Travel assisting platform of turbojet fixed-wing aircraft

Abstract

The invention discloses an assistant platform of a turbojet fixed-wing aircraft, and relates to the related technical field of aircrafts. Comprising a tilting mechanism, a supporting mechanism, a moving mechanism, a rotating shaft, a plurality of guide shaft fixing supports, a fixed pulley block, a manual winch, a steel wire rope, a gear and a chain. The manual winch is shaken, the chain drives the gear to rotate, the inclination mechanism is turned over upwards, and then the inclination angle of the turbojet fixed-wing aircraft can be changed. When the gravity center of the tilting mechanism shifts due to tilting, mechanism resetting is achieved through the synergistic effect of traction force of the steel wire rope and gravitational potential energy, then angle adjustment of the tilting mechanism from 0 degree to 90 degrees is achieved, controllable ignition of aircraft turbojet within the inclination angle range from 0 degree to 90 degrees can be guaranteed, and the ignition process is stable and reliable. A high-credibility experimental environment is constructed for functional verification of the turbojet aircraft, a research platform is provided for optimization and iteration of the turbojet fixed-wing aircraft, and research and development test efficiency and safety are effectively improved.

Description

Technical Field

[0001] The present invention belongs to the technical field related to aircraft, and particularly relates to a cooperation platform for a turbojet fixed-wing aircraft. Background Art

[0002] In recent years, with the rapid development of micro turbojet engine technology, the design of manned aircraft based on such power has gradually become a reality. Compared with traditional power systems, turbojet engines, with their high thrust-to-weight ratio, high-speed performance, and compact structure, provide new possibilities for the application of manned aircraft in complex scenarios. Such aircraft are particularly suitable for solving urban three-dimensional traffic congestion problems, rapid response at disaster sites, and emergency rescue tasks in complex environments such as mountains or seas, and have significant advantages in terms of mobility and timeliness.

[0003] In terms of vertical takeoff and landing capabilities, turbojet manned aircraft can achieve vertical liftoff and hovering without runway support through multi-engine cooperative thrust distribution or vector nozzle design, significantly expanding their deployment capabilities in narrow spaces such as urban dense building clusters, mountain valleys, etc. For example, through the dynamic thrust regulation of distributed turbojet engine groups, the aircraft can complete takeoff and landing in restricted areas such as rooftop helipads and small emergency open spaces, greatly improving the mission execution efficiency. This characteristic makes it irreplaceable in scenarios such as medical emergency supply delivery and rapid arrival of fire rescue personnel.

[0004] However, some micro turbojet engines are limited by the combustion chamber design and fuel supply stability, and cannot achieve reliable low-speed ignition and precise thrust control during the vertical takeoff and landing stage, resulting in large fluctuations in power output at the moment of takeoff, affecting flight stability and safety.

[0005] Therefore, there is a problem that the existing cooperation platform cannot conduct ignition drive tests on turbojet fixed-wing aircraft from an inclined state to a vertical state. Summary of the Invention

[0006] The purpose of the present invention is to solve the problem that the existing cooperation platform cannot conduct ignition drive tests on turbojet fixed-wing aircraft from an inclined state to a vertical state, and to propose a cooperation platform for a turbojet fixed-wing aircraft.

[0007] To achieve the purpose of the present invention, the present invention discloses a cooperation platform for a turbojet fixed-wing aircraft, including an inclination mechanism, a support mechanism, a moving mechanism, a rotating shaft, a first guide shaft fixed support, a second guide shaft fixed support, a third guide shaft fixed support, a fixed pulley group, a manual winch, a steel wire rope, a gear, and a chain;

[0008] One end of the upper surface of the moving mechanism is provided with a support mechanism. One end of the upper surface of the support mechanism is provided with a pair of hinge connection seats. A rotating shaft is arranged between the two hinge connection seats. From left to right on the rotating shaft, there are a first guide shaft fixed support, a second guide shaft fixed support, and a third guide shaft fixed support in sequence. And the bottom surface of the guide shaft fixed support is fixedly connected to the side surface of the tilting mechanism. In the middle of the other end of the moving mechanism, there is a fixed pulley group. After one end of the steel wire rope passes through the fixed pulley group, it is fixedly connected to the middle of the other side of the tilting mechanism. One end of the upper surface of the support mechanism is provided with a manual winch. A gear is arranged on one end of the rotating shaft. The gear is connected to the manual winch through a chain. And the rotating shaft and the gear are integrally and fixedly arranged.

[0009] Further, the tilting mechanism includes an upper hook assembly, a lower hook assembly, an upper cross beam, a lower cross beam, and a frame;

[0010] An upper cross beam is arranged above the interior of the frame. Along the length direction of the upper cross beam, there are two upper hook assemblies in sequence. A lower cross beam is arranged below the interior of the frame. Along the length direction of the lower cross beam, there are two lower hook assemblies in sequence.

[0011] Further, the upper hook assembly is rotatably connected to the upper cross beam, and the lower hook assembly is rotatably connected to the lower cross beam.

[0012] Further, the support mechanism includes a support frame body, a limit baffle, and a vertical rod; In the middle of the upper surface of the support frame body, there are two vertical rods evenly arranged along the width direction. A limit baffle is arranged on the upper part of the side surface of each vertical rod.

[0013] Further, a buffer pad is arranged on the top of each vertical rod.

[0014] Further, the rotating shaft, the first guide shaft fixed support, the second guide shaft fixed support, and the third guide shaft fixed support are integrally arranged.

[0015] Further, a hand ring is arranged at the other end of the steel wire rope.

[0016] Further, the moving mechanism includes a square frame, a cross beam, and a universal wheel group; Along the length direction, a plurality of universal wheel groups are evenly arranged at the edges of the two long sides at the bottom of the square frame. Along the length direction, a plurality of cross beams are evenly arranged on the upper surface of the square frame.

[0017] Further, the distance between the two vertical rods in the support mechanism is less than the width of the frame in the tilting mechanism.

[0018] [ Further, the frame of the tilting mechanism, the support frame body of the support mechanism, and the square frame of the moving mechanism are all composed of aluminum profiles and L-shaped connecting blocks.

[0019] Furthermore, during use, the experimenter fixes the turboprop fixed-wing aircraft between the hook upper component on the upper crossbeam and the hook lower component on the lower crossbeam of the tilting mechanism. According to the size of different turboprop fixed-wing aircraft, by rotating the hook upper component and the hook lower component, the distance between the hook upper component and the hook lower component can be changed, thereby adapting to different models of turboprop fixed-wing aircraft. Through multi-point fixation and structural reinforcement design, the overall stability during the attitude adjustment of the aircraft is maintained;

[0020] Combined with the fact that a pair of hinge connection seats are provided at one end of the upper surface of the support mechanism, a rotating shaft is provided between the two hinge connection seats. A first guide shaft fixed support, a second guide shaft fixed support, and a third guide shaft fixed support are successively arranged on the rotating shaft from left to right. And the bottom surface of the guide shaft fixed support is fixedly connected to the side surface of the tilting mechanism. A manual winch is provided at one end of the upper surface of the support mechanism. A gear is provided at one end of the rotating shaft. The gear is connected to the manual winch through a chain. And the rotating shaft and the gear are integrally fixed. By turning the manual winch, the gear is driven to rotate through the chain, thereby driving the rotating shaft to rotate, and then the tilting mechanism is turned upwards to change the tilting angle of the turboprop fixed-wing aircraft; A fixed pulley set is provided in the middle of the other end of the moving mechanism. After one end of the steel wire rope passes through the fixed pulley set, it is fixedly connected to the middle of the other side of the tilting mechanism. When the center of gravity of the tilting mechanism shifts due to tilting, the mechanism is reset through the synergistic action of the traction force of the steel wire rope and the gravitational potential energy, and then the angle adjustment of the tilting mechanism within 10° to 90° is realized, so as to ensure the controllable ignition of the aircraft turboprop within the inclination angle range of 0° to 90°. The ignition process is stable and reliable; A high-confidence experimental environment is constructed for the function verification of the turboprop aircraft, providing a research platform for the optimization and iteration of the turboprop fixed-wing aircraft, and effectively improving the R & D test efficiency and safety.

[0021] Compared with the prior art, the remarkable progress of the present invention lies in: overcoming the disadvantages of the prior art, a pair of hinge connection seats are provided at one end of the upper surface of the support mechanism, a rotating shaft is provided between the two hinge connection seats, a first guide shaft fixed support, a second guide shaft fixed support and a third guide shaft fixed support are successively arranged on the rotating shaft from left to right, and the bottom surface of the guide shaft fixed support is fixedly connected to the side surface of the tilting mechanism. A manual winch is provided at one end of the upper surface of the support mechanism, a gear is provided at one end of the rotating shaft, the gear is connected to the manual winch through a chain, and the rotating shaft and the gear are integrally fixed. By shaking the manual winch, the gear is driven to rotate through the chain, thereby driving the rotating shaft to rotate, and then the tilting mechanism is turned upwards to change the tilting angle of the turboprop fixed-wing aircraft; a fixed pulley group is provided in the middle of the other end of the moving mechanism. After one end of the steel wire rope passes through the fixed pulley group, it is fixedly connected to the middle of the other side of the tilting mechanism. When the tilting mechanism causes the center of gravity to shift due to tilting, the mechanism is reset through the synergistic action of the traction force of the steel wire rope and the gravitational potential energy, and then the angle adjustment of the tilting mechanism from 0° to 90° is realized, so as to ensure the controllable ignition of the turboprop of the aircraft within the inclination angle range of 0° to 90°, and the ignition process is stable and reliable; a high-confidence experimental environment is constructed for the function verification of the turboprop aircraft, a research platform is provided for the optimization and iteration of the turboprop fixed-wing aircraft, and the R & D test efficiency and safety are effectively improved.

[0022] To more clearly illustrate the functional characteristics and structural parameters of the present invention, the following further explains with reference to the drawings and specific embodiments. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] The drawings described herein are used to provide a further understanding of the present invention, and constitute a part of this application. The schematic embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation of the present invention. In the drawings:

[0024] Figure 1 is a three-dimensional structure schematic diagram of a collaborative platform of a turboprop fixed-wing aircraft according to the present invention;

[0025] Figure 2 is a three-dimensional structure schematic diagram of a support mechanism in a collaborative platform of a turboprop fixed-wing aircraft according to the present invention;

[0026] Figure 3 is a side view of a tilting mechanism in a collaborative platform of a turboprop fixed-wing aircraft according to the present invention;

[0027] Figure 4 is a three-dimensional structure schematic diagram of a tilting mechanism in a collaborative platform of a turboprop fixed-wing aircraft according to the present invention.

[0028] The reference numerals in the figure are: tilting mechanism 1, supporting mechanism 2, moving mechanism 3, rotating shaft 4, first guide shaft fixed support 5, second guide shaft fixed support 6, third guide shaft fixed support 7, fixed pulley set 8, manual winch 9, steel wire rope 10, gear 11, chain 12, upper hook assembly 1-1, lower hook assembly 1-2, upper cross beam 1-3, lower cross beam 1-4, frame 1-5, buffer pad 2-1, limit baffle 2-2, vertical rod 2-3. Detailed implementation manners

[0029] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments; based on the embodiments in the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

[0030] A coordinated platform of a turbojet fixed-wing aircraft of the present invention includes a tilting mechanism 1, a supporting mechanism 2, a moving mechanism 3, a rotating shaft 4, a first guide shaft fixed support 5, a second guide shaft fixed support 6, a third guide shaft fixed support 7, a fixed pulley set 8, a manual winch 9, a steel wire rope 10, a gear 11 and a chain 12.

[0031] One end of the upper surface of the moving mechanism 3 is provided with a supporting mechanism 2. One end of the upper surface of the supporting mechanism 2 is provided with a pair of hinge connection seats. A rotating shaft 4 is provided between the two hinge connection seats. A first guide shaft fixed support 5, a second guide shaft fixed support 6 and a third guide shaft fixed support 7 are successively arranged on the rotating shaft 4 from left to right. The bottom surface of the guide shaft fixed support is fixedly connected to the side surface of the tilting mechanism 1. The middle part of the other end of the moving mechanism 3 is provided with a fixed pulley set 8. After one end of the steel wire rope 10 passes through the fixed pulley set 8, it is fixedly connected to the middle part of the other side of the tilting mechanism 1. One end of the upper surface of the supporting mechanism 2 is provided with a manual winch 9. A gear 11 is provided at one end of the rotating shaft 4. The gear 11 is connected to the manual winch 9 through a chain 12, and the rotating shaft 4 and the gear 11 are integrally and fixedly arranged.

[0032] Specifically, the tilting mechanism 1 includes an upper hook assembly 1-1, a lower hook assembly 1-2, an upper cross beam 1-3, a lower cross beam 1-4 and a frame 1-5.

[0033] An upper cross beam 1-3 is provided above the interior of the frame 1-5. Two upper hook assemblies 1-1 are successively arranged on the upper cross beam 1-3 along the length direction. A lower cross beam 1-4 is provided below the interior of the frame 1-5. Two lower hook assemblies 1-2 are successively arranged on the lower cross beam 1-4 along the length direction.

[0034] Specifically, the upper hook assembly 1-1 is rotatably connected to the upper cross beam 1-3, and the lower hook assembly 1-2 is rotatably connected to the lower cross beam 1-4.

[0035] Specifically, the support mechanism 2 includes a support frame body, a limit baffle 2-2 and a vertical rod 2-3; two vertical rods 2-3 are evenly arranged along the width direction in the middle of the upper surface of the support frame body, and a limit baffle 2-2 is arranged on the upper part of the side surface of each vertical rod 2-3.

[0036] Specifically, a buffer pad 2-1 is arranged on the top of each vertical rod 2-3.

[0037] Specifically, the rotating shaft 4, the first guide shaft fixed support 5, the second guide shaft fixed support 6 and the third guide shaft fixed support 7 are integrally arranged.

[0038] Specifically, a hand ring is arranged at the other end of the steel wire rope 10.

[0039] Specifically, the moving mechanism 3 includes a square frame, a cross beam and a universal wheel set; a plurality of universal wheel sets are evenly arranged along the length direction at the edges of the two long sides at the bottom of the square frame, and a plurality of cross beams are evenly arranged along the length direction on the upper surface of the square frame.

[0040] Specifically, the distance between the two vertical rods 2-3 in the support mechanism 2 is less than the width of the frame 1-5 in the tilting mechanism 1.

[0041] Specifically, the frame 1-5 of the tilting mechanism 1, the support frame body of the support mechanism 2 and the square frame of the moving mechanism 3 are all composed of aluminum profiles and L-shaped connecting blocks.

[0042] Embodiment 1

[0043] Combined with Figure 1 and Figure 4 To illustrate this embodiment, a collaborative platform of a turbojet fixed-wing aircraft described in this embodiment includes a tilting mechanism 1, a support mechanism 2, a moving mechanism 3, a rotating shaft 4, a first guide shaft fixed support 5, a second guide shaft fixed support 6, a third guide shaft fixed support 7, a fixed pulley set 8, a manual winch 9, a steel wire rope 10, a gear 11 and a chain 12;

[0044] One end of the upper surface of the moving mechanism 3 is provided with a support mechanism 2, one end of the upper surface of the support mechanism 2 is provided with a pair of hinge connection seats, a rotating shaft 4 is arranged between the two hinge connection seats, a first guide shaft fixed support 5, a second guide shaft fixed support 6 and a third guide shaft fixed support 7 are arranged on the rotating shaft 4 from left to right in sequence, and the bottom surface of the guide shaft fixed support is fixedly connected with the side surface of the tilting mechanism 1. A fixed pulley set 8 is arranged in the middle of the other end of the moving mechanism 3. After one end of the steel wire rope 10 passes through the fixed pulley set 8, it is fixedly connected with the middle part of the other side of the tilting mechanism 1. A manual winch 9 is arranged at one end of the upper surface of the support mechanism 2, a gear 11 is arranged at one end of the rotating shaft 4, the gear 11 is connected with the manual winch 9 through a chain 12, and the rotating shaft 4 and the gear 11 are integrally and fixedly arranged;

[0045] In this specific embodiment, when in use, the experimenter fixes the turboprop fixed-wing aircraft between the upper hook assembly 1-1 and the lower hook assembly 1-2 on the upper cross beam 1-3 of the tilting mechanism 1. According to the size of different turboprop fixed-wing aircraft, by rotating the upper hook assembly 1-1 and the lower hook assembly 1-2, the distance between the upper hook assembly 1-1 and the lower hook assembly 1-2 can be changed, so as to adapt to different models of turboprop fixed-wing aircraft. Through multi-point fixing and structural reinforcement design, the overall stability during the attitude adjustment of the aircraft is maintained;

[0046] Combined with the fact that a pair of hinge connection seats are provided at one end of the upper surface of the support mechanism 2, a rotating shaft 4 is provided between the two hinge connection seats. From left to right on the rotating shaft 4, a first guide shaft fixing support 5, a second guide shaft fixing support 6 and a third guide shaft fixing support 7 are successively provided. And the bottom surface of the guide shaft fixing support is fixedly connected to the side surface of the tilting mechanism 1. A manual winch 9 is provided at one end of the upper surface of the support mechanism 2. A gear 11 is provided at one end of the rotating shaft 4. The gear 11 is connected to the manual winch 9 through a chain 12. And the rotating shaft 4 and the gear 11 are integrally fixed. By turning the manual winch 9, the gear 11 is driven to rotate through the chain 12, so as to drive the rotating shaft 4 to rotate, and then the tilting mechanism 1 is turned upwards, so as to change the tilting angle of the turboprop fixed-wing aircraft; A fixed pulley group 8 is provided in the middle of the other end of the moving mechanism 3. One end of the steel wire rope 10 passes through the fixed pulley group 8 and is fixedly connected to the middle of the other side of the tilting mechanism 1. When the tilting mechanism 1 causes the center of gravity to shift due to tilting, the mechanism is reset through the combined action of the traction force of the steel wire rope 10 and the gravitational potential energy, and then the angle adjustment of the tilting mechanism 1 from 10° to 90° is realized, so as to ensure the controllable ignition of the aircraft turboprop within the inclination angle range of 0° to 90°. The ignition process is stable and reliable; A high-confidence experimental environment is constructed for the function verification of the turboprop aircraft, and a research platform is provided for the optimization and iteration of the turboprop fixed-wing aircraft, effectively improving the R & D test efficiency and safety.

[0047] Embodiment 2

[0048] Combined with Figure 3 and Figure 4 This embodiment is described. This embodiment is a further limitation on the cooperation platform described in the specific embodiment 1. A cooperation platform for a turboprop fixed-wing aircraft described in this embodiment, the tilting mechanism 1 includes an upper hook assembly 1-1, a lower hook assembly 1-2, an upper cross beam 1-3, a lower cross beam 1-4 and a frame 1-5;

[0049] An upper cross beam 1-3 is provided above the inside of the frame 1-5. Two upper hook assemblies 1-1 are successively provided on the upper cross beam 1-3 along the length direction. A lower cross beam 1-4 is provided below the inside of the frame 1-5. Two lower hook assemblies 1-2 are successively provided on the lower cross beam 1-4 along the length direction;

[0050] In this specific embodiment, the upper hook assembly 1-1 and the lower hook assembly 1-2 serve as a horizontal restraint unit to limit the displacement of the turboprop fixed-wing aircraft on the tilting mechanism 1 in the horizontal direction; the upper hook assembly 1-1 and the lower hook assembly 1-2 also serve as a gravity self-locking unit and are fixed on the upper cross beam 1-3 and the lower cross beam 1-4, and cooperate with the self-weight of the turboprop fixed-wing aircraft to achieve vertical displacement suppression.

[0051] Example Three

[0052] Combined with Figure 3 and Figure 4 This embodiment is described. This embodiment is a further limitation on the collaborative platform described in the second specific embodiment. For a collaborative platform of a turboprop fixed-wing aircraft described in this embodiment, the upper hook assembly 1-1 is rotatably connected to the upper cross beam 1-3, and the lower hook assembly 1-2 is rotatably connected to the lower cross beam 1-4;

[0053] In this specific embodiment, according to the sizes of different turboprop fixed-wing aircraft, by rotating the upper hook assembly 1-1 and the lower hook assembly 1-2, the distance between the upper hook assembly 1-1 and the lower hook assembly 1-2 can be changed, so as to be adapted to different models of turboprop fixed-wing aircraft and improve the versatility of the device.

[0054] Example Four

[0055] Combined with Figure 2 This embodiment is described. This embodiment is a further limitation on the collaborative platform described in the first specific embodiment. For a collaborative platform of a turboprop fixed-wing aircraft described in this embodiment, the support mechanism 2 includes a support frame body, a limit baffle 2-2 and a vertical rod 2-3; two vertical rods 2-3 are evenly arranged along the width direction in the middle of the upper surface of the support frame body, and a limit baffle 2-2 is arranged on the upper part of the side surface of each vertical rod 2-3.

[0056] Example Five

[0057] Combined with Figure 2 This embodiment is described. This embodiment is a further limitation on the collaborative platform described in the fourth specific embodiment. For a collaborative platform of a turboprop fixed-wing aircraft described in this embodiment, a buffer pad 2-1 is arranged on the top of each vertical rod 2-3;

[0058] In this specific embodiment, the buffer pad 2-1 adopts a polyurethane buffer pad. When the T-shaped groove aluminum profile of the frame 1-5 in the tilting mechanism 1 comes into contact with the buffer pad 2-1 to form contact limitation, the over-deflection phenomenon can be effectively inhibited. At the same time, the characteristics of the buffer material can absorb the deflection kinetic energy and avoid structural damage caused by dynamic impact.

[0059] Example Six

[0060] Combined with Figure 4 Figure 4 To illustrate this embodiment, this embodiment is a further limitation on the cooperation platform described in the first specific embodiment. For a cooperation platform of a turboprop fixed-wing aircraft described in this embodiment, the rotating shaft 4, the first guide shaft fixed support 5, the second guide shaft fixed support 6, and the third guide shaft fixed support 7 are integrally provided;

[0061] In this specific embodiment, a rigid coupling is established between the three groups of guide shaft fixed supports and the rotating shaft 4 to ensure the accurate transmission of the tilting angle of the tilting mechanism 1.

[0062] Example Seven

[0063] Combined with Figure 3 Figure 3 To illustrate this embodiment, this embodiment is a further limitation on the cooperation platform described in the first specific embodiment. For a cooperation platform of a turboprop fixed-wing aircraft described in this embodiment, the other end of the steel wire rope 10 is provided with a bracelet.

[0064] Example Eight

[0065] Combined with Figure 1 Figure 1 To illustrate this embodiment, this embodiment is a further limitation on the cooperation platform described in the first specific embodiment. For a cooperation platform of a turboprop fixed-wing aircraft described in this embodiment, the moving mechanism 3 includes a square frame, a cross beam, and a universal wheel set; a plurality of universal wheel sets are uniformly provided along the length direction at the edges of the two long sides of the bottom of the square frame, and a plurality of cross beams are uniformly provided along the length direction on the upper surface of the square frame;

[0066] In this specific embodiment, the universal wheel set uses JDF-40 type engineering plastic universal casters as the core motion unit. Each universal wheel set is modularly connected to the square frame through a gasket group and a T-slot special slider nut. This connection scheme not only ensures the structural rigidity but also has convenient maintenance characteristics, and can realize the omnidirectional movement of the entire cooperation frame, facilitating the testing of turboprop fixed-wing aircraft in different scenarios.

[0067] Example Nine

[0068] Combined with Figure 2 Figure 2 To illustrate this embodiment, this embodiment is a further limitation on the cooperation platform described in the fourth specific embodiment. For a cooperation platform of a turboprop fixed-wing aircraft described in this embodiment, the distance between the two vertical rods 2-3 in the support mechanism 2 is less than the width of the frame 1-5 in the tilting mechanism 1.

[0069] Example Ten

[0070] Combined with Figure 1Regarding this embodiment, this embodiment further defines the collaborative platform described in the fourth specific embodiment. For the collaborative platform of a turboprop fixed-wing aircraft described in this embodiment, the frame 1-5 of the tilting mechanism 1, the support frame body of the support mechanism 2, and the square frame of the moving mechanism 3 are all composed of aluminum profiles and L-shaped connecting blocks;

[0071] In this specific embodiment, the frame 1-5 of the tilting mechanism 1, the support frame body of the support mechanism 2, and the square frame of the moving mechanism 3 are all constructed by grooved aluminum extrusion profiles. The joints of the profiles are rigidly connected by die-cast corner codes. Auxiliary profiles are added in the right-angle intersection area and reinforced rib structures are formed through extrusion angle seats, significantly enhancing the overall stiffness of the frame.

[0072] The working principle of the present invention is as follows: During use, the experimenter fixes the turboprop fixed-wing aircraft between the hook upper component 1-1 on the upper crossbeam 1-3 and the hook lower component 1-2 on the lower crossbeam 1-4 of the tilting mechanism 1. According to the size of different turboprop fixed-wing aircraft, by rotating the hook upper component 1-1 and the hook lower component 1-2, the distance between the hook upper component 1-1 and the hook lower component 1-2 can be changed, thereby adapting to different models of turboprop fixed-wing aircraft. The overall stability during the attitude adjustment of the aircraft is maintained through multi-point fixing and structural reinforcement design;

[0073] Furthermore, a pair of hinge connection seats are provided at one end of the upper surface of the support mechanism 2. A rotating shaft 4 is provided between the two hinge connection seats. From left to right on the rotating shaft 4, there are a first guide shaft fixed support 5, a second guide shaft fixed support 6, and a third guide shaft fixed support 7 in sequence. And the bottom surface of the guide shaft fixed support is fixedly connected to the side surface of the tilting mechanism 1. A manual winch 9 is provided at one end of the upper surface of the support mechanism 2. A gear 11 is provided at one end of the rotating shaft 4. The gear 11 is connected to the manual winch 9 through a chain 12. And the rotating shaft 4 and the gear 11 are integrally fixed. By turning the manual winch 9, the gear 11 is driven to rotate through the chain 12, thereby driving the rotating shaft 4 to rotate, and then the tilting mechanism 1 is turned upward, so as to change the tilting angle of the turboprop fixed-wing aircraft; A fixed pulley group 8 is provided in the middle of the other end of the moving mechanism 3. One end of a steel wire rope 10 passes through the fixed pulley group 8 and is fixedly connected to the middle of the other side of the tilting mechanism 1. When the tilting mechanism 1 causes the center of gravity to shift due to tilting, through the combined action of the traction force of the steel wire rope 10 and the gravitational potential energy, the mechanism is reset, and then the angle adjustment of the tilting mechanism 1 from 10° to 90° is realized, so as to ensure the controllable ignition of the turboprop of the aircraft within the inclination angle range of 0° to 90°. The ignition process is stable and reliable; A high-confidence experimental environment is constructed for the functional verification of the turboprop aircraft, providing a research platform for the optimization and iteration of the turboprop fixed-wing aircraft, and effectively improving the R & D test efficiency and safety.

[0074] It should be noted that in this text, relational terms such as first and second are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any actual relationship or order between these entities or operations. Moreover, the terms "comprising", "including" or any other variant thereof are intended to cover non-exclusive inclusion, such that a process, method, article or device comprising a series of elements not only includes those elements but also includes other elements not expressly listed, or elements inherent to such process, method, article or device.

[0075] Although the embodiments of the present invention have been shown and described, those of ordinary skill in the art can understand that various changes, modifications, substitutions and variations can be made to these embodiments without departing from the principles and spirit of the present invention. The scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. A coordinated flight platform for a turbojet fixed-wing aircraft, characterized in that, One end of the upper surface of the moving mechanism (3) is provided with a support mechanism (2). One end of the upper surface of the support mechanism (2) is provided with a pair of hinge connection seats. A rotating shaft (4) is arranged between the two hinge connection seats. From left to right on the rotating shaft (4), there are successively arranged a first guide shaft fixed support (5), a second guide shaft fixed support (6), and a third guide shaft fixed support (7), and the bottom surface of the guide shaft fixed support is fixedly connected to the side surface of the tilting mechanism (1). In the middle of the other end of the moving mechanism (3), a fixed pulley set (8) is provided. After one end of a steel wire rope (10) passes through the fixed pulley set (8), it is fixedly connected to the middle of the other side of the tilting mechanism (1). One end of the upper surface of the support mechanism (2) is provided with a manual winch (9). One end of the rotating shaft (4) is provided with a gear (11). The gear (11) is connected to the manual winch (9) through a chain (12), and the rotating shaft (4) and the gear (11) are integrally and fixedly arranged.

2. The collaborative platform of a turbojet fixed-wing aircraft according to claim 1, characterized in that The described tilting mechanism (1) includes an upper hook assembly (1-1), a lower hook assembly (1-2), an upper cross beam (1-3), a lower cross beam (1-4), and a frame (1-5). An upper cross beam (1-3) is arranged above the interior of the frame (1-5). Along the length direction on the upper cross beam (1-3), there are successively arranged two upper hook assemblies (1-1). A lower cross beam (1-4) is arranged below the interior of the frame (1-5). Along the length direction on the lower cross beam (1-4), there are successively arranged two lower hook assemblies (1-2).

3. The collaborative platform of a turbojet fixed-wing aircraft according to claim 2, characterized in that, The described upper hook assembly (1-1) is rotationally connected to the upper cross beam (1-3), and the lower hook assembly (1-2) is rotationally connected to the lower cross beam (1-4).

4. The collaborative platform of a turbojet fixed-wing aircraft according to claim 2, characterized in that, The described support mechanism (2) includes a support frame body, a limit baffle (2-2), and a vertical rod (2-3). In the middle of the upper surface of the support frame body, two vertical rods (2-3) are evenly arranged along the width direction. On the upper part of the side surface of each vertical rod (2-3), a limit baffle (2-2) is provided.

5. The collaborative platform of a turbojet fixed-wing aircraft according to claim 4, characterized in that, A buffer pad (2-1) is provided at the top of each of the described vertical rods (2-3).

6. The collaborative platform of a turbojet fixed-wing aircraft according to claim 1, characterized in that, The described rotating shaft (4), the first guide shaft fixed support (5), the second guide shaft fixed support (6), and the third guide shaft fixed support (7) are integrally arranged.

7. The collaborative platform of a turbojet fixed-wing aircraft according to claim 1, characterized in that A hand ring is provided at the other end of the described steel wire rope (10).

8. The collaborative platform of a turbojet fixed-wing aircraft according to claim 4, characterized in that, The described moving mechanism (3) includes a square frame, cross beams, and a universal wheel set. Along the length direction at the edges of the two long sides at the bottom of the square frame, a plurality of universal wheel sets are evenly arranged. Along the length direction on the upper surface of the square frame, a plurality of cross beams are evenly arranged.

9. The collaborative platform of a turbojet fixed-wing aircraft according to claim 4, characterized in that, The distance between the two vertical rods (2-3) in the described support mechanism (2) is less than the width of the frame (1-5) in the tilting mechanism (1).

10. The collaborative platform of a turbojet fixed-wing aircraft according to claim 8, characterized in that, The frame (1-5) of the described tilting mechanism (1), the support frame body of the support mechanism (2), and the square frame of the moving mechanism (3) are all composed of aluminum profiles and L-shaped connection blocks.

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