CN216746181U

CN216746181U - Aviation flight attitude monitoring subsystem test equipment

Info

Publication number: CN216746181U
Application number: CN202122015495.3U
Authority: CN
Inventors: 文张军
Original assignee: Chengdu Huaxin Feikong Technology Co ltd
Current assignee: Chengdu Huaxin Feikong Technology Co ltd
Priority date: 2021-08-25
Filing date: 2021-08-25
Publication date: 2022-06-14
Anticipated expiration: 2031-08-25

Abstract

The utility model discloses test equipment for an aviation flight attitude monitoring subsystem, which comprises a test box, a test disc and a positioning rod, wherein a control panel is installed on one side of the front surface of the test box, the test disc is installed on one side, away from the control panel, in the test box through a rotating shaft, the positioning rod is installed on one side of the front surface of the test disc through a universal ball joint, an aircraft is installed at the tail end of the positioning rod, a fixed plate is installed on the position, below the positioning rod, of the front surface of the test disc, a displacement sensor B is installed on one side, away from the universal ball joint, of the top end of the fixed plate, a displacement sensor A is installed on one side, away from the displacement sensor B, of the top end of the fixed plate, and a fan is installed at the bottom end in the test box. The utility model can carry out all-around monitoring on the flight attitude of the aircraft, thereby detecting the problems which can occur in the actual flight of the aircraft, and can test and monitor the multi-angle flight attitude of the aircraft, thereby improving the test accuracy.

Description

Aviation flight attitude monitoring subsystem test equipment

Technical Field

The utility model relates to the technical field of aviation flight tests, in particular to test equipment of an aviation flight attitude monitoring subsystem.

Background

Flight attitude refers to the state of the three axes of the aircraft in the air relative to a reference line or a reference plane, or a fixed coordinate system. An aircraft flies in the air unlike a vehicle moving on the ground, which has various flight attitudes. This refers to changes in the aircraft's pitch, roll, left lean, right lean, etc. The flight attitude determines the heading of the aircraft, affecting both the altitude and the direction of flight. When flying at low speed, the pilot can judge the attitude of the airplane by observing the ground according to the position of the horizon.

Through mass retrieval, the typical test equipment of the aviation flight attitude monitoring subsystem in the prior art, such as a simulated aircraft engine flight attitude test platform disclosed by the publication number CN109373142A, is found, and a base is a steel frame welding structure, so that the inherent frequency of the equipment can be reduced on the premise of meeting the strength, and the resonance caused by the vibration of a test piece during the test is avoided; the inner frame rolling mechanism and the outer frame pitching mechanism can simulate various attitudes of the aircraft engine during aircraft flight to the maximum extent; the angle range of pitching and rolling can be ensured by the sliding blocks arranged on the pitching turntable and the rolling turntable.

The conventional test equipment for the aviation flight attitude monitoring subsystem can only test the flight attitude in the horizontal or vertical direction, and the test accuracy is not high.

SUMMERY OF THE UTILITY MODEL

The utility model aims to provide test equipment of an aviation flight attitude monitoring subsystem, which has the advantages of being capable of monitoring the flight attitude of an aircraft in all directions so as to detect the possible problems of the aircraft in actual flight, testing and monitoring the multi-angle flight attitude of the aircraft, improving the test accuracy and solving the problems that the conventional test equipment of the aviation flight attitude monitoring subsystem can only test the flight attitude in the horizontal or vertical direction and is low in test accuracy.

In order to achieve the purpose, the utility model provides the following technical scheme: the utility model provides an aviation flight gesture control branch system test equipment, includes test box, test tray and locating lever, control panel is installed to test box front surface one side, the test tray is installed through the pivot to the inside one side that deviates from control panel of test box, the locating lever is installed through universal ball joint to test tray front surface one side, and the locating lever end installs the aircraft, the test tray front surface is located locating lever below position department and installs the fixed plate, displacement sensor B is installed to one side that the fixed plate top deviates from a universal ball joint, the fixed plate top deviates from displacement sensor B and is that one side is installed displacement sensor A, the fan is installed to the inside bottom of test box.

Preferably, the test box bottom end is installed and is removed the wheel, it is equipped with four altogether to remove the wheel, and four it locates the test box bottom end and is close to four angular positions department to remove the wheel branch.

Preferably, a box door is installed on one side, deviating from the control panel, of the front surface of the test box, and a transparent observation window is installed on the front surface of the box door.

Preferably, a positioning plate C is installed at the position, located above the fixing plate, of the bottom end of the positioning rod, and a displacement sensor C is installed at the position, close to the rear surface of the positioning plate C, of the front surface of the test disc.

Preferably, locating plates A are symmetrically installed on one sides, close to the universal ball joint, of the front surface and the rear surface of the locating rod, two displacement sensors A are arranged, and the two displacement sensors A are symmetrically installed on one side, far away from the displacement sensor B, of the top end of the fixing plate and close to the front surface and the rear surface.

Preferably, locating plate B is installed to the side symmetry that locating lever front surface and rear surface deviate from the universal ball joint, displacement sensor B is equipped with two altogether, and two displacement sensor B symmetry is installed and is close to front surface and rear surface position department in the one side that the fixed plate top deviates from the universal ball joint.

Preferably, the front surface of the test disc is provided with a fixing ring, and the fixing ring is sleeved on the outer surface of the positioning rod.

Preferably, surface mounting has the rotation motor behind the test box, rotate motor output and pivot end connection.

Preferably, the tuber pipe is installed to the fan output, tuber pipe surface mounting has the governing valve, the governing valve is equipped with threely altogether, and is three the governing valve equidistance is installed in the tuber pipe surface, and is three one side that the governing valve deviates from the tuber pipe all installs the fan housing.

Compared with the prior art, the utility model has the following beneficial effects:

1. according to the utility model, the displacement sensor A, the displacement sensor B, the displacement sensor C and the fan are arranged, so that the flying attitude of the aircraft can be monitored in all directions, and the effect of detecting the problems which may occur in the actual flying of the aircraft is achieved.

2. According to the utility model, by arranging the test disc and the rotating motor, the multi-angle flight attitude of the aircraft can be tested and monitored, the effect of improving the test accuracy is achieved, the rotating motor works to drive the test disc to rotate to adjust the flight angle of the aircraft, and then the flight attitude test of the aircraft is carried out.

Drawings

FIG. 1 is a schematic structural view of the present invention;

FIG. 2 is a schematic front view of the present invention;

FIG. 3 is a partial front view of the test tray of the present invention;

FIG. 4 is a schematic side view of the test plate of the present invention;

FIG. 5 is a schematic side view of the present invention.

In the figure: 1. a test box; 2. a transparent viewing window; 3. a control panel; 4. a box door; 5. a moving wheel; 6. a test tray; 7. a fan housing; 8. adjusting a valve; 9. an air duct; 10. a fan; 11. positioning a plate A; 12. positioning a rod; 13. a fixing ring; 14. positioning a plate B; 15. an aircraft; 16. a fixing plate; 17. a displacement sensor B; 18. positioning a plate C; 19. a displacement sensor A; 20. a universal ball joint; 21. a displacement sensor C; 22. a rotating shaft; 23. the motor is rotated.

Detailed Description

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. 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 invention.

Referring to fig. 1 to 5, the present invention provides a technical solution of a test device for an aviation flight attitude monitoring subsystem: a test device of an aviation flight attitude monitoring subsystem comprises a test box 1, a test disc 6 and a positioning rod 12, wherein a control panel 3 is installed on one side of the front surface of the test box 1, the test disc 6 is installed on one side, which is far away from the control panel 3, in the test box 1, a fixing ring 13 is installed on the front surface of the test disc 6, the fixing ring 13 is sleeved on the outer surface of the positioning rod 12, the positioning rod 12 is installed on one side of the front surface of the test disc 6 through a universal ball joint 20, a positioning plate C18 is installed at the bottom end of the positioning rod 12 and positioned above a fixing plate 16, a displacement sensor C21 is installed at the position, which is close to the rear surface of the positioning plate C18, the longitudinal movement of an aircraft 15 can be judged through the change of the displacement value of the displacement sensor C21, positioning plates A11 are symmetrically installed on one sides, which are close to the universal ball joint 20, of the front surface and the rear surface of the positioning rod 12, and two displacement sensors A19 are arranged, and two displacement sensors A19 are symmetrically arranged on the top end of the fixed plate 16, which faces away from the displacement sensor B17, near the front surface and the rear surface.

Positioning plates B14 are symmetrically arranged on one sides of the front surface and the rear surface of the positioning rod 12, which are far away from the universal ball joint 20, two displacement sensors B17 are symmetrically arranged on one side of the top end of the fixing plate 16, which is far away from the universal ball joint 20, which is close to the front surface and the rear surface, an aircraft 15 is arranged at the tail end of the positioning rod 12, a fixing plate 16 is arranged on the front surface of the test disc 6, which is below the positioning rod 12, a displacement sensor B17 is arranged on one side of the top end of the fixing plate 16, which is far away from the universal ball joint 20, a displacement sensor A19 is arranged on one side of the top end of the fixing plate 16, which is far away from the displacement sensor B17, the displacement difference between a19 and a displacement sensor B17 can obtain the flight elevation angle and the depression angle of the aircraft 15, a fan 10 is arranged at the bottom end inside the test box 1, a rotating motor 23 is arranged on the rear surface of the test box 1, the output end of the rotating motor 23 is connected with the tail end of a rotating shaft 22, the rotary motor 23 works to drive the test disc 6 to rotate to adjust the flight angle of the aircraft 15, and then the multi-angle flight attitude test of the aircraft 15 is carried out, so that the test accuracy is improved.

Referring to fig. 2 to 4, the present invention provides a technical solution of a test device for an aviation flight attitude monitoring subsystem: the utility model provides an aviation flight attitude monitoring divides system test equipment, including test box 1, test disk 6 and locating lever 12, control panel 3 is installed to 1 front surface one side of test box, test disk 6 is installed through pivot 22 in the inside one side that deviates from control panel 3 of test box 1, locating lever 12 is installed through universal ball joint 20 in 6 front surface one side of test disk, and the aircraft 15 is installed to 12 end of locating lever, test disk 6 front surface is located locating lever 12 below position department and installs fixed plate 16, displacement sensor B17 is installed to the 16 top one side that deviates from a universal ball joint 20 in fixed plate top, 16 tops of fixed plate deviate from displacement sensor B17 and be that one side installs displacement sensor A19.

Fan 10 is installed to 1 inside bottom of test box, tuber pipe 9 is installed to fan 10 output, tuber pipe 9 surface mounting has governing valve 8, governing valve 8 is equipped with threely altogether, and install in tuber pipe 9 surface three governing valve 8 equidistance, fan housing 7 is all installed to one side that three governing valve 8 deviates from tuber pipe 9, at the in-process of 15 models of aircraft flight attitude tests, fan 10 passes through fan housing 7 to 15 surperficial air supplies of aircraft, the natural wind of the real condition of air-out size simulation that adjusts three fan housing 7 simultaneously through governing valve 8, thereby can test out aircraft 15's flight gesture, improve the degree of accuracy of test.

Referring to fig. 1 and 2, the present invention provides a technical solution of a test equipment for an aviation flight attitude monitoring subsystem: a test device of an aviation flight attitude monitoring subsystem comprises a test box 1, a test disc 6 and a positioning rod 12, wherein the bottom end of the test box 1 is provided with four moving wheels 5, the four moving wheels 5 are respectively arranged at the positions, close to four corners, of the bottom end of the test box 1, the moving wheels 5 are arranged to facilitate the movement of the test device, one side, away from a control panel 3, of the front surface of the test box 1 is provided with a box door 4, the front surface of the box door 4 is provided with a transparent observation window 2, the arrangement of the transparent observation window 2 is convenient for observing the test condition of an aircraft 15, one side, away from the control panel 3, of the front surface of the test box 1 is provided with the control panel 3, one side, away from the control panel 3, of the interior of the test box 1 is provided with the test disc 6 through a rotating shaft 22, one side, on the front surface of the test disc 6, is provided with the positioning rod 12 through a universal ball joint 20, the tail end of the positioning rod 12 is provided with the aircraft 15, the front surface of the test disc 6, the positioning rod 12 is provided with a fixing plate 16 at the position, the displacement sensor B17 is installed to the one side that the fixed plate 16 top deviates from a universal ball joint 20, and the displacement sensor A19 is installed to the one side that the fixed plate 16 top deviates from displacement sensor B17, and fan 10 is installed to the inside bottom of test box 1.

The working principle is as follows: the utility model is installed at a place needing to be used, in the flying process of an aircraft 15, the flying elevation angle and the depression angle of the aircraft 15 can be obtained through the displacement difference between a displacement sensor A19 and a displacement sensor B17, the left and right inclination angles of the aircraft 15 can be judged through the displacement difference between two displacement sensors A19 and two displacement sensors B17, the longitudinal movement of the aircraft 15 can be judged through the displacement change of a displacement sensor C21, a fan 10 supplies air to the surface of the aircraft 15 through a fan cover 7, and meanwhile, the air outlet size of three fan covers 7 is adjusted through an adjusting valve 8 to simulate natural wind in real situations, so that the flying attitude of the aircraft 15 can be tested, and accordingly, the working flow of the utility model is completed.

Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the utility model, the scope of which is defined in the appended claims and their equivalents.

Claims

1. The utility model provides an aviation flight attitude control divides system test equipment, includes test box (1), test tray (6) and locating lever (12), its characterized in that: control panel (3) are installed to test box (1) front surface one side, test box (1) inside one side that deviates from control panel (3) installs test disc (6) through pivot (22), test disc (6) front surface one side is installed locating lever (12) through universal ball joint (20), and locating lever (12) end installs aircraft (15), test disc (6) front surface is located locating lever (12) below position department and installs fixed plate (16), one side-mounting of fixed plate (16) top back-off position universal ball joint (20) has displacement sensor B (17), it is one side-mounting displacement sensor A (19) that fixed plate (16) top deviates from displacement sensor B (17), fan (10) are installed to test box (1) inside bottom.

2. The aerial flight attitude monitoring subsystem test equipment of claim 1, wherein: remove wheel (5) are installed to test box (1) bottom, it is equipped with four altogether to remove wheel (5), and four remove wheel (5) branch and locate test box (1) bottom and be close to four angular position departments.

3. The aerial flight attitude monitoring subsystem test equipment of claim 1, wherein: the testing box is characterized in that a box door (4) is installed on one side, deviating from the control panel (3), of the front surface of the testing box (1), and a transparent observation window (2) is installed on the front surface of the box door (4).

4. The aerial flight attitude monitoring subsystem test equipment of claim 1, wherein: the positioning plate C (18) is installed at the position, located above the fixing plate (16), of the bottom end of the positioning rod (12), and a displacement sensor C (21) is installed at the position, close to the rear surface of the positioning plate C (18), of the front surface of the test disc (6).

5. The aerial flight attitude monitoring subsystem test equipment of claim 1, wherein: locating plate A (11) are installed to one side symmetry that locating lever (12) front surface and rear surface are close to universal ball joint (20), displacement sensor A (19) are equipped with two altogether, and two displacement sensor A (19) symmetry is installed and is close to front surface and rear surface position department in one side that fixed plate (16) top deviates from displacement sensor B (17).

6. The aerial flight attitude monitoring subsystem test equipment of claim 1, wherein: locating plate B (14) are installed to one side symmetry that locating lever (12) front surface and rear surface deviate from universal ball joint (20), displacement sensor B (17) are equipped with two altogether, and two displacement sensor B (17) symmetry is installed and is close to front surface and rear surface position department in one side that fixed plate (16) top deviates from universal ball joint (20).

7. The aerial flight attitude monitoring subsystem test equipment of claim 1, wherein: the front surface of the test disc (6) is provided with a fixing ring (13), and the fixing ring (13) is sleeved on the outer surface of the positioning rod (12).

8. The aerial flight attitude monitoring subsystem test equipment of claim 1, wherein: surface mounting has rotation motor (23) behind test box (1), rotation motor (23) output and pivot (22) end-to-end connection.

9. The aerial flight attitude monitoring subsystem test equipment of claim 1, wherein: tuber pipe (9) are installed to fan (10) output, tuber pipe (9) surface mounting has governing valve (8), governing valve (8) are equipped with threely altogether, and three governing valve (8) equidistance is installed in tuber pipe (9) surface, and is three governing valve (8) deviate from one side of tuber pipe (9) and all install fan housing (7).