CN209897506U

CN209897506U - Tracking, monitoring and navigation equipment for civil aircraft

Info

Publication number: CN209897506U
Application number: CN201920002754.9U
Authority: CN
Inventors: 胡一鸣
Original assignee: Jilin Beidou Navigation Position Service Co Ltd
Current assignee: Jilin Beidou Navigation Position Service Co Ltd
Priority date: 2019-01-02
Filing date: 2019-01-02
Publication date: 2020-01-03
Anticipated expiration: 2029-01-02

Abstract

The utility model discloses a monitoring and navigational aid are tracked to civilian airborne vehicle, including airborne vehicle bottom plate and navigator box, the bottom welding of airborne vehicle bottom plate has the dead lever, the welding of one side of dead lever has first backup pad, the bracing piece has been passed in seting up some through-holes in the first backup pad, the one end of bracing piece welds with the bottom of airborne vehicle bottom plate, the welding of one side of airborne vehicle bottom plate has the support curb plate, the welding has the fixed plate on the support curb plate, the bottom joint of branch and navigator box is passed through at the top of fixed plate. The utility model discloses an internally mounted at the navigator box has the scattered hot fin mount pad, installs radiating fin on the radiating fin mount pad, and radiating fin can accelerate the navigator to produce thermal outflow to improve radiating effect.

Description

Tracking, monitoring and navigation equipment for civil aircraft

Technical Field

The utility model relates to an airborne vehicle field specifically is a civilian airborne vehicle is tracked and is kept watch on and navigational equipment.

Background

With the continuous development of the scientific and technological technology in China, the aviation technology in China also obtains a breakthrough result, the use of the aircraft tracking monitoring and navigation equipment is more important in the production of the aircraft, but the existing aircraft tracking monitoring and navigation equipment has certain defects in use, for example, the navigation equipment has poor heat dissipation effect in use, so that the use of internal electronic elements is influenced, and the existing navigation equipment is in an integrated fixed form, cannot be disassembled and installed, and has insufficient practicability.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to provide a civil aviation ware is tracked and is kept watch on and navigational equipment to it is poor to solve current navigational equipment radiating effect when using, can influence inside electronic component's use like this, and moreover, current navigational equipment is fixed form as an organic whole, can't dismantle the installation, problem that the practicality is not enough.

In order to achieve the above object, the utility model provides a following technical scheme: a civil aircraft tracking monitoring and navigation device comprises an aircraft bottom plate and a navigator box body, wherein a fixed rod is welded at the bottom of the aircraft bottom plate, a first supporting plate is welded at one side of the fixed rod, a supporting rod penetrates through a through hole formed in the first supporting plate, one end of the supporting rod is welded with the bottom of the aircraft bottom plate, a supporting side plate is welded at one side of the aircraft bottom plate, a fixed plate is welded on the supporting side plate, the top of the fixed plate is clamped with the bottom of the navigator box body through a supporting rod, a radiating fin mounting seat is clamped in the navigator box body, a plurality of radiating fins are mounted on the radiating fin mounting seat, radiating holes are formed in the surface of the tail of the navigator box body, and a first accommodating cavity and a second accommodating cavity are mounted in the navigator box body, fixedly connected with spring in the first chamber of accomodating, the connecting rod is installed in the one end extrusion of spring, the one end joint of connecting rod is in one side of navigator, the navigator is connected with the inside power electric connection of airborne vehicle.

Preferably, the other end of the supporting rod is welded with the top of the second supporting plate, one side of the second supporting plate is welded on the outer wall of the monitoring instrument, and the monitoring instrument is provided with the monitoring camera.

Preferably, the dust removal net is clamped in the position, close to the radiating fin mounting seat, in the navigator box body.

Preferably, the first receiving cavity and the second receiving cavity are arranged oppositely, and the first receiving cavity and the second receiving cavity are close to the radiating fins.

Preferably, one end of the connecting rod is arranged in the second accommodating cavity, and a fixing screw is screwed in a screw hole in the second accommodating cavity.

Compared with the prior art, the beneficial effects of the utility model are that: the utility model discloses an install the scattered hot fin mount pad in the inside of navigator box, install radiating fin on the radiating fin mount pad, radiating fin can accelerate the outflow of navigator production heat to improve radiating effect; through being equipped with first chamber and the second of accomodating on the navigator box and accomodating the chamber, install the spring in the first chamber of accomodating, connecting rod compression spring on the navigator, then another connecting rod on the navigator is arranged the second in and is accomodate the chamber, uses fixed screw to fix the connecting rod, and it is more convenient to operate, and the installation is dismantled more simply, increases the practicality.

Drawings

Fig. 1 is a schematic view of the overall structure of the present invention.

Fig. 2 is the internal structure schematic diagram of the navigator box of the present invention.

Fig. 3 is a schematic view of the installation structure of the navigator of the present invention.

In the figure: 1. an aircraft floor; 2. fixing the rod; 3. a first support plate; 4. a support bar; 5. a second support plate; 6. a monitor; 7. a surveillance camera; 8. a fixing plate; 9. supporting the side plates; 10. a navigator box body; 11. a heat-dissipating fin mounting base; 12. a heat dissipating fin; 13. a dust removal net; 14. heat dissipation holes; 15. a first receiving cavity; 16. a navigator; 17. a first support bar; 18. a second receiving cavity; 19. a spring; 20. and fixing the screw rod.

Detailed Description

The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.

In the description of the present invention, it should be noted that the terms "upper", "lower", "inner", "outer", "front end", "rear end", "both ends", "one end", "the other end" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplification of description, but do not indicate or imply that the device or element to which the reference is made must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first" and "second" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.

In the description of the present invention, it is to be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "disposed," "connected," and the like are to be construed broadly, and for example, "connected" may be either fixedly connected or detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present invention can be understood in specific cases to those skilled in the art.

Referring to fig. 1 to 3, in an embodiment of the present invention, a civil aircraft tracking monitoring and navigation device includes an aircraft bottom plate 1 and a navigator case 10, a fixing rod 2 is welded to a bottom of the aircraft bottom plate 1, a first supporting plate 3 is welded to one side of the fixing rod 2, a supporting rod 4 passes through a through hole formed in the first supporting plate 3, one end of the supporting rod 4 is welded to a bottom of the aircraft bottom plate 1, a supporting side plate 9 is welded to one side of the aircraft bottom plate 1, a fixing plate 8 is welded to the supporting side plate 9, a top of the fixing plate 8 is clamped to a bottom of the navigator case 10 through a supporting rod, a heat dissipation fin mounting seat 11 is clamped to an inside of the navigator case 10, a heat dissipation fin 12 is mounted on the heat dissipation fin mounting seat 11, the heat dissipation fin 12 is provided with a plurality of heat dissipation holes 14, a first receiving cavity 15 and a second receiving cavity 18 are mounted inside the navigator case 10, fixedly connected with spring 19 in first storage chamber 15, the one end extrusion of spring 19 installs connecting rod 17, the one end joint of connecting rod 17 is in one side of navigator 16, navigator 16 and the inside power electric connection of airborne vehicle, the other end of bracing piece 4 welds mutually with the top of second backup pad 5, one side welding of second backup pad 5 is on the outer wall of monitor 6, install surveillance camera head 7 on the monitor 6, the inside of navigator box 10 is close to radiating fin mount pad 11 department joint and has dust removal net 13, first storage chamber 15 and second storage chamber 18 between the position relative and establish, and first storage chamber 15 and second storage chamber 18 are close to radiating fin 12, the one end of connecting rod 17 is arranged in second storage chamber 18, and the spiro union has fixing screw 20 in the screw in the second storage chamber 18.

The utility model discloses a theory of operation is: during the use, with the connecting rod 17 extrusion of navigator 16 last one end spring 19 in the first storage chamber 15, spring 19 extrudees the shrink back, connecting rod 17 on the other end on the navigator 16 is arranged in the second storage chamber 18, then use clamping screw 20 to carry out the fixed action, navigator 16 can produce certain heat at the in-process that uses, radiating fin 12 on the radiating fin mount pad 11 can accelerate thermal effluvium, thereby improve radiating efficiency, and, dust removal net 13 can avoid the dust in the air to enter into navigator box 10, it is more convenient to use, and, monitor 6 can track the surveillance effect.

It is obvious to a person skilled in the art that the invention is not restricted to details of the above-described exemplary embodiments, but that it can be implemented in other specific forms without departing from the spirit or essential characteristics of the invention. The present embodiments are therefore to be considered in all respects as illustrative and not restrictive, the scope of the invention being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein. Any reference sign in a claim should not be construed as limiting the claim concerned.

Claims

1. Civil aircraft tracking, monitoring and navigation device comprising an aircraft floor (1) and a navigator case (10), characterized in that: the aircraft bottom plate is characterized in that a fixing rod (2) is welded at the bottom of the aircraft bottom plate (1), a first supporting plate (3) is welded at one side of the fixing rod (2), a supporting rod (4) penetrates through a through hole formed in the first supporting plate (3), one end of the supporting rod (4) is welded with the bottom of the aircraft bottom plate (1), a supporting side plate (9) is welded at one side of the aircraft bottom plate (1), a fixing plate (8) is welded on the supporting side plate (9), the top of the fixing plate (8) is clamped with the bottom of a navigator box body (10) through a supporting rod, a radiating fin mounting seat (11) is clamped inside the navigator box body (10), radiating fins (12) are mounted on the radiating fin mounting seat (11), a plurality of radiating holes (12) are formed, and a radiating hole (14) is formed in the surface of the tail of the navigator box body (10), the inside mounting of navigator box (10) has first accomodate chamber (15) and second and accomodates chamber (18), fixedly connected with spring (19) in first accomodate chamber (15), connecting rod (17) are installed in the one end extrusion of spring (19), the one end joint of connecting rod (17) is in the one side of navigator (16), navigator (16) and the inside power electric connection of aircraft.

2. The civil aircraft tracking, monitoring and navigation device according to claim 1, characterized in that: the other end of bracing piece (4) welds with the top of second backup pad (5) mutually, one side welding of second backup pad (5) is on the outer wall of control appearance (6), install surveillance camera head (7) on control appearance (6).

3. The civil aircraft tracking, monitoring and navigation device according to claim 1, characterized in that: and a dust removal net (13) is clamped in the position, close to the radiating fin mounting seat (11), in the navigator box body (10).

4. The civil aircraft tracking, monitoring and navigation device according to claim 1, characterized in that: the first containing cavity (15) and the second containing cavity (18) are arranged oppositely, and the first containing cavity (15) and the second containing cavity (18) are close to the radiating fins (12).

5. The civil aircraft tracking, monitoring and navigation device according to claim 1, characterized in that: one end of the connecting rod (17) is arranged in the second accommodating cavity (18), and a fixing screw rod (20) is screwed in a screw hole in the second accommodating cavity (18).