: The folding and unfolding mechanism of the present invention has a compact structure and high space utilization rate, and is suitable for small variable aircraft. By accurately calculating the structural parameters of the folding and unfolding drive shaft, the symmetrical folding and unfolding of the two wings is ensured. The use of pulleys and chutes enables the folding and unfolding mechanism to be located at the mechanical dead point position when the variable aircraft is in the unfolded or folded state, which is beneficial to preventing the wing load from being reversely transmitted to the control motor, thereby reducing the rated power and control difficulty of the control motor.

[0017] The segmented design method of the cabin of the present invention, on the one hand, makes it convenient to adjust the length dimension of the cabin, and on the other hand, facilitates the disassembly, debugging and maintenance of each part of the cabin. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the following will briefly introduce the drawings required for the description of the embodiments. Obviously, the drawings in the following description are only some embodiments of the present invention. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without creative efforts.

[0019] Figure 1 It is a schematic diagram of the segmented cabin of the present invention;

[0020] Figure 2 It is a schematic diagram of the folding and unfolding mechanism of the present invention;

[0021] Figure 3 It is a schematic diagram of the transmission gear of the present invention;

[0022] Figure 4 It is a schematic diagram of the axis position of the transmission gear of the present invention;

[0023] Figure 5 It is a schematic diagram of the folding and unfolding drive shaft of the present invention;

[0024] Figure 6 It is a schematic diagram of the horizontal folding and unfolding link of the present invention;

[0025] Figure 7 It is a schematic diagram of the vertical folding and unfolding link of the present invention;

[0026] Figure 8 It is a working flow chart of the folding and unfolding mechanism of the present invention.

[0027] In the drawings, the list of components represented by each reference numeral is as follows:

[0028] 1-Head, 2-Fixed wing cabin section, 3-Battery and electronic control cabin section, 4-Tail, 5-Head connection section, 6-Tail connection section, 7-Control motor, 8-Flange, 9-Main drive shaft, 10-Main drive gear, 11-Reversing drive shaft, 12-Reversing drive gear, 13-Shifting lever drive shaft, 14-Shifting lever drive gear, 15-Fork, 16-Folding link, 17-Pulley. Specific implementation mode

[0029] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative work belong to the protection scope of the present invention.

[0030] Please refer to Figure 1 , the present invention provides a technical solution: a folding mechanism and a segmented cabin for a small variable aircraft. The segmented cabin includes a head 1, a fixed wing cabin section 2, a battery and electronic control cabin section 3, a tail 4, as well as a head connection section 5 and a tail connection section 6. The rotor motor is fixedly installed in the head 1, the folding mechanism is fixedly installed in the fixed wing cabin section 2, the battery and the electronic control system are fixedly installed in the battery and electronic control cabin 3, the tail wing and the landing support mechanism are fixedly installed on the tail 4. The head 1 and the fixed wing cabin section 2 are fixedly connected through the head connection section 5, and the tail 4 and the battery and electronic control cabin section 3 are fixedly connected through the tail connection section 6. The battery is electrically connected to the rotor motor and the folding mechanism through the electronic control system, and the fixed wing is fixedly installed on the folding mechanism.

[0031] Please refer to Figure 2 , the folding mechanism includes a control motor 7, a main drive shaft 9, a main drive gear 10, a reversing drive shaft 11, a reversing drive gear 12, a shifting lever drive shaft 13, a shifting lever drive gear 14, a folding link 16, and a fixed support bearing. The control motor 1 is fixedly installed in the fixed wing cabin section 2; one end of the main drive shaft 9 is fixedly installed on the output shaft of the control motor 1 through a flange 8, and the other end is slidably installed inside the fixed wing cabin section 2. A main drive gear 10 is fixedly installed on the main drive shaft 9; one end of the reversing drive shaft 11 is fixedly installed inside the fixed wing cabin section 2, and a reversing drive gear 12 is slidably installed on the reversing drive shaft 11; the shifting lever drive shaft 13 is slidably installed in the fixed wing cabin section 2 through a fixed support bearing, a shifting lever drive gear 14 is fixedly installed on the shifting lever drive shaft 13, and forks 15 are fixedly installed at both ends of the shifting lever drive shaft 13.

[0032] There are two shifting lever drive shafts 13, which are respectively installed on the left and right sides of the control motor 7. The main drive gear 10 meshes with the reversing drive gear 12 and one shifting lever drive gear 14 respectively, and the other shifting lever drive gear meshes with the reversing drive gear.

[0033] One end of the folding link 16 is provided with a fixed seat for connecting the fixed wing, and the other end is provided with a sliding groove.

[0034] There are two rotating shafts, which are respectively installed on the side of the two shift lever transmission shafts 13 away from the control motor 7. Both ends of the rotating shafts pass through the middle of the folding link 16 and are slidably installed in the fixed wing cabin section 2. The sliding groove is cooperatively installed with the shift fork 15, and the shift fork 15 can slide in the sliding groove.

[0035] The shift fork 15 adopts a Z-shaped structure. One end of it is fixedly connected to the shift lever transmission shaft 13, and a pulley 17 is slidably installed at the other end. The pulley 17 is slidably installed in the sliding groove.

[0036] The main transmission gear 10, the reversing transmission gear 12, and the shift lever transmission gear 14 have the same model.

[0037] The four folding links 16 of the folding mechanism are divided into two groups. Two on the left side of the cabin are in one group, and two on the right side are in one group. The angles of the folding links 16 in the same group along the rotating shaft are the same, and the angles of the folding links in different groups along the rotating shaft are symmetric about the vertical longitudinal cutting symmetry plane of the cabin.

[0038] As Figure 3 shown, the main transmission gear 10, the reversing transmission gear 12, and the two shift lever transmission gears 14 are exactly the same, including parameters such as modulus, number of teeth, and orientation of the set screw holes.

[0039] Embodiment 2

[0040] After the two shift lever transmission shafts 13 are installed, the axial directions of the shift forks on the two shift lever transmission shafts have different angles relative to the same reference line. The angle on the side engaged with the main transmission gear is α, and the angle on the side engaged with the reversing transmission gear is β.

[0041] The two shift lever transmission shafts 13 and the rotating shafts are horizontally arranged relative to the interior of the cabin. The included angle between the axis connection line of the reversing transmission shaft and the engaged shift lever transmission shaft and the axis connection line of the two shift lever transmission shafts is θ.

[0042] As Figure 4 shown, let the axial projections of the main transmission gear, the reversing transmission gear, and the two shift lever transmission gears be A, B, C, and D respectively. The line segment AB and the line segment CD intersect at O. The included angle between the line segment CD and the line segment BD is set as θ. The quadrilateral ACBD is a parallelogram, and the line segment CD is in the horizontal direction. The line segment AB is equal in length to the line segment AC or BD. Adjusting the length of the line segment CD can change the compactness of the folding mechanism in different directions.

[0043] α and β should satisfy the following formula:

[0044]

[0045] In the formula: mod (the first parameter, the second parameter) represents the remainder obtained by dividing the first parameter by the second parameter; π is the ratio of a circle's circumference to its diameter; Z is the number of teeth of the gear; N is a non - negative integer, which means that the value of (α - β) is not unique, and the angles corresponding to N teeth difference between different values do not affect the assembly effect of the structure; θ can be calculated according to the cosine theorem;

[0046] As Figure 6 shown, let the axial projections of the lever rotation axis, the pulley axis, and the folding and unfolding link rotation axis be C, F, and E respectively. The line segment CE is in the horizontal direction, and its length is times that of the line segment EF. When the lever is in the Figure 6 shown extreme position, the folding and unfolding link is in the horizontal direction. The rotation range of the lever is 135°. When the lever is in the other extreme position as Figure 7 shown, the folding and unfolding link is in the vertical direction.

[0047] The horizontal and vertical states of the folding and unfolding link respectively correspond to two forms of the variable - shape aircraft before and after deformation, namely the unfolded form and the folded form.

[0048] The folding and unfolding mechanism drives the fixed - wing to perform the folding and unfolding action, so that the small variable - shape aircraft can achieve deformation. Its transmission process is as Figure 8 shown. In the figure, the direction “front end” is close to the nose end of the aircraft, and the “rear end” is close to the tail end; the “right side” and “left side” are, when viewed from the nose direction of the aircraft, the right - hand side is the “right side” and the left - hand side is the “left side”. The subsequent “clockwise” and “counter - clockwise” also take the axis of rotation when viewed from the nose to the tail direction as the reference.

[0049] (1) Unfolding process

[0050] As Figure 8 shown, in the unfolding process, the control motor 7 rotates in the clockwise direction, drives the folding and unfolding link 16 to rotate through the transmission system, and the folding and unfolding link 16 drives the two - side wings to perform the unfolding action.

[0051] (2) Folding process

[0052] The folding process is the reverse process of the unfolding process. The control motor 7 rotates in the counter - clockwise direction, also drives the folding and unfolding link 16 to rotate in the opposite direction through the transmission system, and the folding and unfolding link 16 drives the two - side wings to perform the folding process.

[0053] In the description of this specification, the descriptions referring to the terms "one embodiment", "example", "specific example", etc. mean that the specific features, structures, materials or characteristics described in connection with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described may be combined in any one or more embodiments or examples in a suitable manner.

[0054] The preferred embodiments of the present invention disclosed above are only used to help illustrate the present invention. The preferred embodiments do not describe all the details in detail, nor do they limit the invention to the specific embodiments described. Obviously, many modifications and variations can be made according to the content of this specification. These embodiments are selected and specifically described in this specification in order to better explain the principles and practical applications of the present invention, so that those skilled in the art can understand and utilize the present invention well. The present invention is only limited by the claims and their full scope and equivalents.

Claims

1. A folding and unfolding mechanism and a segmented cabin of a small-sized variant aircraft, characterized in that: The segmented cabin includes a nose, a fixed-wing cabin section, a battery and electronic control cabin section, a tail, and a nose connecting section and a tail connecting section. The rotor motor is fixedly installed in the nose, the folding and unfolding mechanism is fixedly installed in the fixed-wing cabin section, the battery and the electronic control system are fixedly installed in the battery and electronic control cabin, the tail wing and the landing support mechanism are fixedly installed on the tail, the nose and the fixed-wing cabin section are fixedly connected through the nose connecting section, the tail and the battery and electronic control cabin section are fixedly connected through the tail connecting section, the battery is electrically connected to the rotor motor and the folding and unfolding mechanism through the electronic control system, and the fixed wing is fixedly installed on the folding and unfolding mechanism.

2. The folding and unfolding mechanism and segmented cabin of a small-sized variant aircraft according to claim 1, characterized in that: The folding and unfolding mechanism includes a control motor, a main transmission shaft, a main transmission gear, a reversing transmission shaft, a reversing transmission gear, a lever transmission shaft, a lever transmission gear, a folding and unfolding connecting rod, and a fixed support bearing. The control motor is fixedly installed in the fixed-wing compartment section; one end of the main transmission shaft is fixedly installed on the output shaft of the control motor through a flange, and the other end is slidably installed on the inner side of the fixed-wing compartment section, and the main transmission shaft is fixedly installed with a main transmission gear; one end of the reversing transmission shaft is fixedly installed on the inner side of the fixed-wing compartment section, and the reversing transmission gear is slidably installed on the reversing transmission shaft; the lever transmission shaft is slidably installed in the fixed-wing compartment section through a fixed support bearing, and the lever transmission shaft is fixedly installed with a lever transmission gear, and shift forks are fixedly installed at both ends of the lever transmission shaft.

3. The folding and unfolding mechanism and segmented cabin of a small-sized variant aircraft according to claim 2, characterized in that: There are two lever transmission shafts, which are respectively installed on the left and right sides of the control motor. The main transmission gear is engaged with the reversing transmission gear and one lever transmission gear, and the other lever transmission gear is engaged with the reversing transmission gear.

4. The folding and unfolding mechanism and segmented cabin of a small-sized variant aircraft according to claim 2, characterized in that: One end of the folding and unfolding connecting rod is provided with a fixing seat for connecting the fixed wing, and the other end is provided with a sliding groove.

5. A folding and unfolding mechanism and a segmented cabin of a small-sized variant aircraft according to claims 2-4, characterized in that: Two rotating shafts are provided and are respectively installed on the side of the two lever transmission shafts away from the control motor. The two ends of the rotating shaft pass through the middle of the folding connecting rod and are slidably installed in the fixed wing cabin section. The slide groove is installed in cooperation with the shift fork, and the shift fork can slide in the slide groove.

6. The folding and unfolding mechanism and segmented cabin of a small-sized variant aircraft according to claim 5, characterized in that: The shift fork adopts a Z-shaped structure, one end of which is fixedly connected to the shift rod transmission shaft, and the other end is slidably mounted with a pulley, which is slidably mounted in a slide groove.

7. The folding and unfolding mechanism and segmented cabin of a small-sized variant aircraft according to claim 5, characterized in that: The main drive gear, reversing drive gear and shift lever drive gear are of the same model.

8. The folding and unfolding mechanism and segmented cabin of a small-sized variant aircraft according to claim 1, characterized in that: After the two shift lever transmission shafts are installed, the axial directions of the shift forks on the two shift lever transmission shafts have different angles relative to the same reference line, the angle on the side engaging with the main transmission gear is α, and the angle on the side engaging with the reversing transmission gear is β.

9. The folding and unfolding mechanism and segmented cabin of a small-sized variant aircraft according to claim 8, characterized in that: The two lever transmission shafts and the rotating shaft are arranged horizontally relative to the interior of the cabin. The angle between the axis connecting the reversing transmission shaft and the meshing lever transmission shaft and the axis connecting the two lever transmission shafts is θ. α and β should satisfy the following formula: In the formula: mod(first parameter, second parameter) means the remainder of the first parameter to the second parameter; π is the circumference of a circle; Z is the number of teeth on the gear; N is a non-negative integer; θ can be calculated according to the law of cosines.

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