Aircraft ground electromagnetic rapid propulsion mechanism and propulsion method

Abstract

The invention discloses an aircraft ground electromagnetic rapid propulsion mechanism and propulsion method, and belongs to the technical field of electromagnetic propulsion acceleration. The mechanism comprises an ejection vehicle, a connecting rod, a wheel pressure device, a traction cable, a ground guide rail and a ground power vehicle. The catapult car is matched with stress seats on the two sides of an aircraft belly through propelling arms symmetrically arranged on the catapult car and propelling rods on propelling heads, and locking and unlocking are achieved. During propelling, the catapult car is dragged to accelerate by the power car through the traction cable, and the propelling rod abuts against the stress base to push the aircraft to move along the ground guide rail. When the catapult car is braked, the catapult car and the aircraft are automatically separated; the wheel pressing device restrains the front wheels of the aircraft through the U-shaped pressing wheel terminal, and it is guaranteed that the aircraft runs close to the ground along the rail. The device is simple in structure, convenient in butt joint and reliable in unlocking, supports continuous and rapid ejection, and is suitable for ground testing and catapult-assisted take-off of aircrafts such as unmanned aerial vehicles.

Description

Technical Field

[0001] This invention belongs to the field of propulsion and acceleration technology, specifically relating to a ground electromagnetic rapid propulsion mechanism and method for aircraft, applicable to rapid catapult takeoff of manned or unmanned aircraft, as well as ground acceleration testing and evaluation of transportation vehicles. Background Technology

[0002] Currently, using pneumatic, hydraulic, or electromagnetic power sources, objects such as aircraft and transportation vehicles can be rapidly propelled and accelerated to the required speed by instantaneously releasing pre-stored energy. This enables ground overload testing and aerodynamic testing of aircraft and transportation vehicles. In particular, this catapult technology for propulsion and acceleration can achieve ultra-short-distance catapult takeoff of drones, greatly reducing the fuel carried by the aircraft and increasing its carrying capacity. This is the development trend of unmanned aerial vehicle takeoff.

[0003] However, existing propulsion mechanisms still face a series of challenges in terms of rapid connection, reliable locking, smooth acceleration, and safe separation from aircraft. For example, aircraft carrier electromagnetic catapults transmit power to carrier-based aircraft via a rigid connection between the catapult's concave catapult slide (reciprocating carriage) and the aircraft's nose landing gear catapult traction rod. This concave catapult slide propels the catapult traction rod fixed to the aircraft's nose landing gear, accelerating the aircraft. Once the target speed or predetermined position is reached, the traction rod's automatic release mechanism is triggered, disengaging from the concave catapult slide mechanically or electromagnetically. The catapult mechanism then brakes the concave catapult slide to a stop, while the aircraft continues to accelerate and take off. To achieve catapult takeoff, the aircraft's nose landing gear and other components require special reinforcement design, leading to a loss of payload. Different aircraft require different concave catapult slides, or different aircraft may use the same traction rod, necessitating extensive modifications to the aircraft. Applying this approach to unmanned aerial vehicle (UAV) catapults will impose significant costs on UAV suppliers and users.

[0004] Existing patent technologies attempt to address this problem, but still have significant limitations. For example, Chinese patent CN113353278B discloses a high-thrust mechanism and catapult system, which improves thrust and guidance accuracy, but the system structure is complex, requiring the UAV to be hoisted onto the launch pad and then manually connected, making rapid continuous launches difficult. Another patent, CN114435618B, proposes a traction catapult device and system suitable for overhead rails, but its solution is not applicable to rapid ground propulsion scenarios. Furthermore, Chinese patent application 201811269329.2 uses a locking and releasing method that combines a cable and a cable cutter; its unlocking process relies on the precise coordination of both, posing a reliability risk.

[0005] In summary, there is an urgent need for an electromagnetic rapid propulsion mechanism that is suitable for ground propulsion, has a simple structure, can be quickly connected, can be reliably unlocked, can achieve rapid and continuous ejection, and requires minimal modification to the aircraft. Summary of the Invention

[0006] To address the aforementioned technical problems, this invention provides a ground-based electromagnetic rapid propulsion mechanism and method for aircraft, used to propel aircraft and other vehicles through rapid acceleration for catapult takeoff or high-speed operational testing. Typically, these aircraft have landing gear and support wheels. During the acceleration process propelled by the catapult, the support wheels are in direct contact with the ground surface. After the catapult propels the aircraft to accelerate and reaches the target speed or position, the catapult brakes, separating from the aircraft. The aircraft then continues its run and accelerates, achieving short-distance propulsion acceleration for takeoff or high-speed ground operational testing.

[0007] To achieve the above objectives, the present invention adopts the following technical solution:

[0008] A ground electromagnetic rapid propulsion mechanism for an aircraft includes: a catapult vehicle, a wheel press, a connecting rod, a traction cable, a ground guide rail, and a ground power vehicle;

[0009] The catapult vehicle includes a frame body, with push arms symmetrically arranged on both sides of the frame body. A push head is provided at the end of each push arm, and a push rod that can rotate relative to the push head is movably connected to the push head.

[0010] The catapult vehicle engages with the force-bearing seats on both sides of the aircraft's belly via the push rod, which is used to lock or propel the force-bearing seats.

[0011] The ground power vehicle consists of two units, symmetrically arranged on both sides of the ground guide rail. The traction cable passes through the vehicle-mounted fixed pulley group set on the catapult vehicle, and its two ends are respectively connected to the two ground power vehicles to form a V-shaped traction layout.

[0012] The wheel pressure device is connected to the front end of the catapult vehicle and is used to constrain the front landing gear wheels of the aircraft to run close to the ground during propulsion, so as to avoid the aircraft pitching up during acceleration.

[0013] Furthermore, the push head is clamp-shaped with a push rod shaft in the middle. The push rod is fixed on the push rod shaft and can rotate 90° relative to the push head between horizontal and vertical positions. The push head is also equipped with an anti-loosening device, one end of which is fixed on the push head and the other end is fixed on the push rod.

[0014] Furthermore, when the catapult accelerates, the propulsion rod is lifted upward under the action of the aircraft's support seat, the propulsion head is unlocked from the support seat, and at the same time, the body of the propulsion rod pushes against the bearing surface of the support seat to accelerate the aircraft; when the catapult brakes, the propulsion head automatically separates from the aircraft's support seat.

[0015] Furthermore, the wheel pressure device includes upper and lower guide wheels, left and right guide wheels, a U-shaped pressure wheel terminal, and a wheel pressure device adjusting joint; the connecting rod is fixed on the catapult vehicle, the wheel pressure device adjusting joint is fixed at the end of the connecting rod, and the U-shaped pressure wheel terminal is fixed on the wheel pressure device adjusting joint; the upper and lower guide wheels and the left and right guide wheels are symmetrically arranged on both sides of the connecting rod and are located inside the ground guide rail.

[0016] Furthermore, by adjusting the bolts on the wheel pressure adjustment joint, the orientation and force of the U-shaped pressure wheel terminal pressing on the aircraft's front landing gear wheel axle can be adjusted.

[0017] Furthermore, the ground guide rail is composed of several Z-shaped structural units spliced ​​together; the catapult vehicle also includes left and right guide wheels of the frame vehicle body and upper and lower guide wheels of the frame vehicle body. The left and right guide wheels of the frame vehicle body are engaged with the inner wings of the Z-shaped ground guide rail, and the upper and lower guide wheels of the frame vehicle body are engaged with the upper and lower sides of the Z-shaped ground guide rail.

[0018] Furthermore, the ground-powered vehicle includes a drive motor, a drive controller, and a drive transmission mechanism; the drive controller coordinates the drive motor, and through the drive transmission mechanism drives the traction cable to retract or release the cable, thereby accelerating or braking the catapult vehicle.

[0019] On the other hand, the present invention provides a propulsion method applied to the aforementioned propulsion mechanism, comprising:

[0020] Step 1, docking and locking: Move the aircraft to the catapult vehicle, press down the push rods on both sides of the catapult vehicle to lock the load seats on both sides of the aircraft's belly, and at the same time press the wheel pressure device onto the aircraft's front landing gear wheel.

[0021] Step 2, Acceleration and Propulsion: Start the ground power vehicle and use the traction cable to pull the catapult car along the ground guide rail to accelerate; during acceleration, the propulsion rod is lifted upward under the reaction thrust of the force seat, the propulsion head is unlocked from the force seat, and at the same time the rod body of the propulsion rod presses against the force seat, pushing the aircraft to accelerate together;

[0022] Step 3 Braking and Separation: When the aircraft is accelerated to the target speed or reaches the predetermined position, the ground power vehicle is braked, the catapult decelerates, the propulsion head automatically separates from the aircraft's load-bearing seat, and the aircraft continues to glide forward relying on inertia and its own power.

[0023] In a second aspect, the present invention provides a ground-powered vehicle, including a drive motor, a drive controller, and a drive transmission mechanism. The drive controller includes one or more processors and a memory for storing one or more programs. When the one or more programs are executed by the one or more processors, the one or more processors implement the aforementioned propulsion method.

[0024] Thirdly, the present invention provides a ground electromagnetic rapid propulsion system for an aircraft, including the aforementioned propulsion mechanism and an aircraft; force-bearing seats that cooperate with the propulsion rod are provided on both sides of the fuselage of the aircraft.

[0025] The beneficial effects of this invention are as follows:

[0026] Simple structure and low cost: The mechanism adopts a frame-type vehicle body and modular guide rail design, with strong component versatility, low manufacturing and maintenance costs, and a compact overall structure, which facilitates rapid deployment and transfer.

[0027] Reliable connection and safe separation: Through the mechanical engagement of the push rod with the force-bearing seats on both sides of the aircraft's fuselage, reliable locking in the non-operating state and automatic unlocking in the operating state are achieved. The unlocking process is automatically triggered by the acceleration motion, and no external intervention is required during separation, ensuring safety and reliability. The push rod of this invention is not a simple pushing component, but a composite mechanism integrating locking, unlocking, and anti-backlock functions. The cooperation between the push rod and the anti-loosening device enables smooth switching between four states: reliable locking in the non-operating state, automatic unlocking in the acceleration state, anti-backlocking in the propulsion state, and automatic separation in the braking state. This solves the technical problems of traditional catapult systems that require external triggering for separation or have unreliable separation.

[0028] Accelerated and stable operation with controllable aircraft attitude: The unique wheel pressure device, left and right guide wheels, and upper and lower guide wheels cleverly solve the technical problem of nose pitch during aircraft acceleration; the multiple functions of the push rod and anti-loosening device effectively solve the problems of reliable locking, unlocking, and anti-locking.

[0029] Highly adaptable and easy to modify: The aircraft only requires simple load-bearing seats to be symmetrically installed on both sides of the fuselage, without the need for large-scale reinforcement and modification of key load-bearing structures such as the nose landing gear. This significantly reduces the difficulty and cost of modifying the aircraft while effectively preserving its payload capacity. The wheel pressure unit is equipped with adjustable joints to accommodate the nose landing gear of different aircraft models.

[0030] Supports continuous and rapid operations: The docking of multiple catapult vehicles and multiple aircraft can be prepared in parallel, enabling rapid and continuous catapult launches of aircraft in a "queueing" manner, greatly shortening the launch interval time, achieving cluster take-off, and improving overall operational efficiency.

[0031] It has a wide range of applications: it is not only suitable for short-distance catapult takeoff of various unmanned aerial vehicles, but also for various scenarios such as acceleration testing, overload testing and aerodynamic evaluation of ground vehicles. Attached Figure Description

[0032] Figure 1 This is a schematic diagram of a ground electromagnetic propulsion mechanism for an aircraft according to the present invention;

[0033] Figure 2 This is a three-dimensional diagram of a catapult vehicle for a ground electromagnetic propulsion mechanism of an aircraft according to the present invention;

[0034] Figure 3 This is a diagram of the force-bearing base of the catapult vehicle's propulsion rod locking aircraft according to the present invention;

[0035] Figure 4 This is a diagram showing the state of the propellant vehicle after the catapult push rod of the present invention is unlocked;

[0036] Figure 5 This is a diagram of the landing gear wheel compressor for the aircraft of the present invention;

[0037] Figure 6 This is a diagram of the front wheel of the aircraft landing gear wheel press of the present invention;

[0038] Figure 7 This is a schematic diagram of the left and right guide wheels and ground guide rails of the catapult vehicle frame of the present invention;

[0039] Figure 8 This is a schematic diagram of the upper and lower guide wheels and ground guide rails of the catapult vehicle frame of the present invention;

[0040] Figure 9 This is a stress cloud diagram of the catapult vehicle of the present invention.

[0041] Figure label:

[0042] 1. Catapult vehicle; 2. Wheel pressure unit; 3. Traction cable; 4. Ground guide rail; 41. Ground guide rail base plate; 5. Ground power vehicle; 6. Catapult vehicle frame body; 61. Rear main beam of frame body; 62. Front main beam of frame body; 63. Front protruding beam of frame body; 7-1 and 7-2 on-board pulley blocks; 7-3 and 7-4 metal square tubes; 8. Left and right guide wheels of frame body; 9. Upper and lower guide wheels of frame body; 10. Propulsion arm; 11. Propulsion head; 12. Propulsion rod; 13. Anti-loosening device; 14. Push rod shaft; 51. Drive motor; 52. Drive controller; 53. Drive transmission mechanism; 21. Upper and lower guide wheels of wheel pressure unit; 22. Left and right guide wheels of wheel pressure unit; 23. U-shaped pressure wheel terminal; 24. Wheel pressure unit adjusting joint; 25. Connecting rod; 26. Front landing gear wheel of aircraft; 100. Detailed Implementation

[0043] The present invention will be further described below with reference to the accompanying drawings and embodiments.

[0044] Figure 1 This is a schematic diagram of a ground-based electromagnetic rapid propulsion structure for an aircraft. The system includes at least an catapult vehicle 1, a wheel pressure unit 2, a traction cable 3, a ground guide rail 4, and a ground power vehicle 5.

[0045] The catapult vehicle 1 includes a catapult vehicle frame body 6, a front main beam 62 of the frame body, a rear main beam 61 of the frame body, vehicle-mounted fixed pulleys 7-1 and 7-2, left and right guide wheels 8 of the frame body, upper and lower guide wheels 9 of the frame body, a propulsion arm 10, a propulsion head 11, a propulsion rod 12, and an anti-loosening device 13. Meanwhile, a connecting rod 25 is fixed to the outside of the front protruding beam 63 of the frame body, and a wheel pressure device 2 is fixed to the end of the connecting rod 25. The catapult vehicle 1, through the propulsion arm 10 and the propulsion head 11, pushes the aircraft's load-bearing seat 100 along the ground guide rail 4.

[0046] Ground power vehicles 5 are arranged on both sides of the ground guide rail 4. Each ground power vehicle 5 includes a drive motor 51, a drive controller 52, and a drive transmission mechanism 53. The traction cable 3 passes through the vehicle-mounted pulley blocks 7-1 and 7-2, and its two ends are connected to the drive transmission mechanism 53. The drive controllers 52 of the two ground power vehicles 5 coordinate with the drive motors 51 to drive the traction cable 3 to retract or release the cable through the drive transmission mechanism 53, thereby propelling the catapult vehicle 1 to accelerate or brake. The catapult vehicle 1 then propels the aircraft to accelerate.

[0047] Specifically, the two ground-powered vehicles 5 are arranged in a mirror image at a certain distance apart, and the ground guide rail 4 is arranged along the center line between the two ground-powered vehicles 5. The two ground-powered vehicles 5, the traction cable 3, and the catapult vehicle 1 form a slingshot-shaped V-shaped arrangement.

[0048] Figure 2 This is a three-dimensional diagram of an aircraft ground electromagnetic propulsion mechanism catapult vehicle according to the present invention. The catapult vehicle 1 is a frame structure made of composite materials. While ensuring strength under maximum thrust operating conditions, it is designed to be as lightweight as possible, thus reducing the ineffective load during propulsion. The catapult vehicle 1 has a propulsion arm 10 extending symmetrically from each side of the vehicle body. Each propulsion arm 10 is provided with a propulsion head 11 at its end. The propulsion head 11 is provided with a movable propulsion rod 12 and an anti-loosening device 13 for constraining its attitude. The anti-loosening device 13 can be a spring, a hydraulic rod, or a pneumatic rod. The function of the propulsion rod 12 is to interact with the aircraft force-bearing seat 100, locking the aircraft force-bearing seat 100 located on both sides of the aircraft belly so that the aircraft cannot move, or to propel the aircraft force-bearing seat 100 and the aircraft together to accelerate.

[0049] The catapult vehicle frame body 6 is a rectangular frame structure. On the two outer ends of the front main beam 62 of the catapult vehicle frame body, the vehicle-mounted pulley blocks 7-1 and 7-2 are arranged and protrude forward a certain distance from the catapult vehicle frame body 6. The vehicle-mounted pulley blocks 7-1 and 7-2 are respectively fixed on the metal square tubes 7-3 and 7-4 on the outer side of the front main beam 62 of the frame body. The traction cable 3 passes through the vehicle-mounted pulley blocks 7-1 and 7-2 at both ends and is then connected to the drive transmission mechanism 53 of the two ground power vehicles 5.

[0050] The left and right guide wheels 8 and the upper and lower guide wheels 9 of the frame vehicle body are installed on the lower part of the rear main beam 61 of the frame vehicle body. When the catapult vehicle 1 is running, the left and right guide wheels 8 and the upper and lower guide wheels 9 of the frame vehicle body are located inside the ground guide rail 4. The push arm 10 is a frame structure made of metal square tube, which is fixed on both sides of the catapult vehicle frame vehicle body 6 and perpendicular to the catapult vehicle frame vehicle body 6. The push arm 10 is equipped with a push head 11 at the end. The push head 11 is in the shape of a clamp plate, with a push rod shaft 14 arranged in the middle. The push rod 12 is located on the inner side of the clamp plate and is fixed on the push rod shaft 14 on the inner side of the clamp plate. It can rotate 90° between the horizontal and vertical positions.

[0051] Specifically, when the catapult 1 is not activated, the push rod 12 on the push head 11 locks the force-bearing seat 100 of the aircraft. The aircraft cannot unlock and separate from the push head 11 by its own power. At this time, the aircraft cannot move by its own power. When the catapult 1 accelerates, the push rod 12 of the push head 11 raises its head under the action of the force-bearing seats 100 on both sides of the aircraft. The push head 11 unlocks from the force-bearing seat 100, and the force-bearing seat 100 pushed by the push rod 12 accelerates together, driving the aircraft to accelerate as well.

[0052] Figure 3 This is a diagram of the catapult launcher's push rod locking the aircraft's load-bearing seat. Before the catapult launcher 1 accelerates, the push rod 12 is pressed down to lock the aircraft's load-bearing seat 100. If the catapult launcher 1 does not start, the aircraft and load-bearing seat 100 cannot unlock from the push rod 12 even if the engine is running. This ensures that the aircraft and load-bearing seat 100 cannot operate when the catapult launcher 1 is not accelerating. The push head 11 is fixed to the end of the push arm 10. The push head 11 is in the shape of a clamp, with a push rod shaft 14 in the middle. The push rod 12 is located on the inner side of the clamp and fixed on the middle push rod shaft 14 on the inner side of the clamp. It can rotate 90° between horizontal and vertical positions. The anti-loosening device 13 is fixed to one end of the push head 11 and the other end is fixed to the outer side of the push rod 12.

[0053] Figure 4This is a diagram showing the state of the catapult vehicle's push rod unlocking and propulsion of the aircraft. When the catapult vehicle 1 starts to accelerate, the push rod 12 pushes the force-bearing seat 100 of the aircraft, and the push rod 12 lifts up, unlocking from the force-bearing seat 100 of the aircraft, thus propelling the aircraft to accelerate. An anti-loosening device 13 is provided on the push rod 12. At this time, the anti-loosening device 13 pulls the push rod 12 backward to prevent the push rod 12 from accidentally tilting downward and locking the aircraft under the action of other external forces such as aircraft vibration. When the catapult vehicle 1 brakes, it decelerates and stops under the action of external braking force, and the push head 11 automatically separates from the force-bearing seat 100 of the aircraft, and the aircraft continues to move forward.

[0054] When the system is activated and the catapult 1 begins to accelerate, the push rod 12 receives a forward thrust from the aircraft's support seat 100, causing its front end to automatically lift upwards and unlock itself from the support seat 100. After unlocking, the rod body of the push rod 12 presses against the support surface of the support seat 100, propelling the aircraft to accelerate. During this process, the anti-loosening device 13 continuously pulls the push rod 12 backwards to prevent it from accidentally tilting down and relocking the aircraft, ensuring smooth propulsion.

[0055] When the aircraft is accelerated to the target speed or reaches the predetermined position, the catapult 1 brakes and decelerates under external braking force. Since the push rod 12 and the force-bearing seat 100 are in an unlocked pushing state, they will automatically separate. The catapult 1 stops, while the aircraft continues to glide forward by inertia, thereby achieving short takeoff or test operation.

[0056] Figure 5 This is a diagram of the aircraft landing gear wheel pressure device of the present invention. A connecting rod 25 is fixed to the front end of the front protruding beam 63 of the catapult vehicle frame body. The connecting rod 25 is made of aluminum alloy square tube. An aircraft wheel pressure device 2 is installed at the front end of the connecting rod 25. The wheel pressure device 2 is equipped with upper and lower guide wheels 21, left and right guide wheels 22, U-shaped pressure wheel terminals 23, and wheel pressure device adjusting joint 24. The U-shaped pressure wheel terminals 23 press against the axle extension portion of the aircraft's front landing gear wheel 26. When the catapult vehicle 1 moves, the upper and lower guide wheels 21 and the left and right guide wheels of the wheel pressure device... All 22 are located inside the ground guide rail 4, constraining the wheel pressure device 2 to not jump out of the ground guide rail 4, thus constraining the aircraft's front wheel to not leave the ground during operation and to run close to the ground along the ground guide rail 4; the upper and lower guide wheels 21 and the left and right guide wheels 22 of the wheel pressure device are symmetrically arranged on both sides of the connecting rod 25 and fixed at the front and rear; a wheel pressure device adjusting joint 24 is installed at the end of the connecting rod 25, the wheel pressure device adjusting joint 24 is fixed to the end of the connecting rod 25, and the U-shaped pressure wheel terminal 23 is fixed to the wheel pressure device adjusting joint 24 by bolts.

[0057] Furthermore, the wheel pressure device 2 can adjust the orientation and force of the U-shaped pressure wheel terminal 23 pressing on the axle of the aircraft's nose landing gear wheel 26 by adjusting the bolt on the wheel pressure device adjustment joint 24, adapting to the nose landing gear of different aircraft models. The wheel pressure device 2 is made of aluminum alloy or composite material.

[0058] Figure 6 This is an illustration of the landing gear wheel pressure device for an aircraft according to the present invention. It shows that the U-shaped pressure wheel terminal 23 presses against the axle extension of the aircraft's front landing gear wheel 26, constraining the aircraft's front landing gear wheel 26 to not leave the ground during operation, and running close to the ground along the ground guide rail 4. The shape and size of the U-shaped pressure wheel terminal 23 can be designed according to the aircraft's front landing gear wheel 26 to ensure that the aircraft's front landing gear wheel 26 will not detach from the wheel pressure device 2.

[0059] Figure 7 The diagram shows the relationship between the left and right guide wheels and the ground guide rail of the catapult vehicle frame body of the present invention. The ground guide rail base plate 41 is fixed to the ground, and the ground guide rail 4 is fixed on the ground guide rail base plate 41. The left and right guide wheels 8 of the frame body are installed in the middle of the rear main beam 61 of the frame body. The main purpose is to constrain the catapult vehicle 1 to run along the ground guide rail 4 and prevent the catapult vehicle 1 from deviating from the predetermined route when the force is uneven.

[0060] Figure 8 This is a diagram showing the relationship between the guide wheels of the catapult vehicle frame and the ground guide rail of the present invention. The upper and lower guide wheels 9 of the frame vehicle are installed in the middle of the rear main beam 61 of the frame vehicle and are staggered with the left and right guide wheels 8 of the frame vehicle. This is mainly to constrain the catapult vehicle 1 to run close to the ground and prevent the catapult vehicle 1 from being bounced off the ground by an upward external force during operation.

[0061] The ground guide rail 4 has a Z-shaped structure. The left and right guide wheels 8 of the catapult vehicle 1 are engaged with the inner wings of the Z-shaped ground guide rail 4, and the upper and lower guide wheels 9 of the frame vehicle are engaged with the upper and lower sides of the Z-shaped ground guide rail 4. The ground guide rail 4 is made of aluminum alloy. For easy installation and transportation, the Z-shaped ground guide rail 4 is divided into several sections. The lower base plate of each Z-shaped ground guide rail 4 is fixed on the ground guide rail base plate 41. The adjacent sections of the ground guide rail 4 are closely arranged to form a straight ground guide rail, which constrains the up and down movement of the catapult vehicle 1.

[0062] Furthermore, by using multiple catapult vehicles 1, rapid and continuous catapult launches of aircraft can be achieved. After one catapult vehicle 1 completes its propulsion and separation, the next catapult vehicle 1, which is already ready near the ground guide rail 4, can quickly push the next aircraft into the ground guide rail 4, greatly shortening the launch interval and improving operational efficiency.

[0063] Figure 9This diagram illustrates the force analysis of the catapult-launched vehicle propelling the aircraft according to the present invention. The diagram shows the left and right guide wheels 8 and the upper and lower guide wheels 9 of the frame vehicle body mounted on the lower part of the front protruding beam 63 of the frame vehicle body. During operation, the left and right guide wheels 8 and the upper and lower guide wheels 9 are located inside the ground guide rail 4. In the force calculation, corresponding displacement constraints are applied to the left and right guide wheels 8 and the upper and lower guide wheels 9. The maximum displacement occurs at the propulsion head 11, with a maximum displacement of approximately 12mm. The maximum stress occurs simultaneously at the connection between the front main beam 62 of the frame vehicle body and the onboard pulley blocks 7-1 and 7-2. The unit stress across the entire area of ​​the catapult vehicle 1 is below 120MPa, ensuring safe operation.

[0064] On the other hand, the present invention also provides a propulsion method applied to the aforementioned propulsion structure, comprising:

[0065] Step 1, docking and locking: Move the aircraft to the catapult vehicle, press down the push rods on both sides of the catapult vehicle to lock the load seats on both sides of the aircraft's belly, and at the same time press the wheel pressure device onto the aircraft's front landing gear wheel.

[0066] Step 2, Acceleration: Start the ground power vehicle and use the traction cable to pull the catapult car along the ground guide rail to accelerate; during acceleration, the push rod is lifted upward under the thrust of the force seat, the push head is unlocked from the force seat, and at the same time the push rod body is pressed against the force seat, pushing the aircraft to accelerate together;

[0067] Step 3 Braking and Separation: When the aircraft is accelerated to the target speed or reaches the predetermined position, the ground power vehicle is braked, the catapult decelerates, the propulsion head automatically separates from the aircraft's load-bearing seat, and the aircraft continues to glide forward by inertia.

[0068] In summary, the catapult vehicle of the present invention has a simple structure, low cost, and is easy to dock with the aircraft. At the same time, the unlocking and separation of the catapult vehicle and the aircraft is safe and reliable.

[0069] In a second aspect, the present invention provides a ground-powered vehicle, including a drive motor, a drive controller, and a drive transmission mechanism. The drive controller includes one or more processors and a memory for storing one or more programs. When the one or more programs are executed by the one or more processors, the one or more processors implement the aforementioned propulsion method.

[0070] Thirdly, the present invention provides a ground electromagnetic rapid propulsion system for an aircraft, including the aforementioned propulsion mechanism and an aircraft; force-bearing seats that cooperate with the propulsion rod are provided on both sides of the fuselage of the aircraft.

[0071] The specific embodiments described above further illustrate the purpose, technical solution, and beneficial effects of the present invention. It should be understood that the above descriptions are merely specific embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A ground-based electromagnetic rapid propulsion mechanism for aircraft, characterized in that, include: Catapult vehicle, wheel pressure unit, connecting rod, traction cable, ground guide rail, and ground power vehicle; The catapult vehicle includes a frame body, with push arms symmetrically arranged on both sides of the frame body. A push head is provided at the end of each push arm, and a push rod that can rotate relative to the push head is movably connected to the push head. The catapult vehicle engages with the force-bearing seats on both sides of the aircraft's belly via the push rod, which is used to lock or propel the force-bearing seats. The ground power vehicle consists of two units, symmetrically arranged on both sides of the ground guide rail. The traction cable passes through the vehicle-mounted pulley block set on the catapult vehicle, and its two ends are respectively connected to the two ground power vehicles to form a V-shaped traction layout. The wheel pressure unit is connected to the front end of the catapult vehicle and is used to constrain the aircraft's front landing gear wheels to run close to the ground during propulsion.

2. The ground electromagnetic rapid propulsion mechanism for an aircraft according to claim 1, characterized in that, The push head is clamp-shaped with a push rod shaft in the middle. The push rod is fixed on the push rod shaft and can rotate 90° between horizontal and vertical positions relative to the push head. The push head is also equipped with an anti-loosening device, one end of which is fixed on the push head and the other end is fixed on the push rod.

3. The ground electromagnetic rapid propulsion mechanism for an aircraft according to claim 2, characterized in that, When the catapult accelerates, the push rod is lifted upward by the force-bearing seat of the aircraft, the push head is unlocked from the force-bearing seat, and at the same time the rod body pushes against the bearing surface of the force-bearing seat to accelerate the aircraft; when the catapult brakes, the push head automatically separates from the force-bearing seat of the aircraft.

4. The ground electromagnetic rapid propulsion mechanism for an aircraft according to claim 1, characterized in that, The wheel press includes upper and lower guide wheels, left and right guide wheels, U-shaped pressure wheel terminals, and wheel press adjustment joints; the connecting rod is fixed to the catapult vehicle, the wheel press adjustment joint is fixed to the end of the connecting rod, and the U-shaped pressure wheel terminals are fixed to the wheel press adjustment joints; the upper and lower guide wheels and the left and right guide wheels are symmetrically arranged on both sides of the connecting rod and are located inside the ground guide rail.

5. The ground electromagnetic rapid propulsion mechanism for an aircraft according to claim 4, characterized in that, By adjusting the bolts on the wheel pressure adjustment joint, the orientation and force of the U-shaped pressure wheel terminal pressing on the aircraft's front landing gear wheel axle can be adjusted.

6. The ground electromagnetic rapid propulsion mechanism for an aircraft according to claim 1, characterized in that, The ground guide rail is composed of several Z-shaped structural units; the catapult vehicle also includes left and right guide wheels of the frame vehicle body and upper and lower guide wheels of the frame vehicle body. The left and right guide wheels of the frame vehicle body are engaged with the inner wings of the Z-shaped ground guide rail, and the upper and lower guide wheels of the frame vehicle body are engaged with the upper and lower sides of the Z-shaped ground guide rail.

7. The ground electromagnetic rapid propulsion mechanism for an aircraft according to claim 1, characterized in that, The ground power vehicle includes a drive motor, a drive controller, and a drive transmission mechanism; the drive controller coordinates the drive motor and drives the traction cable to retract or release the cable through the drive transmission mechanism.

8. A propulsion method, applied to the propulsion mechanism according to any one of claims 1-7, characterized in that, include: Step 1, docking and locking: Move the aircraft to the catapult vehicle, press down the push rods on both sides of the catapult vehicle to lock the load seats on both sides of the aircraft's belly, and at the same time press the wheel pressure device onto the aircraft's front landing gear wheel. Step 2, Acceleration: Start the ground power vehicle and use the traction cable to pull the catapult car along the ground guide rail to accelerate; during acceleration, the push rod is lifted upward under the thrust of the force seat, the push head is unlocked from the force seat, and at the same time the push rod body is pressed against the force seat, pushing the aircraft to accelerate together; Step 3 Braking and Separation: When the aircraft is accelerated to the target speed or reaches the predetermined position, the ground power vehicle is braked, the catapult decelerates, the propulsion head automatically separates from the aircraft's load-bearing seat, and the aircraft continues to glide forward by inertia.

9. A ground-powered vehicle, characterized in that, The device includes a drive motor, a drive controller, and a drive transmission mechanism. The drive controller includes one or more processors and a memory for storing one or more programs. When the one or more programs are executed by the one or more processors, the one or more processors implement the propulsion method of claim 8.

10. A ground-based electromagnetic rapid propulsion system for aircraft, characterized in that, The aircraft includes the propulsion mechanism as described in any one of claims 1-7, and an aircraft; the aircraft has force-bearing seats on both sides of its fuselage that cooperate with the propulsion rod.

Images