Simulated drop ground test device

Abstract

The invention discloses a simulation putting ground test device, which comprises a foundation, a test frame on the foundation, a heating device below the test frame, a putting recovery device, a fixing tool and a measurement and control system, and is characterized in that the heating device comprises a quartz lamp holder, a tray, a reflecting plate, a copper plate and a quartz lamp; the rear end of the quartz lamp holder is hinged to the rear end of the tray through a pin shaft, the front end of the quartz lamp holder is fixedly connected with the front end of the tray through an air cylinder, supporting foot cups are installed at the lower end of the quartz lamp holder, the reflecting plate and the copper plate are installed on the tray, and the quartz lamp is installed on the copper plate. And the putting and recycling device comprises a buffer pad, a rubber ring and an explosion-proof wall. The requirements for cabin opening action following of the simulated bomb launching device and controllable rapid temperature rising of a designated area can be met, the size limitation of axial launching of the simulated bomb with the initial speed is solved, axial launching of the simulated bomb is effectively recycled, and therefore launching assessment of the simulated bomb launching device in the real high-temperature environment is achieved.

Description

Technical Field

[0001] The invention belongs to the field of testing technology, and in particular relates to a simulated ground delivery test device. Background Art

[0002] High temperature test is one of the main test methods for evaluating equipment reliability. It is often used to evaluate the temperature resistance of equipment in the use environment, so as to ensure the adaptability of equipment to high temperature environment. It is an important item of equipment environmental identification test. Missile launchers use aircraft as carriers to perform diversified tasks and can achieve accurate delivery and strikes on long-distance targets. As modern aircraft develop towards high speed and high maneuverability, when the aircraft is in a high Mach number flight, when the missile launcher is preparing to open the cabin to launch the missile, the bottom of the cabin door will generate high temperature due to friction with the air. Under the conditions of drastic temperature difference, it will affect the normal operation of the missile in the cabin and the drive launcher. In order to verify the structural bearing capacity and thermal characteristics of the missile launcher under the action of aerodynamic heat load in a low-pressure environment during the flight of the high Mach aircraft, it is necessary to conduct a ground simulated structural heat delivery test. Therefore, the delivery reliability assessment in a high temperature environment is of great significance to the safety of the aircraft.

[0003] The existing temperature-controlled launch device release test generally installs the launch device in a large test chamber for high-temperature testing, and then conducts the release test during the high-temperature test. However, there are several problems: (1) The high-temperature environment in the test chamber is for heating the entire launch device, and cannot accurately simulate the test requirements of the local heating of the missile launch device when the aircraft is in high Mach flight state; (2) The axial release test with initial velocity has requirements for the size of the test chamber, and the existing large test chamber is limited in size and cannot meet the release assessment requirements of various types and large-sized rigid bombs; (3) The recovery device must have explosion-proof and high-temperature resistance capabilities, otherwise the impact of the rigid bomb with initial velocity will cause irreversible damage to the test chamber; (4) The traditional high-temperature projectile test device is more time-consuming, labor-intensive and wasteful to implement in terms of test time and test cost. Summary of the invention

[0004] In order to solve the deficiencies in the prior art, the present invention provides a simulated ground drop test device.

[0005] The present invention provides the following technical solutions: A simulated ground test device includes a foundation, a test frame on the foundation, a heating device under the test frame, a release recovery device, a fixed tooling and a measurement and control system, wherein: The test frame includes a base, upright columns, inclined columns and a crossbeam, and a fixing tool is provided at the lower end of the crossbeam; The heating device comprises a quartz lamp holder, a tray, a reflector, a copper plate and a quartz lamp. The copper plate is provided with a lamp trough, a cable interface and an air path interface. An air flow channel is provided inside the copper plate. The air path interface is used to provide an air source to the air flow channel. The reflector and the copper plate are installed on the tray. The rear end of the quartz lamp holder is hinged to the rear end of the tray through a pin shaft. The front end of the quartz lamp holder is fixedly connected to the front end of the tray through a cylinder. A supporting foot cup is installed at the lower end of the quartz lamp holder. The delivery and recovery device comprises a buffer pad, a rubber ring and an explosion-proof wall; The fixing tool comprises a bottom plate and a pair of ear plates on the bottom plate, and the fixing tool is used to fix the launching device; The measurement and control system includes a heating monitoring host computer, a temperature measuring instrument, a heating control host computer, a heating controller, a signal conditioning module, a power distribution cabinet and a switching cabinet. The heating monitoring host computer is connected to the temperature measuring instrument for transmitting monitoring instructions and signal feedback display. The heating control host computer is connected to the heating controller for transmitting control instructions and signal feedback display. A temperature sensor is installed on the bottom surface of the transmitting device, and the temperature sensor feeds back signals to the temperature measuring instrument and the signal conditioning module respectively. The signal conditioning module, the heating controller, the power distribution cabinet and the switching cabinet are connected in sequence, and the switching cabinet is then connected to the heating device through the cable on the copper plate. The signal conditioning module sends the processed signal to the heating controller, which is then transmitted to the power distribution cabinet after processing. The thyristor in the power distribution cabinet adjusts the voltage waveform to realize the regulation of the voltage of the heating device to achieve temperature closed-loop control.

[0006] Compared with the prior art, the present invention has the following beneficial effects: 1. The test device can follow the opening action of the simulated missile launcher and meet the controllable and rapid heating requirements of the designated area, solve the size limitation of the axial delivery of the simulated missile with initial velocity, and effectively recover the axial ejection of the simulated missile, thereby realizing the delivery assessment of the simulated missile launcher in a real high-temperature environment.

[0007] 2. The test frame of the test device can replace the number and length of the base, upright columns, inclined columns and beams according to the size requirements of the launch device. The structural shape of the test frame can be modularly designed to improve the flexibility of the test frame structure to meet the load-bearing and size requirements of various types of simulated missile launchers.

[0008] 3. The fixed tooling can be designed and processed according to the installation interface size of the wing simulation parts, and the real simulation The installation boundaries of the launcher on the aircraft are to meet the installation requirements of different types of launchers.

[0009] 4. The heating device can be adjusted following the descending action of the simulated missile launcher. It can not only provide a high-temperature environment that meets the technical requirements and realize controllable and rapid heating of the designated area, but also cut off the power supply immediately after the temperature reaches the specified temperature, thereby ensuring the safety of the test process to the greatest extent and realizing the accuracy assessment of the simulated missile launcher completing the delivery under high temperature conditions.

[0010] 5. The release and recovery device can purchase mature products according to the requirements of different models, and the materials are all reusable and recyclable, which improves the assessment efficiency of the release test of the simulated missile launcher under high temperature conditions and effectively reduces the test cost. At the same time, the buffer recovery area can be adjusted according to different test technical requirements to meet the recovery requirements of different types of missiles. BRIEF DESCRIPTION OF THE DRAWINGS

[0011] Figure 1 is a schematic diagram of the present invention; Figure 2 is a schematic diagram of the test framework; Figure 3 is a schematic diagram of a heating device; Figure 4 It is a schematic diagram of the deployment and recovery device; Figure 5 is a schematic diagram of a reflector in a heating device; Figure 6 It is a schematic diagram of the copper plate in the heating device; Figure 7 It is a cross-sectional view of the copper plate in the heating device; Figure 8 It is a schematic diagram of the combined structure of the tray, reflector, copper plate and quartz lamp; Fig. 9 It is a schematic diagram of the fixed tooling; Fig.10 is a schematic diagram of the gas exhaust distributor; Fig.11 It is a symbol of explosion-proof bricks Figure 1 ; Fig.12 It is a symbol of explosion-proof bricks Figure 2 ; Fig.13 It is a schematic diagram of the gas circuit and cable connection on the heating device; Fig.14 It is a schematic diagram of the use state of the present invention; Fig.15 It is the control principle diagram of the present invention.

[0012] Among them, 1-foundation, 2-test frame, 21-base, 22-vertical column, 23-inclined column, 24-crossbeam, 3-heating device, 31-quartz lamp holder, 32-tray, 33-reflector, 331-first threaded hole, 34-bronze plate, 341-lamp trough, 342-cable interface, 343-gas line interface, 344-air flow channel, 345-second threaded hole, 35-quartz lamp, 36-cylinder, 37-support foot cup, 38-fastening strip, 4-return Receiving device, 41-buffer pad, 42-rubber ring, 43-explosion-proof wall, 431-explosion-proof brick, 5-fixed tooling, 51-bottom plate, 52-ear plate, 6-heating monitoring host computer, 7-temperature measuring instrument, 8-heating control host computer, 9-heating controller, 10-signal conditioning module, 11-power distribution cabinet, 12-transfer cabinet, 13-wing simulation part, 14-simulated missile launching device, 15-simulated missile, 16-air exhaust distributor, 17-compressed air source, 18-air valve. DETAILED DESCRIPTION

[0013] The technical solution of the present invention is further described below in conjunction with the accompanying drawings and embodiments.

[0014] like Figure 1-Figure 15 As shown, a simulated ground test device includes a foundation 1, a test frame 2 on the foundation 1, a heating device 3 under the test frame 2, a release recovery device 4, a fixed tool 5 and a measurement and control system, wherein: The test frame 2 includes a base 21, upright columns 22, inclined columns 23 and a crossbeam 24, and a fixing tool 5 is provided at the lower end of the crossbeam 24; The heating device 3 includes a quartz lamp holder 31, a tray 32, a reflector 33, a copper plate 34 and a quartz lamp 35. The copper plate 34 is provided with a lamp trough 341, a cable interface 342 and an air path interface 343. An air flow channel 344 is provided inside the copper plate 34. The air path interface 343 is used to provide an air source to the air flow channel 344. The reflector 33 and the copper plate 34 are installed on the tray 32. The rear end of the quartz lamp holder 31 is hinged to the rear end of the tray 32 through a pin shaft. The front end of the quartz lamp holder 31 is fixedly connected to the front end of the tray 32 through a cylinder 36. A supporting foot cup 37 is installed at the lower end of the quartz lamp holder 31. The delivery and recovery device 4 includes a buffer pad 41, a rubber ring 42 and an explosion-proof wall 43; The fixing fixture 5 comprises a bottom plate 51 and a pair of ear plates 52 on the bottom plate 51, and the fixing fixture 5 is used to fix the launching device; The measurement and control system includes a heating monitoring host computer 6, a temperature measuring instrument 7, a heating control host computer 8, a heating controller 9, a signal conditioning module 10, a power distribution cabinet 11 and a switching cabinet 12. The heating monitoring host computer 6 is connected to the temperature measuring instrument 7 for transmitting monitoring instructions and signal feedback display. The heating control host computer 8 is connected to the heating controller 9 for transmitting control instructions and signal feedback display. A temperature sensor is installed on the bottom surface of the transmitting device, and the temperature sensor feeds back signals to the temperature measuring instrument 7 and the signal conditioning module 10 respectively. The signal conditioning module 10, the heating controller 9, the power distribution cabinet 11 and the switching cabinet 12 are connected in sequence. The switching cabinet 12 is then connected to the heating device 3 through the cable on the copper plate 34. The signal conditioning module 10 sends the processed signal to the heating controller 9, which is then transmitted to the power distribution cabinet 11 after processing. The thyristor in the power distribution cabinet 11 adjusts the voltage waveform to adjust the voltage of the heating device 3 to achieve temperature closed-loop control.

[0015] The simulated ground test device has two rows of reflective plates 33 and bronze plates 34 symmetrically installed on both sides of the tray 32 , and the reflective plates 33 are on the outside of the bronze plates 34 .

[0016] In the simulated ground drop test device, a first threaded hole 331 is provided on the reflector 33 , and the reflector 33 is threadedly connected to the tray 32 .

[0017] The quartz lamp 35 of the simulated ground test device is installed in the lamp groove 341 , and a second threaded hole 345 is provided at the bottom of the copper plate 34 . The copper plate 34 is threadedly connected to the tray 32 .

[0018] The launching device comprises a wing simulation part 13 , a simulation missile launching device 14 and a simulation missile 15 .

[0019] The fixed tooling 5 includes a bottom plate 51 and a pair of ear plates 52. The fixed tooling 5 is mounted with a wing simulation component 13. A simulated missile launching device 14 is mounted at the lower end of the wing simulation component 13. A simulated missile 15 can be mounted in the simulated missile launching device 14. A temperature sensor is installed on the lower surface of the simulated missile launching device 14.

[0020] The tray 32 and the reflective plate 33 both have the function of reflecting heat, and a fastening strip 38 is provided under the tray 32 .

[0021] The copper plate 34 is provided with a plurality of lamp slots 341 for installing quartz lamps 35 to form a quartz lamp group.

[0022] The reflective plates 33 and bronze plates 34 are respectively arranged in two columns, each column is composed of a plurality of reflective plates 33 and bronze plates 34, each bronze plate 34 is provided with a cable interface 342, each bronze plate 34 is provided with air path interfaces 343 at both ends, an air flow channel 344 is arranged inside the bronze plate 34, and both ends of the air flow channel 344 are connected to the air path interfaces 343.

[0023] The cable interface 342 and the gas path interface 343 on the copper plate 34 are connected to the cable and the gas pipe respectively, one of which forms a series circuit for power supply control of the heating device 3, and the other forms a gas passage to connect to the compressed gas source to form a cooling system.

[0024] Specifically, the input end of the transfer cabinet 12 and the cable interface 342 on the first end copper plate 34 are connected in sequence through cables, the cable interfaces 342 on the copper plate 34 are connected in series one by one, and then the cable interface 342 on the end copper plate 34 is connected to the output end of the transfer cabinet 12, and finally the transfer cabinet 12 is connected to the distribution cabinet 11.

[0025] The quartz lamp holder 31 is provided with an air exhaust distributor 16, and the multi-pipe air exhaust distributor 16 is functionally divided into an air intake distributor and an air outlet distributor, which respectively play the role of converging inflow and converging outflow. The air intake distributor includes an input interface and multiple output interfaces, and the air outlet distributor includes multiple input interfaces and one output interface. The input interface of the air intake distributor is connected to the interface of the compressed air source 17 through an air pipe in sequence, one of the output interfaces of the air intake distributor is connected to the air path interface 343 on the first end copper plate 34, and then the air path interfaces 343 on the two adjacent copper plates 34 are connected in series in sequence, and finally the air path interface 343 on the end copper plate 34 is connected to one of the input interfaces of the air outlet distributor, and the air pipe is connected to the output interface of the air outlet distributor to let air in. In addition, the cylinder 36 is connected to another interface of the compressed air source 17 through an air pipe, and an air valve 18 is arranged on the pipeline between the cylinder 36 and the compressed air source 17.

[0026] During the test, the plant has multiple compressed gas source interfaces. The above-mentioned gas circuit connection is divided into two paths, one connected to the copper plate 34 to form a gas circuit for cooling, and the other connected to the cylinder 36.

[0027] The test frame 2 is used to provide a stable structural support to withstand the reaction force generated by the ejection of the simulated bullet 15. The test frame 2 is composed of a base 21, a vertical column 22, an inclined column 23 and a crossbeam 24. The above structures are all standard model products manufactured by mechanical processing and have a universal standard interface. The base 21 forms a stable and reliable connection with the foundation 1, and then the vertical column 22, the inclined column 23 and the crossbeam 24 are connected in sequence to form a test frame to ensure the stability and bearing capacity of the entire test system.

[0028] The heating device 3 is used to heat the bottom surface of the simulated missile launcher 14, and the heating device 3 is composed of a quartz lamp holder 31, a tray 32, a reflector 33, a copper plate 34 and a quartz lamp 35. The heating device 3 is fixed to the foundation 1 through the support foot cup 37 at the bottom of the quartz lamp holder 31. The height of the heating device 3 can be adjusted by rotating the thread of the bottom support foot cup 37. A slide rail can also be added to the bottom of the heating device 3 to realize the movable function of the heating device 3, so as to facilitate the simulated missile launcher 14 to drop bombs. In order to avoid interfering with the opening of the hatch of the simulated missile launcher 14, the rear end of the quartz lamp holder 31 is hinged to the tray 32, and the front end is connected through a cylinder 36. The cylinder 36 is connected to the compressed air source 17 through an air pipe, which is used to quickly raise and lower the front end height of the tray 32 after heating is completed, so as to facilitate the opening of the hatch of the simulated missile launcher 14 for dropping, and to follow the opening action of the simulated missile launcher 14.

[0029] The measurement temperature and heating temperature are completed by the measurement and control system, which includes a heating monitoring host computer 6, a temperature measuring instrument 7, a heating control host computer 8, a heating controller 9, a signal conditioning module 10, a power distribution cabinet 11 and a switching cabinet 12. The heating monitoring host computer 6 is connected to the temperature measuring instrument 7 for transmitting monitoring instructions and signal feedback display. The heating control host computer 8 is connected to the heating controller 9 for transmitting control instructions and signal feedback display. A temperature sensor is installed on the bottom surface of the simulated bullet launcher 14, and the temperature sensor feeds back signals to the temperature measuring instrument 7 and the signal conditioning module 10 respectively. The heating control host computer 8 is connected to the heating controller 9 for transmitting control instructions and signal feedback display. The signal conditioning module 10 is connected to the heating controller 9, and the heating controller 9 is connected to the power distribution cabinet 11. The signal conditioning module 10 sends the processed signal to the heating controller 9, and then transmits it to the thyristor in the power distribution cabinet 11 after processing. The power distribution cabinet 11 is connected to the switching cabinet 12, and the switching cabinet 12 is then connected to the heating device 3 through the cable on the copper plate 34. That is to say, the real-time temperature value of the temperature sensor at the temperature control point is fed back to the heating controller 9 through the signal conditioning module 10, and the control signal is output to the power distribution cabinet 11 through the PID closed-loop control algorithm. The thyristor in the power distribution cabinet 11 controls the thyristor trigger angle to adjust the voltage waveform, thereby adjusting the voltage of the heating device 3 and achieving temperature closed-loop control. The heating control system can not only achieve the goal of controlled rapid heating of the specified area, but also immediately cut off the power after the temperature is raised to the specified temperature. The model of the signal conditioning module 10 is S1101D.

[0030] The heating device 3 is 5.6 m long, 0.6 m wide and has a heating area of ​​3.4 m 2The bottom surface of the simulated bullet launching device 14 can be fully covered, the maximum heating power can reach 270kW, the maximum temperature can reach 700°C, and the heating rate of 10°C / s can be achieved. The heating capacity of the heating device 3 can also be improved by adjusting the number of quartz lamps 35.

[0031] The delivery and recovery device 4 is used to simulate the recovery of the axial ejection of the missile 15, and is composed of a high-damping low-rebound cushion 41, a rubber ring 42 and an explosion-proof wall 43, wherein the explosion-proof wall 43 is built with explosion-proof bricks 431, and the explosion-proof bricks 431 are hollow structures filled with sand and gravel, which can quickly absorb energy and buffer when encountering impact.

[0032] According to the test technical requirements, the motion trajectory of the simulated projectile 15 after projection can be approximated as a horizontal projection motion under the action of gravity acceleration. The landing point of the simulated projectile 15 can be calculated by combining the projectile size, the initial velocity of projection, the maximum tilt angle of projection and the projection height of the simulated projectile 15. Considering the deviation distance in extreme cases, the buffer recovery interval can be obtained, and the range of laying high-damping low-rebound buffer pads 41 can be confirmed accordingly. The rebound value of the simulated projectile 15 needs to be verified and confirmed according to the performance parameters of the buffer pads 41 to avoid damage to the simulated projectile 15 or the missile launcher caused by secondary rebound. The bottom surface of this area is laid with buffer pads 41 and rubber rings 42 from bottom to top, and buffer pads 41 and explosion-proof walls 43 are set up on the sides in sequence. Along the projection direction of the simulated projectile 15, high-damping low-rebound buffer pads 41 and explosion-proof walls 43 are set up in sequence at the end of the buffer recovery interval for blocking. The rubber ring 42 is laid above the buffer recovery area in order to increase the sliding friction of the missile, reduce the impact of the missile landing, and fully protect the missile, the test personnel and the test site. In addition, none of the components of the delivery and recovery device are connected to the foundation 1. Among them, the explosion-proof brick 431 has a structure similar to a mortise and tenon structure, which can be embedded and installed with the foundation 1, and is strong enough to withstand the impact of the simulated bullet 15. The buffer pad 41 and the rubber ring 42 are not connected either.

[0033] The simulated projectile 15 used in this experiment is about 4m long, weighs about 200kg, has an axial initial velocity of about 15m / s, and a maximum tilt angle of about 7°. It can be confirmed that the recovery area of ​​the recovery device 4 is about 20m 2 The scope of the buffer recovery area and the laying structure form can also be adjusted according to different test technical conditions to solve the constraints of the axial delivery test with initial velocity on the size of the test box space, so as to meet the effective recovery of axial ejection of various models and large-sized simulated missiles.

[0034] The fixing fixture 5 is used to fix the launch device in the missile launch system. The missile launch system includes a wing simulation part 13, a simulated missile launch device 14, a simulated missile 15 and a launch control simulation test bench, through which the launch action is performed in the test.

[0035] The fixing fixture 5 is composed of a bottom plate 51 and an ear plate 52. The bottom plate 51 is connected to the top cross beam 24 of the test frame 2 by bolts, and the ear plate 52 is connected to four installation points on the wing simulation part 13 by interference fit of the pin. The cross beam 24 at the top of the test frame 2 is connected to the wing simulation part 13 through four fixing fixtures 5. The lower end of the wing simulation part 13 is mounted with a simulated missile launcher 14, which can accurately simulate the installation boundary of the simulated missile launcher 14 on the aircraft.

[0036] The specific steps of the test are as follows: 1. Install the base 21 on the test bearing foundation 1 through large-diameter screws, spacers, and nuts, then install the upright columns 22 and the inclined columns 23 in sequence through bolts, washers, and nuts, and finally fix the crossbeam 24 to the upright columns 22 and the inclined columns 23 through bolts, washers, and nuts to complete the assembly of the test frame 2.

[0037] 2. Place the quartz lamp holder 31 at the projection center position directly below the tic-tac-toe frame formed by the four beams 24 at the top of the test frame 2. The quartz lamp holder 31 is fixed to the foundation 1 through the bottom support foot cup 37. The height of the quartz lamp holder 31 can be adjusted by rotating the thread of the bottom support foot cup 37. The rear end of the quartz lamp holder 31 is hinged to the rear end of the tray 32 through a pin shaft, and the front end of the quartz lamp holder 31 is fixed to the front end of the tray 32 through a cylinder 36. Then, the reflector 33 and the copper plate 34 are installed on the tray 32 in turn, and then the quartz lamps 35 are fixed to the copper plate 34 one by one, and finally, the cables and air pipes are connected to the copper plate 34 in turn. The cables are connected to the power distribution cabinet 11 through the adapter cabinet 12, and the air pipe is connected to the compressed air source 17 through the air valve 18, which are used for power supply and gas cooling of the heating device 3 respectively. In addition, the cylinder 36 is connected to the compressed air source 17 through the air pipe for preliminary testing to confirm the activity of the rear end hinge, fine-tune the position, and monitor the time required for the cylinder 36 to lower the front end height of the tray 32 to the specified position.

[0038] 3. Install four fixing fixtures 5. Specifically, the bottom plate 51 of the fixing fixture 5 is connected to the top crossbeam 24 of the test frame 2 by bolts; the ear plate 52 is connected to the four installation points on the wing simulation component 13 in sequence through the interference fit of the pin shaft. The wing simulation component 13 is installed on the crossbeam 24 at the top of the test frame 2 through the fixing fixture 5. The simulated missile launcher 14 is mounted on the lower end of the wing simulation component 13, and the simulated missile launcher 14 is connected to the launch control simulation test bench with a test cable.

[0039] 4. The landing point of the simulated projectile 15 is calculated according to the test technical requirements, and the buffer recovery interval is obtained in combination with the deviation distance. The delivery and recovery device 4 is laid in this area. The bottom surface of this area is laid with buffer pads 41 and rubber rings 42 from bottom to top, and buffer pads 41 and explosion-proof walls 43 are set up on the sides in sequence. Along the ejection direction of the simulated projectile 15, high-damping low-rebound buffer pads 41 and explosion-proof walls 43 are set up in sequence at the end of the buffer recovery interval for blocking.

[0040] 5. Temperature monitoring points and temperature control points are arranged at the bottom of the simulated missile launcher 14. The temperature sensor of the temperature monitoring point is connected to the temperature measuring instrument 7, and the temperature measuring instrument 7 is connected to the heating monitoring host computer 6 for temperature monitoring; the temperature control point is connected to the heating controller 9 through the signal conditioning module 10, and the control signal is input by the heating control host computer 8 to control the power supply output of the distribution cabinet 11. The distribution cabinet 11 is connected to the transfer cabinet 12, and the transfer cabinet 12 is connected to the copper plate 34 through a cable for heating control.

[0041] 6. Push the simulated missile 15 axially into the simulated missile launching device 14 through the overhead crane, and connect it with the mounting device in the simulated missile launching device 14 through the mounting interface of the simulated missile 15.

[0042] 7. The high-temperature stress of the test piece is achieved through the heating control system. After the temperature is raised to the specified temperature, the simulated projectile 15 is dropped onto the drop and recovery device 4 through the launch control simulation test bench to complete the axial drop test under high temperature conditions.

[0043] In this way, the requirements for following the opening action of the simulated missile launcher and the controllable rapid heating of the designated area are achieved, the size limitation of the axial delivery of the simulated missile with initial velocity is solved, and the axial ejection of the simulated missile is effectively recovered, thereby realizing the delivery assessment of the simulated missile launcher in a real high-temperature environment.

[0044] The present invention perfectly overcomes the shortcomings of the traditional launch device delivery test. First, according to the size requirements of the simulated missile launcher 14, the number and length of the base 21, the upright column 22, the inclined column 23 and the crossbeam 24 can be replaced, and the structural shape of the test frame can be modularly designed, which greatly improves the flexibility of building the test frame. It has the characteristics of simple structure, efficient construction, reusability and safety assurance, and can effectively improve the test efficiency; second, the heating device 3 can adjust the front end height following the delivery action of the simulated missile launcher 14, which can not only meet the launch posture requirements of the inclined launch when the simulated missile launcher 14 opens the cabin to launch the missile, but also provide a high temperature environment for the designated area, realize the technical requirements of controllable rapid heating, and can immediately cut off the power after heating to the specified temperature, so as to ensure the safety during the test to the greatest extent. In short, the heating device can effectively simulate the working state of the simulated missile launcher 14 in the real environment of high-speed flight, and there will be no environmental changes during the delivery process, resulting in insufficient test piece assessment; third, the delivery and recovery device can effectively reduce the rebound of the simulated missile and the sliding impact after landing, and reduce the damage of the simulated missile. The three items of the device can all be directly purchased as mature products based on the requirements of different models, and the materials are all reusable and recyclable, which can effectively reduce the test cost and shorten the time for building a release and recovery platform; Fourth, the fixed tooling 5 is a double-ear structure designed and processed according to the installation interface size of the wing simulation part 13. The appropriate connection form can be selected according to the tolerance matching type and the installation interface size of the wing simulation part 13 to simulate the installation boundary of the simulated missile launcher 14 on the aircraft to ensure the authenticity and accuracy of the assessment.

[0045] The present invention can be widely used in axial delivery tests of various launch devices and axial delivery tests in a climate environment, as well as the design and construction of a delivery test system.

[0046] This article uses specific examples to illustrate the principles and implementation methods of the present invention. The above examples are only used to help understand the method and core ideas of the present invention. The above is only a preferred implementation of the present invention. It should be pointed out that due to the limitations of textual expression and the objective existence of infinite specific structures, ordinary technicians in this technical field can make several improvements, modifications or changes without departing from the principles of the present invention, and can also combine the above technical features in an appropriate manner; these improvements, modifications, changes or combinations, or the direct application of the inventive concept and technical solution to other occasions without improvement, should be regarded as the protection scope of the present invention.

Claims

1. A simulated ground test device, characterized in that: The device comprises a foundation (1), a test frame (2) on the foundation (1), a heating device (3) below the test frame (2), a launching and recovering device (4), a fixing tool (5) and a measurement and control system, wherein: The test frame (2) comprises a base (21), upright columns (22), inclined columns (23) and a crossbeam (24); a fixing tool (5) is provided at the lower end of the crossbeam (24); The heating device (3) comprises a quartz lamp holder (31), a tray (32), a reflector (33), a copper plate (34) and a quartz lamp (35); the copper plate (34) is provided with a lamp trough (341), a cable interface (342) and an air path interface (343); an air flow channel (344) is provided inside the copper plate (34); the air path interface (343) is used to provide an air source to the air flow channel (344); the reflector (33) and the copper plate (34) are mounted on the tray (32); the rear end of the quartz lamp holder (31) is hinged to the rear end of the tray (32) via a pin shaft; the front end of the quartz lamp holder (31) is fixedly connected to the front end of the tray (32) via a cylinder (36); and a supporting foot cup (37) is mounted at the lower end of the quartz lamp holder (31); The delivery and recovery device (4) comprises a buffer pad (41), a rubber ring (42) and an explosion-proof wall (43); The fixing tool (5) comprises a bottom plate (51) and a pair of ear plates (52) on the bottom plate (51), and the fixing tool (5) is used to fix the launching device; The measurement and control system comprises a heating monitoring host computer (6), a temperature measuring instrument (7), a heating control host computer (8), a heating controller (9), a signal conditioning module (10), a power distribution cabinet (11) and a switching cabinet (12). The heating monitoring host computer (6) is connected to the temperature measuring instrument (7) for transmitting monitoring instructions and signal feedback display. The heating control host computer (8) is connected to the heating controller (9) for transmitting control instructions and signal feedback display. The bottom surface of the transmitting device is provided with a temperature sensor. The temperature sensor is respectively provided to The temperature measuring instrument (7) and the signal conditioning module (10) feedback signals. The signal conditioning module (10), the heating controller (9), the power distribution cabinet (11) and the transfer cabinet (12) are connected in sequence. The transfer cabinet (12) is then connected to the heating device (3) via a cable on the copper plate (34). The signal conditioning module (10) sends the processed signal to the heating controller (9), which is then transmitted to the power distribution cabinet (11) after processing. The thyristor in the power distribution cabinet (11) adjusts the voltage waveform to adjust the voltage of the heating device (3) and achieve temperature closed-loop control.

2. The simulated ground test device according to claim 1, characterized in that: The reflective plates (33) and the copper plates (34) are respectively arranged in two rows and symmetrically mounted on both sides of the tray (32), and the reflective plates (33) are located outside the copper plates (34).

3. The simulated ground test device according to claim 1, characterized in that: The reflective plate (33) is provided with a first threaded hole (331), and the reflective plate (33) is threadably connected to the tray (32).

4. The simulated ground launch test device according to claim 1, characterized in that: The quartz lamp (35) is installed in the lamp trough (341); a second threaded hole (345) is provided at the bottom of the copper plate (34); and the copper plate (34) is threadably connected to the tray (32).

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