阅读说明：本技术 模块化的飞机油箱组件及飞机 (Modular aircraft tank subassembly and aircraft ) 是由 盛文星 于 2020-11-24 设计创作，主要内容包括：本申请涉及一种模块化的飞机油箱组件及飞机。模块化的飞机油箱组件包括：第一油箱,包括加油口、第一出油口和第一通气口；第二油箱,包括第一进油口、供油口、回油口和第二通气口,第一出油口连接第一进油口,第一通气口连接第二通气口；温度传感器,用于检测飞机油箱组件内的燃油温度；通气平衡阀,用于平衡飞机油箱组件内部与外界的气压；油量传感器,用于检测飞机油箱组件内的油量。本申请的模块化的飞机油箱组件结构简单,安全性高,便于增加增程油箱。(The application relates to a modularized aircraft fuel tank assembly and an aircraft. A modular aircraft fuel tank assembly comprising: the first oil tank comprises an oil filling port, a first oil outlet and a first air vent; the second oil tank comprises a first oil inlet, an oil supply port, an oil return port and a second vent port, the first oil outlet is connected with the first oil inlet, and the first vent port is connected with the second vent port; a temperature sensor for detecting the temperature of fuel in an aircraft fuel tank assembly; the ventilation balance valve is used for balancing the air pressure inside the aircraft fuel tank assembly and the outside; and the oil quantity sensor is used for detecting the oil quantity in the aircraft oil tank assembly. The modularized aircraft fuel tank assembly is simple in structure, high in safety and convenient to increase a range-extending fuel tank.)

1. A modular aircraft fuel tank assembly, comprising:

the first oil tank comprises an oil filling port, a first oil outlet and a first air vent;

the second oil tank comprises a first oil inlet, an oil supply port, an oil return port and a second vent port, the oil supply port is used for conveying fuel oil to the engine, the oil return port is used for enabling redundant fuel oil of the engine to flow back to the fuel tank assembly of the fuel aircraft, the first oil outlet is connected with the first oil inlet, and the first vent port is connected with the second vent port;

a temperature sensor for detecting a temperature of fuel within the aircraft fuel tank assembly;

a vent balancing valve for balancing air pressure within the aircraft tank assembly with ambient air;

and the oil quantity sensor is used for detecting the oil quantity in the aircraft oil tank assembly.

2. The modular aircraft tank assembly of claim 1, wherein both side surfaces of the first tank and both side surfaces of the second tank are curved surfaces.

3. The modular aircraft fuel tank assembly of claim 1, further comprising a first lightning protection sheet connected at each end to the first and second fuel tanks.

4. The modular aircraft oil tank assembly of claim 1, further comprising a third oil tank, said third oil tank including a second oil inlet, a second oil outlet, a third vent and a fourth vent, said third oil tank disposed between said first oil tank and said second oil tank, said first oil outlet connected to said second oil inlet, said second oil outlet connected to said first oil inlet, said first vent connected to said third vent, said fourth vent connected to said second vent.

5. A modular aircraft tank assembly as claimed in claim 4, in which both sides of the third tank are cambered surfaces.

6. The modular aircraft fuel tank assembly of claim 4, further comprising a second lightning protection sheet and a third lightning protection sheet, wherein the second lightning protection sheet is connected at both ends to the first fuel tank and the third fuel tank, respectively, and the third lightning protection sheet is connected at both ends to the third fuel tank and the second fuel tank, respectively.

7. The modular aircraft tank assembly of claim 1, further comprising a fuel drain valve disposed on the second tank.

8. The modular aircraft tank assembly of claim 1, further comprising a low oil level switch disposed on the second tank.

9. An aircraft comprising a modular aircraft tank assembly as claimed in any one of claims 1 to 8 and a wing having a rib provided with a mounting aperture corresponding to the aircraft tank assembly, the aircraft tank assembly being provided in the rib.

10. An aircraft according to claim 9, wherein the aircraft tank assembly is provided with spacers corresponding to the location of the ribs.

Technical Field

The application relates to the field of aircraft manufacturing, in particular to a modularized aircraft fuel tank assembly and an aircraft.

Background

The general airplane mostly adopts an integral oil tank, and utilizes the internal volume of the airplane structure to store fuel oil by using a vulnerable wing leading edge or a structural space formed by a skin and a wing beam. The integral fuel tank has high requirements on structural tightness, and if the wing leading edge or the skin of the integral fuel tank is slightly damaged, fuel can leak, so that disastrous results are caused.

Moreover, the structural form of the whole oil tank is not beneficial to quick modification of the airplane so as to increase the range, and the structural modification difficulty of the oil tank is large, the cost is high and the period is long.

Disclosure of Invention

Based on the problem of above-mentioned background art, the application provides a modular aircraft tank subassembly and aircraft, and modular aircraft tank subassembly includes a plurality of fuel tanks, has overcome because of the easy slight fuel leakage that damages and lead to of wing leading edge or covering, and the security is high.

One embodiment of the present application provides a modular aircraft oil tank assembly comprising: the first oil tank comprises an oil filling port, a first oil outlet and a first air vent; the second oil tank comprises a first oil inlet, an oil supply port, an oil return port and a second vent port, the oil supply port is used for conveying fuel oil to the engine, the oil return port is used for enabling redundant fuel oil of the engine to flow back to the fuel tank assembly of the fuel aircraft, the first oil outlet is connected with the first oil inlet, and the first vent port is connected with the second vent port; a temperature sensor for detecting a temperature of fuel within the aircraft fuel tank assembly; a vent balancing valve for balancing air pressure within the aircraft tank assembly with ambient air; and the oil quantity sensor is used for detecting the oil quantity in the aircraft oil tank assembly.

According to some embodiments of the application, both sides of the first tank and both sides of the second tank are cambered surfaces.

According to some embodiments of the present application, the modular aircraft fuel tank assembly further comprises a first lightning protection sheet connected at both ends to the first fuel tank and the second fuel tank, respectively.

According to some embodiments of the present application, the modular aircraft fuel tank assembly further comprises a third fuel tank, the third fuel tank comprises a second oil inlet, a second oil outlet, a third vent and a fourth vent, the third fuel tank set up between the first fuel tank and the second fuel tank, the first oil outlet is connected to the second oil inlet, the second oil outlet is connected to the first oil inlet, the first vent is connected to the third vent, the fourth vent is connected to the second vent.

According to some embodiments of the application, both sides of the third tank are cambered surfaces.

According to some embodiments of the present application, the modular aircraft tank assembly further comprises a second lightning protection sheet and a third lightning protection sheet, wherein two ends of the second lightning protection sheet are respectively connected to the first oil tank and the third oil tank, and two ends of the third lightning protection sheet are respectively connected to the third oil tank and the second oil tank.

According to some embodiments of the present application, the modular aircraft tank assembly further comprises a drain valve disposed on the second tank.

According to some embodiments of the present application, the modular aircraft tank assembly further comprises a low oil level switch disposed on the second tank.

An embodiment of the present application provides an aircraft comprising a modular aircraft tank assembly as described above, a wing rib of a wing being provided with a mounting aperture corresponding to the aircraft tank assembly, the aircraft tank assembly being provided in the wing rib.

According to some embodiments of the present application, the aircraft tank assembly is provided with spacers corresponding to the location of the ribs.

The modularized airplane fuel tank assembly comprises a plurality of fuel tanks, the modularized design is realized, the adjacent fuel tanks are flexibly communicated, various deformations of wings under pneumatic load can be adapted, the structural form is simple, and the manufacturing cost is low; the aircraft fuel tank assembly can be installed in the wing ribs of the wings, so that fuel leakage caused by easy damage of the front edges or skins of the wings of the integral fuel tank is avoided, and the aircraft fuel tank assembly is safe and reliable.

Drawings

In order to more clearly illustrate the technical solutions of the present application, the drawings needed to be used in the description of the embodiments are briefly introduced below, it is obvious that the drawings in the following description are only some embodiments of the present application, and it is obvious for a person skilled in the art to obtain other drawings based on these drawings without exceeding the protection scope of the present application.

FIG. 1 is a schematic illustration of a modular aircraft fuel tank assembly in accordance with an embodiment of the present application;

FIG. 2 is a schematic view of a connection between a first fuel tank and a second fuel tank according to an embodiment of the present invention;

fig. 3 is a schematic view of a modular aircraft fuel tank assembly with extended range fuel tanks according to an embodiment of the present application.

Detailed Description

The technical solutions of the present application will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present application, and it is obvious that the described embodiments are some, not all, of the embodiments of the present application. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application.

Example 1

As shown in fig. 1 and 2, one embodiment of the present application provides a modular aircraft fuel tank assembly 100 for storing fuel on board an aircraft. The aircraft fuel tank assembly 100 comprises a plurality of fuel tanks connected in sequence, and in this embodiment, the aircraft fuel tank assembly 100 comprises: a first tank 1 and a second tank 2.

The first oil tank 1 includes an oil filler port 11, a first oil outlet, and a first air vent. In this embodiment, the oil filler port 11 is located on the top surface of the first oil tank 1 for refueling the aircraft oil tank assembly 100. When the aircraft tank assembly 100 is mounted on the wing, the oil filling port 11 is connected with an oil port on the wing for connecting an external oil pipe. The first oil outlet and the first air vent are positioned on one end surface of the first oil tank 1.

The second oil tank 2 comprises a first oil inlet, an oil supply port, an oil return port and a second vent port. The first oil inlet and the second vent are located on one end face of the second oil tank 2, and the oil supply port and the oil return port are located on the other end face of the second oil tank 2. The fuel supply port is used for supplying fuel in the aircraft tank assembly 100 to the engine, and the fuel return port is used for returning excess fuel of the engine to the aircraft tank assembly 100. The first oil outlet is connected with the first oil inlet, and the first air vent is connected with the second air vent, so that the first oil tank 1 is connected with the second oil tank 2. In this embodiment, when the aircraft fuel tank assembly 100 is mounted on the wing, the first fuel tank 1 is located slightly higher than the second fuel tank 2, so that the fuel in the first fuel tank 1 can flow to the second fuel tank 2 through the first oil outlet and the first oil inlet.

The first oil outlet is connected with the first oil inlet and is connected with the first oil inlet through an oil-resistant hose 3, and the first air vent is connected with the second air vent and is connected with the second air vent through an air vent hose. The adjacent fuel tanks are flexibly communicated, so that the modularized aircraft fuel tank assembly 100 can adapt to various deformations of wings under pneumatic load, and the safety of the fuel tanks is improved.

The modular aircraft tank assembly 100 also includes a temperature sensor, a vent balancing valve, and a fuel level sensor. The temperature sensor is used for the temperature of the fuel in the aircraft tank assembly 100. Optionally, a temperature sensor is provided on the second fuel tank 2 to facilitate detection of the temperature of the fuel within the aircraft fuel tank assembly 100. The vent balancing valve is used to balance the air pressure inside the aircraft tank assembly 100 with the outside. Optionally, a ventilation balance valve is arranged on the first fuel tank 1, the ventilation balance valve is communicated with outside air, and the expansion space at the top of the connected fuel tank is communicated through a ventilation hose, so that the balance between the inside of the aircraft fuel tank assembly 100 and the outside air pressure is ensured, and negative pressure is prevented from being formed in the aircraft fuel tank assembly 100 due to the consumption of fuel. The fuel level sensor is used to detect the amount of fuel within the aircraft fuel tank assembly 100. The temperature sensor, the ventilation balance valve and the oil quantity sensor are all selected from existing elements.

The modularized aircraft fuel tank assembly 100 of the embodiment can be installed in a wing rib of a wing, so that fuel leakage caused by easy damage of a wing leading edge or a skin of an existing fuel tank structure is avoided, and the safety of the aircraft is improved.

According to an optional technical scheme of this application, two sides of first oil tank 1 and two sides of second oil tank 2 are the cambered surface. The first tank 1 and the second tank 2 are approximately racetrack shaped in cross-section to facilitate the installation of the aircraft tank assembly 100 into the mounting holes of the ribs. The cross-sections of the first and second tanks 1, 2 may be provided in other shapes as needed.

According to an alternative aspect of the present application, the modular aircraft tank assembly 100 further comprises a first lightning protection sheet 51. One end of the first lightning protection sheet 51 is connected to the first oil tank 1, and the other end is connected to the second oil tank 2. The first lightning protection sheet 51 is connected with the first oil tank 1 and the second oil tank 2, so that the potentials of the first oil tank 1 and the second oil tank 2 can be kept equal, and the safety of the aircraft oil tank assembly 100 is improved.

As shown in fig. 3, according to an alternative embodiment of the present application, the modular aircraft tank assembly 100 further comprises a third tank 6. The third oil tank 6 serves as a range-extended oil tank for storing range-extended fuel oil. The third tank 6 is provided between the first tank 1 and the second tank 2. The third oil tank 6 comprises a second oil inlet, a second oil outlet, a third air port and a fourth air port, the second oil inlet and the third air port are arranged on the end face, close to the first oil tank 1, of the third oil tank 6, and the second oil outlet and the fourth air port are arranged on the end face, close to the second oil tank 2, of the third oil tank 6. The first oil outlet of the first oil tank 1 is connected with the second oil inlet of the third oil tank 6, the second oil outlet of the third oil tank 6 is connected with the first oil inlet of the second oil tank 2, the first air vent of the first oil tank 1 is connected with the third air vent of the third oil tank 6, and the fourth air vent of the third oil tank 6 is connected with the second air vent of the second oil tank 2. All connect through resistant oily hose between each oil inlet and the oil-out, all connect through the breather hose between each blow vent, realize the flexonics between the adjacent oil tank.

The modularized aircraft fuel tank assembly 100 of the application only needs to set the third fuel tank 6 between the first fuel tank 1 and the second fuel tank 2 when fuel with extended range is needed, and the third fuel tank is communicated with the second fuel tank 2. This application modular increases journey oil tank can install fast on the basis of first oil tank 1 and second oil tank 2, and is with low costs, need not reequip convenient operation to first oil tank 1 and second oil tank 2.

According to an optional technical scheme of this application, both sides of third oil tank 6 are the cambered surface. The third tank 6 has the same cross-sectional shape as the first and second tanks 1 and 2, and facilitates the installation of the aircraft tank assembly 100.

According to an alternative aspect of the present application, the modular aircraft tank assembly 100 further includes a second lightning protection sheet 52 and a third lightning protection sheet 53. One end of the second lightning protection sheet 52 is connected with the first oil tank 1, and the other end is connected with the third oil tank 6. One end of the third lightning protection sheet 53 is connected with the third oil tank 6, and the other end is connected with the second oil tank 2. Through setting up the lightning protection piece for the electric potential of a plurality of fuel tanks equals in aircraft tank subassembly 100, improves aircraft tank subassembly 100's security.

According to an alternative aspect of the present application, the modular aircraft tank assembly 100 further comprises a fuel drain valve. Since the second tank 2 is located at the lowest position, a drain valve is provided on the second tank 2, and the drain valve is used for discharging deposits in the aircraft tank assembly 100 and also for discharging fuel in the aircraft tank assembly 100.

According to an alternative aspect of the present application, the modular aircraft tank assembly 100 further comprises a low oil level switch disposed on the second tank 2. The fuel in the aircraft tank assembly 100 is gradually reduced with use, and when the fuel quantity is lower than a preset value, the low fuel level switch sends out an alarm signal for reminding a pilot that the aircraft has a small residual fuel quantity.

Optionally, the fuel tanks are made of light materials such as aluminum alloy or nylon, so as to reduce the weight of the modular aircraft fuel tank assembly 100.

Example 2

The present embodiment provides an aircraft comprising a modular aircraft tank assembly 100 and a wing as described above. The wing rib of the wing is provided with a mounting hole corresponding to the aircraft tank assembly 100, and the aircraft tank assembly 100 is arranged in the wing rib. The aircraft tank assembly 100 is supported by a plurality of ribs.

Alternatively, for a wing in a double spar configuration, the aircraft tank assembly 100 is mounted within the rib intermediate the two spars, the aircraft tank assembly 100 being protected by the remaining high strength double spar. For a wing with a single spar configuration, the aircraft tank assembly 100 is mounted in the rib intermediate the spars and longitudinal walls, and the aircraft tank assembly 100 is protected by the spars and longitudinal walls which have high residual strength.

The modularized aircraft fuel tank assembly 100 of the embodiment has high reliability in fuel storage, avoids fuel leakage caused by slight damage, scratch and other accidental conditions of the front edge of the wing and the skin, reduces the possibility of direct damage and leakage of the fuel tank when the aircraft accidentally falls into the ground, and improves the viability of a driver and passengers.

According to an alternative solution of the present application, the spacer 7 is provided at the position of the aircraft tank assembly 100 corresponding to the rib. Optionally, the spacers 7 are rubber spacers and are adhered to the outer wall of each fuel tank to prevent the fuel tank from being scratched due to direct contact with the wing ribs.

The embodiments of the present application are described in detail above. The principle and the implementation of the present application are explained herein by applying specific examples, and the above description of the embodiments is only used to help understand the technical solutions and the core ideas of the present application. Therefore, the person skilled in the art should, according to the idea of the present application, change or modify the embodiments and applications of the present application based on the scope of protection of the present application. In view of the above, the description should not be taken as limiting the application.