A flight test platform for airborne avionics equipment

Abstract

The present invention relates to the field of avionics equipment testing technology, and in particular to an avionics equipment flight test platform for aviation, including a chassis and an avionics equipment body, including: an environmental control module for simulating the pressure and temperature environment during the test of the avionics equipment body, a test frame, a panning module driven by a motor is installed on the test frame, the inner wall of the test frame is rotatably connected to a pitch frame, the panning module drives the pitch frame to periodically reciprocate, and the inner wall of the pitch frame is rotatably connected to a rotatable main shaft. During the test of the present invention, the front and rear left and right shaking, axial vibration and longitudinal vibration of the avionics equipment body in the test flight state can be achieved synchronously and integratedly by a single motor under ground working conditions, and the multi-axis and multi-effect motion occurs during the test of the avionics equipment body, thereby truly simulating the physical working environment of the avionics equipment body during the flight test.

Description

Technical Field

[0001] The present invention relates to the technical field of avionics equipment testing, and in particular to an airborne avionics equipment flight test platform. Background Art

[0002] Before being assembled and used, avionics equipment must undergo a series of systematic safety and reliability tests, especially through aerial mounting, to verify the integrity of various functions and technical indicators of avionics equipment in a real flight environment. Based on the verification results, faults and defects in design and manufacturing are discovered and eliminated, system parameters are adjusted, and verification is repeated until the fault or defect is overcome.

[0003] In the prior art, the patent document with the publication number CN205193189U discloses an aviation airborne avionics equipment flight test platform, including an aircraft with airborne avionics equipment, an avionics equipment to be tested and a recording device, wherein the recording device and the avionics equipment to be tested are respectively connected to the onboard power supply of the aircraft to obtain electric energy, and the above device records the operation data of the avionics equipment to be tested and the onboard avionics equipment of the aircraft in different stages of the aircraft's navigation or different flight states in a real flight environment, so as to judge whether the radio communication and navigation system to be tested has functional or performance defects according to the recorded data, but the above device is not convenient for realizing the front and back left and right shaking, axial vibration and longitudinal vibration of the avionics equipment body in the test flight state through a single motor in a synchronous and integrated manner under ground working conditions, and then it is not convenient to truly simulate the physical working environment of the avionics equipment body during the flight test under ground working conditions and truly simulate and measure the working performance and durability of the avionics equipment body. Based on this, the present invention proposes an aviation airborne avionics equipment flight test platform. Summary of the invention

[0004] The purpose of the present invention is to solve the shortcomings existing in the background technology and to propose an aviation airborne avionics equipment flight test platform.

[0005] In order to achieve the above objectives, the technical solution adopted by the present invention is: an aviation airborne avionics equipment flight test platform, including a chassis and an avionics equipment body, and also including:

[0006] Environmental control module, used for pressure and temperature environment simulation during avionics equipment testing;

[0007] A test frame, on which a panning module driven by a motor is installed, the inner wall of the test frame is rotatably connected to a pitch frame, the panning module drives the pitch frame to periodically reciprocate, and the inner wall of the pitch frame is rotatably connected to a rotatable main shaft;

[0008] A shaft vibration component and a shaft vibration table, wherein the shaft vibration table is driven by the shaft vibration component and moves back and forth along the axis direction of the main shaft, and a longitudinal vibration component and a fixed vibration shaft that are linked with the main shaft are installed on the shaft vibration table;

[0009] A longitudinal vibration platform, the longitudinal vibration platform is driven by a longitudinal vibration component and moves back and forth along the axis direction of the fixed vibration shaft, the inner wall of the longitudinal vibration platform is rotatably connected to a pylon that can reciprocate periodically, and the avionics equipment body is fixedly connected to the pylon;

[0010] A set of bidirectional elastic limiters is used to elastically limit the position of the longitudinal vibration table.

[0011] Preferably, the environmental control module includes a distance adjusting member and a pressure control box and a temperature control box slidably connected to the base frame, the pressure control box is equipped with a pressure regulating pump and a pressure gauge, the temperature control box is equipped with an air conditioner body and a temperature probe, the pressure control box and the temperature control box are both equipped with a single-chip microcomputer, and the distance adjusting member is used to adjust the distance between the temperature control box and the pressure control box.

[0012] Preferably, the distance adjusting member includes a distance adjusting screw which is rotatably connected to the base frame and driven by an adjusting motor, and the distance adjusting screw is symmetrically provided with a positive thread section and a negative thread section, the positive thread section is transmission connected to the pressure control box, and the negative thread section is transmission connected to the temperature control box.

[0013] Preferably, the rocking transmission module includes a transmission shaft installed on the output shaft end of the motor, rocking sleeves are installed on both side surfaces of the pitch frame, and the two rocking sleeves are rotatably connected to the test frame. The first torsion spring is provided at the rotational connection between the two rocking sleeves and the test frame, a passive bevel gear is installed on one rocking sleeve and the inner wall of the rocking sleeve is rotatably connected to the differential shaft, the differential shaft and the main shaft are installed with first bevel gears, the two first bevel gears are meshed with each other, the differential shaft and the transmission shaft are installed with second bevel gears, the two second bevel gears are meshed with each other, a secondary shaft coaxially arranged with the transmission shaft is rotatably installed on the test frame, a third bevel gear is installed on the secondary shaft, the third bevel gear is transmission-connected to the second bevel gear on the differential shaft, the transmission shaft and the secondary shaft are installed with first missing bevel gears, and the two first missing bevel gears are adaptably connected to the passive bevel gears.

[0014] Preferably, the shaft vibration component includes a grooved shaft rotatably connected to the shaft vibration table, the grooved shaft is transmission connected to the main shaft, the upper connecting shaft and the lower connecting shaft are rotationally connected to the pitch frame respectively, the upper connecting shaft is transmission connected to the lower connecting shaft through a chain belt, the main shaft and the upper connecting shaft are both equipped with fourth bevel gears, the two fourth bevel gears are meshed with each other, the lower connecting shaft is equipped with a first half-tooth gear, and the shaft vibration table is equipped with a vertical tooth plate transmission connected to the first half-tooth gear.

[0015] Preferably, the shaft vibration component also includes a reciprocating shaft rotatably connected to the inner wall of the shaft vibration table, a shaking shaft installed on the back of the bracket and driven by the fixed shaking shaft, a second torsion spring is provided at the connection between the fixed shaking shaft and the shaft vibration table, the reciprocating shaft and the groove shaft are both equipped with fifth bevel teeth, the two fifth bevel teeth are meshed with each other, the reciprocating shaft is equipped with a second half-tooth gear, a flat tooth plate transmission-connected to the second half-tooth gear is installed on the longitudinal vibration table, two second missing bevel teeth are installed on the groove shaft, and a rear bevel tooth is installed at the tail of the fixed shaking shaft, and the two second missing bevel teeth are both transmission-connected to the rear bevel tooth.

[0016] Preferably, the two first-missing bevel teeth are respectively arranged on both sides of the passive bevel teeth, and the two second-missing bevel teeth are respectively arranged on both sides of the rear bevel teeth, and the two first-missing bevel teeth and the two second-missing bevel teeth are provided with tooth surfaces and toothless surfaces, the full arc of the tooth surface is 35°, and the tooth surfaces on the two first-missing bevel teeth and the tooth surfaces on the two second-missing bevel teeth are staggered.

[0017] Preferably, the groove shaft is fixedly provided with a first connecting groove with a top opening and slidably connected to the main shaft, and the cross-sections of the first connecting groove and the main shaft are both regular polygons. The fixed rocking shaft is fixedly provided with a second connecting groove with a front opening and slidably connected to the rocking shaft, and the cross-sections of the second connecting groove and the rocking shaft are both regular polygons.

[0018] Preferably, each of the bidirectional elastic limit members includes a slide table slidably connected to the inner wall of the pitch frame, an axial spring is installed between the slide table and the pitch frame, a T-shaped suspension rod is slidably connected to the inner wall of the slide table, the bottom end of the T-shaped suspension rod is fixedly connected to the longitudinal vibration table, and a radial spring is sleeved on the T-shaped suspension rod and at a position corresponding to the top of the slide table.

[0019] Preferably, the axis of the main shaft is perpendicular to the axis of the rocking shaft, and the axis of the rocking sleeve is perpendicular to the axis of the main shaft.

[0020] Compared with the prior art, the present invention has the following beneficial effects:

[0021] 1. During the test of the present invention, the front and rear left and right shaking, axial vibration and longitudinal vibration of the avionics equipment body in the test flight state can be realized by a single motor in a synchronous and integrated manner under ground working conditions. The multi-axis and multi-effect motions of the avionics equipment body during the flight test can be realized, thereby truly simulating the physical working environment of the avionics equipment body during the flight test, and then accurately measuring the working performance and durability of the avionics equipment body.

[0022] 2. In the present invention, when the avionics equipment body is tested, the pressure control box and the temperature control box are bonded together under the action of the distance adjustment member to form a closed chamber for testing the avionics equipment body. The pressure regulating pump and the pressure gauge on the pressure control box are arranged to set the air pressure in the closed chamber, thereby simulating the air pressure value of the avionics equipment body under different flight test environments. The air conditioning body and the temperature probe on the temperature control box are arranged to set the ambient temperature in the closed chamber, thereby simulating the temperature value of the avionics equipment body under different flight test environments. By simulating the air pressure environment and the temperature environment, a real simulation test of the avionics equipment body under different flight test environments is achieved under ground working conditions. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 1 This is a structural schematic diagram of an aviation airborne avionics equipment flight test platform of the present invention;

[0024] Figure 2 It is a structural schematic diagram of another angle of an aviation airborne avionics equipment flight test platform of the present invention;

[0025] Figure 3 It is a structural schematic diagram of a test frame and a lower connecting shaft in a flight test platform for airborne avionics equipment of the present invention;

[0026] Figure 4 The present invention is an aviation airborne avionics equipment flight test platform Figure 3 The structural diagram at A in the middle;

[0027] Figure 5 It is a structural schematic diagram of a transmission shaft and a secondary shaft in an aviation airborne avionics equipment flight test platform of the present invention;

[0028] Figure 6 It is a structural schematic diagram of the main shaft and the flat gear plate of the present invention;

[0029] Figure 7 It is a schematic diagram of the structure of the T-shaped suspension rod and the slide table of the present invention;

[0030] Figure 8 It is a schematic diagram of the exploded structure of the main shaft and the slot shaft of the present invention;

[0031] Fig. 9 It is a schematic structural diagram of the differential shaft and the pitch frame of the present invention.

[0032] 1. Chassis; 2. Avionics equipment body; 3. Test stand; 4. Motor; 5. Pitch frame; 6. Main shaft; 7. Shaft vibration table; 8. Fixed rocking shaft; 9. Longitudinal vibration table; 10. Hanging rack; 11. Pitch adjustment piece; 12. Pressure control box; 13. Temperature control box; 14. Rocking sleeve; 15. First torsion spring; 16. Differential shaft; 17. Transmission shaft; 18. Secondary shaft; 19. First missing bevel tooth; 20. Slotted shaft; 21. Upper connecting shaft; 22. Lower connecting shaft; 23. First half-tooth gear; 24. Vertical tooth plate; 25. Reciprocating shaft; 26. Rocking shaft; 27. Second torsion spring; 28. Second half-tooth gear; 29. ​​Flat tooth plate; 30. Second missing bevel tooth; 31. Rear bevel tooth; 32. Shaft spring; 33. T-shaped suspension rod; 34. Diameter spring; 35. Barometer; 36. Temperature probe; 37. Slide; 38. Single chip microcomputer; 39. Pressure regulating pump; 40. Air conditioner body; 41. Passive bevel tooth. DETAILED DESCRIPTION

[0033] The following description is used to disclose the present invention so that those skilled in the art can implement the present invention. The preferred embodiments described below are only examples, and those skilled in the art may think of other obvious variations.

[0034] like Figure 1-Figure 9 The flight test platform of an airborne avionics device shown in the figure comprises a chassis 1 and an avionics device body 2, and further comprises:

[0035] Environmental control module, used for simulating the pressure and temperature environment during the testing of the avionics equipment body 2;

[0036] like Figure 1 and Figure 2 As shown, the environmental control module includes a distance adjusting member 11 and a pressure control box 12 and a temperature control box 13 which are slidably connected to the base frame 1. A pressure regulating pump 39 and a barometer 35 are installed on the pressure control box 12, an air conditioner body 40 and a temperature probe 36 are installed on the temperature control box 13, and a single chip computer 38 is installed on both the pressure control box 12 and the temperature control box 13. The distance adjusting member 11 is used to adjust the distance between the temperature control box 13 and the pressure control box 12;

[0037] The temperature probe 36 on the temperature control box 13 is data-connected to the single-chip microcomputer 38 on the temperature control box 13;

[0038] When the avionics device body 2 is tested, the pressure control box 12 and the temperature control box 13 are bonded together under the action of the distance adjusting member 11 to form a closed chamber for testing the avionics device body 2.

[0039] By setting the pressure regulating pump 39 and the barometer 35 on the pressure control box 12, the air pressure in the closed chamber is set, thereby simulating the air pressure value of the avionics equipment body 2 under different test flight environments;

[0040] By setting the air conditioning body 40 and the temperature probe 36 on the temperature control box 13, the ambient temperature in the closed chamber is set, thereby simulating the temperature value of the avionics equipment body 2 under different test flight environments;

[0041] By simulating the air pressure environment and the temperature environment, the real simulation test of the avionics device body 2 under different test flight environments can be realized;

[0042] like Figure 1 and Figure 2 As shown, the distance adjusting member 11 includes a distance adjusting screw rod which is rotatably connected to the base frame 1 and driven by the adjusting motor 4. The distance adjusting screw rod is symmetrically provided with a positive thread segment and a negative thread segment. The positive thread segment is transmission-connected to the pressure control box 12, and the negative thread segment is transmission-connected to the temperature control box 13.

[0043] By setting the distance adjusting member 11, the distance between the temperature control box 13 and the pressure control box 12 can be quickly adjusted. By adjusting the distance between the temperature control box 13 and the pressure control box 12, the installation of the avionics equipment body 2 on the device and the real simulation of the test flight environment can be quickly realized.

[0044] The test frame 3 is fixedly connected to the base frame 1. A panning module driven by a motor 4 is installed on the test frame 3. The inner wall of the test frame 3 is rotatably connected to a pitch frame 5. The panning module drives the pitch frame 5 to periodically reciprocate.

[0045] The inner wall of the pitch frame 5 is rotatably connected to a rotatable main shaft 6;

[0046] like Figure 3 , Figure 5 , Figure 6 , Figure 8 and Fig. 9 As shown, the rocking transmission module includes a transmission shaft 17 installed on the output shaft end of the motor 4, and rocking sleeves 14 are installed on both sides of the pitch frame 5. The axis of the rocking sleeves 14 is perpendicular to the axis of the main shaft 6. The two rocking sleeves 14 are rotatably connected to the test frame 3, and the first torsion springs 15 are provided at the rotational connection between the two rocking sleeves 14 and the test frame 3;

[0047] A passive bevel gear 41 is installed on a rocker sleeve 14, and the inner wall of the rocker sleeve 14 is rotatably connected to a differential shaft 16. The differential shaft 16 and the main shaft 6 are both installed with first bevel gears, and the two first bevel gears are meshed with each other.

[0048] The differential shaft 16 and the transmission shaft 17 are both provided with second bevel gears, and the two second bevel gears mesh with each other;

[0049] A countershaft 18 coaxially arranged with the transmission shaft 17 is rotatably mounted on the test stand 3, a third bevel gear is mounted on the countershaft 18, the third bevel gear is transmission-connected with the second bevel gear on the differential shaft 16, and first missing bevel gears 19 are mounted on both the transmission shaft 17 and the countershaft 18, and the two first missing bevel gears 19 are both adaptably connected with the passive bevel gears 41;

[0050] The two first missing bevel teeth 19 are respectively arranged on both sides of the passive bevel tooth 41;

[0051] When the motor 4 outputs the speed, the first torsion spring 15 and the two first missing bevel teeth 19 are arranged so that the rocking sleeve 14 and the pitch frame 5 can rock back and forth within the set angle range. The pitch frame 5 rock back and forth within the set angle range, thereby simulating the back and forth rocking condition of the avionics equipment body 2 in the test flight environment;

[0052] A shaft vibration component and a shaft vibration table 7, the shaft vibration table 7 is driven by the shaft vibration component and moves back and forth along the axis direction of the main shaft 6;

[0053] The shaft vibration component includes a slotted shaft 20 rotatably connected to the shaft vibration platform 7, and the slotted shaft 20 is transmission-connected to the main shaft 6;

[0054] A first coupling groove with an opening at the top and slidably connected to the main shaft 6 is fixedly provided inside the groove shaft 20, and the cross sections of the first coupling groove and the main shaft 6 are both regular polygons;

[0055] The first coupling groove and the regular polygonal cross section of the main shaft 6 are arranged so that when the shaft vibration table 7 is displaced along the axis direction of the main shaft 6, the main shaft 6 can continuously drive the groove shaft 20;

[0056] like Figure 3 , Figure 5 , Figure 6 , Figure 8 and Fig. 9 As shown, the pitch frame 5 is rotatably connected with an upper connecting shaft 21 and a lower connecting shaft 22, the upper connecting shaft 21 is transmission-connected with the lower connecting shaft 22 through a chain belt, and the main shaft 6 and the upper connecting shaft 21 are both equipped with fourth bevel gears, and the two fourth bevel gears are meshed with each other;

[0057] A first half-toothed gear 23 is mounted on the lower connecting shaft 22, and a vertical toothed plate 24 drivingly connected to the first half-toothed gear 23 is mounted on the shaft vibration platform 7;

[0058] During the flight test, the first half-toothed gear 23, the vertical tooth plate 24 and the bidirectional elastic limiter are arranged so that after the main shaft 6 rotates, the first half-toothed gear 23 can rotate at a set speed. After the first half-toothed gear 23 rotates, the half-face tooth-shaped arrangement of the first half-toothed gear 23 can drive the shaft oscillating table 7 and the grooved shaft 20 to move back and forth along the axial direction of the main shaft 6;

[0059] By moving the shaft vibration table 7 and the slotted shaft 20 back and forth along the axis of the main shaft 6, the axial vibration condition of the avionics equipment body 2 in the flight test environment is simulated;

[0060] The longitudinal vibration component and the fixed vibration shaft 8 which are linked with the main shaft 6 are installed on the shaft vibration table 7;

[0061] A longitudinal vibration table 9, which is driven by a longitudinal vibration component and moves back and forth along the axis direction of the fixed vibration shaft 8;

[0062] The inner wall of the longitudinal vibration table 9 is rotatably connected with a rack 10 that can periodically reciprocate, and the avionics equipment body 2 is fixedly connected to the rack 10;

[0063] like Figure 6 , Figure 8 and Fig. 9 As shown, the shaft vibration component also includes a reciprocating shaft 25 rotatably connected to the inner wall of the shaft vibration platform 7, a shaking shaft 26 installed on the back of the bracket 10 and driven by the fixed shaking shaft 8, the axis of the main shaft 6 is perpendicular to the axis of the shaking shaft 26, and a second torsion spring 27 is provided at the connection between the fixed shaking shaft 8 and the shaft vibration platform 7;

[0064] A second coupling groove with a front end opening and slidably connected to the rocking shaft 26 is fixedly provided inside the fixed rocking shaft 8, and the cross sections of the second coupling groove and the rocking shaft 26 are both regular polygons;

[0065] The reciprocating shaft 25 and the groove shaft 20 are both provided with fifth bevel gears, and the two fifth bevel gears mesh with each other;

[0066] A second half-toothed gear 28 is mounted on the reciprocating shaft 25, and a flat toothed plate 29 drivingly connected to the second half-toothed gear 28 is mounted on the longitudinal vibration table 9;

[0067] During the flight test of the avionics equipment body 2, the second half-toothed gear 28, the flat gear plate 29 and the bidirectional elastic limiter are arranged so that after the motor 4 outputs the speed, the longitudinal vibration table 9 can be reciprocated along the axis direction of the fixed roll shaft 8. The longitudinal vibration condition of the avionics equipment body 2 in the test flight environment is simulated by the reciprocating movement of the longitudinal vibration table 9 along the axis direction of the fixed roll shaft 8.

[0068] Two second missing bevel teeth 30 are installed on the groove shaft 20, and a rear bevel tooth 31 is installed at the tail of the fixed rocker shaft 8, and the two second missing bevel teeth 30 are both in transmission connection with the rear bevel tooth 31;

[0069] The two second missing bevel teeth 30 are respectively arranged on both sides of the rear bevel tooth 31;

[0070] The two first conical teeth 19 and the two second conical teeth 30 are both provided with tooth surfaces and non-tooth surfaces, the full arc of the tooth surfaces is 35°, and the tooth surfaces on the two first conical teeth 19 and the tooth surfaces on the two second conical teeth 30 are both staggered;

[0071] By setting the positions of the two first bevel-missing teeth 19 and staggering the tooth surfaces of the two first bevel-missing teeth 19, the pitch frame 5 can be reciprocated in the front-rear direction.

[0072] By setting the positions of the two second bevel-less teeth 30 and staggering the tooth surfaces of the two second bevel-less teeth 30, the rack 10 can be reciprocated in the left and right directions.

[0073] During the flight test of the avionics equipment body 2, the front and rear left and right shaking and the axial vibration and the longitudinal vibration occur synchronously, thereby truly simulating the physical working environment of the avionics equipment body 2 during the flight test, so as to accurately test the working performance of the avionics equipment body 2. During the test, the avionics equipment body 2 is connected to the external single-chip microcomputer 38 for data, and various data during the test of the avionics equipment body 2 are transmitted to the single-chip microcomputer 38 in real time, and the single-chip microcomputer 38 monitors the working parameters of the avionics equipment body 2 during the test in real time;

[0074] A set of bidirectional elastic limiters is used to elastically limit the position of the longitudinal vibration table 9.

[0075] like Figure 1 , Figure 2 and Figure 7 As shown, each bidirectional elastic limit member includes a slide 37 slidably connected to the inner wall of the pitch frame 5, an axial spring 32 is installed between the slide 37 and the pitch frame 5, a T-shaped suspension rod 33 is slidably connected to the inner wall of the slide 37, the bottom end of the T-shaped suspension rod 33 is fixedly connected to the longitudinal vibration table 9, and a radial spring 34 is sleeved on the T-shaped suspension rod 33 and at a position corresponding to the top of the slide 37.

[0076] The working principle of the present invention is: when the avionics equipment body 2 is tested, under the action of the distance adjusting member 11, the pressure control box 12 and the temperature control box 13 are fitted together to form a closed chamber for testing the avionics equipment body 2. The pressure regulating pump 39 and the barometer 35 on the pressure control box 12 are set to set the air pressure in the closed chamber, thereby simulating the air pressure value of the avionics equipment body 2 under different test flight environments. The air conditioning body 40 and the temperature probe 36 on the temperature control box 13 are set to set the environment in the closed chamber. The ambient temperature is set to simulate the temperature value of the avionics equipment body 2 in different test flight environments. By simulating the air pressure environment and the temperature environment, the real simulation test of the avionics equipment body 2 in different test flight environments is realized. During the test flight test, the first half-tooth gear 23, the vertical tooth plate 24 and the bidirectional elastic limiter are set so that after the main shaft 6 rotates, the first half-tooth gear 23 can rotate at a set speed. After the first half-tooth gear 23 rotates, the half-face tooth shape of the first half-tooth gear 23 can drive the shaft vibration table 7 and the groove shaft 20. It can be reciprocated along the axial direction of the main shaft 6, and the axial vibration table 7 and the slot shaft 20 are reciprocated along the axial direction of the main shaft 6 to simulate the axial vibration working condition of the avionics equipment body 2 under the flight test environment. During the flight test of the avionics equipment body 2, the second half-tooth gear 28, the flat gear plate 29 and the bidirectional elastic limiter are set, so that after the motor 4 outputs the speed, the longitudinal vibration table 9 can be reciprocated along the axial direction of the fixed rock shaft 8, and the longitudinal vibration working condition of the avionics equipment body 2 under the flight test environment is simulated by the reciprocating displacement of the longitudinal vibration table 9 along the axial direction of the fixed rock shaft 8, and the longitudinal vibration working condition of the avionics equipment body 2 under the flight test environment is simulated. During the flight test of the avionics equipment body 2, the front and back left and right shaking and the axial vibration and the longitudinal vibration occur synchronously, so as to truly simulate the physical working environment of the avionics equipment body 2 during the flight test, so as to accurately test the working performance of the avionics equipment body 2. During the test, the avionics equipment body 2 is connected to the external single-chip microcomputer 38 for data, and various data during the test of the avionics equipment body 2 are transmitted to the single-chip microcomputer 38 in real time, and the single-chip microcomputer 38 monitors the working parameters of the avionics equipment body 2 during the test in real time.

[0077] The above shows and describes the basic principles, main features and advantages of the present invention. Those skilled in the art should understand that the present invention is not limited to the above embodiments. The above embodiments and descriptions only describe the principles of the present invention. The present invention may be subject to various changes and improvements without departing from the spirit and scope of the present invention. These changes and improvements fall within the scope of the present invention. The scope of protection claimed by the present invention is defined by the attached claims and their equivalents.

Claims

1. An airborne avionics equipment flight test platform, comprising a chassis (1) and an avionics equipment body (2), characterized in that: Also includes: Environmental control module, used for simulating the pressure and temperature environment during the testing of the avionics equipment body (2); A test frame (3), wherein a panning module driven by a motor (4) is mounted on the test frame (3), an inner wall of the test frame (3) is rotatably connected to a pitch frame (5), and the panning module drives the pitch frame (5) to periodically reciprocate; The inner wall of the pitch frame (5) is rotatably connected to a rotatable main shaft (6); A shaft vibration component and a shaft vibration table (7), wherein the shaft vibration table (7) is driven by the shaft vibration component and moves back and forth along the axis direction of the main shaft (6); The shaft vibration platform (7) is provided with a longitudinal vibration component and a fixed vibration shaft (8) which are linked with the main shaft (6); A longitudinal vibration table (9), the longitudinal vibration table (9) is driven by a longitudinal vibration component and moves back and forth along the axial direction of the fixed vibration shaft (8), the inner wall of the longitudinal vibration table (9) is rotatably connected to a pylon (10) that can periodically reciprocate, and the avionics equipment body (2) is fixedly connected to the pylon (10); The rocking transmission module comprises a transmission shaft (17) mounted on the output shaft end of the motor (4); rocking sleeves (14) are mounted on both sides of the pitch frame (5); the two rocking sleeves (14) are rotatably connected to the test frame (3); the rotational connection between the two rocking sleeves (14) and the test frame (3) is provided with a first torsion spring (15); a passive bevel gear (41) is mounted on one of the rocking sleeves (14); and the inner wall of the rocking sleeve (14) is rotatably connected to a differential shaft (16); the differential shaft (16) and the main shaft (6) are both mounted with first bevel gears; and the two rocking sleeves (14) are rotatably connected to the test frame (3). The first bevel teeth are meshed with each other, the differential shaft (16) and the transmission shaft (17) are both provided with second bevel teeth, the two second bevel teeth are meshed with each other, a secondary shaft (18) coaxially arranged with the transmission shaft (17) is rotatably mounted on the test stand (3), the secondary shaft (18) is provided with third bevel teeth, the third bevel teeth are transmission-connected with the second bevel teeth on the differential shaft (16), the transmission shaft (17) and the secondary shaft (18) are both provided with first missing bevel teeth (19), the two first missing bevel teeth (19) are both adaptively connected with the passive bevel teeth (41); The shaft vibration component comprises a slotted shaft (20) rotatably connected to the shaft vibration platform (7), the slotted shaft (20) being transmission-connected to the main shaft (6), the pitch frame (5) being rotationally connected to an upper connecting shaft (21) and a lower connecting shaft (22), the upper connecting shaft (21) being transmission-connected to the lower connecting shaft (22) via a chain belt, the main shaft (6) and the upper connecting shaft (21) being both provided with fourth bevel gears, the two fourth bevel gears being meshed with each other, the lower connecting shaft (22) being provided with a first half-tooth gear (23), the shaft vibration platform (7) being provided with a vertical tooth plate (24) transmission-connected to the first half-tooth gear (23), and when the first half-tooth gear (23) is rotated, the shaft vibration platform (7) and the slotted shaft (20) are driven to move back and forth along the axis direction of the main shaft (6); The shaft vibration component also includes a reciprocating shaft (25) rotatably connected to the inner wall of the shaft vibration platform (7), and a shaking shaft (26) mounted on the back of the bracket (10) and driven by the fixed shaking shaft (8); a second torsion spring (27) is provided at the connection between the fixed shaking shaft (8) and the shaft vibration platform (7); the reciprocating shaft (25) and the slot shaft (20) are both mounted with fifth bevel teeth, and the two fifth bevel teeth are meshed with each other; the reciprocating shaft (25) is mounted with a second half-tooth gear (28); the longitudinal vibration platform (9) is mounted with a flat tooth plate (29) drivingly connected to the second half-tooth gear (28); the slot shaft (20) is mounted with two second missing bevel teeth (30); a rear bevel tooth (31) is mounted at the tail of the fixed shaking shaft (8), and the two second missing bevel teeth (30) are both drivingly connected to the rear bevel tooth (31); A set of bidirectional elastic limiting members is used to elastically limit the position of the longitudinal vibration table (9).

2. The flight test platform for airborne avionics equipment according to claim 1, characterized in that: The environmental control module comprises a distance adjusting member (11) and a pressure control box (12) and a temperature control box (13) which are slidably connected to the base frame (1); a pressure regulating pump (39) and a barometer (35) are installed on the pressure control box (12); an air conditioner body (40) and a temperature probe (36) are installed on the temperature control box (13); a single chip computer (38) is installed on both the pressure control box (12) and the temperature control box (13); and the distance adjusting member (11) is used to adjust the distance between the temperature control box (13) and the pressure control box (12).

3. The flight test platform for airborne avionics equipment according to claim 2, characterized in that: The pitch adjusting member (11) comprises a pitch adjusting screw which is rotatably connected to the base frame (1) and driven by an adjusting motor (4), wherein a positive thread section and a negative thread section are symmetrically arranged on the pitch adjusting screw, wherein the positive thread section is transmission-connected to a pressure control box (12), and the negative thread section is transmission-connected to a temperature control box (13).

4. The flight test platform for airborne avionics equipment according to claim 1, characterized in that: The two first conical teeth (19) are respectively arranged on both sides of the passive conical teeth (41), and the two second conical teeth (30) are respectively arranged on both sides of the rear conical teeth (31). The two first conical teeth (19) and the two second conical teeth (30) are both provided with tooth surfaces and non-tooth surfaces, the full arc of the tooth surfaces is 35°, and the tooth surfaces on the two first conical teeth (19) and the tooth surfaces on the two second conical teeth (30) are both staggered.

5. The flight test platform for airborne avionics equipment according to claim 1, characterized in that: The groove shaft (20) is internally fixed with a first coupling groove having a top opening and being slidably connected to the main shaft (6), and the cross-sections of the first coupling groove and the main shaft (6) are both regular polygons. The fixed rocking shaft (8) is internally fixed with a second coupling groove having a front opening and being slidably connected to the rocking shaft (26), and the cross-sections of the second coupling groove and the rocking shaft (26) are both regular polygons.

6. The flight test platform for airborne avionics equipment according to claim 1, characterized in that: Each of the bidirectional elastic limiting members comprises a slide table (37) slidably connected to the inner wall of the pitch frame (5); an axial spring (32) is installed between the slide table (37) and the pitch frame (5); a T-shaped suspension rod (33) is slidably connected to the inner wall of the slide table (37); the bottom end of the T-shaped suspension rod (33) is fixedly connected to the longitudinal vibration table (9); and a radial spring (34) is sleeved on the T-shaped suspension rod (33) and at a position corresponding to the upper side of the slide table (37).

7. The flight test platform for airborne avionics equipment according to claim 1, characterized in that: The axis of the main shaft (6) is perpendicular to the axis of the rocking shaft (26), and the axis of the rocking sleeve (14) is perpendicular to the axis of the main shaft (6).

Images