A compact antenna panel deployment and retraction mechanism for a reconnaissance aircraft

Abstract

The present invention discloses a compact antenna panel deployment and retraction mechanism for a reconnaissance aircraft, belonging to the field of structural and mechanism design of deformable aircraft. The mechanism includes: a fixed antenna panel, a movable antenna panel, a telescopic rod mechanism, and a driving mechanism; the fixed antenna panel includes a first fixed antenna panel and a second fixed antenna panel; the movable antenna panel includes a first movable antenna panel and a second movable antenna panel; the fixed antenna panel is located below, and the telescopic rod mechanism is installed inside the fixed antenna panel. The movable antenna panel is located above the fixed antenna panel and is connected to the fixed antenna panel through the telescopic rod mechanism. The movable antenna panel moves along the lateral and normal directions of the antenna panel under the drive of the telescopic rod mechanism. The antenna panel deployment and retraction mechanism of the present invention ensures that the lower surface of the movable antenna panel is flush with the lower surface of the fixed antenna panel after deployment, and has a compact structure, maintains compactness during operation, does not change the appearance of the antenna panel, and can be deployed and retracted within the atmosphere.

Description

Technical Field

[0001] The present invention belongs to the field of the structure and mechanism design of deformable aircraft, and relates to a radar antenna panel deployment and retraction mechanism for a reconnaissance / strike aircraft, belonging to a reusable deployment / retraction mechanism. Background Art

[0002] A reconnaissance missile is a missile system used to obtain information about enemy targets. Compared with satellites, reconnaissance missiles have the advantages of rapid deployment, flexible operation, and close-range reconnaissance. Reconnaissance missiles carry sensors such as optical, infrared, and radar, and collect information about enemy targets during flight. To improve detection effectiveness, reconnaissance missiles usually need to be equipped with a relatively large antenna panel. To save space, it is required that part of the antenna panel can be retracted during storage of the reconnaissance missile, and the antenna panel is deployed again when flying to the reconnaissance position after launch. After completing the reconnaissance mission, the aircraft enters the atmosphere and glides using the lift provided by the antenna panel. When a certain distance from the target, the antenna panel needs to be retracted again to improve the lateral maneuverability of the aircraft.

[0003] If a traditional telescopic mechanism (such as a telescopic wing) is used, it is difficult for the lower surfaces of the movable antenna panel and the non-movable antenna panel to be flush after the antenna panel is deployed, which does not meet the working requirements of the detection sensor. Taking a radar sensor as an example, the uneven surface of the detection sensor may cause the propagation path of the radar wave to change, resulting in a time delay or phase difference of the reflected signal, thus affecting the detection accuracy. Although some other deployment / retraction methods (such as a rotary door type) can ensure that the working surface of the antenna panel is flush after deployment, the movement stroke during the deployment and retraction process is relatively large, the structure is not compact enough, and usually the driving mechanism needs to be installed outside the antenna panel, which will significantly change the appearance of the aircraft and is difficult to work in the atmosphere, and also does not meet the requirements of the reconnaissance missile during the flight stage in the atmosphere. Summary of the Invention

[0004] The present invention designs a rotatable telescopic rod mechanism, and based on this, designs a compact antenna panel deployment / retraction mechanism. This mechanism can ensure that the lower surfaces of the moving part and the non-moving part are flush after the antenna panel is deployed, and the structure is compact, can work in the atmosphere, and meets the requirements of the reconnaissance missile.

[0005] In view of the requirements for the deployment and retraction functions of the reconnaissance missile antenna panel, the present invention designs a compact antenna panel deployment and retraction mechanism based on a rotatable telescopic rod, ensuring that the lower surfaces of the movable antenna panel and the immovable antenna panel are flush after deployment, and without changing the appearance of the antenna panel, and can be deployed and retracted in the atmosphere.

[0006] The present invention is implemented as follows:

[0007] A compact antenna panel deployment and retraction mechanism for a reconnaissance aircraft, characterized in that the mechanism comprises: a fixed antenna panel, a moving antenna panel, a telescopic rod mechanism, and some connection and drive mechanisms; the fixed antenna panel includes a first fixed antenna panel and a second fixed antenna panel; the moving antenna panel includes a first moving antenna panel and a second moving antenna panel; the first fixed antenna panel and the second fixed antenna panel are located below, and a telescopic rod mechanism is installed inside the fixed antenna panel. The first moving antenna panel and the second moving antenna panel are respectively located above the first fixed antenna panel and the second fixed antenna panel. The moving antenna panel is connected to the fixed antenna panel through the telescopic rod mechanism, and the moving antenna panel moves along the lateral and normal directions of the antenna panel under the drive of the telescopic rod mechanism.

[0008] Further, the telescopic rod mechanism: a housing, an external gear, a crank structure, and a telescopic rod; the telescopic rod is connected to the housing in a sleeve manner, and the two are in sliding fit. A linear motor is used inside to drive its telescopic movement. The round rod part of the crank structure is connected to the telescopic rod in a sleeve manner, and the two are in sliding fit; the external gear is fixedly connected to the housing by a set screw, and driving the external gear to rotate can drive the entire telescopic rod mechanism to rotate around its axis.

[0009] Further, both the first fixed antenna panel and the second fixed antenna panel are provided with semi-open circular grooves and circular cavities. Among them, the semi-open circular grooves are for the telescopic rod with a crank structure to perform extension and contraction movements, and the circular cavities are used to install the housing of the telescopic rod mechanism; after the telescopic rod mechanism is fully extended, it can be rotated in the semi-open circular grooves and circular cavities by driving the external gear;

[0010] Both the first moving antenna panel and the second moving antenna panel are provided with round holes, and the round holes are used to connect with the shaft of the crank structure on the telescopic rod mechanism. After connection, the two can rotate relative to each other; both the first moving antenna panel and the second moving antenna panel are also provided with concave cavities, which are used to provide a storage space for the crank structure when the telescopic rod is in the retracted state.

[0011] Further, in order to make the lower surface of the antenna panel just flush after the telescopic rod rotates, the axis of the circular hole cavity on the moving antenna panel and the axis of the round hole on the fixed antenna panel need to satisfy the following relationship:

[0012]

[0013] In the formula: δ1 is the distance from the center line of the round hole to the lower surface of the moving antenna panel, δ2 is the distance from the axis of the telescopic rod mechanism to the lower surface of the fixed antenna panel, and d is the thickness of the antenna panel.

[0014] Further, in order to make the unfolding and folding processes of the antenna plates stable and reliable, at least two telescopic rod mechanisms are used to support and drive each moving antenna plate, and the two antenna plates are required to extend and rotate synchronously; the extension and rotation speeds of the telescopic rods are controlled to ensure accurate synchronization. The telescopic rod mechanism includes a first telescopic rod mechanism, a second telescopic rod mechanism, a third telescopic rod mechanism, and a fourth telescopic rod mechanism.

[0015] Further, the first telescopic rod mechanism, the second telescopic rod mechanism (including the crank structures on the first telescopic rod mechanism and the second telescopic rod mechanism), the second immovable antenna plate, and the first moving antenna plate form a parallelogram in the spanwise direction. When the first telescopic rod mechanism and the second telescopic rod mechanism extend and then rotate 180 degrees synchronously, the first moving antenna plate will be driven to move to a position flush with the first immovable antenna plate.

[0016] Further, the telescopic rod mechanism also includes a rotation drive member, a first locking mechanism, and a second locking mechanism; the moving antenna plate also includes a circular hole cover plate to facilitate the assembly of the crank structure and the moving antenna plate; the crank structure also includes a through hole for locking the entire mechanism with a plug locking mechanism in the unfolded and folded states; the moving antenna plate has a leading-edge swept-back structure, and the reconnaissance projectile has good aerodynamic characteristics after the moving antenna plate is fully unfolded.

[0017] Further, the rotation drive member includes a first motor, a connecting rod, and a transmission gear set. The first motor drives the external gear fixed to the telescopic rod to rotate through the transmission gear set, thereby driving the telescopic rod to rotate; the first locking mechanism includes a second motor, a screw rod, a slider plug, and a baffle with a guide rail. The second motor drives the screw rod to rotate. Due to the limitation of the baffle with a guide rail, the slider plug can only move translationally along the axis of the screw rod. The slider plug is inserted into the through hole of the crank mechanism to complete the locking of the mechanism; the second locking mechanism is the same as the first locking mechanism.

[0018] A compact reconnaissance aircraft antenna plate unfolding and folding mechanism according to the present invention is characterized in that the lower surfaces of the immovable antenna plate and the moving antenna plate are detection sensor surfaces, and it is required that these surfaces be flush after unfolding; the processes of the antenna plate unfolding and folding movements are as follows:

[0019] Step 1: Establish an XYZ coordinate system. The telescopic rod mechanisms extend synchronously and drive the moving antenna plate to move along the spanwise ±y direction through the crank structure, and the moving antenna plate is fully unfolded in the spanwise direction.

[0020] Step 2: The telescopic rod mechanisms rotate 180 degrees synchronously along the axis of the telescopic rods under the action of an external torque, and drive the moving antenna plate to move downward along the -z direction through the crank structure, so that the lower surface of the moving antenna plate is flush with the lower surface of the immovable antenna plate.

[0021] Step 3: All of the above-mentioned movement processes are reversible. The antenna panel can be retracted by moving in the reverse direction. Locking is required in both the deployed and retracted states of the antenna panel, and the crank structure can be locked to achieve this.

[0022] The beneficial effects of the present invention compared with the prior art are as follows:

[0023] The present invention designs a compact antenna panel deployment and retraction mechanism using a rotary telescopic rod, which can ensure that the working surface of the antenna panel is flush after deployment. All parts of this deployment / retraction mechanism are ingeniously integrated inside the antenna panel, occupying a relatively small space and not changing the appearance of the antenna panel. It is particularly suitable for scenarios with limited space and can be used for the deployment and retraction of antenna panels of aircraft such as reconnaissance projectiles and reconnaissance satellites. The present invention expands the functions of traditional telescopic deployment schemes and provides a new solution for the deployment and retraction of antenna panels. Brief Description of the Drawings

[0024] Figure 1 It is a schematic diagram of the overall mechanism of a compact reconnaissance aircraft antenna panel deployment and retraction mechanism before deployment of the present invention;

[0025] Figure 2 It is a schematic diagram of the overall mechanism of a compact reconnaissance aircraft antenna panel deployment and retraction mechanism after deployment in the spreading direction of the present invention;

[0026] Figure 3 It is a schematic diagram of the overall mechanism of a compact reconnaissance aircraft antenna panel deployment and retraction mechanism after normal deployment of the present invention;

[0027] Figure 4 It is a schematic diagram of the retracted state of the telescopic rod mechanism of a compact reconnaissance aircraft antenna panel deployment and retraction mechanism of the present invention;

[0028] Figure 5 It is a schematic diagram of the extended state of the telescopic rod mechanism of a compact reconnaissance aircraft antenna panel deployment and retraction mechanism of the present invention;

[0029] Figure 6 It is a schematic diagram of the structure of the first immovable antenna panel;

[0030] Figure 7 It is a schematic diagram of the structure of the second immovable antenna panel;

[0031] Figure 8 It is a schematic diagram of the structure of the first movable antenna panel;

[0032] Figure 9 It is a schematic diagram of the structure of the second movable antenna panel;

[0033] Figure 10 It is an assembly schematic diagram of the telescopic rod mechanism and the immovable antenna panel (retracted state);

[0034] Figure 11 Schematic diagram of the assembly of the telescopic rod mechanism and the immovable antenna panel (expansion in the span direction);

[0035] Figure 12 Schematic diagram of the assembly of the telescopic rod mechanism and the immovable antenna panel (fully expanded);

[0036] Figure 13 Schematic diagram of the assembly of the telescopic rod mechanism, the first immovable antenna panel and the first movable antenna panel (retracted state);

[0037] Figure 14 Schematic diagram of the retracted state of the embodiment of the present invention;

[0038] Figure 15 Schematic diagram of the rotation driving member in the embodiment of the present invention;

[0039] Figure 16 Schematic diagram of the assembly of the rotation driving member and the telescopic rod in the embodiment of the present invention;

[0040] Figure 17 Schematic diagram of the crank structure in the embodiment of the present invention;

[0041] Figure 18 Schematic diagram of the assembly of the crank structure and the movable antenna panel in the embodiment of the present invention;

[0042] Figure 19 Schematic diagram of the plug rod locking mechanism in the embodiment of the present invention;

[0043] Figure 20 Schematic diagram of the locking process of the plug rod locking mechanism in the embodiment;

[0044] Figure 21 Schematic diagram of the fully expanded state of the movable antenna panel in the span direction in the embodiment;

[0045] Figure 22 Schematic diagram of the movable antenna panel after normal movement in the embodiment.

[0046] Among them, 1 - the first immovable antenna panel, 2 - the second immovable antenna panel, 3 - the first movable antenna panel, 4 - the second movable antenna panel, 5 - the first telescopic rod mechanism, 6 - the second telescopic rod mechanism, 7 - the third telescopic rod mechanism, 8 - the fourth telescopic rod mechanism, 9 - the housing, 10 - the external gear, 11 - the crank structure, 12 - the telescopic rod, 13 - the semi-open circular groove, 14 - the circular hole cavity, 15 - the round hole, 16 - the concave cavity, 17 - the rotation driving member, 18 - the first locking mechanism, 19 - the second locking mechanism, 20 - the round hole cover plate, 21 - the first motor, 22 - the connecting rod, 23 - the transmission gear set, 24 - the through hole, 25 - the second motor, 26 - the screw rod, 27 - the slider plug rod, 28 - the baffle with a guide rail. Detailed implementation manners

[0047] To make the objectives, technical solutions and effects of the present invention clearer and more definite, the following examples are given to further elaborate on the present invention in detail. It should be noted that the specific implementations described herein are only used to explain the present invention and are not used to limit the present invention.

[0048] The present invention uses telescopic rods to achieve the lateral movement of the antenna board, and rotates the telescopic rods to achieve the normal movement of the movable antenna board, so that the lower surfaces of the movable antenna board and the immovable antenna board are flush after deployment, and this deployment process is reversible, and the antenna board can also be retracted after deployment. The overall assembly diagram of the antenna board deployment / retraction mechanism of the present invention is as Figure 1 shown. The described mechanism includes: an immovable antenna board, a movable antenna board, a telescopic rod mechanism, and a driving mechanism; the immovable antenna board includes a first immovable antenna board 1 and a second immovable antenna board 2; the movable antenna board includes a first movable antenna board 3 and a second movable antenna board 4; the first immovable antenna board 1 and the second immovable antenna board 2 are located below, and a telescopic rod mechanism is installed inside the immovable antenna board. The first movable antenna board 3 and the second movable antenna board 4 are respectively located above the first immovable antenna board 1 and the second immovable antenna board 2. The movable antenna board is connected to the immovable antenna board through the telescopic rod mechanism, and the movable antenna board moves along the lateral and normal directions of the antenna board under the drive of the telescopic rod mechanism. The lower surfaces of the first immovable antenna board 1, the second immovable antenna board 2, the first movable antenna board 3, and the second movable antenna board 4 are the surfaces of the detection sensors, and it is required that these surfaces be flush after deployment. The principles of the antenna board deployment and retraction movements are as follows:

[0049] Step 1: The telescopic rod mechanisms (the first telescopic rod mechanism 5, the second telescopic rod mechanism 6, the third telescopic rod mechanism 7, and the fourth telescopic rod mechanism 8) extend synchronously and drive the movable antenna boards 3 and 4 to move along the lateral direction ( Figure 1 the ±y direction in the figure) through the crank until the first movable antenna board 3 and the second movable antenna board 4 are fully deployed in the lateral direction, as Figure 2 shown;

[0050] Step 2: The telescopic rod mechanisms (the first telescopic rod mechanism 5, the second telescopic rod mechanism 6, the third telescopic rod mechanism 7, and the fourth telescopic rod mechanism 8) rotate 180 degrees synchronously along the axis of the telescopic rods under the action of an external torque, and drive the movable antenna boards to move downward ( Figure 2 the -z direction in the figure) through the crank, so that the lower surfaces of the movable antenna boards and the immovable antenna board are flush, as Figure 3 shown.

[0051] Step 3: All the above movement processes are reversible, and the reverse movement can realize the retraction of the antenna board.

[0052] The main components and features of this deployment and retraction mechanism are as follows:

[0053] (1) The retracted state and extended state of the telescopic rod mechanism are shown in Figure 4 and Figure 5 respectively. The parts included in the telescopic rod mechanism are: housing 9, external gear 10, crank structure 11, and telescopic rod 12. The telescopic rod 12 is connected to the housing 9 by a sleeve method, and they are in sliding fit with each other. A linear motor is used inside to drive its telescopic movement. The round rod part of the crank structure 11 is connected to the telescopic rod 12 by a sleeve method, and they are in sliding fit with each other; the external gear 10 is fixedly connected to the housing 9 by a set screw. Driving the rotation of the external gear can drive the entire telescopic rod mechanism to rotate around its axis. The telescopic rod mechanism can be extended or contracted along the length direction under the action of the linear motor, specifically depending on the current direction. The telescopic rod technology is currently relatively mature and can be directly purchased or customized according to size and stroke requirements. The external gear 10 is fixedly connected to the housing 9, and driving the external gear can drive the entire telescopic rod mechanism to rotate around its axis.

[0054] (2) In order to make the unfolding and retracting movement processes of the antenna board stable and reliable, at least two sets of telescopic rod mechanisms are used to support and drive each moving antenna board, and the two sets of antenna boards are required to expand and contract and rotate synchronously. Therefore, it is necessary to control the telescopic and rotational speeds of the telescopic rod to ensure accurate synchronization.

[0055] (3) The first immovable antenna board 1 and the second immovable antenna board 2 are provided with semi-open circular grooves 13 and circular cavities 14, as shown in Figure 6 and Figure 7 respectively. Among them, the semi-open circular groove 13 is for the telescopic rod with a crank structure to perform expansion and contraction movements, and the circular cavity 14 is used to install the housing 9 of the telescopic rod mechanism. After the telescopic rod mechanism is fully extended, it can be rotated in the semi-open circular groove 13 and the circular cavity 14 by driving the external gear 10.

[0056] (4) The first moving antenna board 3 and the second moving antenna board 4 are provided with round holes 15, as shown in Figure 8 and Figure 9 respectively. This round hole is used to connect with the shaft of the crank structure 11 on the telescopic rod mechanism, and the two can rotate relative to each other after connection. The moving antenna board is provided with a concave cavity 16, which is used to provide a storage space for the crank structure 11 when the telescopic rod is in the retracted state.

[0057] (5) The first telescopic rod mechanism 5, the second telescopic rod mechanism 6 (including the crank structures 11 on the two telescopic rod mechanisms), the immovable antenna board 2, and the movable antenna board 3 form a parallelogram in the spanwise direction. When the telescopic rods 5 and 6 are extended and rotated synchronously by 180 degrees, the moving antenna board 3 will be driven to move to a position flush with the immovable antenna board 1.

[0058] (6) In order to make the lower surface of the antenna board exactly flush after the telescopic rod rotates, the axes of the hole cavity 14 on the moving antenna board and the round hole 15 on the immovable antenna board need to satisfy the following relationship

[0059]

[0060] In the formula: δ1 is the distance from the center line of the round hole 15 to the lower surface of the moving antenna board, δ2 is the distance from the axis of the telescopic rod mechanism to the lower surface of the immovable antenna board, and d is the thickness of the antenna board.

[0061] (7) The effects after the immovable antenna boards 1 and 2 are assembled with the telescopic rod mechanism 5-8 are as Figures 10 to 13 shown. Among them, Figure 10 is the state before the telescopic rod extends, Figure 11 is the state after the telescopic rod extends, Figure 12 is the state after the telescopic rod mechanism rotates 180 degrees around the center line. Figure 13 The assembly effects of the immovable antenna board 1, the telescopic rod mechanism (the first telescopic rod mechanism 5, the second telescopic rod mechanism 6, the third telescopic rod mechanism 7, the fourth telescopic rod mechanism 8), and the first moving antenna board 3 are given (see the complete assembly effect in Figure 1 ). (8) The antenna board needs to be locked in both the deployed and retracted states, and locking the crank is sufficient.

[0062] A case of the antenna board deployment mechanism of a reconnaissance bomb is designed, as Figure 14 shown. Based on the basic structure of the present invention described above, some accessory parts are added to this application case: the telescopic rod mechanism is increased with a rotation drive member 17, a first locking mechanism 18, and a second locking mechanism 19, the moving antenna is increased with a round hole cover plate 20, and a through hole 24 is added to the telescopic rod crank. In addition, the first moving antenna board 3 and the second moving antenna board 4 are designed with a swept leading edge, so that the reconnaissance bomb has better aerodynamic characteristics after the first moving antenna board 3 and the second moving antenna board 4 are fully deployed.

[0063] The following is the function description of the main newly added parts:

[0064] (1) As Figure 15 shown, the rotation drive member 17 is composed of a first motor 21, a connecting rod 22, and a transmission gear set 23. The first motor 21 drives the external gear 10 fixed to the telescopic rod to rotate through the transmission gear set 23, thereby driving the telescopic rod to rotate. The connection schematic diagram of the rotation drive member 17 and the telescopic rod is as Figure 16 shown.

[0065] (2) As Figure 17 shown, a through hole 24 is added to the crank structure 11 for locking the entire mechanism with a plug locking mechanism in the deployed and retracted states.

[0066] (3) The connection scheme between the crank structure 11 and the first moving antenna plate 3 is as Figure 18 shown. A detachable cover plate 20 is designed under the moving antenna plate to facilitate the assembly of the crank structure 11 and the moving antenna plate.

[0067] (4) The first locking mechanism 18 consists of a second motor 25, a screw rod 26, a slider plug rod 27, and a baffle plate 28 with a guide rail, as Figure 19 shown. The second motor 25 drives the screw rod 26 to rotate. Due to the restriction of the baffle plate 28 with a guide rail, the slider plug rod 27 can only move translationally along the axis of the screw rod 26. Figure 22 A schematic diagram of the locking process of the plug rod locking mechanism is given. The plug rod 27 is inserted into the through hole 24 of the crank mechanism to complete the locking of the mechanism.

[0068] The unfolding and folding processes of this embodiment are given below:

[0069] Step 1: The antenna plates are initially in the folded state, as Figure 14 shown. Before unfolding, the second motor 25 in the first locking mechanism 18 drives the screw rod 26 to rotate. The slider plug rod 26 moves along the axis of the plug rod under the constraint of the baffle plate 28 with a guide rail and retracts from the through hole 24 on the crank structure 11 to complete unlocking.

[0070] Step 2: The telescopic rod 5 extends under the action of the synchronous linear motor, and the moving antenna plates 3 and 4 are pushed by the crank structure 11 on the telescopic rod to unfold in the unfolding direction. The effect of unfolding in the unfolding direction is as Figure 21 shown.

[0071] Step 3: When the first moving antenna plate 3 and the second moving antenna plate 4 are fully unfolded in the unfolding direction, the first telescopic rod mechanism 5 rotates 180 degrees under the drive of the rotary drive member 17, and the other telescopic rods are the same. The rotation of the four sets of telescopic rod mechanisms drives the first moving antenna plate 3 and the second moving antenna plate 4 to complete the normal movement. According to the movement rule of the parallelogram, when the crank structure 11 rotates 180° along the axis of the telescopic rod, the first moving antenna plate 3 and the second moving antenna plate 4 will move to a position flush with the fixed antenna plates 1 and 2, as Figure 22 shown.

[0072] Step 4: After the first moving antenna plate 3 and the second moving antenna plate 4 complete the normal movement, the second motor 25 in the second locking mechanism 19 starts to work, so that the slider plug rod 27 extends into the through hole 24 in the crank structure 11 to complete the locking.

[0073] Step 5: The above movement process is reversible, and the reverse movement can complete the folding of the antenna plates.

[0074] To further verify the feasibility of the technical solution of the present invention, an antenna panel deployment / retraction demonstration and verification model was made. To improve the display effect, an aircraft shell was configured for the deployment mechanism. Among them, the antenna panel on the right side in the flight direction is equipped with a deployment / retraction mechanism, and the left antenna panel is fixed relative to the aircraft shell.

[0075] The above case verifies that the technical solution of the present invention is feasible, can drive the antenna panel to perform in-plane and normal movements, and makes the lower surface of the deployed antenna panel flat, meeting the requirements of the reconnaissance bomb.

[0076] The above are only the preferred embodiments of the present invention. It should be noted that for those of ordinary skill in the art, several improvements can be made without departing from the principle of the present invention, and these improvements should also be regarded as the protection scope of the present invention.

Claims

1. A compact antenna panel deployment and retraction mechanism for a reconnaissance aircraft, characterized in that, The described mechanism includes: a fixed antenna plate, a moving antenna plate, a telescopic rod mechanism, and a driving mechanism; The fixed antenna plate includes a first fixed antenna plate (1) and a second fixed antenna plate (2); The moving antenna plate includes a first moving antenna plate (3) and a second moving antenna plate (4); The first fixed antenna plate (1) and the second fixed antenna plate (2) are located below. A telescopic rod mechanism is installed inside the fixed antenna plate. The first moving antenna plate (3) and the second moving antenna plate (4) are respectively located above the first fixed antenna plate (1) and the second fixed antenna plate (2). The moving antenna plate is connected to the fixed antenna plate through the telescopic rod mechanism and moves along the lateral and normal directions of the antenna plate under the drive of the telescopic rod mechanism; The telescopic rod mechanism includes: a housing (9), an external gear (10), a crank structure (11), and a telescopic rod (12); The telescopic rod (12) is connected to the housing (9) in a sleeve manner, and the two are in sliding fit. A linear motor is used inside to drive its telescopic movement. The round rod part of the crank structure (11) is connected to the telescopic rod (12) in a sleeve manner, and the two are in sliding fit; The external gear (10) is fixedly connected to the housing (9) by a set screw. Driving the external gear to rotate can drive the entire telescopic rod mechanism to rotate around its axis.

2. The unfolding and folding mechanism of a compact reconnaissance aircraft antenna panel according to claim 1, characterized in that, Both the first fixed antenna plate (1) and the second fixed antenna plate (2) are provided with semi-open circular grooves (13) and circular cavities (14). Among them, the semi-open circular grooves (13) are for the telescopic rod (12) with a crank structure to perform stretching and contracting movements, and the circular cavities (14) are used to install the housing (9) of the telescopic rod mechanism; After the telescopic rod mechanism is fully extended, it can be rotated in the semi-open circular grooves (13) and circular cavities (14) by driving the external gear (10); Both the first moving antenna plate (3) and the second moving antenna plate (4) are provided with round holes (15). The round holes (15) are used to connect with the shaft of the crank structure (11) on the telescopic rod mechanism. After connection, the two can rotate relative to each other; The first moving antenna plate (3) and the second moving antenna plate (4) are also provided with concave cavities (16) for providing a storage space for the crank structure (11) when the telescopic rod is in the retracted state.

3. A compact reconnaissance aircraft antenna panel deployment and retraction mechanism according to claim 2, characterized in that, In order to make the lower surface of the antenna plate just flush after the telescopic rod rotates, the axis of the circular cavity (14) on the moving antenna plate and the axis of the round hole (15) on the fixed antenna plate need to satisfy the following relationship: In the formula: δ1 is the distance from the center line of the round hole (15) to the lower surface of the moving antenna plate, δ2 is the distance from the axis of the telescopic rod mechanism to the lower surface of the fixed antenna plate, and d is the thickness of the antenna plate.

4. A compact antenna panel deployment and retraction mechanism for a reconnaissance aircraft according to claim 1, characterized in that, In order to make the unfolding and folding movement processes of the antenna plate stable and reliable, each moving antenna plate is supported and driven by at least two sets of telescopic rod mechanisms, and the two sets of antenna plates are required to expand and contract and rotate synchronously; Control the telescopic and rotational speeds of the telescopic rod to ensure accurate synchronization.

5. A compact reconnaissance aircraft antenna panel deployment and retraction mechanism according to claim 4, characterized in that, The telescopic rod mechanism includes a first telescopic rod mechanism (5), a second telescopic rod mechanism (6), a third telescopic rod mechanism (7), and a fourth telescopic rod mechanism (8).

6. A compact antenna panel deployment and retraction mechanism for a reconnaissance aircraft according to claim 5, characterized in that, The first telescopic rod mechanism (5), the second telescopic rod mechanism (6) (including the crank structures on the first telescopic rod mechanism (5) and the second telescopic rod mechanism (6)), the second immovable antenna plate (2), and the first movable antenna plate (3) form a parallelogram in the spanwise direction. When the first telescopic rod mechanism (5) and the second telescopic rod mechanism (6) synchronously rotate 180 degrees after elongation, the first movable antenna plate (3) will be driven to move to a position flush with the first immovable antenna plate (1).

7. A compact antenna panel deployment and retraction mechanism for a reconnaissance aircraft according to claim 5, characterized in that, The telescopic rod mechanism also includes a rotary drive member (17), a first locking mechanism (18), and a second locking mechanism (19); the movable antenna plate also includes a round hole cover plate (20) to facilitate the assembly of the crank structure (11) and the movable antenna plate; the crank structure (11) also includes a through hole (24) for locking the entire mechanism with a plug locking mechanism in the deployed and retracted states.

8. A compact antenna panel deployment and retraction mechanism for a reconnaissance aircraft according to claim 7, characterized in that The rotary drive member (17) includes a first motor (21), a connecting rod (22), and a transmission gear set (23). The first motor (21) drives the external gear (10) fixed to the telescopic rod to rotate through the transmission gear set (23), thereby driving the telescopic rod (12) to rotate; the first locking mechanism (18) includes a second motor (25), a screw (26), a slider plug (27), and a baffle (28) with a guide rail. The second motor (25) drives the screw (26) to rotate. Due to the limitation of the baffle (28) with a guide rail, the slider plug (27) can only move translationally along the axis of the screw (26). The slider plug (27) is inserted into the through hole (24) of the crank mechanism to complete the locking of the mechanism; the second locking mechanism (19) is the same as the first locking mechanism.

9. A compact antenna panel deployment and retraction mechanism for a reconnaissance aircraft, according to any one of claims 1 to 8, characterized in that The lower surfaces of the immovable antenna plate and the movable antenna plate are the surfaces of the detection sensors, and it is required that these surfaces be flush after deployment; the process of the deployment and retraction of the antenna plate is as follows: Step 1: Establish an XYZ coordinate system. The telescopic rod mechanisms extend synchronously and drive the movable antenna plate to move along the spanwise ±y direction through the crank structure (11), and the movable antenna plate is fully deployed in the spanwise direction. Step 2: The telescopic rod mechanisms synchronously rotate 180 degrees along the axis of the telescopic rod under the action of an external torque, and drive the movable antenna plate to move downward along the -z direction through the crank structure (11), so that the lower surface of the movable antenna plate is flush with the lower surface of the immovable antenna plate. Step 3: All the above movement processes are reversible, and the reverse movement can realize the retraction of the antenna plate. The antenna plate needs to be locked in both the deployed and retracted states, and it is only necessary to lock the crank structure (11).

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