CN112066986B - Navigation cabin for aircraft - Google Patents

Abstract

The present application relates to a navigation cabin for an aircraft, and to the technical field of inertial navigation equipment. The navigation cabin includes an inertial measurement unit and a cabin body, the inertial measurement unit includes a base and a cover body arranged on the base, a body component and a control component are arranged side by side on the base, and the cover body and the control component form a sealed area separated from the body component, and a spatial rectangular coordinate system is established with the length direction, height direction and width direction of the cover body as the x-axis, y-axis and z-axis, respectively, and the projection distance between the center of mass of the body component and the center of mass of the inertial measurement unit on the yoz plane of the coordinate system is 0 to 5 mm, and the cabin body is used to accommodate the inertial measurement unit, and the projection distance between the center axis of the cabin body and the center of mass of the inertial measurement unit on the yoz plane of the coordinate system is 0 to 10 mm. The navigation cabin for an aircraft provided by the present application can effectively improve the vibration resistance of the inertial measurement unit, reduce the influence of temperature on the measurement accuracy of the inertial measurement unit, and reduce the production cycle during small batch production.

Description

A navigation cabin for an aircraft

Technical Field

The present application relates to the technical field of inertial navigation equipment, and in particular to a navigation cabin for an aircraft.

Background Art

The inertial measurement unit is an important part of the inertial navigation system. It can not only control the flight trajectory of an object, but also transmit the acceleration, attitude, pitch angle and other information of the object during flight to other components. Among them, the inertial measurement unit is mainly composed of a fiber optic gyroscope and an accelerometer. The fiber optic gyroscope is mainly used to measure angular velocity information, and the accelerometer is used to measure acceleration information. The inertial measurement unit has great advantages in the navigation system. It is little affected by external conditions such as the environment and has high accuracy. However, it also has some disadvantages and problems.

As sensitive devices, the fiber optic gyroscope and accelerometer of the inertial measurement unit are significantly affected by dynamic loads. Therefore, the vibration adaptability of the inertial measurement unit determines the dynamic characteristics of the inertial measurement unit in the use environment. Generally, the larger the outer diameter of the fiber optic gyroscope, the higher the accuracy. However, as the outer diameter of the fiber optic gyroscope increases, the center of gravity of the whole machine will shift, and then the line-angle coupling problem will appear. The line-angle coupling will seriously affect the measurement accuracy and have a great impact on the vibration resistance of the inertial measurement unit, and will also affect the cabin. Therefore, the effect of vibration excitation is relative. For line-angle coupling, the inertial measurement unit and the cabin will interact with each other, thereby affecting the navigation attitude of the entire missile.

Furthermore, the larger the size of the corresponding fiber optic gyroscope is, the larger the size of the corresponding internal load-bearing frame is required. Since it involves the fine processing of the sensitive installation surface, the larger the size of the load-bearing frame is, the more complicated the processing procedures are. When the production volume is not large, the production cost and production cycle are greatly increased.

Furthermore, as fiber optic gyroscopes and accelerometers are sensitive devices, their accuracy is significantly affected by temperature. Specifically, the temperature of the fiber optic gyroscope itself is too high or too low, which directly affects the output accuracy. The structural thermal deformation caused by the change in temperature field affects the installation orthogonality error of the fiber optic gyroscope and accelerometer. Due to size reasons, the sensitive devices are close to heat sources such as power supplies, motherboards and other components, and are inevitably affected by temperature.

Summary of the invention

The embodiment of the present application provides a navigation cabin for an aircraft, so as to simultaneously solve the problems in the related art that the entire navigation cabin has line-angle coupling, the measurement structure is significantly affected by temperature, and the processing and manufacturing are difficult.

In a first aspect, a navigation cabin for an aircraft is provided, comprising:

An inertial measurement unit, comprising a base and a cover body covered on the base, a main body component and a control component are arranged side by side on the base, and the cover body and the control component form a sealed area separated from the main body component, a spatial rectangular coordinate system is established with the length direction, height direction and width direction of the cover body as the x-axis, y-axis and z-axis respectively, and the projection distance between the center of mass of the main body component and the center of mass of the inertial measurement unit on the yoz plane of the coordinate system is 0 to 5 mm;

A cabin body, comprising a large head end and a small head end, the cabin body is used to accommodate the inertial measurement unit, and the main body component is located in the cabin body near the large head end, and the projection distance between the central axis of the cabin body and the center of mass of the inertial measurement unit on the yoz plane of the coordinate system is 0 to 10 mm.

In some embodiments, the body assembly includes:

The body assembly comprises:

A base, wherein a receiving cavity is provided inside the base, wherein a mounting platform is provided inside the receiving cavity, and four supporting ears are symmetrically provided on the outer walls of both sides of the receiving cavity, and each of the supporting ears is provided with a large shock absorber;

Three accelerometers, wherein the three accelerometers are installed on the mounting platform in a spatially orthogonal manner in pairs;

Three fiber optic gyroscopes are installed on the side wall of the accommodating cavity in a spatially orthogonal manner in pairs.

In some embodiments, the fiber optic gyroscope parallel to the xoy plane of the coordinate system is arranged on the inner wall of the accommodating cavity, the fiber optic gyroscope parallel to the yoz plane of the coordinate system is arranged on the outer wall of the accommodating cavity, the fiber optic gyroscope parallel to the xoz plane of the coordinate system is arranged on the outer side of the bottom of the accommodating cavity, and the distance between the fiber optic gyroscope parallel to the xoy plane of the coordinate system and the corresponding surface of the mounting table along the z-axis is 10 mm.

In some embodiments, the distance between the center of mass of the body component and the center of the rectangle formed by the projections of the four large vibration absorbers on the vibration absorption plane is 0 to 10 mm.

In some embodiments, the distance along the y-axis between the plane where the tops of the four ears are located and the top of the opposite surface of the side surface of the inner side of the base on which the fiber optic gyroscope is provided is 0 to 5 mm, the distance along the y-axis between the bottom of the mounting platform and the symmetry plane of the four ears parallel to the xoz plane of the coordinate system is not greater than 15 mm, and the distance along the z-axis between the center of the bottom of the mounting platform and the centroid of the rectangle formed by the projection of the central axes passing through the four large vibration dampers on the vibration damping plane and the plane parallel to the xoy plane of the coordinate system is not greater than 30 mm.

In some embodiments, two bosses are provided on the base, and the two bosses are respectively connected to the four ears through four large vibration absorbers.

In some embodiments, the control component includes:

A stand module, which is arranged at one side of the main body component and is arranged in a direction away from the fiber optic gyroscope parallel to the yoz plane of the coordinate system, the stand module comprising a stand, sealing gaskets are arranged on the four edges of the stand in contact with the base and the cover, a light source and a data processing board are arranged on a surface of the stand facing away from the main body component, and a heat sink is arranged on the light source;

The side panel module is arranged on the side of the vertical panel away from the main body component. The side panel module includes a side panel. Sealing gaskets are also provided on the four edges of the side panel in contact with the base and the cover body. A sealing area is formed between the side panel and the base, the cover body and the vertical panel to be separated from the main body component. A power block and an I/F module are provided on the side of the side panel close to the vertical panel.

In some embodiments, a layer of heat insulation pad is laid on a surface of the vertical plate close to the main body assembly.

In some embodiments, the control component also includes a plurality of small shock absorbers, which are respectively arranged on the light source component, data processing board, power block and I/F module, and are respectively used to connect the light source component and data processing board to the vertical panel, and to connect the power block and I/F module to the side panel.

In some embodiments, three fiber optic gyroscope mainboards are further disposed on the base, and the three fiber optic gyroscope mainboards are arranged side by side between the vertical plate and the side plate along the direction of the Z axis.

The beneficial effects of the technical solution provided by this application include:

The embodiment of the present application provides a navigation cabin for an aircraft, wherein a cover body and a control assembly form a sealed area separated from a main body assembly, which can better separate the heat generated by the control assembly from the main body assembly provided with sensitive devices, thereby preventing the sensitive devices on the main body assembly from being affected by temperature and affecting the measurement or installation accuracy; in addition, the projection distance between the center of mass of the main body assembly and the center of mass of the inertial measurement combination on the yoz plane of the coordinate system is 0 to 5 mm, and the projection distance between the central axis of the cabin and the center of mass of the inertial measurement combination on the yoz plane of the coordinate system is 0 to 10 mm, which makes the projection distance between the center of mass of the main body assembly, the center of mass of the inertial measurement combination and the central axis of the cabin on the yoz plane of the coordinate system limited to a very small unit, so as to minimize the problem of line-angle coupling that may be caused by vibration caused by too large deviation, and the main body assembly is located in the cabin near the big head end, so that the center of mass of the inertial measurement combination is close to the big head end, which can reduce the amplification effect of vibration excitation at the bottom of the main body assembly, reduce the response magnitude of the main body assembly, and reduce line-angle coupling.

BRIEF DESCRIPTION OF THE DRAWINGS

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

FIG1 is a schematic diagram of the internal structure of an inertial measurement unit for a navigation cabin of an aircraft provided in an embodiment of the present application;

FIG2 is a schematic diagram of an exploded structure of a body assembly of a navigation cabin for an aircraft provided in an embodiment of the present application;

FIG3 is a schematic structural diagram of a body assembly of a navigation cabin for an aircraft provided in an embodiment of the present application;

FIG4 is a schematic structural diagram of a navigation cabin for an aircraft provided in an embodiment of the present application;

FIG5 is a schematic diagram of the structure of an inertial measurement unit for a navigation cabin of an aircraft provided in an embodiment of the present application;

FIG6 is a schematic structural diagram of a cover for a navigation cabin of an aircraft provided in an embodiment of the present application;

FIG7 is a schematic exploded view of the structure of a vertical plate module for a navigation cabin of an aircraft provided in an embodiment of the present application;

FIG8 is a schematic diagram of an exploded structure of a side panel module for a navigation cabin of an aircraft provided in an embodiment of the present application;

FIG9 is a side view of the large end of a navigation cabin for an aircraft provided in an embodiment of the present application;

FIG10 is a schematic cross-sectional view along the x-axis direction of a navigation cabin for an aircraft provided in an embodiment of the present application.

In the figure: 1- inertial measurement unit, 100- base, 101- cover, 102- boss, 11- main body assembly, 110- base, 111- accelerometer, 112- fiber optic gyroscope, 113- mounting table, 114- ear, 115- large vibration absorber, 116- counterweight, 12- control assembly, 120- vertical plate, 121- light source component, 122- data processing board, 123- heat sink, 124- side plate, 125- power supply block, 126- I/F module, 127- small vibration absorber, 128- fiber optic gyroscope mainboard, 2- cabin.

DETAILED DESCRIPTION

In order to make the purpose, technical solution and advantages of the embodiments of the present application clearer, the technical solution in the embodiments of the present application will be clearly and completely described below in conjunction with the drawings in the embodiments of the present application. Obviously, the described embodiments are part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of this application.

The embodiment of the present application provides a navigation cabin for an aircraft, which can solve the problems in the related art that the entire navigation cabin has line-angle coupling, the measurement structure is significantly affected by temperature, and the processing and manufacturing are difficult.

Referring to FIGS. 1 and 4 , the navigation cabin includes an inertial measurement unit 1 and a cabin body 2. The inertial measurement unit 1 includes a base 100 and a cover 101 disposed on the base 100. A main body component 11 and a control component 12 are disposed side by side on the base 100. The cover 101 and the control component 12 form a sealed area separated from the main body component 11. A spatial rectangular coordinate system is established with the length direction, height direction and width direction of the cover 101 as the x-axis, y-axis and z-axis, respectively. Referring to FIG. 9 , the navigation cabin includes an inertial measurement unit 1 and a cabin body 2. The projection distance between the center of mass of the body component 11 and the center of mass of the inertial measurement unit 1 on the coordinate system yoz plane is 0 to 5 mm, and the projection distance is defined as a; Referring to FIG9 and FIG10, the cabin 2 includes a large head end and a small head end, the cabin 2 is used to accommodate the inertial measurement unit 1, and the body component 11 is located in the cabin 2 near the large head end, wherein the projection distance between the central axis of the cabin 2 and the center of mass of the inertial measurement unit 1 on the coordinate system yoz plane is 0 to 10 mm, and the projection distance is defined as b. Here, the origin o of the spatial coordinate system is the intersection of the plane where the small head end of the cabin 2 is located and the central axis of the cabin 2.

Specifically, the projection distance between the center of mass of the main body component 11 and the center of mass of the inertial measurement combination 1 on the yoz plane of the coordinate system is limited to 0 to 5 mm, and the projection distance between the central axis of the cabin 2 and the center of mass of the inertial measurement combination 1 on the yoz plane of the coordinate system is limited to 0 to 10 mm. The purpose is to minimize the problem of line-angle coupling during vibration caused by eccentricity, thereby affecting the measurement accuracy. Because the engine of the aircraft is located at the tail end, and the big end of the cabin 2 is close to the tail end of the aircraft, the vibration excitation generated by the engine mainly acts on the big end of the cabin 2, and the vibration excitation of the big end accessories will act on the mounting surface of the inertial measurement unit 1. For the vibration excitation along the x-axis, the vibration excitation of the mounting surface will act on the bottom mounting surface of the body component 11. If the inertial measurement unit 1 is installed in the cabin 2 as a whole and does not meet the above distance limit, the inertial measurement unit 1 as a whole will first produce line-angle coupling, resulting in inconsistent excitation magnitudes at different locations on the body component 11, resulting in different vibration excitations at different locations, causing line-angle coupling of the body component 11, and at this time, the inertial measurement unit 1 as a whole will also act on the cabin 2 as an excitation source, resulting in line-angle coupling of the cabin 2. Therefore, ensuring that the projection of the center of mass of the body component 11, the center of mass of the inertial measurement unit 1 and the central axis of the cabin 2 on the coordinate system yoz plane is within a certain range can minimize the impact of vibration excitation between structures, minimize the occurrence of line-angle coupling as much as possible, and ensure the navigation attitude of the entire aircraft.

In addition, when the inertial measurement unit 1 is installed as a whole in the cabin 2, one end with the main body component 11 is arranged in the cabin 2 close to the large head end. This can avoid further amplification of the vibration excitation acting on the main body component 11 along the y-axis and z-axis directions, which can reduce the response magnitude of the main body component 11 and reduce the line-angle coupling.

Further, referring to FIGS. 2 and 3 , the main body component 11 specifically includes a base 110, three accelerometers 111 and three fiber optic gyroscopes 112, wherein the base 110 is the main supporting skeleton of the main body component 11, and has a structure similar to a rectangular parallelepiped. A accommodating cavity is provided in the base 110, and a mounting platform 113 is provided in the accommodating cavity. Four ears 114 are symmetrically provided on the outer walls on both sides of the accommodating cavity along the length direction thereof, and the two ears 114 on each side of the outer wall are also symmetrical. A large vibration damper 115 is provided on each ear 114, and the four large vibration dampers 115 are respectively installed on the four ears 114, wherein the symmetry plane of the four ears 114 along the y-axis direction is the vibration damping plane, and the centroid of the rectangle formed by the four-point projections of the four large vibration dampers 115 on the vibration damping plane is the vibration damping center. Preferably, the large vibration damper 115 is a T-shaped large vibration damper. The three accelerometers 111 are installed on the mounting platform 113 in pairs and orthogonally in space; the three fiber optic gyroscopes 112 are installed on the side wall of the accommodating cavity in pairs and orthogonally in space.

Furthermore, the fiber optic gyroscope 112 parallel to the coordinate system xoy plane is arranged on the inner wall of the accommodating cavity, the fiber optic gyroscope 112 parallel to the coordinate system yoz plane is arranged on the outer wall of the accommodating cavity, the fiber optic gyroscope 112 parallel to the coordinate system xoz plane is arranged on the outer side of the bottom of the accommodating cavity, and the fiber optic gyroscope 112 parallel to the coordinate system xoy plane is arranged at a distance of 10 mm along the z-axis from the side opposite to the mounting platform 113. The purpose of such arrangement is that one of the fiber optic gyroscopes 112 is arranged on the inner wall of the accommodating cavity, which can ensure that the fiber optic gyroscope 112 does not interfere with the distribution position of the four large vibration dampers 115 along the x-axis, and ensure that the distribution of the four large vibration dampers 115 in the direction along the x-axis is not restricted. If it is not arranged in this distribution manner, when the space occupied along the z-axis direction is the same, the large vibration absorber 115 needs to avoid the corresponding fiber optic gyroscope 112, which will inevitably cause the occupied space along the x-axis direction to increase; if the size along the x-axis direction is not changed, the large vibration absorber 115 needs to bypass the corresponding fiber optic gyroscope 112 with a relatively large cantilever structure, which will inevitably increase the occupied space along the z-axis direction and is not conducive to the stiffness of the vibration reduction mounting surface.

Furthermore, the distance between the center of mass of the main assembly 11 and the centroid of the rectangle formed by the projection of the four large vibration absorbers 115 on the vibration reduction plane is 0 to 10 mm, that is, the distance between the center of mass of the main assembly 11 and the vibration reduction center is 0 to 10 mm. The fiber optic gyroscope 112 parallel to the xoy plane of the coordinate system and the three accelerometers 111 and the mounting platform 113 arranged inside the accommodating cavity are all arranged near the middle of the main assembly 11. The fiber optic gyroscope 112, the three accelerometers 111 and the mounting platform 113 are components with a certain weight. Therefore, the structure of the main assembly 11 is conducive to the coincidence of the projection of the center of mass of the main assembly 11 and the center of the vibration reduction plane formed by the four large vibration absorbers 115 on the xoz plane of the coordinate system. In addition, a counterweight block 116 is also provided on the base 110, which is used to adjust the center of mass of the entire main assembly 11.

The main body component 11 adopts this structure, which not only ensures its own structural rigidity, but also reduces the dimensions along the x-axis and z-axis directions to the greatest extent, ensuring the miniaturization of the overall structure. After reducing the external dimensions of the main components, plates and bars can be used as raw materials. At the same time, the dimensions meet the rough processing requirements of general machine tools, which can avoid the casting process of the components and reduce production costs and production cycles.

Furthermore, the distance along the y-axis between the plane where the tops of the four ears 114 are located and the top of the opposite side of the side of the base 110 on which the fiber optic gyroscope 112 is provided is 0 to 5 mm, the distance along the y-axis between the bottom of the mounting platform 113 and the symmetry plane of the four ears 114 parallel to the xoz plane of the coordinate system is not greater than 15 mm, and the distance along the z-axis between the center of the bottom of the mounting platform 113 and the plane parallel to the xoy plane of the coordinate system and the centroid of the rectangle formed by the projection of the four large vibration dampers 115 on the vibration damping plane is not greater than 30 mm. The limitation of the distances at these three positions can better adjust the position of the center of mass of the body assembly 11, that is, adjust the heavier components to the position close to the center of the vibration damping plane as much as possible, ensure that the overall structure is as small as possible, and also ensure that the projections of the center of mass on the corresponding plane overlap as much as possible. In addition, the lever arm from the three accelerometers 111 to the center of the vibration reduction plane can be reduced. A smaller lever arm is beneficial to the corresponding calculation of the value of the accelerometer 111. Here, the position of the mounting platform 113 along the three directions of the coordinate axis can be adjusted, which is beneficial to the overall vibration reduction performance of the mounting platform 113 and the three accelerometers 111.

Furthermore, two bosses 102 are provided on the base 100 , and the two bosses 102 are respectively connected to four ears 114 . Specifically, the base 110 is fixed to the bosses 102 of the base 100 through four large shock absorbers 115 .

Further, referring to FIG. 5 and FIG. 6 , the cover body 101 is specifically formed by splicing a plurality of plates, and a side corresponding to the small end of the cabin body 2 is an open end. In addition, in order to save installation space, a portion of the top corners of the cover body 101 are chamfered.

Further, referring to Figures 7 and 8, the control component 12 specifically includes a vertical plate module and a side plate module. The vertical plate module is arranged on one side of the main body component 11 and is arranged in a direction away from the fiber optic gyroscope 112 parallel to the plane of the coordinate system yoz. The vertical plate module specifically includes a vertical plate 120. Sealing gaskets are provided on the four edges of the vertical plate 120 that are in contact with the base 100 and the cover body 101. A light source 121 and a data processing board 122 are provided on the side of the vertical plate 120 that is away from the main body component 11. A heat sink 123 is provided on the light source 121, so that the main heat sources such as the light source 121 and the data processing board 122 are completely isolated from the main body component 11. The side panel module is arranged on the side of the vertical plate 120 away from the main body component 11, and the side panel module includes a side panel 124. Sealing pads are also provided on the four edges of the side panel 124 that are in contact with the base 100 and the cover body 101. Therefore, a sealing area separated from the main body component 11 is formed between the side panel 124 and the base 100, the cover body 101 and the vertical plate 120. A power block 125 and an I/F module 126 are provided on the side of the side panel 124 close to the vertical plate 120. Here, the I/F module 126 is a current/frequency conversion module. The sealing area can isolate the heat-generating components from the main body component 11 to minimize the impact of temperature on sensitive devices in the main body component 11.

Furthermore, in order to ensure the heat insulation effect, a layer of heat insulation pad is laid on the surface of the vertical plate 120 close to the main body assembly 11.

Further, the control assembly 12 also includes a plurality of small vibration dampers 127 and a light source mounting bracket, a data processing board mounting bracket, a power block mounting bracket and an I/F module mounting bracket. The plurality of small vibration dampers 127 are respectively arranged on the light source 121, the data processing board 122, the power block 125 and the I/F module 126, and are respectively used to connect the light source 121 and the data processing board 122 to the vertical plate 120, and to connect the power block 125 and the I/F module 126 to the side plate 124 through the corresponding mounting brackets. Here, a thermal conductive silicone pad is provided between the light source 121, the data processing board 122, the power block 125 and the I/F module 126 and the corresponding mounting brackets.

Furthermore, three fiber optic gyroscope mainboards 128 are provided on the base 100. The three fiber optic gyroscope mainboards 128 are arranged side by side between the vertical plate 120 and the side plate 124 along the direction of the Z axis and are located in the formed sealing area. A fiber optic gyroscope mainboard bracket is also provided at the bottom of the three fiber optic gyroscope mainboards 128, and a thermal conductive silicone pad is also provided between the fiber optic gyroscope mainboard bracket and the fiber optic gyroscope mainboard 128.

Furthermore, the vertical plate 120 is processed with fiber routing holes, fiber routing grooves and fiber coiling bosses to facilitate the routing of the optical fiber; a fiber routing groove is also provided on the base 110 of the main body component 11 for routing the optical fiber of the fiber optic gyroscope 112, and a weight reduction hole is also provided on the base 110.

In the description of the present application, it should be noted that the terms "upper", "lower", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present application 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 a limitation on the present application. Unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" 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 it can be an indirect connection through an intermediate medium, or it can be a connection between the two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present application can be understood according to the specific circumstances.

It should be noted that, in this application, relational terms such as "first" and "second" are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the terms "include", "comprise" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device. In the absence of further restrictions, the elements defined by the sentence "comprise a ..." do not exclude the presence of other identical elements in the process, method, article or device including the elements.

The above description is only a specific implementation of the present application, so that those skilled in the art can understand or implement the present application. Various modifications to these embodiments will be apparent to those skilled in the art, and the general principles defined herein can be implemented in other embodiments without departing from the spirit or scope of the present application. Therefore, the present application will not be limited to the embodiments shown herein, but will conform to the widest range consistent with the principles and novel features applied for herein.

Claims (6)

1. A navigational pod for an aircraft, comprising:

The inertial measurement unit (1) comprises a base (100) and a cover body (101) covered on the base (100), wherein a body component (11) and a control component (12) are arranged on the base (100) side by side, the cover body (101) and the control component (12) form a sealing area separated from the body component (11), a space rectangular coordinate system is established by taking the length direction, the height direction and the width direction of the cover body (101) as an x axis, a y axis and a z axis respectively, and the projection distance between the mass center of the body component (11) and the mass center of the inertial measurement unit (1) on the plane of the coordinate system yoz is 0-5 mm;

The cabin body (2) comprises a big head end and a small head end, the cabin body (2) is used for accommodating the inertial measurement unit (1), the body component (11) is located at a position, close to the big head end, in the cabin body (2), and the projection distance between the central axis of the cabin body (2) and the center of mass of the inertial measurement unit (1) on the plane of the coordinate system yoz is 0-10 mm;

the body assembly (11) comprises:

The base (110) is internally provided with a containing cavity, the containing cavity is internally provided with a mounting table (113), four lugs (114) are symmetrically arranged on the outer walls of two sides of the containing cavity, and each lug (114) is provided with a large shock absorber (115);

three accelerometers (111), wherein the three accelerometers (111) are arranged on the mounting table (113) in a pairwise orthogonal mode;

The three optical fiber gyroscopes (112) are arranged on the side wall of the accommodating cavity in a pairwise orthogonal mode;

The optical fiber gyroscope (112) parallel to the coordinate system xoy plane is arranged on the inner side wall of the accommodating cavity, the optical fiber gyroscope (112) parallel to the coordinate system yoz plane is arranged on the outer side wall of the accommodating cavity, the optical fiber gyroscope (112) parallel to the coordinate system xoz plane is arranged on the outer side of the bottom of the accommodating cavity, and the distance between the optical fiber gyroscope (112) parallel to the coordinate system xoy plane and the corresponding surface of the mounting table (113) along the z axis is 10mm;

The distance between the centroid of the body assembly (11) and the centroid of a rectangle formed by the projection of the four large vibration absorbers (115) on the vibration absorption plane is 0-10 mm;

Two bosses (102) are arranged on the base (100), and the two bosses (102) are respectively connected with four supporting lugs (114) through four large shock absorbers (115).

2. A navigational pod for an aircraft according to claim 1, wherein: the distance between the plane where the tops of the four lugs (114) are located and the top of the opposite surface of the side face of the optical fiber gyroscope (112) arranged on the inner side of the base (110) along the y axis is 0-5 mm, the distance between the bottom of the mounting table (113) and the symmetry plane of the four lugs (114) parallel to the plane of the coordinate system xoz along the y axis is not more than 15mm, and the distance between the center of the bottom of the mounting table (113) and the centroid of a rectangle formed by the projection of the center shafts of the four large vibration absorbers (115) on the vibration absorption plane together and the plane parallel to the coordinate system xoy plane along the z axis is not more than 30mm.

3. A navigational pod for an aircraft according to claim 1, wherein the control assembly (12) comprises:

The vertical plate module is arranged on one side of the body assembly (11) and is arranged along the direction parallel to the plane of the coordinate system yoz, away from the fiber optic gyroscope (112), the vertical plate module comprises a vertical plate (120), sealing gaskets are arranged on the peripheral edges of the vertical plate (120) contacted with the base (100) and the cover body (101), a light source piece (121) and a data processing plate (122) are arranged on one surface of the vertical plate (120) away from the body assembly (11), and a heat dissipation plate (123) is arranged on the light source piece (121);

The side plate module is arranged on one side, far away from the body assembly (11), of the vertical plate (120), the side plate module comprises a side plate (124), sealing gaskets are arranged on the peripheral edges, where the side plate (124) is in contact with the base (100) and the cover body (101), of the side plate module, sealing areas, separated from the body assembly (11), are formed between the side plate (124) and the base (100), between the cover body (101) and the vertical plate (120), and a power supply block (125) and an I/F module (126) are arranged on one surface, close to the vertical plate (120), of the side plate module (124).

4. A navigational pod for an aircraft according to claim 3, wherein: a layer of heat insulation pad is paved on one surface of the vertical plate (120) close to the body assembly (11).

5. A navigational pod for an aircraft according to claim 3, wherein: the control assembly (12) further comprises a plurality of small vibration absorbers (127), the plurality of small vibration absorbers (127) are respectively arranged on the light source piece (121), the data processing plate (122), the power supply block (125) and the I/F module (126), and are respectively used for connecting the light source piece (121) and the data processing plate (122) with the vertical plate (120), and connecting the power supply block (125) and the I/F module (126) with the side plate (124).

6. A navigational pod for an aircraft according to claim 3, wherein: and three fiber-optic gyro main boards (128) are further arranged on the base (100), and the three fiber-optic gyro main boards (128) are arranged between the vertical board (120) and the side board (124) side by side along the Z-axis direction.