Small missile-borne antenna unfolding mechanism based on torsion spring driving

Abstract

The invention belongs to the technical field of missile mechanical structures, and particularly relates to a small missile-borne antenna unfolding mechanism based on torsion spring driving, which comprises an antenna mechanism base, an antenna mounting seat, an antenna torsion spring, a first antenna rotating shaft, a second antenna rotating shaft, an antenna locking spring, an antenna locking pin and a plug, the L-shaped extending end of the antenna mounting seat is in contact with the interior of the launching box / launching cylinder, so that the antenna mechanism is kept in a folded state; when the missile is launched out of the cylinder, the internal constraint of the antenna mounting seat and the launching box / launching cylinder is relieved, the antenna mounting seat and the launching box / launching cylinder start to rotate around the first antenna rotating shaft and the second antenna rotating shaft under the action of the antenna torsion spring, and when the antenna mounting seat and the launching cylinder rotate to the unfolding position, the antenna locking pin is locked into the conical hole of the antenna mounting seat under the pushing of the antenna locking spring, and the antenna mechanism is unfolded and locked. According to the antenna mechanism, the torsional spring is used as driving force, automatic unfolding and locking of the missile-borne antenna are achieved, the structure is simple, installation is easy and convenient, and unfolding reliability is high.

Description

Technical Field

[0001] The present invention belongs to the technical field of missile mechanical structures, and in particular relates to a small missile-borne antenna deployment mechanism driven by a torsion spring. Background Art

[0002] As part of the missile structure, the missile-borne antenna primarily facilitates networking and communication between missile-borne terminals and between missile payloads. To maximize its performance, the requirements for its structure are becoming increasingly stringent: first, the antenna must conform to the missile's body during storage, transport, and operational use, ensuring excellent storage and adaptability; second, the antenna must automatically and reliably deploy after the missile leaves the launch box / tube to achieve optimal antenna performance. Traditional missile-borne antenna structures often suffer from numerous structural parts, making assembly and disassembly difficult, complex deployment and locking mechanisms, and low space utilization. These issues indirectly increase the hidden costs of completing combat missions. Summary of the Invention

[0003] (1) Technical issues to be solved

[0004] The technical problem to be solved by the present invention is: in view of the problems that the missile-borne antenna mechanism has many structural parts, is inconvenient to disassemble and assemble, and has a complex deployment and locking mechanism, how to provide a small missile-borne antenna deployment mechanism with a simple structure, easy installation, and reliable deployment and locking.

[0005] (2) Technical solution

[0006] In order to solve the above technical problems, the present invention provides a small missile-borne antenna deployment mechanism based on torsion spring drive, the small missile-borne antenna deployment mechanism comprising: an antenna mechanism base (1), an antenna mounting base (2), an antenna torsion spring (3), a first antenna rotating shaft (4), a second antenna rotating shaft (5), an antenna locking spring (6), an antenna locking pin (7), and a plug (8);

[0007] The antenna mechanism base (1) is connected and fixed to the missile and serves as the base of the entire antenna deployment mechanism; the antenna mechanism base (1) has a U-shaped cross section and is provided with two parallel mounting surfaces, and the two parallel mounting surfaces are provided with corresponding through holes for passing the first antenna rotating shaft (4) and the second antenna rotating shaft (5);

[0008] The midpoint of the line connecting the centers of the two through holes is used as the origin of the coordinate system. The axis direction of the through hole is defined as the X direction, the direction perpendicular to the X direction on the horizontal plane is defined as the Y direction, and the direction perpendicular to the XY plane is defined as the Z direction. Thus, a reference coordinate system XYZ is established.

[0009] The antenna mounting seat (2) is connected to the antenna mechanism base (1) at a through hole via a first antenna rotating shaft (4) and a second antenna rotating shaft (5); the first antenna rotating shaft (4) and the second antenna rotating shaft (5) are in a nested assembly relationship, forming an antenna rotating shaft assembly;

[0010] The antenna torsion spring (3) is sleeved on the antenna rotating shaft assembly and is used to provide a driving force for the antenna mounting seat (2) to rotate around the antenna rotating shaft assembly in the YZ plane, and the rotation direction of the antenna mounting seat (2) is from the Z positive direction to the Y axis positive direction, or vice versa;

[0011] The antenna mounting seat (2) is connected and fixed to the antenna (9), and the antenna (9) is configured to be able to rotate around the antenna rotation axis assembly along with the antenna mounting seat (2) to achieve conversion from a folded state to an unfolded state.

[0012] In the orientation defined by the positive direction of the Z axis and the positive direction of the Y axis, a receiving cavity is provided on the side of the antenna mechanism base (1) along the positive direction of the Y axis, and a locking assembly consisting of an antenna locking spring (6) and an antenna locking pin (7) is provided in a pin hole passing through the interior of the receiving cavity along the Y axis;

[0013] The locking assembly is used to lock the antenna mounting seat (2) when the antenna (9) is in an unfolded state;

[0014] The antenna locking spring (6) is sleeved on the antenna locking pin (7) to provide a preset driving force, and a plug (8) is provided at the tail opening of the accommodating cavity to seal the pin hole of the accommodating cavity.

[0015] Wherein, when the antenna is in the folded state, the antenna mounting seat (2) is fixedly connected to the antenna rotating shaft assembly along one end of the Z axis, and the top end of the end, i.e., the positive end of the Z axis, is provided with a tapered hole for accommodating the pin head of the antenna locking pin (7); the other end of the antenna mounting seat (2) extends along the Z axis to form a mounting platform, and the antenna (9) is mounted on the mounting platform along the Y axis.

[0016] Wherein, when the antenna is in the folded state, the end of the antenna mounting seat (2) along the other end of the Z axis is further provided with an L-shaped extension end, and the antenna deployment mechanism is restrained by the contact between the L-shaped extension end and the inner wall of the launch box / launch tube to maintain the folded state;

[0017] The L-shaped protruding end is designed with chamfered corners so that the antenna deployment mechanism will not damage the inner wall when it moves forward along the launch box / launch tube with the missile, and ensures that there will be no dead zone when the antenna deployment mechanism is deployed when the inner wall contact constraint is released.

[0018] The antenna torsion spring (3) is provided with a pair, wherein the first end of each pair of antenna torsion springs (3) is connected to the antenna mechanism base (1), and the second end of each pair of antenna torsion springs (3) is connected to one of the first antenna rotation shaft (4) and the second antenna rotation shaft (5); that is, the second end of the first antenna torsion spring (3) is connected to the first antenna rotation shaft (4), and the second end of the other antenna torsion spring (3) is connected to the second antenna rotation shaft (5), and vice versa.

[0019] The antenna torsion spring (3) is designed with a pre-twisted angle when installed, providing an unfolding driving force for the antenna unfolding mechanism. After being unfolded into place, it presents an unfolded state. The unfolding principle is simple and the process is reliable.

[0020] The spring force of the antenna locking spring (6) is set to be smaller than the spring force of the antenna torsion spring (3).

[0021] The antenna locking pin (7) is driven by the antenna locking spring (6) and is integrated into the accommodating cavity of the antenna mechanism base (1);

[0022] When the antenna is in the folded state, the pin head of the antenna locking pin (7) presses against the Y-axis positive side wall of the antenna mounting seat (2) which is set as an arc surface under the driving force of the antenna locking spring (6);

[0023] Since the spring force of the antenna locking spring (6) is smaller than the spring force of the antenna torsion spring (3), when the antenna is turned from the folded state to the unfolded state, the spring force of the antenna torsion spring (3) overcomes the spring force of the antenna locking spring (6), drives the antenna shaft assembly to rotate, and drives the antenna mounting seat (2) and the antenna (9) to rotate from the Z-axis positive direction toward the Y-axis positive direction;

[0024] When the antenna (9) is in place and in the deployed position, the antenna mounting base (2) completes a 90° rotation, and the conical hole originally facing the positive direction of the Z axis now faces the positive direction of the Y axis, just aligned with the pin hole of the accommodating cavity of the antenna mechanism base (1). The antenna locking pin (7) in the pin hole is pushed by the antenna locking spring (6) and locked into the conical hole of the antenna mounting base (2), and the antenna mechanism is locked after being deployed into place.

[0025] The antenna mechanism base (1) is connected and fixed to the missile via four M3 screws.

[0026] Wherein, the through hole on the antenna mechanism base (1) is an elliptical through hole.

[0027] The antenna mounting base (2) and the antenna (9) are connected and fixed via four M2 screws.

[0028] (3) Beneficial effects

[0029] Compared with the prior art, the technical effects of the present invention are reflected in the following aspects.

[0030] (1) The present invention has good overall installation integration, small structural space occupation, simple installation, simple processing technology, and high process maturity.

[0031] (2) The present invention uses a spring as a driving force to realize the automatic deployment and locking of the antenna mechanism. The deployment mechanism is simple and the deployment process is reliable.

[0032] (3) The present invention adopts an L-shaped extension end design, which fully utilizes the space constraints of the launch box / tube wall and reliably maintains the folded state of the antenna mechanism inside the launch box / tube. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] Figure 1 It is a schematic diagram of the composition of the antenna mechanism of the present invention.

[0034] Figure 2 It is a schematic diagram of the folded and unfolded states of the antenna mechanism of the present invention.

[0035] As shown in the figure: 1-antenna mechanism base, 2-antenna mounting base, 3-antenna torsion spring, 4-first antenna rotation shaft, 5-second antenna rotation shaft, 6-antenna locking spring, 7-antenna locking pin, 8-plug, 9-antenna. DETAILED DESCRIPTION

[0036] In order to make the purpose, content, and advantages of the present invention more clear, the specific implementation methods of the present invention are further described in detail below with reference to the accompanying drawings and examples.

[0037] In order to solve the above technical problems, the present invention provides a small missile-borne antenna deployment mechanism based on torsion spring drive, the small missile-borne antenna deployment mechanism comprising: an antenna mechanism base (1), an antenna mounting base (2), an antenna torsion spring (3), a first antenna rotating shaft (4), a second antenna rotating shaft (5), an antenna locking spring (6), an antenna locking pin (7), and a plug (8);

[0038] The antenna mechanism base (1) is connected and fixed to the missile and serves as the base of the entire antenna deployment mechanism; the antenna mechanism base (1) has a U-shaped cross section and is provided with two parallel mounting surfaces, and the two parallel mounting surfaces are provided with corresponding through holes for passing the first antenna rotating shaft (4) and the second antenna rotating shaft (5);

[0039] The midpoint of the line connecting the centers of the two through holes is used as the origin of the coordinate system. The axis direction of the through hole is defined as the X direction, the direction perpendicular to the X direction on the horizontal plane is defined as the Y direction, and the direction perpendicular to the XY plane is defined as the Z direction. Thus, a reference coordinate system XYZ is established.

[0040] The antenna mounting seat (2) is connected to the antenna mechanism base (1) at a through hole via a first antenna rotating shaft (4) and a second antenna rotating shaft (5); the first antenna rotating shaft (4) and the second antenna rotating shaft (5) are in a nested assembly relationship, forming an antenna rotating shaft assembly;

[0041] The antenna torsion spring (3) is sleeved on the antenna rotating shaft assembly and is used to provide a driving force for the antenna mounting seat (2) to rotate around the antenna rotating shaft assembly in the YZ plane, and the rotation direction of the antenna mounting seat (2) is from the Z positive direction to the Y axis positive direction, or vice versa;

[0042] The antenna mounting seat (2) is connected and fixed to the antenna (9), and the antenna (9) is configured to be able to rotate around the antenna rotation axis assembly along with the antenna mounting seat (2) to achieve conversion from a folded state to an unfolded state.

[0043] In the orientation defined by the positive direction of the Z axis and the positive direction of the Y axis, a receiving cavity is provided on the side of the antenna mechanism base (1) along the positive direction of the Y axis, and a locking assembly consisting of an antenna locking spring (6) and an antenna locking pin (7) is provided in a pin hole passing through the interior of the receiving cavity along the Y axis;

[0044] The locking assembly is used to lock the antenna mounting seat (2) when the antenna (9) is in an unfolded state;

[0045] The antenna locking spring (6) is sleeved on the antenna locking pin (7) to provide a preset driving force, and a plug (8) is provided at the tail opening of the accommodating cavity to seal the pin hole of the accommodating cavity.

[0046] Wherein, when the antenna is in the folded state, the antenna mounting seat (2) is fixedly connected to the antenna rotating shaft assembly along one end of the Z axis, and the top end of the end, i.e., the positive end of the Z axis, is provided with a tapered hole for accommodating the pin head of the antenna locking pin (7); the other end of the antenna mounting seat (2) extends along the Z axis to form a mounting platform, and the antenna (9) is mounted on the mounting platform along the Y axis.

[0047] Wherein, when the antenna is in the folded state, the end of the antenna mounting seat (2) along the other end of the Z axis is further provided with an L-shaped extension end, and the antenna deployment mechanism is restrained by the contact between the L-shaped extension end and the inner wall of the launch box / launch tube to maintain the folded state;

[0048] The L-shaped protruding end is designed with chamfered corners so that the antenna deployment mechanism will not damage the inner wall when it moves forward along the launch box / launch tube with the missile, and ensures that there will be no dead zone when the antenna deployment mechanism is deployed when the inner wall contact constraint is released.

[0049] The antenna torsion spring (3) is provided with a pair, wherein the first end of each pair of antenna torsion springs (3) is connected to the antenna mechanism base (1), and the second end of each pair of antenna torsion springs (3) is connected to one of the first antenna rotation shaft (4) and the second antenna rotation shaft (5); that is, the second end of the first antenna torsion spring (3) is connected to the first antenna rotation shaft (4), and the second end of the other antenna torsion spring (3) is connected to the second antenna rotation shaft (5), and vice versa.

[0050] The antenna torsion spring (3) is designed with a pre-twisted angle when installed, providing an unfolding driving force for the antenna unfolding mechanism. After being unfolded into place, it presents an unfolded state. The unfolding principle is simple and the process is reliable.

[0051] The spring force of the antenna locking spring (6) is set to be smaller than the spring force of the antenna torsion spring (3).

[0052] The antenna locking pin (7) is driven by the antenna locking spring (6) and is integrated into the accommodating cavity of the antenna mechanism base (1);

[0053] When the antenna is in the folded state, the pin head of the antenna locking pin (7) presses against the Y-axis positive side wall of the antenna mounting seat (2) which is set as an arc surface under the driving force of the antenna locking spring (6);

[0054] Since the spring force of the antenna locking spring (6) is smaller than the spring force of the antenna torsion spring (3), when the antenna is turned from the folded state to the unfolded state, the spring force of the antenna torsion spring (3) overcomes the spring force of the antenna locking spring (6), drives the antenna shaft assembly to rotate, and drives the antenna mounting seat (2) and the antenna (9) to rotate from the Z-axis positive direction toward the Y-axis positive direction;

[0055] When the antenna (9) is in place and in the deployed position, the antenna mounting base (2) completes a 90° rotation, and the conical hole originally facing the positive direction of the Z axis now faces the positive direction of the Y axis, just aligned with the pin hole of the accommodating cavity of the antenna mechanism base (1). The antenna locking pin (7) in the pin hole is pushed by the antenna locking spring (6) and locked into the conical hole of the antenna mounting base (2), and the antenna mechanism is locked after being deployed into place.

[0056] The antenna mechanism base (1) is connected and fixed to the missile via four M3 screws.

[0057] Wherein, the through hole on the antenna mechanism base (1) is an elliptical through hole.

[0058] The antenna mounting base (2) and the antenna (9) are connected and fixed via four M2 screws.

[0059] Example 1

[0060] The present embodiment provides a small missile-borne antenna deployment mechanism based on torsion spring drive, comprising an antenna mechanism base (1), an antenna mounting base (2), an antenna torsion spring (3), a first antenna rotating shaft (4), a second antenna rotating shaft (5), an antenna locking spring (6), an antenna locking pin (7), and a plug (8). The antenna mechanism base (1) is connected to the missile body interface via four M3 screws. The antenna mounting base (2) is connected to the antenna mechanism base (1) via the first antenna rotating shaft (4) and the second antenna rotating shaft (5), and the antenna mounting base (2) can rotate along with the first antenna rotating shaft (4) and the second antenna rotating shaft (5). Two sets of antenna torsion springs (3) are installed through the limiting holes of the antenna mechanism base (1) and the limiting holes on the first antenna rotating shaft (4) and the second antenna rotating shaft (5), and are designed with a pre-twisted angle to provide driving force for the rotating shaft. The first antenna rotating shaft (4) and the second antenna rotating shaft (5) are nested and fastened by M2 screws. After being connected, they can rotate as a whole around the mounting hole of the antenna mechanism base (1) under the drive of the antenna torsion spring (3), and drive the antenna mounting base (2) to rotate together. The antenna locking pin (7) is assembled through the pin hole of the antenna mechanism base (1), and the antenna locking spring (6) is assembled in the antenna locking pin (7) to provide driving force, and finally locked by the plug (8).

[0061] All parts of the antenna mechanism are made of 45# steel and are machined to ensure reliable strength. The specific unfolding and locking principle is as follows: the L-shaped protruding end of the antenna mounting seat (2) of the antenna mechanism contacts the inside of the launch box / launch tube, and this constraint keeps the antenna mechanism in a folded state; when the missile is launched out of the box / tube, the antenna mounting seat (2) of the antenna mechanism is released from the constraint inside the launch box / launch tube, and begins to rotate around the first antenna rotating shaft (4) and the second antenna rotating shaft (5) under the action of the antenna torsion spring (3). When the antenna mechanism rotates to the unfolded position, the antenna locking pin (7) is pushed by the antenna locking spring (6) and locked into the conical hole of the antenna mounting seat (2), and the antenna mechanism completes the unfolding and locking. The antenna mechanism uses the torsion spring as a driving force to realize the automatic unfolding and locking of the missile-borne antenna, and has a simple structure, is easy to install, and has high unfolding reliability.

[0062] According to the present invention, the front end of the antenna mounting seat is designed with an extended end, and the antenna mechanism contacts the inner wall of the launch box / launch tube through the extended end to maintain a folded state; the extended end is designed with a rounded corner so that the antenna mechanism will not damage the inner wall when it moves along the launch direction of the launch box / launch tube with the missile, and ensures that when the contact constraint of the inner wall is released, there will be no dead zone when the antenna mechanism is unfolded.

[0063] According to the present invention, a pair of antenna torsion springs is used to enhance the deployment power of the antenna mechanism, making the deployment process more reliable.

[0064] According to the present invention, the antenna locking pin is driven by the antenna locking spring and is integrated into the base of the antenna mechanism. When the antenna mechanism rotates to the deployed position, the antenna locking pin is pushed by the antenna locking spring and locked into the conical hole of the antenna mounting base, and the antenna mechanism completes deployment and locking.

[0065] Example 2

[0066] As Figure 1 、 2 As shown, the present invention relates to a small missile-borne antenna deployment mechanism based on torsion spring drive, comprising an antenna mechanism base (1), an antenna mounting base (2), an antenna torsion spring (3), a first antenna rotating shaft (4), a second antenna rotating shaft (5), an antenna locking spring (6), an antenna locking pin (7), and a plug (8). The antenna mechanism base (1) is connected to the missile body interface via four M3 screws. The antenna mounting base (2) is connected to the antenna mechanism base (1) via the first antenna rotating shaft (4) and the second antenna rotating shaft (5), and the antenna mounting base (2) can rotate along with the first antenna rotating shaft (4) and the second antenna rotating shaft (5). Two groups of antenna torsion springs (3) are installed through the limiting holes of the antenna mechanism base (1) and the limiting holes on the first antenna rotating shaft (4) and the second antenna rotating shaft (5), and are designed with a pre-twisted angle to provide driving force for the rotating shaft. The first antenna rotating shaft (4) and the second antenna rotating shaft (5) are nested and fastened by M2 screws. After being connected, they can rotate as a whole around the mounting hole of the antenna mechanism base (1) under the drive of the antenna torsion spring (3), and drive the antenna mounting base (2) to rotate together. The antenna locking pin (7) is assembled through the pin hole of the accommodating cavity of the antenna mechanism base (1). The antenna locking spring (6) is assembled in the antenna locking pin (7) to provide driving force, and finally locked by the plug (8).

[0067] All parts are made of 45# steel and are machined to ensure reliable strength. The specific unfolding and locking principle is as follows: the L-shaped protruding end of the antenna mounting seat (2) of the antenna mechanism contacts the inside of the launch box / launch tube, and this constraint keeps the antenna mechanism in a folded state; when the missile is launched out of the box / tube, the antenna mounting seat (2) of the antenna mechanism is released from the constraint inside the launch box / launch tube, and begins to rotate around the first antenna rotating shaft (4) and the second antenna rotating shaft (5) under the action of the antenna torsion spring (3). When it rotates to the unfolded position, the antenna locking pin (7) is pushed by the antenna locking spring (6) and locked into the conical hole of the antenna mounting seat (2), and the antenna mechanism completes unfolding and locking. The antenna mechanism uses the torsion spring as a driving force to realize the automatic unfolding and locking of the missile-borne antenna, and has high unfolding reliability.

[0068] This antenna mechanism features a simple structure, clear mechanism, and easy installation. The L-shaped extension of the antenna mounting base secures the antenna mechanism in its folded position within the launch box / tube, achieving high space utilization and conformity with the missile body. A dual torsion spring drive design ensures sufficient driving force during deployment, making the process faster and more reliable. The antenna mechanism utilizes an antenna locking spring as its driving force, and the locking pin automatically locks the antenna mechanism into place after deployment, ensuring reliable locking.

[0069] The small missile-borne antenna deployment mechanism based on torsion spring drive provided by the present invention can be promoted and applied to a variety of small missiles. Modifications or changes made thereto also fall within the scope defined by the claims attached to this application.

[0070] The above is only a preferred embodiment of the present invention. It should be pointed out that for ordinary technicians in this technical field, several improvements and modifications can be made without departing from the technical principles of the present invention. These improvements and modifications should also be regarded as the scope of protection of the present invention.

Claims

1. A small missile-borne antenna deployment mechanism based on torsion spring drive, characterized in that: The small missile-borne antenna deployment mechanism comprises: an antenna mechanism base (1), an antenna mounting base (2), an antenna torsion spring (3), a first antenna rotation shaft (4), and a second antenna rotation shaft (5); The antenna mechanism base (1) is connected and fixed to the missile and serves as the base of the entire antenna deployment mechanism; the antenna mechanism base (1) has a U-shaped cross section and is provided with two parallel mounting surfaces, and the two parallel mounting surfaces are provided with corresponding through holes for passing the first antenna rotating shaft (4) and the second antenna rotating shaft (5); The midpoint of the line connecting the centers of the two through holes is used as the origin of the coordinate system. The axis direction of the through hole is defined as the X direction, the direction perpendicular to the X direction on the horizontal plane is defined as the Y direction, and the direction perpendicular to the XY plane is defined as the Z direction. Thus, a reference coordinate system XYZ is established. The antenna mounting seat (2) is connected to the antenna mechanism base (1) at a through hole via a first antenna rotating shaft (4) and a second antenna rotating shaft (5); the first antenna rotating shaft (4) and the second antenna rotating shaft (5) are in a nested assembly relationship, forming an antenna rotating shaft assembly; The antenna torsion spring (3) is sleeved on the antenna rotating shaft assembly and is used to provide a driving force for the antenna mounting seat (2) to rotate around the antenna rotating shaft assembly in the YZ plane, and the rotation direction of the antenna mounting seat (2) is from the Z positive direction to the Y axis positive direction, or vice versa; The antenna mounting seat (2) is connected and fixed to the antenna (9), and the antenna (9) is configured to be able to rotate around the antenna rotation axis assembly along with the antenna mounting seat (2) to achieve conversion from a folded state to an unfolded state.

2. The small missile-borne antenna deployment mechanism based on torsion spring drive according to claim 1, characterized in that: The small missile-borne antenna deployment mechanism further includes: an antenna locking spring (6), an antenna locking pin (7), and a plug (8); In the orientation defined by the positive direction of the Z axis and the positive direction of the Y axis, a receiving cavity is provided on the side of the antenna mechanism base (1) along the positive direction of the Y axis, and a locking assembly consisting of an antenna locking spring (6) and an antenna locking pin (7) is provided in a pin hole passing through the interior of the receiving cavity along the Y axis; The locking assembly is used to lock the antenna mounting seat (2) when the antenna (9) is in an unfolded state; The antenna locking spring (6) is sleeved on the antenna locking pin (7) to provide a preset driving force, and a plug (8) is provided at the tail opening of the accommodating cavity to seal the pin hole of the accommodating cavity.

3. The small missile-borne antenna deployment mechanism based on torsion spring drive according to claim 2, characterized in that: When the antenna is in a folded state, the antenna mounting seat (2) is fixedly connected to the antenna rotating shaft assembly at one end along the Z axis, and the top end of the end, i.e., the positive end of the Z axis, is provided with a tapered hole for accommodating the pin head of the antenna locking pin (7); the other end of the antenna mounting seat (2) extends along the Z axis to form a mounting platform, and the antenna (9) is mounted on the mounting platform along the Y axis; The antenna mounting seat (2) is further provided with an L-shaped extension at the other end along the Z axis, and the antenna deployment mechanism is restrained by the contact between the L-shaped extension and the inner wall of the launch box / launch tube to maintain a folded state; The L-shaped protruding end is designed with chamfered corners so that the antenna deployment mechanism will not damage the inner wall when it moves forward along the launch box / launch tube with the missile, and ensures that there will be no dead zone when the antenna deployment mechanism is deployed when the inner wall contact constraint is released.

4. The small missile-borne antenna deployment mechanism based on torsion spring drive according to claim 1, characterized in that: The antenna torsion spring (3) is provided in a pair, wherein the first end of each of the pair of antenna torsion springs (3) is connected to the antenna mechanism base (1), and the second end of each of the pair of antenna torsion springs (3) is connected to one of the first antenna rotation shaft (4) and the second antenna rotation shaft (5); that is, the second end of the first antenna torsion spring (3) is connected to the first antenna rotation shaft (4), and the second end of the other antenna torsion spring (3) is connected to the second antenna rotation shaft (5), and vice versa.

5. The small missile-borne antenna deployment mechanism based on torsion spring drive according to claim 4, characterized in that: The antenna torsion spring (3) is designed with a pre-twisted angle when installed, providing an unfolding driving force for the antenna unfolding mechanism. After being unfolded to the right position, it presents an unfolded state. The unfolding principle is simple and the process is reliable.

6. The small missile-borne antenna deployment mechanism based on torsion spring drive according to claim 2, characterized in that: The spring force of the antenna locking spring (6) is set to be smaller than the spring force of the antenna torsion spring (3).

7. The small missile-borne antenna deployment mechanism based on torsion spring drive according to claim 6, characterized in that: The antenna locking pin (7) is driven by the antenna locking spring (6) and is integrated into the accommodating cavity of the antenna mechanism base (1); When the antenna is in the folded state, the pin head of the antenna locking pin (7) presses against the Y-axis positive side wall of the antenna mounting seat (2) which is set as an arc surface under the driving force of the antenna locking spring (6); Since the spring force of the antenna locking spring (6) is smaller than the spring force of the antenna torsion spring (3), when the antenna is turned from the folded state to the unfolded state, the spring force of the antenna torsion spring (3) overcomes the spring force of the antenna locking spring (6), drives the antenna shaft assembly to rotate, and drives the antenna mounting seat (2) and the antenna (9) to rotate from the Z-axis positive direction toward the Y-axis positive direction; When the antenna (9) is in place and in the deployed position, the antenna mounting base (2) completes a 90° rotation, and the conical hole originally facing the positive direction of the Z axis now faces the positive direction of the Y axis, just aligned with the pin hole of the accommodating cavity of the antenna mechanism base (1). The antenna locking pin (7) in the pin hole is pushed by the antenna locking spring (6) and locked into the conical hole of the antenna mounting base (2), and the antenna mechanism is locked after being deployed into place.

8. The small missile-borne antenna deployment mechanism based on torsion spring drive according to claim 1, characterized in that: The antenna mechanism base (1) is connected and fixed to the missile via four M3 screws.

9. The small missile-borne antenna deployment mechanism based on torsion spring drive according to claim 1, characterized in that: The through hole on the antenna mechanism base (1) is an elliptical through hole.

10. The small missile-borne antenna deployment mechanism based on torsion spring drive according to claim 1, characterized in that: The antenna mounting base (2) and the antenna (9) are connected and fixed by four M2 screws.

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