Transverse folding control surface and aircraft

Abstract

The utility model relates to the field of aircrafts, in particular to a transverse folding control surface. Comprising a rudder root, a rudder tip and a torsion spring. The bottom of the rudder tip is rotationally connected with the top of the rudder root. The side face of the rudder tip can rotate in the direction close to or away from the side face of the rudder root. The first end of the torsion spring is fixedly connected with the rudder root, and the second end is fixedly connected with the rudder tip. When the torsion spring is in an initial state, the first end and the second end are in the same plane. During use, the transverse folding control surface is assembled on the side face of the head of the aircraft, and when the aircraft is located in a launching cabin, the rudder tip rotates in the direction close to the side face of the rudder root, so that the top of the rudder tip abuts against the inner wall of the launching cabin. After the aircraft is launched, the rudder tip restores to be in the same plane with the rudder root under the acting force of the torsional spring. According to the utility model, the rudder surface with a larger size can be accommodated in the launching cabin by folding the rudder tip, so that the technical problem that the size of the rudder surface is limited by the size of the launching cabin in the prior art is solved.

Description

Technical Field

[0001] The utility model relates to the field of aircraft, in particular to a transverse folding rudder surface and an aircraft. Background Art

[0002] In order to improve the flight performance of canister-launched aircraft, rudders are often added to the side of the aircraft's head for guidance modification, and the aircraft's flight attitude is adjusted by controlling the direction of the rudders. However, canister-launched aircraft rely on the launch cabin to provide initial flight power, and the size of the rudders is restricted by the size of the launch cabin, resulting in larger rudders being unable to be used for aircraft modification. Utility Model Content

[0003] The utility model provides a probe drying device, which solves the technical problem in the prior art that the size of the rudder surface is restricted by the size of the launch cabin.

[0004] In order to solve the above technical problems, the technical solution adopted in this embodiment is as follows:

[0005] In an embodiment of the first aspect, the utility model provides a transverse folding rudder surface, comprising:

[0006] A rudder root, the bottom of which is equipped with a rudder shaft for connecting with the side wall of the aircraft;

[0007] A rudder tip, the bottom of which is rotatably connected to the top of the rudder root; the side of the rudder tip can be rotated toward or away from the side of the rudder root;

[0008] A torsion spring, wherein the first end is fixedly connected to the rudder root, and the second end is fixedly connected to the rudder tip; when the torsion spring is in an initial state, the first end and the second end are in the same plane.

[0009] In some embodiments, the top of the rudder root has a groove, the bottom of the groove is provided with a first protrusion, and the first protrusion has a first through hole; the bottom of the rudder tip is provided with a second protrusion, and the second protrusion has a second through hole; the transverse folding rudder surface also includes an axis, the first end of the axis is connected to the first side surface of the groove, and the second end of the axis is connected to the second side surface of the groove; the axis passes through the first through hole and the second through hole; the torsion spring is sleeved on the axis.

[0010] In some embodiments, a first limit block is provided at the top of the rudder root, and the first limit block is located at a first side of the rudder tip; when the torsion spring is in an initial state, the first limit block contacts the first side surface of the rudder tip.

[0011] In some embodiments, the torsion spring is a torsion-compression composite spring, which is located between the first protrusion and the second protrusion, and the coils at both ends of the torsion spring are respectively abutted against the first protrusion and the second protrusion; a second limit block is provided at the top of the rudder root; when the rudder tip and the rudder root are in different planes, the distance between the first protrusion and the second protrusion is a first length, and the end face of the rudder tip abuts against the second limit block; when the rudder tip and the rudder root are in the same plane, the distance between the first protrusion and the second protrusion increases to a second length, the second limit block is located on the second side of the rudder tip, and the second limit block contacts the second side face of the rudder tip.

[0012] In an embodiment of the second aspect, the utility model provides an aircraft, whose head has a conical structure, and whose head side is equipped with any of the above-mentioned transverse folding rudder surfaces; the distance between the top surface of the rudder root and the axis of the aircraft is less than the maximum cross-sectional radius of the aircraft; a rotary drive mechanism is installed in the aircraft, and the rotating end of the rotary drive mechanism is transmission-connected to the rudder shaft.

[0013] In some embodiments, a third through hole is formed in the side wall of the aircraft, a base is installed in the third through hole, and the base is transmission-connected to the rotating end of the rotary drive mechanism; the base has a hole that matches the shape and size of the rudder shaft; a mounting portion is provided between the bottom surface of the rudder root and the rudder shaft, the mounting portion has a fourth through hole, and the base has a threaded hole that matches the position and size of the fourth through hole.

[0014] In some embodiments, the cross-section of the rudder shaft is an oval shape.

[0015] Beneficial Effects

[0016] The utility model enables a larger rudder surface to be accommodated in a launch cabin by folding the rudder tip, thereby solving the technical problem in the prior art that the size of the rudder surface is restricted by the size of the launch cabin.

[0017] Additional aspects and advantages of the embodiments of the present invention will be given in part in the following description, and in part will become apparent from the following description, or will be understood through the practice of the embodiments of the present invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings required for use in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0019] The methods, systems and / or programs in the accompanying drawings will be further described according to exemplary embodiments. These exemplary embodiments will be described in detail with reference to the drawings. These exemplary embodiments are non-limiting exemplary embodiments, wherein example numbers represent similar mechanisms in the various views of the accompanying drawings.

[0020] Figure 1 It is a schematic structural diagram of the transverse folding rudder surface provided by an embodiment of the first aspect of the utility model.

[0021] Figure 2 It is a schematic structural diagram of an aircraft equipped with transverse folding control surfaces in a launch cabin provided by an embodiment of the first aspect of the utility model.

[0022] Figure 3 It is a structural schematic diagram of one side of the transverse folding rudder surface provided by the first aspect embodiment of the utility model when it is in an intermediate state between the folded state and the unfolded state.

[0023] Figure 4 It is a structural schematic diagram of the other side when the transversely folded rudder surface provided by the embodiment of the first aspect of the utility model is in an intermediate state.

[0024] Figure 5 It is a structural schematic diagram of one side of the transverse folding rudder surface provided by the first aspect embodiment of the utility model when it is in a folded state.

[0025] Figure 6 It is a structural schematic diagram of the other side of the transverse folding rudder surface provided by the embodiment of the first aspect of the utility model when it is in a folded state.

[0026] Figure 7 yes Figure 6 Schematic diagram of the local enlarged structure in.

[0027] Figure 8 It is a structural schematic diagram of an aircraft provided by an embodiment of the second aspect of the utility model.

[0028] Description of reference numerals:

[0029] 001-Launch cabin;

[0030] 100- transverse folding rudder;

[0031] 110-rudder root; 111-rudder shaft; 112-groove; 113-first protrusion; 114-first limit block; 115-mounting portion; 116-fourth through hole; 117-second limit block; 1171-first side surface of the second limit block; 1172-second side surface of the second limit block;

[0032] 120 - rudder tip; 121 - second protruding portion;

[0033] 130-torsion spring;

[0034] 140-axis;

[0035] 200 - aircraft; 210 - third through hole. DETAILED DESCRIPTION

[0036] In order to make the purpose, technical scheme and advantages of the embodiment of the utility model clearer, the technical scheme in the embodiment of the utility model will be clearly and completely described below in conjunction with the drawings in the embodiment of the utility model. Obviously, the described embodiment is a part of the embodiment of the utility model, rather than all the embodiments. The components of the embodiment of the utility model generally described and shown in the drawings here can be arranged and designed in various different configurations. Therefore, the following detailed description of the embodiment of the utility model provided in the drawings is not intended to limit the scope of the utility model for protection, but merely represents the selected embodiment of the utility model. Based on the embodiments in the utility model, all other embodiments obtained by ordinary technicians in this field without making creative work belong to the scope of protection of the utility model.

[0037] It should be noted that similar reference numerals and letters denote similar items in the following drawings, and therefore, once an item is defined in one drawing, further definition and explanation thereof is not required in subsequent drawings.

[0038] In the description of the present utility model, it should be noted that the terms "first", "second", "third", etc. are only used to distinguish the description and cannot be understood as indicating or implying relative importance.

[0039] In the description of the present invention, it is also necessary to explain that, unless otherwise clearly specified and limited, the term "connection" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a direct connection, or an indirect connection through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0040] See also Figure 1 In an embodiment of the first aspect, the utility model provides a transverse folding rudder surface 100, including a rudder root 110, a rudder tip 120 and a torsion spring 130. The bottom of the rudder root 110 is equipped with a rudder shaft 111 for connecting to the side wall of the aircraft. The bottom of the rudder tip 120 is rotatably connected to the top of the rudder root 110. The side of the rudder tip 120 can rotate in a direction close to or away from the side of the rudder root 110. The first end of the torsion spring 130 is fixedly connected to the rudder root 110, and the second end is fixedly connected to the rudder tip 120. When the torsion spring 130 is in an initial state, its first end and the second end are in the same plane. Please refer to Figure 2When in use, the folded rudder surface 100 is mounted on the side of the head of the aircraft. When the aircraft is in the launch cabin 001, the rudder tip 120 is rotated toward the side close to the rudder root 110. At this time, the torsion spring 130 applies a force opposite to the rotation direction of the rudder tip 120 to the rudder tip 120 and the rudder root 110, so that the top of the rudder tip 120 abuts against the inner wall of the launch cabin 001. After the aircraft is launched, the rudder tip 120 is restored to the state of being in the same plane as the rudder root 110 under the force of the torsion spring 130. The utility model allows a larger rudder surface to be accommodated in the launch cabin 001 by folding the rudder tip 120, thereby solving the technical problem in the prior art that the size of the rudder surface is restricted by the size of the launch cabin 001.

[0041] See also Figure 1 In some embodiments, the top of the rudder root 110 has a groove 112, the bottom of the groove 112 is provided with a first protrusion 113, and the first protrusion 113 is provided with a first through hole. The bottom of the rudder tip 120 is provided with a second protrusion 121, and the second protrusion 121 is provided with a second through hole. The transverse folding rudder surface 100 also includes a shaft 140, the first end of the shaft 140 is connected to the first side of the groove 112, and the second end of the shaft 140 is connected to the second side of the groove 112. The shaft 140 passes through the first through hole and the second through hole, and the torsion spring 130 is sleeved on the shaft 140. When in use, an external force is applied to one side of the rudder tip 120, and the rudder tip 120 rotates around the shaft 140 toward the side of the rudder root 110, and the torsion spring 130 applies a force opposite to the rotation direction of the rudder tip 120 to the rudder tip 120 and the rudder root 110.

[0042] See also Figure 3 and Figure 4 In some embodiments, a first stopper 114 is disposed on the top of the rudder root 110, and the first stopper 114 is located on the first side of the rudder tip 120. When the torsion spring 130 is in the initial state, the first stopper 114 contacts the first side surface of the rudder tip 120. When in use, the first stopper 114 can limit the rudder tip 120 from rotating toward the first side surface, thereby preventing the rudder tip 120 from rotating due to the pressure of air on the rudder tip 120 during high-speed flight, thereby affecting the flight state of the aircraft.

[0043] See also Figures 3 to 7In some embodiments, the torsion spring 130 is a torsion-compression composite spring (i.e., a torsion spring with a gap between coils), which is located between the first protrusion 113 and the second protrusion 121, and the coils at both ends thereof abut against the first protrusion 113 and the second protrusion 121, respectively. A second stopper 117 is provided at the top of the rudder root 110. When the rudder tip 120 and the rudder root 110 are in different planes, the distance between the first protrusion 113 and the second protrusion 121 is a first length, and the end face of the rudder tip 120 abuts against the first side face 1171 of the second stopper. When the rudder tip 120 and the rudder root 110 are in the same plane, the distance between the first protrusion 113 and the second protrusion 121 increases to a second length, the second stopper 117 is located at the second side of the rudder tip 120, and the second side face 1172 of the second stopper contacts with the second side face of the rudder tip 120. When in use, when the rudder tip 120 and the rudder root 110 are in different planes, the transverse folding rudder surface 100 is in a folded state, and the end surface of the rudder tip 120 abuts against the first side surface 1171 of the second limiting block, so that the first protrusion 113 and the second protrusion 121 compress the compression spring; when the transverse folding rudder surface 100 is in an unfolded state, the rudder tip 120 and the rudder root 110 are in the same plane, at this time, the end surface of the rudder tip 120 is staggered from the second limiting block 117, and the end surface of the rudder tip 120 loses the restriction of the second limiting block 117, so that the distance between the first protrusion 113 and the second protrusion 121 increases from the first length to the second length (first from the first length to the second length) due to the pressure of the compression spring. Figure 5 The status becomes Figure 3 status, and then from Figure 3 The status becomes Figure 1 The second stopper 117 is used to prevent the rudder tip 120 from rotating toward its second side surface, thereby preventing the rudder tip 120 from rotating due to the pressure of air on the rudder tip 120 during high-speed flight, thereby affecting the flight state of the aircraft.

[0044] See also Figure 8In the embodiment of the second aspect, the utility model provides an aircraft 200, whose head has a conical structure, and whose side is equipped with a transverse folding rudder surface 100, which can be the transverse folding rudder surface 100 provided in the embodiment of the first aspect. The distance between the top surface of the rudder root 110 of the transverse folding rudder surface 100 and the axis of the aircraft 200 is less than the maximum cross-sectional radius of the aircraft 200. A rotary drive mechanism is installed in the aircraft 200, and the rotating section of the rotary drive mechanism is connected to the rudder shaft 111 in a transmission manner. When in use, the rudder tip 120 is rotated in the direction close to the side of the rudder root 110, and at this time, the torsion spring 130 applies a force opposite to the rotation direction of the rudder tip 120 to the rudder tip 120 and the rudder root 110, so that the top of the rudder tip 120 abuts against the inner wall of the launch cabin 001. The technical problem that the guided transformation of the aircraft 200 in the prior art is restricted by the size of the launch cabin is solved.

[0045] In some embodiments, the side wall of the aircraft 200 is provided with a third through hole 210, in which a base is installed, and the base is in transmission connection with the rotating end of the rotary drive mechanism, so that the base can rotate in the third through hole 210 along the axis of the third through hole 210. The base is provided with a hole that matches the shape and size of the rudder shaft 111. A mounting portion 115 is provided between the bottom surface of the rudder root 110 and the rudder shaft 111, and the mounting portion 115 is provided with a fourth through hole 116, and the base is provided with a threaded hole that matches the position and size of the fourth through hole 116. When in use, the operator can use a screw to pass through the fourth through hole 116 and screw it into the threaded hole to install the transverse folding rudder surface 100 on the side of the head of the aircraft 200. When disassembling, the disassembly operation can be completed by only screwing out the screw, so that the aircraft 200 can quickly return to its original aerodynamic shape.

[0046] Furthermore, the cross-section of the rudder shaft 111 is an oval shape. When in use, after the rudder shaft 111 is inserted into the hole, there is no need to repeatedly adjust the position of the rudder root 110 and the side of the head of the aircraft 200 to align the fourth through hole 116 with the threaded hole, thereby improving the efficiency of the installation operation.

[0047] It should be noted that the cross-sectional shape of the rudder shaft 111 can also be square, polygonal, elliptical or other irregular shapes to achieve the purpose of improving the efficiency of the installation operation. From the perspective of ease of production, it is preferred to use an oval rudder shaft 111.

[0048] Although the embodiments of the present invention have been shown and described above, it can be understood that the above embodiments are illustrative and cannot be understood as limitations on the present invention. Ordinary technicians in this field can change, modify, replace and modify the above embodiments within the scope of the present invention. The scope of the present invention is defined by the claims and their equivalents.

Claims

1. A transverse folding rudder surface (100), characterized in that: include: A rudder root (110), the bottom of which is equipped with a rudder shaft (111) for connecting to the side wall of the aircraft; A rudder tip (120), the bottom of which is rotatably connected to the top of the rudder root (110); the side of the rudder tip (120) can rotate in a direction close to or away from the side of the rudder root (110); A torsion spring (130) has a first end fixedly connected to the rudder root (110) and a second end fixedly connected to the rudder tip (120); when the torsion spring (130) is in an initial state, the first end and the second end are in the same plane.

2. The lateral folding rudder surface (100) according to claim 1, characterized in that: The top of the rudder root (110) is provided with a groove (112), the bottom of the groove (112) is provided with a first protrusion (113), and the first protrusion (113) is provided with a first through hole; the bottom of the rudder tip (120) is provided with a second protrusion (121), and the second protrusion (121) is provided with a second through hole; the transverse folding rudder surface (100) also includes a shaft (140), the first end of the shaft (140) is connected to the first side surface of the groove (112), and the second end of the shaft (140) is connected to the second side surface of the groove (112); the shaft (140) passes through the first through hole and the second through hole; the torsion spring (130) is sleeved on the shaft (140).

3. The lateral folding rudder surface (100) according to claim 2, characterized in that: A first limit block (114) is provided at the top of the rudder root (110), and the first limit block (114) is located on a first side of the rudder tip (120); when the torsion spring (130) is in an initial state, the first limit block (114) contacts a first side surface of the rudder tip (120).

4. The lateral folding rudder surface (100) according to claim 3, characterized in that: The torsion spring (130) is a torsion-compression composite spring, and is located between the first protrusion (113) and the second protrusion (121), and the coils at both ends thereof are respectively in contact with the first protrusion (113) and the second protrusion (121); a second limit block (117) is provided at the top of the rudder root (110); when the rudder tip (120) and the rudder root (110) are in different planes, the first protrusion (113) and the second protrusion (121) are in contact with each other. 1) is a first length, and the end surface of the rudder tip (120) abuts against the second limit block (117); when the rudder tip (120) and the rudder root (110) are in the same plane, the distance between the first protrusion (113) and the second protrusion (121) increases to a second length, the second limit block (117) is located on the second side of the rudder tip (120), and the second limit block (117) contacts the second side surface of the rudder tip (120).

5. An aircraft (200) having a conical head, characterized in that: The side surface of the head is equipped with a transverse folding rudder surface (100) as described in any one of claims 1 to 4; the distance between the top surface of the rudder root (110) and the axis of the aircraft (200) is less than the maximum cross-sectional radius of the aircraft (200); the aircraft (200) is equipped with a rotary drive mechanism, and the rotating end of the rotary drive mechanism is transmission-connected to the rudder shaft (111).

6. The aircraft (200) according to claim 5, characterized in that A third through hole (210) is formed on the side wall of the aircraft (200), a base is mounted in the third through hole (210), and the base is drivingly connected to the rotating end of the rotating drive mechanism; a hole is formed on the base, the shape and size of which match those of the rudder shaft (111); a mounting portion (115) is provided between the bottom surface of the rudder root (110) and the rudder shaft (111), the mounting portion (115) has a fourth through hole (116), and the base has a threaded hole that matches the position and size of the fourth through hole (116).

7. The aircraft (200) according to claim 6, characterized in that The cross section of the rudder shaft (111) is oval.

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