Aircraft radome transport vehicle

Abstract

The utility model discloses an aircraft radome transport vehicle, and belongs to the field of aircraft manufacturing. The transport vehicle comprises a vehicle body, a lifting mechanism, a clamp, a first adjusting mechanism and a second adjusting mechanism. The vehicle body comprises a first frame, a second frame and trundles, the first frame is located above the second frame, and the trundles are arranged on the second frame. The lifting mechanism is arranged between the first frame and the second frame. The clamp is arranged on the first frame and comprises a first arc-shaped frame and a second arc-shaped frame, and the first arc-shaped frame and the second arc-shaped frame are arranged at the two ends of the first frame. The first adjusting mechanism and the second adjusting mechanism are arranged between the first frame and the clamp, the first adjusting mechanism is used for adjusting the longitudinal positions of the first arc-shaped frame and the second arc-shaped frame on the first frame, and the second adjusting mechanism is used for adjusting the transverse positions of the first arc-shaped frame and the second arc-shaped frame on the first frame. According to the aircraft radome transport vehicle, the first frame can be lifted to enable the clamp to be close to an aircraft radome and then clamp and fix the aircraft radome, operation is easy, safety and reliability are achieved, and the efficiency of aircraft radome transport work is improved.

Description

Technical Field

[0001] The utility model belongs to the field of aircraft manufacturing, and particularly relates to an aircraft radome transport vehicle. Background Art

[0002] In the aviation field, the aircraft radome plays an irreplaceable role. It can support a protective umbrella for the complex radar system inside the radome on the basis of not interfering with the radar detection performance, so that it is protected from various forms of damage. The radome is mostly a composite material shell, and is also equipped with complex systems such as lightning protection, anti-static electricity and rain erosion protection, presenting the characteristics of a large and complex structure as a whole.

[0003] The radar is an electronic device that can provide important information about the surrounding environment of the aircraft for the pilot, such as thunderstorm conditions, terrain obstacles, and the position information of other surrounding aircraft. This fully demonstrates the important position of the radar in flight activities. In the operation process related to the radar, the transportation link is crucial. For the aircraft radome, it is very difficult in the disassembly, installation and transportation process. On the one hand, due to its complex and large structure, it needs to be protected in all directions during transportation to prevent damage. However, most of the current transportation equipment adopts a hard connection method, which is prone to shaking during transportation, and this shaking has a great risk of damaging the radome. On the other hand, the height of the aircraft radome is relatively high, which brings inconvenience to the manual disassembly and installation operations.

[0004] The existing vehicle for transporting the radome has many problems. For example, it lacks a lifting function. When transporting the radome, it has to rely on a mobile platform and manual handling, which is not only complicated in operation but also has potential safety hazards. At the same time, the existing transportation vehicle does not effectively fix the radome. During transportation, the shaking of the vehicle is very likely to cause damage to the radome. These problems seriously restrict the efficiency and safety of the aircraft radome transportation, and new solutions are urgently needed to improve the situation. Summary of the Invention

[0005] Aiming at the deficiencies existing in the related technologies, the purpose of the utility model is to provide an aircraft radome transport vehicle to solve the problems put forward in the above background art.

[0006] To achieve the above purpose, the utility model provides the following technical solutions:

[0007] An aircraft radome transport vehicle, comprising:

[0008] A vehicle body, which includes a first frame, a second frame and casters. The first frame is located above the second frame, and the casters are arranged on the second frame;

[0009] A lifting mechanism, which is arranged between the first frame and the second frame, and the lifting mechanism is used to lift the first frame;

[0010] The clamp is mounted on the first frame and includes a first arc frame and a second arc frame. The first arc frame is mounted at one end of the first frame and the second arc frame is mounted at the other end of the first frame. The first arc frame and the second arc frame are used to clamp and fix the aircraft radome.

[0011] The first adjustment mechanism is located between the first frame and the clamp. There are two first adjustment mechanisms, which are used to adjust the longitudinal position of the first arc frame and the second arc frame on the first frame, respectively.

[0012] The second adjustment mechanism is located between the first frame and the clamp. There are two second adjustment mechanisms, which are used to adjust the lateral position of the first arc frame and the second arc frame on the first frame, respectively.

[0013] In some embodiments, the lifting mechanism includes a scissor mechanism and a hydraulic system. One end of the scissor mechanism is connected to a first frame and the other end is connected to a second frame. The hydraulic system is located on the second frame and drives the scissor mechanism to extend or retract to lift the first frame.

[0014] In some embodiments, the hydraulic system includes:

[0015] Fuel tank, the fuel tank stores fuel;

[0016] A hydraulic cylinder, which has a piston rod, is connected to a scissor mechanism;

[0017] The drive pump is connected to the oil tank and the hydraulic cylinder through pipelines. The drive pump pressurizes the oil in the oil tank so that the oil enters the hydraulic cylinder to retract or extend the piston rod of the hydraulic cylinder.

[0018] A two-position four-way directional valve has a valve core and is located on the pipeline between the drive pump and the hydraulic cylinder. The two-position four-way directional valve is connected to the oil tank through the pipeline. The two-position four-way directional valve switches the direction of oil flow by changing the position of the valve core. When the valve core is in the first position, the oil flows from the drive pump to the rodless chamber of the hydraulic cylinder, and the piston rod of the hydraulic cylinder extends. When the valve core is in the second position, the oil flows from the drive pump to the rod chamber of the hydraulic cylinder, and the piston rod of the hydraulic cylinder retracts.

[0019] In some embodiments, the hydraulic system further includes a filter and a relief valve. Two filters are provided, one on the pipeline connecting the drive pump to the oil tank and the other on the pipeline connecting the drive pump to the hydraulic cylinder. The relief valve is connected in parallel with the drive pump.

[0020] In some embodiments, the driving pumps are a hand-cranked pump and an electric pump connected in parallel, both of which have a check valve.

[0021] In some embodiments, the aircraft radome transport vehicle also includes an electronic control system and a cable reel, which are mounted on a second frame. The electronic control system is electrically connected to an electric pump and is connected to an external power source via a power cord wound on the cable reel.

[0022] In some embodiments, the vehicle body also includes a tow bar, which is mounted on a hydraulic system and connected to a hand pump to serve as a handle for the hand pump. The tow bar is also used to tow the vehicle body.

[0023] In some embodiments, the hydraulic system also includes a three-way valve located on the pipeline connecting the hand pump to the hydraulic cylinder. The three-way valve is connected in parallel with the electric pump and is connected to the oil tank via a pipeline. The three-way valve is used to allow the oil in the hand pump to flow back to the oil tank when the tow bar pulls the vehicle body.

[0024] In some embodiments, the caster includes two swivel wheels and two fixed wheels.

[0025] In some embodiments, the first frame and the second frame are welded from square steel.

[0026] Compared with the prior art, the beneficial effects of this utility model are:

[0027] 1. The aircraft radome transport vehicle provided by this utility model consists of a vehicle body, a lifting mechanism, a clamp, a first adjustment mechanism, and a second adjustment mechanism. It has a simple structure. After the first frame is raised to bring the clamp close to the aircraft radome, the first adjustment mechanism and the second adjustment mechanism adjust the position of the clamp to be directly below the aircraft radome. Then, the aircraft radome is clamped and fixed for transport. The operation is simple, safe and reliable, and improves the efficiency of aircraft radome transport.

[0028] 2. The lifting mechanism of the aircraft radome transport vehicle provided by this utility model includes a hydraulic system. The driving pump of the hydraulic system is a hand-cranked pump and an electric pump connected in parallel. When the first frame is raised to bring the clamp close to the aircraft radome, the electric pump is used to quickly adjust the clamp to a general range close to the aircraft radome, and then the hand-cranked pump is used for more precise fine-tuning. The adjustment accuracy is high, the adjustment difficulty is low, and the efficiency of the entire adjustment work is improved. Attached Figure Description

[0029] The accompanying drawings, which are included to provide a further understanding of the present invention and form part of this application, illustrate exemplary embodiments of the present invention and, together with the description thereof, serve to explain the present invention and do not constitute an undue limitation thereof. In the drawings:

[0030] Figure 1 This is a schematic diagram of the structure of one embodiment of the aircraft radome transport vehicle of this utility model;

[0031] Figure 2This is a schematic front view of one embodiment of the aircraft radome transport vehicle of this utility model;

[0032] Figure 3 This is a schematic left view of one embodiment of the aircraft radome transport vehicle of this utility model;

[0033] Figure 4 This is a schematic top view of one embodiment of the aircraft radome transport vehicle of this utility model;

[0034] Figure 5 This is a schematic diagram of the hydraulic system of one embodiment of the aircraft radome transport vehicle of this utility model.

[0035] In the picture:

[0036] 1. Vehicle body; 11. First frame; 12. Second frame; 13. Casters; 131. Universal casters; 132. Fixed casters; 14. Tow bar; 2. Lifting mechanism; 21. Scissor mechanism; 22. Hydraulic system; 221. Oil tank; 222. Hydraulic cylinder; 223. Drive pump; 2231. Hand pump; 2232. Electric pump; 224. Two-position four-way directional valve; 225. Filter; 226. Overflow valve; 227. Three-way valve; 3. Clamp; 31. First arc frame; 32. Second arc frame; 4. First adjusting mechanism; 41. First rail; 42. First lead screw; 43. First slider; 44. First hand crank; 5. Second adjusting mechanism; 51. Second rail; 52. Second lead screw; 53. Second slider; 54. Second hand crank; 6. Electrical control system. Detailed Implementation

[0037] The technical solutions in the embodiments of this utility model will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of this utility model, and not all of them. All other embodiments obtained by those skilled in the art based on the embodiments of this utility model without creative effort are within the scope of protection of this utility model.

[0038] In the description of this utility model, it should be understood that the terms "center", "lateral", "longitudinal", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", and "outer" indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this utility model and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this utility model.

[0039] In the description of this utility model, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "joining" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this utility model based on the specific circumstances.

[0040] See attached Figures 1 to 5 This paper presents an illustrative embodiment of the aircraft radome transport vehicle proposed in this utility model. The aircraft radome transport vehicle includes a vehicle body 1, a lifting mechanism 2, a clamp 3, a first adjustment mechanism 4, and a second adjustment mechanism 5.

[0041] The vehicle body 1 includes a first frame 11, a second frame 12, and casters 13. The first frame 11 and the second frame 12 are welded from square steel. The first frame 11 is located above the second frame 12, and the casters 13 are mounted on the second frame 12 to facilitate the movement of the vehicle body 1 to change its working position or for transportation. A lifting mechanism 2 is located between the first frame 11 and the second frame 12, and is used to lift the first frame 11. A clamp 3 is mounted on the first frame 11 and includes a first arc-shaped frame 31 and a second arc-shaped frame 32. The first arc-shaped frame 31 is located at one end of the first frame 11, and the second arc-shaped frame 32 is located at the other end of the first frame 11. The first arc-shaped frame 31 and the second arc-shaped frame 32 are used to clamp and fix the aircraft radome. When the lifting mechanism 2 raises the first frame 11, the clamp 3 approaches the aircraft radome to clamp and fix it.

[0042] In this embodiment, the first arc-shaped frame 31 and the second arc-shaped frame 32 are in direct contact with the aircraft radome. The two arc-shaped frames have the same shape as the aircraft radome. Since the aircraft radome uses radar-absorbing material, felt is placed at the contact points between the first arc-shaped frame 31 and the second arc-shaped frame 32 and the aircraft radome to protect the radome. The first arc-shaped frame 31 is a fixed arc-shaped frame, while the second arc-shaped frame 32 is a height-adjustable arc-shaped frame. The bottom end of the second arc-shaped frame 32 has multiple fixing holes. By inserting a pin into different fixing holes, the height of the second arc-shaped frame 32 can be changed, achieving fine-tuning of the height of the second arc-shaped frame 32.

[0043] Two first adjustment mechanisms 4 are located between the first frame 11 and the clamp 3. These two mechanisms are used to adjust the longitudinal positions of the first arc-shaped frame 31 and the second arc-shaped frame 32 on the first frame 11, respectively. Two second adjustment mechanisms 5 are also located between the first frame 11 and the clamp 3. These two mechanisms are used to adjust the lateral positions of the first arc-shaped frame 31 and the second arc-shaped frame 32 on the first frame 11, respectively. When the lifting mechanism 2 raises the first frame 11, bringing the clamp 3 closer to the aircraft radome, the clamp 3 is adjusted to be directly below the aircraft radome through the cooperation of the first and second adjustment mechanisms 4 and 5, ensuring smooth clamping and fixing.

[0044] The first adjustment mechanism 4 includes a first track 41, a first lead screw 42, a first slider 43, and a first hand crank 44. The first track 41 is disposed on the first frame 11, the first slider 43 is disposed on the first track 41 to slide along the first track 41, the first lead screw 42 is disposed on the first frame 11, and the first lead screw 42 is threadedly connected to the first slider 43 so that when the first lead screw 42 rotates, it drives the first slider 43 to slide along the first track 41, and the first hand crank 44 is disposed at one end of the first lead screw.

[0045] The second adjustment mechanism 5 includes a second track 51, a second lead screw 52, ​​a second slider 53, and a second hand crank 54. The second track 51 is disposed on the first slider 43, and the second slider 53 is disposed on the second track 51 to slide along the second track 51. The second slider 53 is connected to the fixing clamp 3. The second lead screw 52 is disposed on the first slider 43 and is threadedly connected to the second slider 53 so that when the second lead screw 52 rotates, it drives the second slider 53 to slide along the second track 51. The second hand crank 54 is disposed at one end of the second lead screw.

[0046] The lifting mechanism 2 includes a scissor mechanism 21 and a hydraulic system 22. One end of the scissor mechanism 21 is connected to the first frame 11, and the other end is connected to the second frame 12. The hydraulic system 22 is located on the second frame 12. The hydraulic system 22 drives the scissor mechanism 21 to unfold or retract to lift the first frame 11.

[0047] The hydraulic system 22 includes an oil tank 221, a hydraulic cylinder 222, a drive pump 223, and a two-position four-way directional valve 224. The oil tank 221 stores hydraulic fluid. The hydraulic cylinder 222 has a piston rod, which is connected to a scissor mechanism 21. The drive pump 223 is connected to the oil tank 221 and the hydraulic cylinder 222 via a pipeline. The drive pump 223 pressurizes the hydraulic fluid in the oil tank 221, causing the hydraulic fluid to enter the hydraulic cylinder 222 and retract or extend the piston rod. The two-position four-way directional valve 224 has a valve core and is located on the pipeline between the drive pump 223 and the hydraulic cylinder 222. The two-position four-way directional valve 224 is connected to the oil tank 221 via a pipeline, and the valve core switches the direction of hydraulic fluid flow. When the valve core is in the first position, oil flows from the drive pump 223 to the rodless chamber of the hydraulic cylinder 222, the piston rod of the hydraulic cylinder 222 extends, the scissor mechanism 21 unfolds, and the first frame 11 rises. When the valve core is in the second position, oil flows from the drive pump 223 to the rod chamber of the hydraulic cylinder 222, the piston rod of the hydraulic cylinder 222 retracts, the scissor mechanism 21 retracts, and the first frame 11 descends.

[0048] The hydraulic system 22 also includes a filter 225 and a relief valve 226. Two filters 225 are provided, one on the pipeline connecting the drive pump 223 to the oil tank 221 and the other on the pipeline connecting the drive pump 223 to the hydraulic cylinder 222. The relief valve 226 is connected in parallel with the drive pump 223. The filters 225 effectively filter out impurities in the hydraulic fluid, preventing these impurities from entering the internal components and causing wear, thereby extending the service life of the components and reducing maintenance costs. During operation, the hydraulic system 22 may experience pressure increases due to various reasons, such as a sudden increase in load or oil circuit blockage. The relief valve 226 automatically opens when the pressure in the hydraulic system 22 exceeds a set value, draining excess oil back to the oil tank 221, thus protecting the components in the hydraulic system 22 from damage due to excessive pressure.

[0049] The drive pump 223 consists of a hand-cranked pump 2231 and an electric pump 2232 connected in parallel, both of which have one-way valves. Specifically, during operation, the electric pump 2232 can be used to raise the first frame 11 to a position close to the aircraft radome, and then the hand-cranked pump 2231 can be used to fine-tune the height of the first frame 11. This provides high adjustment precision, low adjustment difficulty, and improves the efficiency of the entire adjustment process.

[0050] In this embodiment, the hand-cranked pump 2231 can be model SB-6A, with a flow rate of 15 ml / cycle, a handle operating force of approximately 170 N, and uses No. 15 aviation hydraulic oil. The working pressure is 14.7 MPa, the overload pressure is 22.1 MPa, and the handle rotation angle is 0–60°. The electric pump 2232 can be model MCY14-1B, with a nominal pressure reaching 31.5 MPa and a nominal displacement of 2.5 ml / r. The pump body is made of No. 45 steel, and the inlet is equipped with a corrosion-resistant sealing ring, ensuring durability and efficient, stable, and safe operation of the machine.

[0051] The aircraft radome transport vehicle also includes an electronic control system 6 and a cable reel, which are mounted on the second frame 12. The electronic control system 6 is electrically connected to the electric pump 2232 and is connected to an external power source via a power cable wound on the cable reel. The external power source is a 220V power supply, and considering the field operating environment, a 30-meter power cable is provided for the convenience of maintenance personnel.

[0052] The electrical control system 6 can adjust the motor speed of the electric pump 2232. The electrical control system 6 includes a control panel with an emergency stop switch, a power switch, an up button, a down button, and a speed control knob. Pressing the emergency stop switch stops the electric pump 2232, and the lifting mechanism 2 stops in an emergency. Pressing the power switch powers on the electrical control system 6. Pressing the up button extends the piston rod of the hydraulic cylinder 222. Pressing the down button retracts the piston rod of the hydraulic cylinder 222. The speed of the electric pump 2232 is adjusted by the speed control knob, thereby controlling the lifting speed of the first frame 11.

[0053] The vehicle body 1 also includes a tow bar 14, which is mounted on the hydraulic system 22. The tow bar 14 is connected to the hand pump 2231 to serve as the handle of the hand pump 2231, and is also used to tow the vehicle body 1. The tow bar 14 has a long lever arm to make it easy for the operator to operate.

[0054] The hydraulic system 22 also includes a three-way valve 227, which is located on the pipeline connecting the hand pump 2231 to the hydraulic cylinder 222. The three-way valve 227 is connected in parallel with the electric pump 2232 and is connected to the oil tank 221 through a pipeline. The three-way valve 227 is used to return the oil in the hand pump 2231 to the oil tank 221 when the tow bar 14 pulls the vehicle body 1.

[0055] The caster 13 includes two swivel casters 131 and two fixed casters 132. In this embodiment, the two front casters 131 can be controlled by the tow bar 141, and the two rear casters 132 are fixed casters. Specifically, the swivel casters 131 are model JDD-50, and the fixed casters 132 are model JDB-50. The casters 13 are wear-resistant and equipped with brakes, which can be used to brake during installation to ensure the aircraft radome transport vehicle is stably parked under the aircraft.

[0056] In the above illustrative embodiments, the aircraft radome transport vehicle has a simple structure. After the first frame is raised to bring the clamp close to the aircraft radome, the first adjustment mechanism and the second adjustment mechanism adjust the position of the clamp to be directly below the aircraft radome, and then clamp and fix the aircraft radome for transport. The operation is simple, safe and reliable, and improves the efficiency of aircraft radome transport.

[0057] Finally, it should be noted that the various embodiments in this specification are described in a progressive manner, with each embodiment focusing on the differences from other embodiments. The same or similar parts between the various embodiments can be referred to each other.

[0058] The above embodiments are only used to illustrate the technical solution of this utility model and not to limit it; although the utility model has been described in detail with reference to preferred embodiments, those skilled in the art should understand that modifications can still be made to the specific implementation of this utility model or equivalent substitutions can be made to some technical features without departing from the spirit of the technical solution of this utility model, and all such modifications and substitutions should be covered within the scope of the technical solution claimed by this utility model.

Claims

1. An aircraft radome transport vehicle, characterized in that, include: The vehicle body includes a first frame, a second frame, and casters, wherein the first frame is located above the second frame, and the casters are mounted on the second frame; A lifting mechanism is provided between the first frame and the second frame, and the lifting mechanism is used to lift the first frame. The clamp is disposed on the first frame and includes a first arc frame and a second arc frame. The first arc frame is disposed at one end of the first frame and the second arc frame is disposed at the other end of the first frame. The first arc frame and the second arc frame are used to clamp and fix the aircraft radome. The first adjustment mechanism is located between the first frame and the clamp. There are two first adjustment mechanisms, which are used to adjust the longitudinal position of the first arc frame and the second arc frame on the first frame, respectively. The second adjustment mechanism is located between the first frame and the clamp. There are two second adjustment mechanisms, which are used to adjust the lateral position of the first arc frame and the second arc frame on the first frame, respectively.

2. The aircraft radome transport vehicle according to claim 1, characterized in that, The lifting mechanism includes a scissor mechanism and a hydraulic system. One end of the scissor mechanism is connected to the first frame and the other end is connected to the second frame. The hydraulic system is located on the second frame and drives the scissor mechanism to extend or retract to lift the first frame.

3. The aircraft radome transport vehicle according to claim 2, characterized in that, The hydraulic system includes: Fuel tank, which stores oil; A hydraulic cylinder having a piston rod, the piston rod of which is connected to the scissor mechanism; A drive pump is connected to the oil tank and the hydraulic cylinder via a pipeline. The drive pump pressurizes the oil in the oil tank so that the oil enters the hydraulic cylinder and retracts or extends the piston rod of the hydraulic cylinder. A two-position four-way directional valve, having a valve core, is located on the pipeline between the drive pump and the hydraulic cylinder. The two-position four-way directional valve is connected to the oil tank via a pipeline. The two-position four-way directional valve switches the direction of oil flow by changing the position of the valve core. When the valve core is in the first position, oil flows from the drive pump to the rodless chamber of the hydraulic cylinder, and the piston rod of the hydraulic cylinder extends. When the valve core is in the second position, oil flows from the drive pump to the rod chamber of the hydraulic cylinder, and the piston rod of the hydraulic cylinder retracts.

4. The aircraft radome transport vehicle according to claim 3, characterized in that, The hydraulic system also includes a filter and a relief valve. There are two filters, which are respectively located on the pipeline connecting the drive pump to the oil tank and the pipeline connecting the drive pump to the hydraulic cylinder. The relief valve is connected in parallel with the drive pump.

5. The aircraft radome transport vehicle according to claim 3, characterized in that, The drive pump consists of a hand-cranked pump and an electric pump connected in parallel, and both the hand-cranked pump and the electric pump have a one-way valve.

6. The aircraft radome transport vehicle according to claim 5, characterized in that, It also includes an electronic control system and a winding reel, which are mounted on the second frame. The electronic control system is electrically connected to the electric pump and is connected to an external power source via a power cord, which is wound around the winding reel.

7. The aircraft radome transport vehicle according to claim 5, characterized in that, The vehicle body also includes a tow bar, which is mounted on the hydraulic system. The tow bar is connected to the hand pump to serve as the handle of the hand pump, and is also used to tow the vehicle body.

8. The aircraft radome transport vehicle according to claim 7, characterized in that, The hydraulic system also includes a three-way valve, which is located on the pipeline connecting the hand pump to the hydraulic cylinder. The three-way valve is connected in parallel with the electric pump and is connected to the oil tank through a pipeline. The three-way valve is used to allow the oil in the hand pump to flow back to the oil tank when the tow bar pulls the vehicle body.

9. The aircraft radome transport vehicle according to any one of claims 1-8, characterized in that, The casters include two swivel wheels and two fixed wheels.

10. The aircraft radome transport vehicle according to any one of claims 1-8, characterized in that, The first frame and the second frame are made of square steel welded together.

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