A simulated ground test device

Abstract

The present invention discloses a simulated ground launch test device, comprising a foundation, a test frame on the foundation, a heating device below the test frame, a launch recovery device, fixed fixtures, and a measurement and control system. The heating device comprises a quartz lamp holder, a tray, a reflector, a bronze plate, and a quartz lamp. The rear end of the quartz lamp holder is hinged to the rear end of the tray via a pin, and the front end of the quartz lamp holder is fixed to the front end of the tray via a cylinder. A supporting foot cup is installed at the lower end of the quartz lamp holder. The reflector and bronze plate are mounted on the tray, and the quartz lamp is mounted on the bronze plate. The launch recovery device comprises a cushion, a rubber ring, and an explosion-proof wall. The present invention can achieve the requirements of following the opening action of the simulated missile launcher and the controllable rapid heating of the designated area, solve the size limitation of the axial launch of the simulated missile with initial velocity, and effectively recover the axial ejection of the simulated missile, thereby realizing the launch assessment of the simulated missile launcher in a real high-temperature environment.

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 testing is one of the primary test methods for evaluating equipment reliability. It is often used to assess the equipment's temperature resistance in its operating environment, thereby ensuring its adaptability to high-temperature environments. It is a key component of equipment environmental qualification testing. Missile launchers, based on aircraft, are used to carry out diverse missions, enabling precise delivery and strike of missiles at long-range targets. As modern aircraft advance towards high speeds and increased maneuverability, when the aircraft is flying at high Mach numbers and the missile launcher is preparing to launch its missile, friction between the hatch bottom and the air generates high temperatures. These drastic temperature fluctuations can affect the proper functioning of the missile and the launcher within the cabin. To verify the structural load-bearing capacity and thermal properties of missile launchers under the aerodynamic thermal loads of a low-pressure environment during high-Mach flight, ground-based simulated structural thermal delivery tests are required. Therefore, assessing delivery reliability in high-temperature environments is crucial for aircraft safety.

[0003] The existing temperature-controlled launch device release test generally involves installing the launch device in a large test chamber for high-temperature testing, and then performing 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 projectiles; (3) The recovery device must be explosion-proof and high-temperature resistant, otherwise the impact of the rigid projectile with initial velocity will cause irreversible damage to the test chamber; (4) The traditional high-temperature test device is more time-consuming, labor-intensive and wasteful 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:

[0006] A simulated ground test device includes a foundation, a test frame on the foundation, a heating device below the test frame, a release and recovery device, a fixed tooling, and a measurement and control system, wherein:

[0007] 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;

[0008] The heating device includes 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, and the air path interface is used to provide an air source to the air flow channel. The reflector and the copper plate are mounted on the tray. The rear end of the quartz lamp holder is hinged to the rear end of the tray via a pin shaft. The front end of the quartz lamp holder is fixedly connected to the front end of the tray via a cylinder. A supporting foot cup is installed at the lower end of the quartz lamp holder.

[0009] The delivery and recovery device includes a buffer pad, a rubber ring and an explosion-proof wall;

[0010] The fixing fixture includes a base plate and a pair of ear plates on the base plate, and the fixing fixture is used to fix the launching device;

[0011] 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 transfer 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 transfer cabinet are connected in sequence, and the transfer 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, and then transmits it 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 and achieve temperature closed-loop control.

[0012] Compared with the prior art, the present invention has the following beneficial effects:

[0013] 1. The test device can follow the opening action of the simulated missile launcher and meet the requirements of controlled and rapid temperature rise in the designated area. It can also solve the size limitation of the axial delivery of simulated missiles 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.

[0014] 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.

[0015] 3. The fixed tooling can be designed and processed according to the installation interface size of the wing simulation parts, and the real simulation

[0016] The installation boundaries of the launcher on the aircraft are to meet the installation requirements of different types of launchers.

[0017] 4. The heating device can be adjusted as the simulated missile launcher descends and releases. It can not only provide a high-temperature environment that meets technical requirements and achieve controllable and rapid heating of the designated area, but also immediately cut off the power supply after the temperature reaches the specified temperature, thereby ensuring safety during the test to the greatest extent and achieving accuracy assessment of the simulated missile launcher's release under high temperature conditions.

[0018] 5. The launch and recovery device can purchase mature products based on the requirements of different models, and the materials are all reusable and recyclable, which improves the assessment efficiency of the launch test of the simulated missile launch device 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

[0019] Figure 1 is a schematic diagram of the present invention;

[0020] Figure 2 is a schematic diagram of the experimental framework;

[0021] Figure 3 is a schematic diagram of the heating device;

[0022] Figure 4 It is a schematic diagram of the deployment and recovery device;

[0023] Figure 5 is a schematic diagram of a reflective plate in a heating device;

[0024] Figure 6 It is a schematic diagram of the copper plate in the heating device;

[0025] Figure 7 It is a cross-sectional view of the copper plate in the heating device;

[0026] Figure 8 This is a schematic diagram of the combined structure of the tray, reflector, copper plate and quartz lamp;

[0027] Figure 9 It is a schematic diagram of the fixed tooling;

[0028] Figure 10 is a schematic diagram of the air exhaust distributor;

[0029] Figure 11 This is a diagram of explosion-proof bricks Figure 1 ;

[0030] Figure 12 This is a diagram of explosion-proof bricks Figure 2 ;

[0031] Figure 13 It is a schematic diagram of the gas circuit and cable connections on the heating device;

[0032] Figure 14 It is a schematic diagram of the use state of the present invention;

[0033] Figure 15 It is a control principle diagram of the present invention.

[0034] 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 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-base 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-adapter 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

[0035] The technical solution of the present invention is further described below with reference to the accompanying drawings and embodiments.

[0036] like Figures 1-15 As shown, a simulated ground test device includes a foundation 1, a test frame 2 on the foundation 1, a heating device 3 below the test frame 2, a release and recovery device 4, a fixed tool 5 and a measurement and control system, wherein:

[0037] 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;

[0038] The heating device 3 includes a quartz lamp holder 31, a tray 32, a reflector 33, a bronze plate 34, and a quartz lamp 35. The bronze 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 bronze 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 bronze 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, and the front end of the quartz lamp holder 31 is fixed to the front end of the tray 32 via a cylinder 36. A supporting foot cup 37 is installed at the lower end of the quartz lamp holder 31.

[0039] The delivery and recovery device 4 includes a buffer pad 41, a rubber ring 42 and an explosion-proof wall 43;

[0040] The fixing fixture 5 includes 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;

[0041] 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 distribution cabinet 11 and a transfer 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 distribution cabinet 11 and the transfer cabinet 12 are connected in sequence. The transfer 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, and then transmits it to the distribution cabinet 11 after processing. The thyristor in the distribution cabinet 11 adjusts the voltage waveform to realize the regulation of the voltage of the heating device 3 and achieve temperature closed-loop control.

[0042] The simulated ground drop test device has two rows of reflective plates 33 and two rows of bronze plates 34 symmetrically mounted on both sides of the tray 32 , with the reflective plates 33 on the outside of the bronze plates 34 .

[0043] 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 .

[0044] 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.

[0045] The launching device includes a wing simulation part 13 , a simulation missile launching device 14 and a simulation missile 15 .

[0046] The fixed tooling 5 includes a base plate 51 and a pair of ear plates 52. The fixed tooling 5 is mounted with a wing simulation component 13. The lower end of the wing simulation component 13 is mounted with a simulated missile launcher 14. The simulated missile launcher 14 can be mounted with a simulated missile 15. A temperature sensor is installed on the lower surface of the simulated missile launcher 14.

[0047] 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 .

[0048] The copper plate 34 is provided with a plurality of lamp slots 341 for mounting quartz lamps 35 to form a quartz lamp assembly.

[0049] 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 an air path interface 343 at both ends, an air flow channel 344 is provided inside the bronze plate 34, and both ends of the air flow channel 344 are connected to the air path interface 343.

[0050] The cable interface 342 and the gas path interface 343 on the bronze plate 34 are connected to the cable and the gas pipe respectively. One forms a series circuit for power supply control of the heating device 3, and the other forms a gas path for connecting to a compressed gas source to form a cooling system.

[0051] 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 plates 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.

[0052] The quartz lamp holder 31 is provided with an air exhaust distributor 16. The multi-pipe air exhaust distributor 16 is functionally divided into an air inlet distributor and an air outlet distributor, which respectively play the role of converging inflow and merging outflow. The air inlet 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 inlet 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 inlet 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. 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. The output interface of the air outlet distributor is connected to an air pipe to allow air to flow in. In addition, the cylinder 36 is connected to another interface of the compressed air source 17 through an air pipe. An air valve 18 is provided on the pipeline between the cylinder 36 and the compressed air source 17.

[0053] During the test, the plant contained multiple compressed gas source interfaces. The above-mentioned gas connection was divided into two routes, one connected to the copper plate 34 to form a gas circuit for cooling, and the other connected to the cylinder 36.

[0054] The test frame 2 provides stable structural support to withstand the reaction force generated by the ejection of the simulated projectile 15. It consists of a base 21, upright columns 22, inclined columns 23, and crossbeams 24. All of these components are machined and manufactured in standard models with universal standard interfaces. The base 21 forms a stable and reliable connection with the foundation 1. The upright columns 22, inclined columns 23, and crossbeams 24 are then connected in sequence to form the test frame, ensuring the stability and load-bearing capacity of the entire test system.

[0055] The heating device 3 is used to heat the bottom surface of the simulated missile launcher 14. The heating device 3 consists of a quartz lamp holder 31, a tray 32, a reflector 33, a bronze plate 34, and a quartz lamp 35. The heating device 3 is fixed to the foundation 1 via a support foot 37 at the bottom of the quartz lamp holder 31. The height of the heating device 3 can be adjusted by rotating the threaded support foot 37 at the bottom. Slide rails can also be added to the bottom of the heating device 3 to make the heating device 3 movable, facilitating the release of the simulated missile launcher 14. 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 via a cylinder 36. The cylinder 36 is connected to the compressed air source 17 via an air pipe. After heating is completed, the front end of the tray 32 is quickly raised or lowered to facilitate the opening of the hatch of the simulated missile launcher 14 for release, thereby tracking the opening of the hatch of the simulated missile launcher 14.

[0056] Temperature measurement and heating temperature are performed by a 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 transfer cabinet 12. The heating monitoring host computer 6 is connected to the temperature measuring instrument 7 for transmitting monitoring instructions and signal feedback. The heating control host computer 8 is connected to the heating controller 9 for transmitting control instructions and signal feedback. A temperature sensor is mounted on the bottom surface of the simulated missile launcher 14, which provides feedback 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. The signal conditioning module 10 is connected to the heating controller 9, which is in turn connected to the power distribution cabinet 11. The signal conditioning module 10 transmits processed signals to the heating controller 9, which then processes and transmits them to the thyristors in the power distribution cabinet 11. The power distribution cabinet 11 is connected to the transfer cabinet 12, which is then connected to the heating device 3 via the cable on the copper plate 34. In other words, the real-time temperature value of the temperature sensor at the temperature control point is fed back to the heating controller 9 via the signal conditioning module 10. The PID closed-loop control algorithm then outputs a control signal to the power distribution cabinet 11. The thyristors within this cabinet 11 then control the thyristor trigger angle to adjust the voltage waveform, thereby regulating the voltage of the heating device 3 and achieving closed-loop temperature control. This heating control system not only achieves the goal of controlled and rapid heating of a designated area, but also immediately shuts off power after the temperature reaches the specified temperature. The model number of the signal conditioning module 10 is S1101D.

[0057] The heating device 3 is 5.6m long, 0.6m wide and has a heating area of ​​3.4m 2The bottom surface of the simulated missile launcher 14 can be fully covered, the maximum heating power can reach 270kW, the maximum temperature can reach 700°C, and the heating rate can be achieved at 10°C / s. The heating capacity of the heating device 3 can also be improved by adjusting the number of quartz lamps 35.

[0058] 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. The explosion-proof wall 43 is built with explosion-proof bricks 431. The explosion-proof bricks 431 are hollow structures filled with sand and gravel, which can quickly absorb energy and buffer impact.

[0059] According to the test's technical requirements, the trajectory of the simulated projectile 15 after launch can be approximated as a horizontal projection under the influence of gravity. The impact point of the simulated projectile 15 can be calculated by combining the projectile's dimensions, initial launch velocity, maximum drop angle, and the launch height of the simulated projectile 15. Taking into account the deviation distance in extreme cases, the buffer recovery zone can be determined. This area can be used to determine the location of high-damping, low-rebound cushions 41. The rebound value of the simulated projectile 15 must be verified based on the performance parameters of the cushions 41 to prevent secondary rebound damage to the simulated projectile 15 or the missile launcher. The bottom of this zone is laid with cushions 41 and rubber rings 42, arranged in sequence from bottom to top. The sides are then followed by cushions 41 and explosion-proof walls 43. At the end of the buffer recovery zone, high-damping, low-rebound cushions 41 and explosion-proof walls 43 are installed in sequence, along the launch direction of the simulated projectile 15, to provide a barrier. The rubber ring 42 is laid above the buffer recovery zone to increase the missile's sliding friction, reduce the impact of the missile landing, and fully protect the missile, test personnel, and test site. Furthermore, none of the components of the launch and recovery device are connected to the foundation 1. The explosion-proof bricks 431, similar to the mortise and tenon structure, can be embedded in the foundation 1 and are secure enough to withstand the impact of the simulated projectile 15. The cushion 41 and rubber ring 42 are also not connected.

[0060] 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 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.

[0061] The fixing fixture 5 is used to fix the launch device in the missile launch system. The missile launch system includes a wing simulation component 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.

[0062] The fixture 5 consists of a base plate 51 and lug plates 52. The base plate 51 is bolted to the top crossbeam 24 of the test frame 2, while the lug plates 52 are connected to four mounting points on the wing simulator 13 via an interference fit of pins. The crossbeam 24 at the top of the test frame 2 is connected to the wing simulator 13 via four fixtures 5. The lower end of the wing simulator 13 carries a simulated missile launcher 14, accurately simulating the installation boundaries of the simulated missile launcher 14 on the aircraft.

[0063] The specific steps of the test are as follows:

[0064] 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. 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.

[0065] 2. Place the quartz lamp holder 31 at the center of the projection directly below the grid formed by the four horizontal beams 24 at the top of the test frame 2. The quartz lamp holder 31 is secured to the foundation 1 via the bottom support cups 37. The height of the quartz lamp holder 31 can be adjusted by rotating the threads of the bottom support cups 37. The rear end of the quartz lamp holder 31 is hinged to the rear end of the tray 32 via a pin. The front end of the quartz lamp holder 31 is fixed to the front end of the tray 32 via a cylinder 36. Then, install the reflector 33 and bronze plate 34 on the tray 32 in sequence. Then, secure the quartz lamps 35 to the bronze plates 34 one by one. Finally, connect the cables and air pipes to the bronze plates 34 in sequence. 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.

[0066] 3. Install four fixing fixtures 5. Specifically, the base plate 51 of the fixing fixture 5 connects the fixing fixture 5 to the top crossbeam 24 of the test frame 2 through bolts; the ear plate 52 is connected to the four mounting 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.

[0067] 4. Calculate the landing point of the simulated projectile 15 according to the test technical requirements, and derive the buffer recovery interval based on the deviation distance. Lay the delivery and recovery device 4 in this area. Lay the buffer pad 41 and rubber ring 42 on the bottom of this area from bottom to top, and set up the buffer pad 41 and explosion-proof wall 43 on the side. Along the ejection direction of the simulated projectile 15, a high-damping low-rebound buffer pad 41 and explosion-proof wall 43 are set up at the end of the buffer recovery interval to block it.

[0068] 5. A temperature monitoring point and a temperature control point are arranged at the bottom of the simulated missile launcher 14. The temperature sensor at the temperature monitoring point is connected to a temperature measuring instrument 7, which is in turn connected to a heating monitoring host computer 6 for temperature monitoring. The temperature control point is connected to a heating controller 9 via a signal conditioning module 10. The heating control host computer 8 inputs control signals to control the power output of a power distribution cabinet 11. The power distribution cabinet 11 is connected to a transfer cabinet 12, which is then connected to a copper plate 34 via a cable for heating control.

[0069] 6. Use the overhead crane to push the simulated missile 15 axially into the simulated missile launcher 14, and connect it with the mounting device in the simulated missile launcher 14 through the mounting interface of the simulated missile 15.

[0070] 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.

[0071] In this way, the requirements of following the opening action of the simulated missile launcher and the controllable rapid heating of the designated area are realized, 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.

[0072] The present invention effectively overcomes the shortcomings of traditional launcher drop tests. First, the number and length of the base 21, uprights 22, inclined uprights 23, and crossbeams 24 can be interchanged based on the size of the simulated missile launcher 14. This modularizes the test frame's structural shape, greatly enhancing the flexibility of the test frame. This design features simple structure, efficient construction, reusability, and safety, effectively improving test efficiency. Second, the heating device 3 adjusts its front end height as the simulated missile launcher 14 descends. This not only meets the requirements for the inclined launch posture when the simulated missile launcher 14 opens its hatch to release a missile, but also provides a high-temperature environment in a designated area, achieving the technical requirements of controlled and rapid temperature rise. Furthermore, the device can immediately shut off power after reaching the designated temperature, maximizing safety during the test. In short, the heating device effectively simulates the operating conditions of the simulated missile launcher 14 under real-world high-speed flight conditions, eliminating environmental changes during the drop process that could result in inadequate test specimen testing. Third, the drop and recovery device effectively reduces the rebound and sliding impact of the simulated missile after landing, minimizing damage to 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 to build 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 fit 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.

[0073] 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 delivery test systems.

[0074] 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 of the present invention and its core ideas. The above is only a preferred implementation method of the present invention. It should be pointed out that due to the limitations of textual expression, there are objectively infinite specific structures. For ordinary technicians in this technical field, without departing from the principles of the present invention, they can make several improvements, modifications or changes, 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 scope of protection 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), wherein 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 fixed to the front end of the tray (32) through a cylinder (36); and a supporting foot cup (37) is installed 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 fixture (5) comprises a base plate (51) and a pair of ear plates (52) on the base plate (51), and the fixing fixture (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) and the temperature measuring instrument (7) are connected to transmit monitoring instructions and signal feedback display. The heating control host computer (8) and the heating controller (9) are connected to transmit control instructions and signal feedback display. The bottom surface of the transmitting device is equipped with a temperature sensor, and the temperature sensor is respectively 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) 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 achieve regulation of the voltage of the heating device (3) and achieve temperature closed-loop control.

2. The simulated ground launch test device according to claim 1, characterized in that: The reflective plates (33) and the bronze 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 bronze plates (34).

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

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