A carrier aircraft catapult electric drive device

Abstract

The application discloses a carrier-based aircraft catapult electric driving device, which comprises a brushless motor, one end of the brushless motor is provided with a speed reduction mechanism, the other end of the brushless motor is provided with an electromagnetic brake, and the brushless motor and the electromagnetic brake are electrically connected with a controller through cables. The brushless motor cooperates with the speed reduction mechanism to replace a hydraulic motor to drive the retraction and release of a catapult rod, and the electromagnetic brake is used to replace a hydraulic lock to be locked, so that the problem that the hydraulic driving device cannot accurately control the position of the catapult rod and influences the working safety of the catapult rod is avoided.

Description

Technical Field

[0001] This invention relates to the field of servo control technology, and more specifically, to an electric drive device for a catapult launch stick of a shipborne aircraft. Background Technology

[0002] Currently, the catapult control systems on existing aircraft are all hydraulically driven, using high-pressure oil to drive a hydraulic motor to extend and retract the catapult stick, which is then locked in place by a hydraulic lock. The hydraulic piping and devices occupy considerable space and are heavy, increasing the overall weight of the aircraft. Furthermore, hydraulic drives are inefficient, achieving only about 30% efficiency, wasting valuable energy. The inability to precisely control the catapult stick's position compromises its operational safety. Therefore, it is necessary to propose an electric catapult control system for carrier-based aircraft to at least partially address the problems existing in the current technology. Summary of the Invention

[0003] The summary section introduces a series of simplified concepts, which will be further explained in detail in the detailed description section. The summary section of this invention is not intended to limit the key features and essential technical features of the claimed technical solution, nor is it intended to determine the scope of protection of the claimed technical solution.

[0004] To at least partially solve the above problems, the present invention provides an electric drive device for a carrier-based aircraft catapult stick, comprising:

[0005] The brushless motor has a reduction gear at one end and an electromagnetic brake at the other end. Both the brushless motor and the electromagnetic brake are electrically connected to the controller via cables.

[0006] Preferably, the deceleration mechanism includes:

[0007] The housing contains a primary transmission mechanism, a secondary transmission mechanism, and a tertiary transmission mechanism. The secondary transmission mechanism is located within the housing, and the primary transmission mechanism is connected to the secondary transmission mechanism. The tertiary transmission mechanism is located on the side of the secondary transmission mechanism away from the primary transmission mechanism, and is connected to the secondary transmission mechanism.

[0008] Preferably, the primary transmission mechanism includes:

[0009] The first gear is connected to the first gear, and the output shaft of the brushless motor extends into the housing.

[0010] The second gear is rotatably disposed inside the housing via a rotating shaft, and the second gear meshes with the first gear.

[0011] The third gear is rotatably disposed within the housing via the first rotating rod, and the third gear meshes with the second gear.

[0012] Preferably, the secondary transmission mechanism includes:

[0013] The first sun gear is sleeved on the first rotating rod;

[0014] The second rotating rod has one end connected to the first planetary carrier. The first planetary carrier is evenly provided with a plurality of first planetary gears, and the first sun gear meshes with all of the first planetary gears.

[0015] The first internal gear ring is located on the outer periphery of the first planetary gear and its inner wall meshes with the first planetary gear. The first internal gear ring is fixed to the inner wall of the housing.

[0016] Preferably, the secondary transmission mechanism further includes:

[0017] The second sun gear is fitted onto the second rotating rod;

[0018] The third rotating rod, one end of which is connected to the second planetary carrier, is provided with a plurality of second planetary gears evenly distributed on the second planetary carrier, and the second sun gear meshes with all the second planetary gears;

[0019] The second internal gear ring is located on the outer periphery of the second planetary gear and its inner wall meshes with the second planetary gear. The second internal gear ring is fixed to the inner wall of the housing.

[0020] Preferably, the three-stage transmission mechanism includes a fourth gear, which is mounted on the third rotating rod;

[0021] The fourth rotating rod has two ends rotatably mounted on the inner wall of the housing. A fifth gear and a sixth gear are sleeved on the fourth rotating rod. The fifth gear meshes with the fourth gear, and the sixth gear meshes with the seventh gear. The seventh gear is rotatably mounted on the inner wall of the housing via the fifth rotating rod.

[0022] An output shaft passes through the housing, and an eighth gear is sleeved on the output shaft, which meshes with the seventh gear.

[0023] Preferably, the housing further includes a locking mechanism, the locking mechanism comprising:

[0024] A DC motor is fixed inside the housing and electrically connected to a controller. The output end of the DC motor is provided with a drive gear, which meshes with a ninth gear, which is rotatably disposed inside the housing.

[0025] A lead screw, both ends of which are rotatably connected to the inner wall of the housing, a tenth gear and a sliding block are sleeved on the lead screw, the tenth gear meshes with the ninth gear, the sliding block is slidably connected to the inner wall of the housing, the sliding block is fixedly connected to the outer wall of the ratchet, the output shaft passes through the ratchet, and several pawls are fixed on the output shaft, the pawls being adapted to the ratchet.

[0026] Preferably, the output shaft is further provided with a dual-redundant position measuring mechanism, the dual-redundant position measuring mechanism comprising:

[0027] The measuring devices are symmetrically located at both ends of the output shaft.

[0028] Preferably, the measuring device includes:

[0029] Mounting base, the mounting base is provided with a position sensor, the position sensor is electrically connected to the controller via a cable, the cable passes through the mounting base, the position sensor is rotatably provided with a first transmission wheel (38), the mounting base is rotatably provided with a second transmission wheel, the first transmission wheel and the second transmission wheel mesh;

[0030] The third transmission wheel is sleeved on the output shaft and meshes with the second transmission wheel.

[0031] Preferably, the diameter of the eighth gear is larger than that of the sixth gear.

[0032] Compared with the prior art, the present invention has at least the following beneficial effects:

[0033] The present invention discloses an electric drive device for a carrier-based aircraft catapult stick. The device uses a controller to control a brushless motor in conjunction with a reduction mechanism to drive the catapult stick to extend and retract, instead of a hydraulic motor. An electromagnetic brake is used instead of a hydraulic lock for locking, thus avoiding the problem that the hydraulic drive device cannot accurately control the position of the catapult stick, which affects the safety of the catapult stick's operation.

[0034] The present invention relates to an electric drive device for a catapult launch stick of a shipborne aircraft. Other advantages, objectives and features of the present invention will be apparent in part from the following description, and in part from the understanding of those skilled in the art through study and practice of the invention. Attached Figure Description

[0035] The accompanying drawings are provided to further illustrate the invention and form part of the specification. They are used in conjunction with embodiments of the invention to explain the invention and do not constitute a limitation thereof. In the drawings:

[0036] Figure 1 This is a schematic diagram of the structure of an electric drive device for a shipborne aircraft catapult lever according to the present invention;

[0037] Figure 2 This is a schematic diagram of the structure of an electric drive device for a shipborne aircraft catapult lever according to the present invention;

[0038] Figure 3 This is a schematic diagram of the brushless motor mechanism of an electric drive device for a catapult launch bar of a shipborne aircraft according to the present invention.

[0039] Figure 4 This is a side view of the deceleration mechanism of an electric drive device for a shipborne aircraft catapult stick according to the present invention;

[0040] Figure 5 This is a side view of the deceleration mechanism of an electric drive device for a shipborne aircraft catapult stick according to the present invention;

[0041] Figure 6 This is a side view of the locking mechanism of an electric drive device for a carrier-based aircraft catapult lever according to the present invention;

[0042] Figure 7 This is a side view of the locking mechanism of an electric drive device for a carrier-based aircraft catapult lever according to the present invention;

[0043] Figure 8 This is a schematic diagram of a measuring device for an electric drive device for a shipborne aircraft catapult lever according to the present invention;

[0044] Figure 9 This is a side view of the first sun gear of an electric drive device for a carrier-based aircraft catapult lever according to the present invention;

[0045] Figure 10 This is a side view of the second sun gear of an electric drive device for a carrier-based aircraft catapult lever according to the present invention;

[0046] Figure 11 This is a schematic diagram of a high-precision real-time position control system for an electric drive device for a shipborne aircraft catapult boom according to the present invention.

[0047] Explanation of reference numerals in the attached drawings: 1. Controller; 2. Cable; 3. Housing; 4. Brushless motor; 5. Electromagnetic brake; 6. Mounting base; 7. Locking mechanism; 8. Reduction mechanism; 9. Dual-redundancy position measuring mechanism; 10. First gear; 11. Third gear; 12. Second gear; 14. First planetary gear; 15. Second planetary gear; 16. Fourth gear; 17. Fifth gear; 18. Sixth gear; 19. Eighth gear; 20. First rotating rod; 21. First sun gear; 22. Second... 23. Rotating rod; 24. Second sun gear; 25. Third rotating rod; 26. Fourth rotating rod; 27. Seventh gear; 28. Fifth rotating rod; 29. ​​Output shaft; 30. Drive gear; 31. Tenth gear; 32. Ratchet; 33. Pawl; 34. Ninth gear; 35. Lead screw; 36. DC motor; 37. Sliding block; 38. Position sensor; 39. First transmission wheel; 40. Third transmission wheel; 41. Second transmission wheel; 42. First internal gear ring; 43. Second internal gear ring. Detailed Implementation

[0048] The present invention will now be described in further detail with reference to the accompanying drawings and embodiments, so that those skilled in the art can implement it based on the description.

[0049] It should be understood that terms such as “having,” “comprising,” and “including” as used herein do not exclude the presence or addition of one or more other elements or combinations thereof.

[0050] like Figures 1-10 As shown, the present invention provides an electric drive device for a carrier-based aircraft catapult launch stick, comprising:

[0051] A brushless motor 4 is provided with a reduction mechanism 8 at one end and an electromagnetic brake 5 at the other end. Both the brushless motor 4 and the electromagnetic brake 5 are electrically connected to the controller 1 via a cable 2.

[0052] The working principle and beneficial effects of the above technical solution are as follows: In actual use, the controller 1 controls the brushless motor 4 in conjunction with the reduction mechanism 8 to drive the launch rod to extend and retract instead of the hydraulic motor, and the electromagnetic brake 5 replaces the hydraulic lock for locking. This avoids the problem that the hydraulic drive device cannot accurately control the position of the launch rod, which affects the safety of the launch rod.

[0053] In one embodiment, the deceleration mechanism 8 includes:

[0054] The housing 3 contains a primary transmission mechanism, a secondary transmission mechanism, and a tertiary transmission mechanism. The secondary transmission mechanism is located within the housing 3, and the primary transmission mechanism is connected to the secondary transmission mechanism. The tertiary transmission mechanism is located on the side of the secondary transmission mechanism away from the primary transmission mechanism, and the tertiary transmission mechanism is connected to the secondary transmission mechanism.

[0055] The working principle and beneficial effects of the above technical solution are as follows: In actual use, the brushless motor 4 drives the secondary transmission mechanism through the primary transmission mechanism, and drives the tertiary transmission mechanism through the secondary transmission mechanism, thereby achieving a large transmission ratio reduction within a limited space.

[0056] In one embodiment, the primary transmission mechanism includes:

[0057] First gear 10, the output shaft of the brushless motor 4 extends into the housing 3 and is connected to the first gear 10;

[0058] The second gear 12 is rotatably disposed inside the housing 3 via a rotating shaft, and the second gear 12 meshes with the first gear 10.

[0059] The third gear 11 is rotatably disposed inside the housing 3 via the first rotating rod 20, and the third gear 11 meshes with the second gear 12.

[0060] The working principle and beneficial effects of the above technical solution are as follows: In actual use, the brushless motor 4 drives the first gear 10 to rotate through the output shaft. The first gear drives the third gear 11 to rotate through the second gear 12. The third gear 11 drives the secondary transmission mechanism to rotate through the first rotating rod 20, so that the secondary transmission mechanism is set parallel to the brushless motor, thereby saving a lot of space.

[0061] In one embodiment, the secondary transmission mechanism includes:

[0062] The first sun gear 21 is sleeved on the first rotating rod 20;

[0063] The second rotating rod 22 has one end connected to the first planetary carrier. The first planetary carrier is evenly provided with a plurality of first planetary gears 14. The first sun gear 21 meshes with all the first planetary gears 14.

[0064] The first internal gear ring 41 is located on the outer periphery of the first planetary gear 14 and the inner wall of the first internal gear ring 41 meshes with the first planetary gear 14. The first internal gear ring 41 is fixed on the inner wall of the housing 3.

[0065] The second sun gear 23 is sleeved on the second rotating rod 22;

[0066] The third rotating rod 24, one end of which is connected to the second planetary carrier, and the second planetary carrier is evenly provided with a plurality of second planetary gears 15, and the second sun gear 23 meshes with all the second planetary gears 15;

[0067] The second internal gear ring 42 is located on the outer periphery of the second planetary gear 15 and its inner wall meshes with the second planetary gear 15. The second internal gear ring 42 is fixed on the inner wall of the housing 3.

[0068] The working principle and beneficial effects of the above technical solution are as follows: In actual use, the first rotating rod 20 drives the first sun gear 21 to rotate. The first sun gear 21 drives the second rotating rod 22 to rotate through multiple first planetary gears 14 and the first planetary carrier. The second rotating rod 22 drives the second sun gear 23 to rotate. The second sun gear 23 drives the third rotating rod 24 to rotate through the second planetary gears 15 and the second planetary carrier. In the transmission process from the first rotating rod 20 to the third rotating rod 24, the speed is reduced through two planetary mechanisms, achieving a large transmission ratio for speed reduction.

[0069] In one embodiment, the three-stage transmission mechanism includes: a fourth gear 16, which is disposed on the third rotating rod 24;

[0070] The fourth rotating rod 25 has two ends rotatably mounted on the inner wall of the housing 3. A fifth gear 17 and a sixth gear 18 are sleeved on the fourth rotating rod 25. The fifth gear 17 meshes with the fourth gear 16, and the sixth gear 18 meshes with the seventh gear 26. The seventh gear 26 is rotatably mounted on the inner wall of the housing 3 via the fifth rotating rod 27.

[0071] An output shaft 28 passes through the housing 3, and an eighth gear 19 is sleeved on the output shaft 28. The eighth gear 19 meshes with the seventh gear 26.

[0072] The working principle and beneficial effects of the above technical solution are as follows: In actual use, the third rotating rod 24 drives the fifth gear 17 to rotate, the fifth gear 17 drives the fourth rotating rod 25 to rotate through the sixth gear 18, the fourth rotating rod 25 drives the seventh gear 26 to rotate through the sixth gear 18, the seventh gear 26 drives the output shaft 28 to rotate through the eighth gear 19, and the output shaft 28 drives the release and retraction of the ejector rod.

[0073] In one embodiment, the housing 3 is further provided with a locking mechanism 7, the locking mechanism 7 comprising:

[0074] A DC motor 35 is fixed inside the housing 3 and electrically connected to the controller 1. The output end of the DC motor 35 is provided with a drive gear 29, which meshes with a ninth gear 33. The ninth gear 33 is rotatably disposed inside the housing 3.

[0075] A lead screw 34 is rotatably connected to the inner wall of the housing 3 at both ends. A tenth gear 30 and a sliding block 36 are sleeved on the lead screw 34. The tenth gear 30 meshes with the ninth gear 33. The sliding block 36 is slidably connected to the inner wall of the housing 3 and fixedly connected to the outer wall of the ratchet 31. The output shaft 28 passes through the ratchet 31 and is fixedly provided with several pawls 32. The pawls 32 are adapted to the ratchet 31. The lead screw 34 is arranged parallel to the output shaft 28. The output shaft 28 and the sliding block 36 are connected by threads.

[0076] The working principle and beneficial effects of the above technical solution are as follows: In actual use, when locking is required, the DC motor 35 is started, the DC motor 35 drives the drive gear 29 to rotate, the drive gear 29 drives the tenth gear 30 to rotate through the ninth gear 33, the tenth gear 30 drives the lead screw 34 to rotate, the lead screw 34 drives the sliding block 36 to move through the thread, the sliding block 36 drives the ratchet 31 to move, so that the ratchet 31 engages with several pawls 32, thereby completing the locking of the output shaft 28. The locking mechanism 7 completes the locking of the output shaft 28, increasing the stability of the locking.

[0077] In one embodiment, the output shaft 28 is further provided with a dual-redundancy position measuring mechanism 9, the dual-redundancy position measuring mechanism 9 comprising:

[0078] The measuring devices are symmetrically located at both ends of the output shaft 28;

[0079] The measuring device includes:

[0080] Mounting base 6, the mounting base 6 is provided with a position sensor 37, the position sensor 37 is electrically connected to the controller 1 through a cable 2, the cable 2 passes through the mounting base 6, the position sensor 37 is rotatably provided with a first transmission wheel 38, the mounting base 6 is rotatably provided with a second transmission wheel 40, the position sensor 37 is provided with a first transmission wheel 38, the first transmission wheel 38 and the second transmission wheel 40 mesh.

[0081] The third transmission wheel 39 is sleeved on the output shaft 28 and meshes with the second transmission wheel 40.

[0082] The working principle and beneficial effects of the above technical solution are as follows: In actual use, the output shaft 28 drives the second transmission wheel 40 to rotate through the third transmission wheel 39, and the second transmission wheel 40 drives the first transmission wheel 38 to rotate, thereby transmitting the rotation angle of the output shaft 28 to the position sensor 37, so as to realize the accurate measurement of the position of the output shaft.

[0083] In one embodiment, the diameter of the eighth gear 19 is larger than that of the sixth gear 18.

[0084] The working principle and beneficial effects of the above technical solution: The diameter of the eighth gear 19 is larger than that of the sixth gear 18, which enables the three-stage transmission mechanism to achieve a certain transmission ratio reduction.

[0085] like Figure 11 As shown, it also includes: a high-precision real-time position control system, which receives instructions from the host computer, drives the actuator to rotate in real time, and feeds back relevant information to the host computer in real time.

[0086] The controller features a high-speed CPU and MOSFET module protection in its hardware design.

[0087] The working principle and beneficial effects of the above technical solution are as follows: The high-precision real-time position control system receives instructions from the host computer, drives the actuator to rotate in real time, and feeds back relevant information to the host computer in real time. It also performs high-precision real-time sampling of voltage, current, temperature and position sensor signals, real-time conversion of Hall signals, electromagnetic interference and surge suppression, parameter storage and management, etc.

[0088] In the description of this invention, it should be understood that the terms "center," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," "counterclockwise," "axial," "radial," and "circumferential" indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing this invention and simplifying the description, and are not intended to indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this invention.

[0089] In this invention, unless otherwise explicitly specified and limited, the terms "installation," "connection," "linking," and "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection, an electrical connection, or a connection that allows communication between them; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components, unless otherwise explicitly limited. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0090] Although embodiments of the present invention have been disclosed above, they are not limited to the applications listed in the specification and embodiments. They can be applied to various fields suitable for the present invention. Other modifications can be easily made by those skilled in the art. Therefore, without departing from the general concept defined by the claims and their equivalents, the present invention is not limited to the specific details and illustrations shown and described herein.

Claims

1. A shipboard aircraft catapult electric drive apparatus characterized by, Include: Brushless motor (4), one end of the brushless motor (4) is provided with a reduction mechanism (8), the other end of the brushless motor (4) is provided with an electromagnetic brake (5), the brushless motor (4) and electromagnetic brake (5) are electrically connected through the cable (2) with the controller (1); The reduction mechanism (8) comprises: The shell (3) is provided with a primary transmission mechanism, a secondary transmission mechanism and a tertiary transmission mechanism, the secondary transmission mechanism is arranged in the shell (3), the primary transmission mechanism is in transmission connection with the secondary transmission mechanism, the tertiary transmission mechanism is arranged on the side, away from the primary transmission mechanism, of the secondary transmission mechanism, and the tertiary transmission mechanism is in transmission connection with the secondary transmission mechanism, the brushless motor (4) drives the secondary transmission mechanism through the primary transmission mechanism, and drives the tertiary transmission mechanism through the secondary transmission mechanism, and the tertiary transmission mechanism comprises an output shaft (28), and the output shaft (28) drives the extension and retraction of the ejection rod; The shell (3) is also provided with a locking mechanism (7), and the locking mechanism (7) comprises: A DC motor (35) is fixedly arranged in the shell (3), the DC motor (35) is electrically connected with the controller (1), the output end of the DC motor (35) is provided with a driving gear (29), the driving gear (29) is in mesh with a ninth gear (33), and the ninth gear (33) is rotatably arranged in the shell (3); A lead screw (34) is rotatably connected to the inner wall of the shell (3) at both ends, a tenth gear (30) and a sliding block (36) are sleeved on the lead screw (34), the tenth gear (30) is in mesh with the ninth gear (33), the sliding block (36) is slidably connected to the inner wall of the shell (3), the sliding block (36) is fixedly connected with the outer wall of a ratchet wheel (31), the output shaft (28) penetrates through the ratchet wheel (31), a plurality of pawls (32) are fixedly arranged on the output shaft (28), and the pawls (32) are matched with the ratchet wheel (31).

2. The aircraft ejection rod electric drive device according to claim 1, wherein The primary transmission mechanism comprises: A first gear (10), the output shaft of the brushless motor (4) extends into the shell (3) and is connected with the first gear (10); A second gear (12) is rotatably arranged in the shell (3) through a rotating shaft, and the second gear (12) is in mesh with the first gear (10); A third gear (11) is rotatably arranged in the shell (3) through a first rotating rod (20), and the third gear (11) is in mesh with the second gear (12).

3. The aircraft ejection rod electric drive device according to claim 2, wherein The secondary transmission mechanism comprises: A first sun gear (21) is sleeved on the first rotating rod (20); A second rotating shaft (22) is connected to the first carrier, and a plurality of first planetary gears (14) are evenly arranged on the first carrier, and the first sun gear (21) is engaged with all the first planetary gears (14); A first inner ring gear (41) is arranged on the outer periphery of the first planetary gear (14), and the inner wall of the first inner ring gear (41) is engaged with the first planetary gear (14), and the first inner ring gear (41) is fixed on the inner wall of the shell (3).

4. The electric drive device for a carrier-based aircraft catapult according to claim 3, wherein the second transmission mechanism further comprises: The second transmission mechanism further comprises: A second sun gear (23) is sleeved on the second rotating shaft (22); A third rotating shaft (24) is connected to the second carrier, and a plurality of second planetary gears (15) are evenly arranged on the second carrier, and the second sun gear (23) is engaged with all the second planetary gears (15); A second inner ring gear (42) is arranged on the outer periphery of the second planetary gear (15), and the inner wall of the second inner ring gear (42) is engaged with the second planetary gear (15), and the second inner ring gear (42) is fixed on the inner wall of the shell (3).

5. The electric drive device for a carrier-based aircraft catapult according to claim 4, wherein the third transmission mechanism further comprises: The third transmission mechanism further comprises: A fourth rotating shaft (25) is rotatably arranged on the inner wall of the shell (3), and a fifth gear (17) and a sixth gear (18) are sleeved on the fourth rotating shaft (25), the fifth gear (17) is engaged with the fourth gear (16), the sixth gear (18) is engaged with a seventh gear (26), and the seventh gear (26) is rotatably arranged on the inner wall of the shell (3) through a fifth rotating shaft (27); The output rotating shaft (28) passes through the shell (3), and an eighth gear (19) is sleeved on the output rotating shaft (28), and the eighth gear (19) is engaged with the seventh gear (26).

6. The electric drive device for a carrier-based aircraft catapult according to claim 5, wherein the output rotating shaft (28) is further provided with a dual-redundancy position measuring mechanism (9), and the dual-redundancy position measuring mechanism (9) comprises: Two measuring devices are symmetrically arranged at both ends of the output rotating shaft (28).

7. The electric drive device for a carrier-based aircraft catapult according to claim 6, wherein the measuring device comprises: ​ ​ The mounting seat (6) is provided with a position sensor (37), the position sensor (37) is electrically connected with the controller (1) through a cable (2), the cable passes through the mounting seat (6), a first transmission wheel (38) is rotatably arranged on the position sensor (37), a second transmission wheel (40) is rotatably arranged on the mounting seat (6), and the first transmission wheel (38) and the second transmission wheel (40) are engaged. A third transmission wheel (39) is sleeved on the output rotating shaft (28), and the third transmission wheel (39) is engaged with the second transmission wheel (40).

8. The electric drive device for a carrier-based aircraft catapult according to claim 5, characterized in that The diameter of the eighth gear (19) is greater than that of the sixth gear (18).

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