CN210526856U

CN210526856U - Aircraft with suspension device

Info

Publication number: CN210526856U
Application number: CN201822015442.XU
Authority: CN
Inventors: 陆屹; 金琳乘; 程立波; 张悦
Original assignee: China National Aero Technology Import and Export Corp CATIC; Shenyang Aircraft Design and Research Institute Aviation Industry of China AVIC
Current assignee: China National Aero Technology Import and Export Corp CATIC; Shenyang Aircraft Design and Research Institute Aviation Industry of China AVIC
Priority date: 2018-12-03
Filing date: 2018-12-03
Publication date: 2020-05-15
Anticipated expiration: 2028-12-03

Abstract

The present application provides an aircraft having a suspension device. The airplane with the suspension device comprises wings, the suspension device and a control system, wherein at least one first suspension device is arranged on the wings; the suspension device is provided with a second suspension device; a first suspension device is electromagnetically connected with a corresponding second suspension device; the control system is connected with the first suspension device and used for controlling the connection or disconnection of the electromagnetic connection of the first suspension device and the second suspension device; the suspension device is provided with an accommodating space, and the accommodating space is used for accommodating an external fire control system of the airplane. The suspension device of the application has at least the following beneficial technical effects: the external fire control system is accommodated through the accommodating space, so that the aircraft with the external fire control system can be suitable for the aircraft with the external fire control system, and the problem that the conventional suspension device of the aircraft cannot be used is solved.

Description

Aircraft with suspension device

Technical Field

The application belongs to the technical field of aircrafts, and particularly relates to an aircraft with a suspension device.

Background

The existing suspension device does not have an accommodating space, and cannot be applied to an external fire control system, and the structure of the existing suspension device is not suitable for the external fire control system, so that the strength cannot be guaranteed, and the external fire control system cannot be protected.

The suspension device and the hangers of the existing airplane are mechanically connected and cannot be controlled when the control is needed.

Accordingly, a technical solution is desired to overcome or at least alleviate at least one of the above-mentioned drawbacks of the prior art.

SUMMERY OF THE UTILITY MODEL

The object of the present application is to provide an aircraft with a suspension device to solve at least one of the technical problems described above.

The technical scheme of the application is as follows: an aircraft with a suspension device, the aircraft with a suspension device comprises a wing, a suspension device and a control system, wherein at least one first suspension device is arranged on the wing; the suspension device is provided with a second suspension device; one of said first suspension means being electromagnetically coupled to a corresponding one of said second suspension means; the control system is connected with the first suspension device and is used for controlling the connection or disconnection of the electromagnetic connection of the first suspension device and the second suspension device; and the suspension device is provided with an accommodating space which is used for accommodating an external fire control system of the airplane.

Optionally, an accommodating space is formed in the first suspension device, a telescopic lifting lug is arranged in the accommodating space, and the telescopic lifting lug can extend out of the accommodating space or retract into the accommodating space;

the second suspension device is provided with a connecting part, and the connecting part is suitable for being connected with the telescopic lifting lug.

Optionally, the number of the accommodating spaces is two, one of the accommodating spaces is arranged at one end of the suspension device, and the other accommodating space is arranged at the other end of the suspension device.

Optionally, the two accommodating spaces are communicated with each other through a pipeline.

Optionally, a temperature sensor is arranged in the pipeline, and the temperature sensor is used for measuring the temperature in the pipeline.

Optionally, the suspension device includes a vibration source and a control end, the control end is connected to the vibration source and the temperature sensor, the control end is disposed in a cockpit of the aircraft, and the vibration source is disposed in the pipeline; wherein the content of the first and second substances,

the control end is used for receiving the signal of the temperature sensor so as to control the vibration source to vibrate.

Alternatively, an end of the pipe connected to one of the accommodating spaces extends from the one of the accommodating spaces to the other accommodating space at an angle, which is referred to as a first end.

Optionally, the other end of the pipe connected to the other accommodating space extends obliquely from the accommodating space to the first end of the pipe, and is communicated with the first end.

Optionally, a drain is provided at the junction of the first end of the conduit and the other end of the conduit.

The airplane with the suspension device at least has the following beneficial technical effects: the external fire control system is accommodated through the accommodating space, so that the aircraft with the external fire control system can be suitable for the aircraft with the external fire control system, and the problem that the conventional suspension device of the aircraft cannot be used is solved. The first suspension device and the second suspension device are electromagnetically connected, and when control is needed, the first suspension device and the second suspension device are controlled through the control system, so that the connection can be disconnected.

Drawings

In order to more clearly illustrate the technical solutions provided by the present application, the following briefly introduces the accompanying drawings. It is to be expressly understood that the drawings described below are only illustrative of some embodiments of the invention.

Fig. 1 is a schematic view of a suspension device.

Fig. 2 is a schematic structural diagram of a suspension front section.

Fig. 3 is a schematic structural diagram of a suspended rear section.

Fig. 4 is a schematic structural view of the accommodating space.

Reference numerals:

1-accommodating space, 2-pipeline; 3-a temperature sensor; 4-a vibration source; 5-a first suspension device; 6-a second suspension;

100-suspension front section, 110-front section, 120-front section middle section, 130-front section tail section, 140-inertial navigation equipment, 150-GPS equipment, 160-wireless antenna, 111-front section door, 121-middle section door, 112 a-front left side surface, 112 b-front right side surface, 122-sliding rail, 131-tail interface and 132-sliding groove;

200-hanging middle section, 210 a-first upper interface front, 210 b-first upper interface rear, 220 a-second upper interface front, 220 b-second upper interface rear, 230 a-third upper interface front, 230 b-third upper interface rear, 240 a-lower interface front, 240 b-lower interface rear, 250 a-upper support front arm, 250 b-upper support rear arm, 260-hanging elastic hook;

300-hanging rear section, 310-front section, 320-rear section, 311-fire control computing equipment, 312-power supply equipment, 313-clamping groove, 314-shaft pin, 315-rear section door, 321-quick release lock, 322 a-rear upper side, 322 b-rear lower side and 322 c-rear arc surface.

Detailed Description

In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are a subset of the embodiments in the present application and not all embodiments in the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application and should not be construed as limiting 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. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.

In the description of the present application, it is to be understood that the terms "center", "longitudinal", "lateral", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience in describing the present application and for simplifying the description, and do not indicate or imply that the referenced device or element must have a particular orientation, be constructed in a particular orientation, and be operated, and therefore should not be construed as limiting the scope of the present application.

The suspension device is typically mounted on the aircraft, in particular outside the aircraft, more particularly under the wing or under the cabin of the aircraft.

Fig. 1 is a schematic view of a suspension device. Fig. 2 is a schematic structural diagram of a suspension front section. Fig. 3 is a schematic structural diagram of a suspended rear section. Fig. 4 is a schematic structural view of the accommodating space.

The aircraft with suspension device as shown in fig. 1 and 4 comprises a wing, a suspension device and a control system, wherein at least one first suspension device 5 is arranged on the wing; the suspension device is provided with a second suspension device 6;

a first suspension 5 is electromagnetically connected to a corresponding second suspension 6;

the control system is connected with the first suspension device 5 and is used for controlling the connection or disconnection of the electromagnetic connection of the first suspension device 5 and the second suspension device 6;

the suspension device is provided with an accommodating space 1, and the accommodating space 1 is used for accommodating an external fire control system of the airplane.

In this embodiment, the first suspension device is provided with an accommodating space, and a telescopic lifting lug is arranged in the accommodating space and can extend out of the accommodating space or retract into the accommodating space;

the second suspension device is provided with a connecting part which is suitable for being connected with the telescopic lifting lug.

In this embodiment, by arranging the telescopic lifting lug to be matched with the connecting part, the mechanical connection can be adopted under the condition that the electromagnetic connection is not good.

Referring to fig. 4, in the present embodiment, the accommodating space is two, one of which is provided at one end of the suspension device and the other of which is provided at the other end of the suspension device.

In the present embodiment, the two accommodation spaces communicate with each other through the duct 2.

In the present embodiment, a temperature sensor 3 is provided in the pipe, and the temperature sensor 3 is used to measure the temperature in the pipe. By adopting the structure, the temperature of the pipeline can be monitored constantly, and the pipeline is prevented from icing due to too low temperature.

In this embodiment, the suspension device includes a vibration source 4 and a control end, the control end is respectively connected with the vibration source and the temperature sensor, the control end is arranged in a cockpit of the aircraft, and the vibration source is arranged in the pipeline; the control end is used for receiving signals of the temperature sensor so as to control the vibration source to vibrate. By setting a threshold value, the control end can start the vibration source when receiving the temperature transmitted by the temperature sensor and exceeding the threshold value, so that the vibration source vibrates to make the ice on the pipeline fall off.

In this embodiment, an end of the pipe connected to one accommodation space extends from the one accommodation space to the other accommodation space obliquely, and this end is referred to as a first end.

The other end of the pipeline, which is connected with the other accommodating space, extends obliquely from the accommodating space to the first end of the pipeline and is communicated with the first end.

In this way, the falling ice pieces or crushed ice can be collected to the lowermost end of the inclined extension.

In this embodiment, a drain opening is provided at the junction of the first end of the conduit and the other end of the conduit.

Referring to fig. 1, the suspension device of the present application includes a suspension front section 100, a suspension middle section 200, and a suspension rear section 300, the suspension front section 100, the suspension middle section 200, and the suspension rear section 300 are sequentially connected in the reverse direction of the heading H, wherein the upper side of the suspension middle section 200 is provided with a plurality of types of upper interfaces for adapting to different aircraft platforms, and the lower side of the suspension middle section 200 is provided with a plurality of types of lower interfaces for mounting different types of projectiles.

Wherein, go up the interface and include hangers type structure and insert ear type structure. In the embodiment shown in fig. 1, the upper interfaces are of three types, including a first upper interface of a first length of hitching distance formed by a first upper interface front 210a and a first upper interface front 210b, a second upper interface of a second length of hitching distance formed by a second upper interface front 220a and a second upper interface front 220b, and a third upper interface of a third length of hitching distance formed by a third upper interface front 230a and a third upper interface front 230 b. The second upper interface and the third upper interface are both in a lifting lug type, namely the aircraft platform extends out of the hook for hanging, and the first upper interface is in an insertion lug type, namely the aircraft platform is provided with a protruding piece/structure which is fixedly connected with the first upper interface in an insertion and matching manner.

In addition, in the present application, the middle suspension section 200 has an arm structure consisting of an upper front support arm 250a and an upper rear support arm 250 b.

In this embodiment, the first length hitching distance of the first upper interface is 1150mm, the second length hitching distance of the second upper interface is 720mm, and the third length hitching distance of the third upper interface is 355.6 mm. By setting different suspension distances, the suspension device can be adapted to different aircraft platforms.

The lower interface of the suspension device of the present application of the embodiment shown in fig. 1 includes a first lower interface of one specification consisting of a lower interface front part 240a and a lower interface rear part 240b and a second lower interface consisting of a hook 260, which can be used to mount a weapon, and the first lower interface can mount other items such as a projectile or the like.

It should be noted that, the upper interface and the lower interface in the present application are all of various types, and in the embodiment, three specifications are given for the upper interface, and two specifications are given for the lower interface, so that the various references in the present application are not less than two.

Referring to fig. 1, in the present application, the front suspension section 100 and the rear suspension section 300 have a width or a sectional area larger than that of the middle suspension section 200. The interior of the middle suspension section 100 and the rear suspension section 300 is used for accommodating some electric or electronic devices, so the outer shape of the middle suspension section 100 and the rear suspension section 300 is larger than that of the middle suspension section 200.

For this purpose, the front suspension section 100 and the rear suspension section 300 are hollow for accommodating devices, and the rear suspension section 200 has a duct for accommodating cables or other devices for connecting the devices inside the front suspension section 100 and the rear suspension section 300.

As shown in fig. 2, the suspension front section 100 of the suspension front section structure of the embodiment of the present application includes a front section front portion 110, a front section middle portion 120, and a front section tail portion 130, wherein the front section front portion 110 is fixed to the front section middle portion 120, and the front section tail portion 130 is slidably connected to the front section middle portion 120, for maintaining the inertial navigation device 140 installed inside the front section middle portion 120. The lower side of the front section tail 130 is provided with a sliding groove 132, the lower side of the front section middle part 120 is provided with a sliding rail 122 matched with the sliding groove 132, the sliding rail and the sliding groove are matched for use, and when the inertial navigation equipment 140 needs to be installed or maintained, the front section tail 130 can be pulled out along the reverse direction of the heading H.

In addition, in order to maintain the inertial navigation device 140, a middle section hatch 121 is opened on the side of the front section middle part 120 to communicate with the space for placing the inertial navigation device 140 in the front section middle part 120.

In the present application, since the inertial navigation device 140 needs precise guidance, in order to improve the guidance accuracy of the inertial navigation device 140, a plurality of positioning reference surfaces are provided in the front section middle portion 120, and the inertial navigation device 140 is installed with the positioning reference surfaces for ensuring the working accuracy of the inertial navigation device.

In the embodiment of the present application, the GPS device 150 and the wireless antenna 160 are installed on the upper side of the front end front portion 110, and the front hatch 111 is installed on the side of the front end front portion 110, and although the GPS device 150 and the wireless antenna 160 are installed on the upper side of the front end front portion 110, the related circuits thereof are disposed in the hollow space of the front end front portion 110, so that the GPS device 150 and/or the wireless antenna 160 can be conveniently maintained by the opened front hatch 111.

It should be noted that, in the embodiment of the present application, the front hatch 111 and the middle hatch 121 are preferentially opened on the same side, and on the basis of being able to implement maintenance on the GPS device 150 and the wireless antenna 160 on the upper side of the front end front portion 110 and the inertial navigation device 140 in the front section middle portion 120, the front hatch 111 and the middle hatch 121 may also be opened on different sides.

In the embodiment of the present application, the front section front portion 110 includes a front left side 112a and a front right side 112b along the heading direction H, and the front left side 112a and the front right side 112b are symmetrically arranged in a left-right direction to form a tapered front end, so that the wind resistance can be reduced to the maximum.

The suspended front section 100 is installed in cooperation with the suspended middle section 200 through the rectangular tail interface 131 of the front section tail 130.

In the embodiment of the present application, the rear suspension section 300 includes a front section 310 and a rear section 320, the rear section 310 has a groove 313 at the rear end, the rear section 320 has a protruding quick release lock 321, and the groove 313 and the quick release lock 321 cooperate to fix and quickly release the front section 310 and the rear section 320.

The rear section front part 310 has a front space for accommodating the fire control computing device 311 and a rear space for accommodating the power supply device 312, and the power supply device 312 is fixed to the rear section front part 310 by a pin 314. When the power supply equipment 312 needs to be installed or maintained, the rear section front part 310 is separated from the rear section tail part 320 through the quick separation of the groove 313 and the quick-release lock 321, and then the power supply equipment 312 can be maintained.

In addition, the rear section front 310 is flanked by a rear section door 315 for servicing the fire control computing equipment 311 within the rear section front.

It should be noted that the rear hatch 315 may also be preferentially opened on the same side as the front hatch 111 and the middle hatch 121 to reduce the detectivity by radar, and the three hatches may also be opened on different sides on the premise of being able to implement maintenance of corresponding equipment.

In the embodiment of the present application, the rear-section tail 320 includes a rear-section upper side 322a and a rear-section lower side 322b along the heading H direction, and the rear-section upper side 322a and the rear-section lower side 322b symmetrically form a wake structure, so as to reduce wind resistance.

Further, the rear section tail 320 further includes a rear section arc surface 322c, and the rear section arc surface 322c smoothly and excessively connects the rear section upper side 322a and the rear section lower side 322b, so as to prevent or reduce the turbulence formed at the tail of the suspension device.

The utility model provides a linkage has the suspension user demand that compound general interface can the different aircraft platforms of adaptation, hang point and different grade type weapon on the whole, and have special streamlined structure and realized installing and integrating equipment such as GPS, wireless antenna, be used to lead, fire control computer, battery power, for external machine carries weapon fire control system and provides general structure platform, it hangs to collect, the carrying, throw in the linkage as an organic whole such as function and antenna/power supply/control management equipment installation function, the usability and the expansibility of device are improved by a wide margin.

In the present embodiment, the accommodating space 1 refers to a hollow structure including the interiors of the front suspension section 100 and the rear suspension section 300. The two hollow structures are communicated through the hanging middle section (pipeline), and the inner sides can be wired. In this embodiment, the conduit is not inclined, in other embodiments the conduit is inclined.

The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.

Claims

1. Aircraft with suspension, characterized in that it comprises a wing, on which at least one first suspension (5) is arranged, a suspension and a control system; a second suspension device (6) is arranged on the suspension device;

-one of said first suspension means (5) is electromagnetically connected to a corresponding one of said second suspension means (6);

the control system is connected with the first suspension device (5) and is used for controlling the connection or disconnection of the electromagnetic connection of the first suspension device (5) and the second suspension device (6);

an accommodating space (1) is arranged on the suspension device, and the accommodating space (1) is used for accommodating an external fire control system of the airplane;

an accommodating space is formed in the first suspension device, a telescopic lifting lug is arranged in the accommodating space, and the telescopic lifting lug can extend out of the accommodating space or retract into the accommodating space;

2. An aircraft having a suspension arrangement according to claim 1, wherein the receiving space is two, one being provided at one end of the suspension arrangement and the other being provided at the other end of the suspension arrangement.

3. Aircraft with suspension according to claim 2, characterised in that the two said containment spaces are in communication with each other through a duct (2).

4. An aircraft with a suspension device according to claim 3, characterized in that a temperature sensor (3) is arranged in the conduit, which temperature sensor (3) is adapted to measuring the temperature in the conduit.

5. An aircraft with a suspension device according to claim 4, wherein the suspension device comprises a vibration source (4) and a control end, the control end being connected to the vibration source and a temperature sensor, respectively, the control end being arranged in the cockpit of the aircraft, the vibration source being arranged in the duct; wherein the content of the first and second substances,