A test load vehicle capable of simulating a variety of aircraft

Abstract

The present invention provides a test load vehicle capable of simulating a variety of aircrafts, relates to the technical field of test devices, and solves the technical problem of the single simulated aircraft model in the test devices in the prior art. The device comprises a front frame, a rear frame, a front landing gear, a main landing gear and a cab, wherein the front frame and the rear frame are detachably connected, the front landing gear is detachably connected to the front frame, the cab is installed at the front end of the front frame, and the main landing gear is detachably connected to the rear frame; the number of the main landing gears is at least two, the wheelbases of all the main landing gears and the front landing gears are different, and a lifting structure is arranged on the main landing gears.

Description

Technical Field

[0001] The invention relates to the technical field of testing devices, in particular to a testing load vehicle capable of simulating multiple aircrafts. Background Art

[0002] At present, domestic wheeled aircraft tractors are still in the early stages of development. In order to better test the relevant performance of the tractor, corresponding test equipment is needed. Currently, there are very few relevant test equipment, and there are problems such as a single simulated aircraft model, a large difference between the front landing gear and the real aircraft, and a relatively bulky test equipment. Summary of the invention

[0003] The purpose of the present invention is to provide a test load vehicle that can simulate multiple aircrafts, so as to solve the technical problem of the single simulated aircraft type in the test device in the prior art. The preferred technical solution among the many technical solutions provided by the present invention can produce many technical effects as described below.

[0004] To achieve the above object, the present invention provides the following technical solutions:

[0005] The present invention provides a test load vehicle capable of simulating multiple aircrafts, comprising a front frame, a rear frame, a front landing gear, a main landing gear and a cab, wherein the front frame and the rear frame are detachably connected, the front landing gear is detachably connected to the front frame, the cab is installed at the front end of the front frame, and the main landing gear is detachably connected to the rear frame;

[0006] There are at least two main landing gears, all the main landing gears have different wheelbases from the front landing gear, and a lifting structure is provided on the main landing gear.

[0007] Optionally, a hydraulic outrigger cylinder is provided on the front frame.

[0008] Optionally, it also includes an engine system, a hydraulic system, an electrical system and a monitoring system.

[0009] Optionally, a counterweight system is further included, and the counterweight system is connected to the rear frame.

[0010] Optionally, it further comprises an outrigger cylinder, and the rear frame is connected to the outrigger cylinder.

[0011] Optionally, there is a height difference between the front end and the rear end of the front frame.

[0012] Optionally, the wheelbases on all the main landing gears are different.

[0013] Optionally, a detachable connecting plate is connected to the bottom of the connection between the front frame and the rear frame.

[0014] The present invention provides a test load vehicle capable of simulating a variety of aircrafts. The front landing gear is detachably connected to the front frame, and the front landing gears of different heights can be replaced with the corresponding front frames. The two main landing gears can be raised and lowered by a lifting structure, so that different wheelbases can be simulated, thereby simulating a variety of aircraft models, thus solving the technical problem of a single simulated aircraft model in the test device in the prior art. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0016] Figure 1 This is a front view of a test load vehicle capable of simulating a variety of aircrafts provided by an embodiment of the present invention;

[0017] Figure 2 It is a top view of a test load vehicle capable of simulating a variety of aircrafts provided by an embodiment of the present invention;

[0018] Figure 3 It is a right view of a test load vehicle capable of simulating various aircrafts provided by an embodiment of the present invention;

[0019] In the figure, 1, front frame; 11, hydraulic outrigger cylinder;

[0020] 2. Rear frame;

[0021] 3. Front landing gear;

[0022] 4. Main landing gear;

[0023] 5. Counterweight system;

[0024] 6. Outrigger cylinder;

[0025] 7. Connecting plate. DETAILED DESCRIPTION

[0026] To make the purpose, technical solution and advantages of the present invention clearer, the technical solution of the present invention will be described in detail below. Obviously, the described embodiments are only part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments of the present invention, all other implementation methods obtained by ordinary technicians in this field without creative work belong to the scope of protection of the present invention.

[0027] In the description of the present invention, it should be noted that, unless otherwise specified, the meaning of "plurality" is two or more; the orientations or positional relationships indicated by the terms "upper", "lower", "left", "right", "inner", "outer", "front end", "rear end", "head", "tail", etc. are based on the orientations or positional relationships shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limiting the present invention. In addition, the terms "first", "second", "third", etc. are only used for descriptive purposes and cannot be understood as indicating or implying relative importance.

[0028] In the description of the present invention, it is also necessary to explain that, unless otherwise clearly specified and limited, the terms "installation", "connection", and "connection" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0029] Embodiment 1:

[0030] The present invention provides a test load vehicle capable of simulating a variety of aircrafts, comprising a front frame 1, a rear frame 2, a front landing gear 3, a main landing gear 4 and a cab, wherein the front frame 1 and the rear frame 2 are detachably connected, the front landing gear 3 is detachably connected to the front frame 1, the cab is installed at the front end of the front frame 1, a tester can collect relevant data in the cab, and the main landing gear 4 is detachably connected to the rear frame 2;

[0031] The number of main landing gears 4 is at least two, and the wheelbases of all main landing gears 4 and front landing gears 3 are different. A lifting structure is provided on the main landing gears 4. When testing, after one main landing gear 4 touches the ground, the other main landing gears 4 can be lifted up by the lifting structure, so that different wheelbases can be selected. The present invention provides a test load vehicle that can simulate multiple aircrafts. The front landing gear 3 is detachably connected to the front frame 1, and the front landing gears 3 of different heights can be replaced with the corresponding front frame 1. The two main landing gears 4 can be lifted and lowered by the lifting structure, so that different wheelbases can be simulated, so that multiple aircraft models can be simulated, which solves the technical problem of the single simulation model of the test device in the prior art.

[0032] Embodiment 2:

[0033] The present invention provides a test load vehicle capable of simulating a variety of aircrafts, comprising a front frame 1, a rear frame 2, a front landing gear 3, a main landing gear 4 and a cab, wherein the front frame 1 and the rear frame 2 are detachably connected, the front landing gear 3 is detachably connected to the front frame 1, the cab is installed at the front end of the front frame 1, a tester can collect relevant data in the cab, and the main landing gear 4 is detachably connected to the rear frame 2;

[0034] There are at least two main landing gears 4, and the wheelbases of all main landing gears 4 and the front landing gear 3 are different. A lifting structure is provided on the main landing gear 4. When testing, after one main landing gear 4 touches the ground, the other main landing gears 4 can be lifted up by the lifting structure, so that different wheelbases can be selected.

[0035] As an optional implementation, a hydraulic leg cylinder 11 is provided on the front frame 1. When replacing the front landing gear 3, the hydraulic leg cylinder 11 can be lowered to lift up the front end of the front frame 1 to facilitate replacement of the front landing gear 3.

[0036] Embodiment 3:

[0037] The present invention provides a test load vehicle capable of simulating a variety of aircrafts, comprising a front frame 1, a rear frame 2, a front landing gear 3, a main landing gear 4 and a cab, wherein the front frame 1 and the rear frame 2 are detachably connected, the front landing gear 3 is detachably connected to the front frame 1, the cab is installed at the front end of the front frame 1, a tester can collect relevant data in the cab, and the main landing gear 4 is detachably connected to the rear frame 2;

[0038] There are at least two main landing gears 4, and the wheelbases of all main landing gears 4 and the front landing gear 3 are different. A lifting structure is provided on the main landing gear 4. When testing, after one main landing gear 4 touches the ground, the other main landing gears 4 can be lifted up by the lifting structure, so that different wheelbases can be selected.

[0039] As an optional implementation, it also includes an engine system, a hydraulic system, an electrical system and a monitoring system. The engine system can provide a hydraulic power source and a power source for the whole vehicle. The monitoring system is used to record the surrounding conditions of the vehicle. At the same time, due to the increase in the size of the test load vehicle, there are more blind spots during the test. The monitoring system also provides the tractor driver with a blind spot image to ensure safety during the test. The hydraulic system can drive the lifting structure and the hydraulic leg cylinder 11 to move.

[0040] As an optional embodiment, a counterweight system 5 is further included, and the counterweight system 5 is connected to the rear frame 2. A plurality of counterweight connection areas are provided on the rear frame 2, and the counterweight system can adjust the counterweight position according to the simulated aircraft model, so as to connect to the corresponding counterweight connection area, thereby simulating the real aircraft gross weight and center of gravity position.

[0041] As an optional implementation, it also includes an outrigger cylinder 6, the rear frame 2 is connected to the outrigger cylinder 6, a outrigger cylinder connecting plate is provided on the rear frame 2, the outrigger cylinder 6 is bolted to the outrigger cylinder connecting plate, and when the front frame 1 needs to be replaced, the outrigger cylinder 6 is connected to the corresponding outrigger cylinder connecting plate, so as to support the front end of the rear frame 2 to prevent the rear frame 2 from tipping over after the front frame 1 is disassembled.

[0042] As an optional implementation, there is a height difference between the front end and the rear end of the front frame 1. Front frames 1 of different specifications have different height differences, so that corresponding front landing gears 3 of different heights can be installed. The front landing gear 3 includes a front landing gear of a real aircraft and a mounting plate, the front landing gear of the real aircraft is connected to the mounting plate, a connecting section is provided on the front frame 1, and the mounting plate and the connecting section are bolted.

[0043] As an optional implementation, the wheelbases of all main landing gears 4 are different, so that the wheelbases of different aircraft can be simulated. When the wheelbase and wheelbase are determined, the corresponding main landing gear 4 is supported on the ground, and the other main landing gears 4 are lifted up. The main landing gear 4 includes a support frame plate and two roller seats, the two roller seats are respectively connected to the two ends of the support frame plate, and the lifting structure is connected to the roller seats. The lifting structure can lift or lower the rollers on the roller seats. The support frame plate is bolted to the rear frame 2, and the lifting structure can be a hydraulic lifting mechanism.

[0044] As an optional implementation, a detachable connecting plate 7 is connected to the bottom of the connection between the front frame 1 and the rear frame 2 , and the connecting plate 7 is used to strengthen the connection between the front frame 1 and the rear frame 2 .

[0045] The present invention can simulate the stress of the front landing gear of an aircraft to the greatest extent by using the front landing gear of a real aircraft. At the same time, the wheelbase and track of the whole vehicle are consistent with those of a real aircraft, ensuring that the stress of the front landing gear 3 in each test condition is the same as that of a real aircraft. In addition, by adjusting the position and number of the corresponding counterweight system 5, the total weight of the test load vehicle and the load of the front landing gear 3 can be consistent with those of a real aircraft. More importantly, different front landing gears 3 can be replaced, and the main landing gear 4 can be switched. The counterweight is a movable counterweight, and a variety of aircraft can be simulated by adjustment; the large parts of the whole vehicle are connected by bolts, which is convenient for disassembly and transportation of the whole vehicle during off-site testing; the main landing gear 4 adopts a lifting method, which is convenient for switching the simulated aircraft model; the weight and center of gravity position of the whole vehicle can be adjusted in real time according to the simulated aircraft model.

[0046] The above is only a specific embodiment of the present invention, but the protection scope of the present invention is not limited thereto. Any person skilled in the art can easily think of changes or substitutions within the technical scope disclosed by the present invention, which should be included in the protection scope of the present invention. Therefore, the protection scope of the present invention should be based on the protection scope of the claims.

Claims

1. A test load vehicle capable of simulating a variety of aircraft, characterized in that: It comprises a front frame (1), a rear frame (2), a front landing gear (3), a main landing gear (4) and a cab, wherein: The front frame (1) and the rear frame (2) are detachably connected, the front landing gear (3) is detachably connected to the front frame (1), the cab is installed at the front end of the front frame (1), and the main landing gear (4) is detachably connected to the rear frame (2); The number of the main landing gears (4) is at least two, the wheelbases of all the main landing gears (4) and the front landing gear (3) are different, and a lifting structure is provided on the main landing gears (4); The front frame (1) is provided with a hydraulic outrigger cylinder (11); There is a height difference between the front end and the rear end of the front frame (1); It also includes a leg cylinder (6), and the rear frame (2) is connected to the leg cylinder (6); The wheelbases of all the main landing gears (4) are different; When the wheelbase and track width are determined, the corresponding main landing gear (4) is supported on the ground, and the other main landing gears (4) are lifted up. The main landing gear (4) includes a support frame plate and two roller seats, the two roller seats are respectively connected to the two ends of the support frame plate, and the lifting structure is connected to the roller seats. The lifting structure can lift or lower the rollers on the roller seats, and the support frame plate is bolted to the rear frame (2).

2. A test load vehicle capable of simulating multiple aircrafts according to claim 1, characterized in that: It also includes engine systems, hydraulic systems, electrical systems and monitoring systems.

3. A test load vehicle capable of simulating multiple aircrafts according to claim 1, characterized in that: It also includes a counterweight system (5), and the counterweight system (5) is connected to the rear frame (2).

4. A test load vehicle capable of simulating multiple aircrafts according to claim 1, characterized in that: A detachable connecting plate (7) is connected to the bottom of the connection between the front frame (1) and the rear frame (2).

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