A deployment model structure for unmanned aerial flight tests

Abstract

This invention discloses a deployment model structure for unmanned aerial flight tests, comprising: a flight test deployment model body, an aircraft model, a rocket model, and a fuselage. The flight test deployment model body has a fuselage, and the fuselages are connected by a central wing that reduces the center of gravity and symmetry disturbances of the flight test deployment model body during flight. The mounting device has a pylon or hook connected to the central wing, and the flight deployment component is connected to the pylon. The pylon is located at the center of the central wing. The wings are used to ensure the flight test deployment model body can stably deploy the flight deployment component during flight deployment. The left and right sides of the flight test deployment model body are connected to wings, which are also located on the upper side of the fuselage. The lower side of the fuselage has sufficient space. The beneficial effects of this invention are: shortening the flight test preparation cycle and compensating for the deficiencies in the model flight test envelope.

Description

Technical Field

[0001] This invention relates to the field of aircraft technology, and more specifically to a deployment model structure for unmanned aerial flight tests. Background Technology

[0002] Model flight testing is a simulated flight testing method that studies aerodynamic problems by having a model aircraft fly in the atmosphere. Existing scaled-down aeronautical test models primarily use turbojet engines as propulsion, employing ground-based takeoff and landing methods. This approach has certain drawbacks: the residual thrust at engine idle and the inertial coupling torque between engine speed and fuselage shaft angular rate affect spin test results, making it impossible to accurately measure spin characteristics and conduct precise spin tests. Furthermore, due to the influence of residual engine thrust and the difficulty of calibration via ground testing, the actual acceleration sensor measurement is the acceleration generated by the combined force of air resistance and residual engine thrust on the scaled-down aeronautical test model; the magnitude of acceleration caused by drag cannot be measured. Therefore, the drag coefficient of powered scaled-down aeronautical test models cannot be accurately measured.

[0003] Spaceflight test models are launched using rockets to conduct hypersonic aerodynamic experiments at predetermined altitudes and speeds. These experiments typically involve vertical launch from the ground, and the process includes rocket boost, model gliding, testing under specific conditions, and model return. This method has two main drawbacks: ① Ground launch requires overcoming air resistance and gravitational potential energy. ② It makes it difficult to conduct energy-managed, unpowered autonomous landing and recovery experiments.

[0004] On the other hand, due to the small number of aircraft in my country, most of them are deployed to front-line troops for combat readiness and military training, lacking aircraft platforms that can be converted into airborne flight test and deployment platforms. In addition, my country has strict management of manned aircraft, and the preliminary coordination work, procedures, and testing cycles for using manned aircraft for scientific research are extensive, which hinders the large-scale application of airborne flight test and research verification platforms in my country. As a result, there are few relevant application cases, and only a few projects have carried out related applications.

[0005] For the reasons mentioned above, there is a need to conduct unpowered delivery tests of scaled-down aerospace models and scaled-down space models by using unmanned aerial flight test delivery platforms. Summary of the Invention

[0006] The technical problem to be solved by this invention is that the existing unmanned aerial flight test delivery platform structure requires a long preparation period for flight test delivery. The purpose of this invention is to provide a delivery model structure for unmanned aerial flight tests. This invention utilizes a universal unmanned aerial flight test delivery platform to shorten the flight test preparation period, make up for the insufficient envelope of the model flight test, improve the efficiency of model flight tests, reduce the cost of model flight tests, and help to normalize model flight tests.

[0007] This invention is achieved through the following technical solution:

[0008] A deployment model structure for an unmanned aerial flight test includes a flight test deployment model body, which comprises:

[0009] At least two fuselages;

[0010] The central wing is connected to the adjacent fuselage.

[0011] The wings are located on both sides of the flight test launch model body, and each wing is connected to a fuselage.

[0012] A mounting device is attached to the center wing and is used to attach flight-deployed components.

[0013] The fuselage has a streamlined structure with a length, and is divided into a forward section, a central section, and a rear section. The forward section is cylindrical in shape, and its cross-sectional area gradually increases from the front to the rear. The front of the forward section has a hemispherical surface. The front and rear ends of the central section connect the forward section and the rear section, respectively. The central section connects the central wing and the wing. The front of the central section is a rounded cylinder, and the rear of the central section is a square cylinder. The central wing and the wing are connected to the central section of this square cylinder. The rear section is cylindrical, and its cross-sectional area gradually decreases from the front to the rear. The tail of the fuselage is flat.

[0014] The central wing and the wings are located on the upper side of the central section and close to the front side of the rear section.

[0015] The central wing and the wings are connected to the upper side of the fuselage. The tail fin is located at the tail of the fuselage or at the rear of the rear section. The tail fin is arranged with a single vertical tail and two horizontal tails.

[0016] The flight test launch model body has a four-point landing gear, which is located inside the lower side of the left fuselage and inside the lower side of the right fuselage.

[0017] The flight test launch model body has a turbofan engine as its power system, and the turbofan engine is mounted on the wing.

[0018] The mounting device is located on the lower side of the center position of the central wing, and the mounting device is a bracket or a hook.

[0019] The fuselage has a hard shell and trusses. The hard shell is covered with a skin, and the hard shell is connected to the trusses inside. The hard shell, the trusses inside the hard shell, and the skin outside the hard shell together form a mixed load-bearing structure.

[0020] The central wing has a double-beam structure, with beams on the front and rear sides. A reinforcing rib connects the front and rear beams to the central wing. The beams on the front and rear sides, along with the skin and reinforcing ribs, form a closed wing box structure. The stringers have stringers and longitudinal beams. The longitudinal beams are arranged along the longitudinal direction of the fuselage, and the stringers are arranged along the circumferential direction of the fuselage. The longitudinal beams are connected to the stringers and arranged perpendicularly to each other. Each fuselage has four longitudinal beams and multiple stringers. A bulkhead is installed inside the fuselage, connected to the stringers. A cabin is located inside the fuselage, with the bulkhead situated between the cabin and the stringers. The stringers are located outside the bulkhead. A structural frame is connected to the exterior of the hard shell, situated between the skin and the hard shell. The structural frame, the hard shell, and the skin form a box-type load-bearing structure.

[0021] The flight test launch model body has a fuel tank, which is located at the lower end of the left and right wings and close to the fuselage. The mounting device is welded or connected to the lower end of the central wing by screws.

[0022] Compared with the prior art, the present invention has the following advantages and beneficial effects:

[0023] 1. This invention adopts a twin-fuselage layout design, with the left and right fuselages connected by a central wing. The central wing connects the two fuselages, enabling the flight test model to be launched. The twin-fuselage layout reduces disturbances to the center of gravity and symmetry of the overall structure of the flight test model, and also increases the space for fuel loading. At the lower end of the connection between the two central wings, a mounting device is adapted according to the needs of the launched load. The mounting device can attach different flight launch components, i.e., aircraft models or rocket models, to conduct aeronautical model flight tests. The wings plus the central wing allow the flight test model to be launched smoothly during flight. This invention, with its twin fuselages connected by a central wing and the central wing connected to the wings, and the central wing then connected to the fuselage, shortens the preparation cycle for flight tests, thereby reducing ground launch air resistance and overcoming gravitational potential energy, ensuring stable flight, and enabling energy management and unpowered autonomous landing and recovery.

[0024] 2. The fuselage of this invention has a streamlined structure with a length. The forward section is cylindrical, and its cross-sectional area gradually increases from the front to the rear to reduce fluid friction at the front of the fuselage. The front of the forward section has a hemispherical surface, which increases the lift of the flight test launch model during takeoff. The front of the central section is a rounded-corner cylinder, and the rear of the central section is a square cylinder. The central wing and the fuselage are connected to the central section of this square cylinder. The square cylinder at the rear of the central section ensures that the central wing and the fuselage are parallel to the ground. Connected to the central section of the rectangular column, the central wing and the wings are close to the rear section, that is, close to the center of gravity of the fuselage. This allows the fluid passing through the front of the fuselage to pass through the central wing and the wings, making the flight test model stable. The rear section is cylindrical, and the cross-sectional area of ​​the rear section gradually decreases from the front to the rear. The tail of the fuselage is flat. This design of the rear section prevents the fluid at the front of the fuselage from rubbing against the rear section during flight. The rear section is used for fuselage stabilization and flight direction control, ensuring stable flight.

[0025] 3. This invention utilizes a turbofan engine powered by a flight control and management system to take off via a runway. After takeoff, the landing gear is retracted, and the aircraft climbs to the target altitude. It then cruises at the target altitude to the designated airspace. Once the unmanned aerial flight test platform structure enters the designated airspace, the test can commence. After the test, the aircraft returns to the designated airspace, decreasing its altitude during the return journey. When the altitude reaches the recovery requirements, it enters the return landing mode, deploys the landing gear, maintains a certain flight attitude, aligns with the runway, and lands via a runway, finally coming to a stop. This invention can shorten the flight test preparation cycle, compensate for the insufficient envelope of model flight tests, and improve the efficiency of model flight tests. Attached Figure Description

[0026] To more clearly illustrate the technical solutions of the exemplary embodiments of the present invention, the accompanying drawings used in the embodiments will be briefly described below. It should be understood that the following drawings only show some embodiments of the present invention and should not be considered as a limitation of the scope. For those skilled in the art, other related drawings can be obtained based on these drawings without creative effort. In the drawings:

[0027] Figure 1 A schematic diagram of a deployment test method for an aircraft model;

[0028] Figure 2 This is a schematic diagram of another method for launching and testing aerospace models.

[0029] The attached diagram shows the markings and corresponding component names:

[0030] 1-Flight test launch model body, 2-Aircraft model, 3-Rocket model, 4-Fuselage, 41-Forward section, 42-Central section, 43-Rear section, 5-Central wing, 6-Wing, 7-Turbofan engine. Detailed Implementation

[0031] To make the objectives, technical solutions, and advantages of the present invention clearer, the present invention will be further described in detail below with reference to the embodiments and accompanying drawings. The illustrative embodiments and descriptions of the present invention are only used to explain the present invention and are not intended to limit the present invention.

[0032] Example 1

[0033] like Figure 1-2 As shown in the figure, this embodiment of a flight test launch model structure includes: a flight test launch model body 1, an aircraft model 2, a rocket model 3, and a fuselage 4. The flight test launch model body 1 has a fuselage 4, and the fuselage 4 is connected to the fuselage 4 by a central wing 5 that can reduce the disturbance of the center of gravity and symmetry during flight. The mounting device has a pylon or hook, which is connected to the central wing 5. The flight launch component includes the aircraft model 2 and the rocket model 3, and the flight launch component is mounted on the pylon or hook. The pylon or hook is located in the central wing 5. The central position of the central wing 5 (the pylon is connected to the central wing 5 by screws or welding) and the wing 6 enable the flight test launch model body 1 to smoothly launch the flight launch items during flight launch. The left and right sides of the flight test launch model body 1 are connected to the straight wings 6. The wings 6 are located on the upper side of the fuselage 4, and there is sufficient space on the lower side of the fuselage 4. The airplane model 2 and the rocket model 3 are set at the lower end of the connection position of the two central wings 5. The pylon is used to attach the items to be launched during the flight test launch of the flight test launch model body 1.

[0034] The fuselage 4 is a streamlined structure with a length, divided into a front section 41, a central section 42, and a rear section 43. The front section 41 is cylindrical in shape, and its cross-sectional area gradually increases from the front to the rear to reduce fluid friction at the front of the fuselage. The front of the front section 41 has a hemispherical surface, which increases the lift of the flight test model during takeoff. The central section 42... The front and rear ends are connected to the front fuselage section 41 and the rear fuselage section 43, respectively. The central section 42 connects the central wing 5 and the wing 6. The front side of the central section 42 is a rounded cylinder, and the rear side of the central section 42 is a square cylinder. The central wing 5 and the wing 6 are connected to the central section 42 of this square cylinder. The square cylinder on the rear side of the central section 42 makes the central wing 5 and the wing 6 parallel to the ground and connected to the central section 42 of the rectangular cylinder. The central wing 5 and the wing 6 are close to the rear fuselage section 43, that is, the central wing and the wing are close to each other. The center of gravity of the fuselage is positioned so that the fluid passing through the front of fuselage 4 then passes through the central wing 5 and wing 6, ensuring stable flight of the model body 1 during flight testing. The rear section 43 is cylindrical, and its cross-sectional area gradually decreases from the front to the rear of the rear section 43. The tail of fuselage 4 is flattened. The flat, rear section 43 design prevents the fluid on the front of the fuselage 4 from rubbing against the rear section 43 during flight (the fluid flows from the rounded cylinder on the front of the central section 42 to the square cylinder on the rear of the central section 42, and the cross-section of the front of the rear section 43 is smaller than the cross-section of the square cylinder on the rear of the central section 42, so the fluid on the front of the fuselage 4 will not rub against the rear section 43). The rear section 43 is used to stabilize the fuselage 4 and control its flight direction, ensuring stable flight of the fuselage 4.

[0035] The central wing 5 and the wing 6 are located on the upper side of the central section 42 and close to the front side of the rear section 43. The fuselage 4 has a tail fin at the tail or the rear side of the rear section 43. The tail fin is arranged with a single vertical tail and a double horizontal tail.

[0036] The flight test launch model body 1 has a four-point landing gear, which includes two main landing gears and two nose landing gears. The two main landing gears and the two nose landing gears are respectively located inside the lower side of the left fuselage 4 and inside the lower side of the right fuselage 4. The landing gears can be retracted and extended to the lower side of the fuselage 4 by signal operation or control.

[0037] The flight test launch model body 1 has a power system, which is a turbofan engine 7, and the turbofan engine 7 is hoisted and set at the lower end of the central wing 5.

[0038] The fuselage 4 has a hard shell and a truss. The hard shell is covered with a skin, and the hard shell is connected to the truss inside. The hard shell, the truss inside the hard shell, and the skin outside the hard shell together form the hybrid load-bearing structure.

[0039] The central wing 5 has a double-beam structure, with beams on the front and rear sides. A reinforcing rib is located between the beams on the front and rear sides of the central wing 5. The beams on the front and rear sides of the central wing 5, together with the skin and the reinforcing rib, form a closed wing box structure. The stringers have stringers and longitudinal beams. The longitudinal beams are arranged along the longitudinal direction of the fuselage 4, and the stringers are arranged along the circumferential direction of the fuselage 4. The longitudinal beams are connected to the stringers and arranged perpendicularly to each other. Each fuselage 4 has four longitudinal beams and multiple stringers. A bulkhead is provided inside the fuselage 4. The bulkhead is connected to the stringers. A cabin is located inside the fuselage 4. The bulkhead is located between the cabin and the stringers, and the stringers are located outside the bulkhead.

[0040] The hard shell is connected to a structural frame, which is located between the skin and the hard shell. The structural frame, the hard shell, and the skin together form a box-type load-bearing structure.

[0041] The flight test launch model body 1 has a fuel tank, which is located at the lower end of the central wing 5 connected to the left and right wings 6. The fuel tank is close to the fuselage 4, that is, the fuel tank is located between the turbofan engine 7 and the fuselage 4.

[0042] The mounting device is welded or screwed to the lower end of the central wing 5, and the two central wings 5 ​​can be connected together by welding or screws.

[0043] Example 2

[0044] This invention adopts a twin-fuselage layout design, with the left and right fuselages connected by a central wing. The twin-fuselage layout can reduce the disturbance to the overall center of gravity and symmetry of the structure when deploying the airborne flight test platform structural model, and can also increase the fuel loading space.

[0045] The tail section of fuselage 4 adopts a single vertical tail and twin horizontal tail layout, which can avoid the blockage of the release channel behind the pylon point.

[0046] It adopts a straight monoplane layout, with wing 6 located on the upper side of fuselage 4. The space under wing 6 is relatively large, which facilitates the fixation of the deployed models (airplane model 2, rocket model 3, or pylon), and provides sufficient space for the deployed models.

[0047] The hybrid load-bearing structure allows the longitudinal beams, stringers, and fuselage skin to share the load, dispersing the aerodynamic load and concentrated load transmission paths, improving the load-bearing efficiency per unit weight of material, and enabling the fuselage structure to meet the strength and weight requirements.

[0048] The beams, skin, and reinforcing ribs on the front and rear sides of the central wing 5 form a closed wing box structure to transfer bending and torsional loads; the cabin adopts an integral bulkhead partition, and the longitudinal beams, stringers, and bulkhead are enclosed by skin to form a box structure, which has a good stress condition.

[0049] The fuselage uses a structural frame as the main load-bearing component. The structural frame and skin jointly bear the aerodynamic loads of the fuselage, the aerodynamic loads of the wings, the loads of the target delivery vehicle, and the impact loads of takeoff and landing. The structural frame and skin form a box-type load-bearing structure, which gives the fuselage structure tensile and compressive stability and appropriate strength, ensuring the flight safety of the model delivery test and research platform. As the main load-bearing structure of the fuselage, the structural frame facilitates the installation and fixing of landing gear, engines and other equipment that generate concentrated loads.

[0050] This invention can be adapted to different mounting frames, aircraft models 2 or rocket models 3, depending on the needs of the payload, to carry out flight tests of aviation models.

[0051] The unmanned aerial flight test and delivery platform of this invention has 14 control surfaces arranged in seven pairs symmetrically, including one pair each of outer ailerons, inner ailerons, outer flaps, inner flaps, outer ellipse, inner ellipse, and rudder. The control surfaces adopt a redundant layout, with at least one pair of control surfaces having the same function. However, the efficiency of control surfaces in different positions varies, requiring simulation studies of different control surface configurations to find the most suitable control surface configuration. This invention uses a conventional fixed configuration scheme. Compared with composite control schemes, this scheme has a simple and practical control logic, clear physical concepts, facilitates fault detection and control system reconfiguration, reduces the difficulty of control law design, and reduces the workload of control system design and management. Specifically, the inner and outer ailerons are mainly used for lateral control; the inner and outer ellipses are mainly used for longitudinal control; and the inner and outer flaps are mainly used for lift enhancement during takeoff and landing.

[0052] This invention employs a 5% MAC static stability design. Static stability design can reduce the design difficulty of flight control systems and shorten the development cycle; it can reduce the bandwidth, speed and other indicators of actuators such as servos, saving development costs; it can slow down the attitude divergence speed under fault conditions, reduce the difficulty of control strategy reconfiguration, and improve system survivability.

[0053] Example 3

[0054] The working principle of this invention is as follows:

[0055] Under the control of the flight control and management system, the unmanned aerial flight test delivery platform structure is powered by a turbofan engine and takes off using a runway takeoff method. After takeoff, the landing gear is retracted. According to the mission requirements, it climbs to the target altitude and cruises to the mission delivery airspace. When the unmanned aerial flight test delivery platform structure enters the delivery window and meets all the conditions for the delivery test, the delivery test can be carried out. After the test, it returns to the required airspace and lowers its flight altitude during the return journey. When the flight altitude reaches the recovery requirements, it then enters the return landing mode, lowers its landing gear, maintains a certain flight attitude, aligns with the runway, and lands using a runway takeoff method, finally coming to a stop.

[0056] This invention is an unmanned aerial flight test deployment model, which uses electromechanical control to operate the unmanned aerial flight test deployment platform structure. This invention mainly describes the mechanical structure, and the electronic control circuit is not within the scope of protection of this invention and will not be described in detail. Therefore, this invention only combines the electronic control part of the unmanned aerial flight test deployment platform structure with the mechanical structure.

[0057] 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 description is only a specific embodiment of the present invention and is not intended to limit the scope of protection of the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. A deployment model structure for an unmanned aerial flight test, characterized in that, Includes a flight test deployment model body (1), which includes: At least two fuselages (4), the fuselage (4) is a streamlined structure with a length, divided into a front section (41), a central section (42) and a rear section (43). The front section (41) is cylindrical in shape and has a hemispherical surface on the front side. The cross-sectional area gradually increases from the front side to the rear side. The central section (42) is a rounded cylinder on the front side and a square cylinder on the rear side. The rear section (43) is cylindrical and the cross-sectional area gradually decreases from the front side to the rear side. The tail section is flat. The central wing (5) is connected to the adjacent fuselage (4) through the central wing (5). The central wing (5) is a double-beam structure with beams on the front and rear sides and reinforcing ribs between the beams, forming a closed wing box structure with the skin. Wings (6) are provided on both sides of the flight test launch model body (1). The wings (6) on both sides are connected to a fuselage (4). The central wing (5) and the wings (6) are located on the upper side of the central section (42) of the fuselage and close to the front side of the rear section (43), so that the lower side of the fuselage (4) has space to accommodate the flight launch component. The mounting device is located on the lower side of the center of the central wing (5), and is a bracket or hook for connecting flight launch components, which include an airplane model (2) or a rocket model (3). The flight test launch model body (1) adopts a twin-fuselage layout, with the two fuselages (4) connected by a central wing (5) to reduce the center of gravity and symmetry disturbance during flight. The tail section (4) or the rear side of the rear fuselage section (43) is equipped with a tail fin with a single vertical tail and a twin horizontal tail.

2. The deployment model structure for an unmanned aerial flight test according to claim 1, characterized in that, The front and rear ends of the central section (42) are connected to the front body section (41) and the rear body section (43) respectively. The central section (42) is connected to the central wing (5) and the wing (6). The central wing (5) and the wing (6) are connected to the central section (42) of the square column.

3. The deployment model structure for an unmanned aerial flight test according to claim 1, characterized in that, The flight test launch model body (1) has a four-point landing gear, which is located inside the lower side of the left fuselage (4) and inside the lower side of the right fuselage (4).

4. The deployment model structure for an unmanned aerial flight test according to claim 1, characterized in that, The flight test launch model body (1) has a turbofan engine (7) as its power system, and the turbofan engine (7) is mounted on the wing (6).

5. The deployment model structure for an unmanned aerial flight test according to claim 1, characterized in that, The mounting device is located on the lower side of the center of the central wing (5), and the mounting device is a hanger or a hook.

6. The deployment model structure for an unmanned aerial flight test according to claim 1, characterized in that, The fuselage (4) has a hard shell and a truss. The hard shell is covered with a skin, and the hard shell is connected to the truss. The hard shell, the truss inside the hard shell, and the skin outside the hard shell together form a mixed load-bearing structure.

7. The deployment model structure for an unmanned aerial flight test according to claim 6, characterized in that, The truss has long trusses and longitudinal beams. The longitudinal beams are arranged along the longitudinal direction of the fuselage (4), and the long trusses are arranged along the circumferential direction of the fuselage (4). The longitudinal beams are connected to the long trusses and arranged perpendicular to each other. Each fuselage (4) has four longitudinal beams and multiple long trusses. A bulkhead is provided inside the fuselage (4), the bulkhead is connected to the truss, the fuselage (4) has a cabin, the bulkhead is located between the cabin and the truss, the truss is located outside the bulkhead, the hard shell is connected to a structural skeleton, the structural skeleton is located between the skin and the hard shell, and the structural skeleton, hard shell and skin form a box-type load-bearing structure.

8. The deployment model structure for an unmanned aerial flight test according to claim 1, characterized in that, The flight test launch model body (1) has a fuel tank, which is located at the lower end of the left and right wings (6) and close to the fuselage (4). The mounting device is welded or connected to the lower end of the central wing (5) by screws.

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