CN111665817A - Carrier rocket launching support equivalent test method - Google Patents

Abstract

The invention provides a carrier rocket launching support equivalent test method, which is used for a carrier rocket launching support equivalent control system, and comprises the following steps: the erecting simulation erecting arm is in a horizontal state to a vertical state, and a first inclination angle sensor arranged on the simulation erecting arm transmits an inclination angle signal of the simulation erecting arm to the control device; adjusting the levelness of the analog launching platform, and transmitting a levelness signal to the control device by a second inclination angle sensor arranged on the analog launching platform; the signal output of the proximity switch on the proximity switch simulation board is monitored, and the control device receives different proximity switch signals and sends corresponding instructions. The carrier rocket launching support equivalent test method provides guarantee for synchronous development and factory leaving in advance of a control system of an actual carrier rocket launching support system.

Description

An Equivalent Test Method for Launch Support of Launch Vehicles

technical field

The invention relates to the field of launch vehicle launch, in particular to an equivalent test method for launch support of a launch vehicle.

Background technique

With the rapid development of my country's aerospace industry, the "three-level" measurement and launch mode of launch vehicles has gradually emerged. In the equipment development process of the "Sanping" test and launch mode, the actual launch vehicle launch support system equipment development process and cycle are very long, and its control system equipment has no actual launch vehicle launch support system equipment during the development process. It can be used for system debugging and delivery. Acceptance, if tested on the actual launch vehicle launch support system, not only wastes time but also increases development costs.

In view of this, it is urgent to design an equivalent test method for launch support of a launch vehicle, which avoids a long development cycle and saves the time of joint adjustment of the actual launch support system of the launch vehicle.

SUMMARY OF THE INVENTION

The purpose of the present invention is to overcome the deficiencies of the prior art and provide an equivalent test method for launch support of a launch vehicle.

The invention provides an equivalent test method for launch support of a launch vehicle. The method is used for an equivalent control system for launch support of a launch vehicle. The control system includes a simulated launch platform, a simulated vertical arm, a proximity switch simulation board and a control device. The control device is electrically connected to the analog launch platform, the analog erector arm and the proximity switch analog board, and the test method includes: erecting the analog erector arm from a horizontal state to a vertical state, and setting it at the The first inclination sensor on the simulated erecting arm transmits the inclination signal of the simulated erecting arm to the control device; the level of the simulated launching platform is adjusted, and the second inclination sensor arranged on the simulated launching platform will The level signal is transmitted to the control device; the signal output of the proximity switch on the proximity switch analog board is monitored, and the control device receives different proximity switch signals and sends out corresponding commands.

According to an aspect of the present invention, the adjusting the levelness of the simulated launch platform includes: controlling the lengths of at least three movable legs supporting the simulated launch platform, so that the absolute level of the second inclination sensor is The value is between 0 degrees and 0.5 degrees.

According to one aspect of the present invention, the equivalent test method for launch support of a launch vehicle further includes: when the simulated erecting arm is erected at a degree greater than 91.5 degrees relative to the simulated launch platform, the control device sends an alarm signal and closes the simulated Command to raise the arm.

According to an aspect of the present invention, the monitoring the signal output of the proximity switch on the proximity switch analog board includes: monitoring four proximity switches on the proximity switch analog board simulating the erector arm, which are erection arms respectively. In-position proximity switch, leveling in-position proximity switch, pre-rewinding in-position proximity switch and quick-rewinding in-position proximity switch.

According to an aspect of the present invention, the simulated erecting arm is set to a horizontal state, and when the simulated erecting arm is raised, when the erecting angle is greater than 1 degree, the signal output of the leveling position proximity switch is monitored, and when the When the erection angle of the simulated erector arm is greater than 89.5 degrees, the signal output of the erection position proximity switch is monitored.

According to an aspect of the present invention, the control system includes a take-off simulation button for simulating a take-off signal of the launch vehicle, and the test method further includes: pressing the take-off simulation button and sending a take-off signal of the launch vehicle, the After receiving the take-off signal, the control device turns on the fast rewind command of the simulated erecting arm, and monitors the signal output of the fast rewind position proximity switch.

According to one aspect of the present invention, the monitoring of the signal output of the proximity switch on the proximity switch analog board includes: monitoring the proximity switches of two upper clamps on the proximity switch analog board, respectively, when the upper clamp is opened in place. The proximity switch and the upper clamp hold the proximity switch in place.

According to an aspect of the present invention, the control device activates the upper clamp unlocking instruction, and monitors the signal output of the proximity switch when the upper clamp is unlocked in place; the control device activates the upper clamp clamping instruction, and monitors the upper clamp Hold the signal output of the proximity switch in place.

According to one aspect of the present invention, the monitoring of the signal output of the proximity switch on the proximity switch analog board includes: monitoring the proximity switches of two types of windproof devices on the proximity switch simulation board, respectively, when the windproof device is unlocked in place and approaching The switch and draft shield lock into place for the proximity switch.

According to one aspect of the present invention, the control device activates an unlocking command of the windproof device, and monitors the signal output of the proximity switch when the windproof device is unlocked; Signal output of proximity switch.

The equivalent test method for launch support of a launch vehicle provided by the present invention includes the test of the simulated erecting arm, the test of the simulated launch platform and the test of the proximity switch simulation board, which can conveniently complete the debugging of the control sub-system of the actual launch support system of the launch vehicle , comprehensive test, factory acceptance and system fault separation, to provide guarantee for the synchronous development and early delivery of the control system of the actual launch vehicle launch support system.

It is to be understood that the foregoing general description and the following detailed description are exemplary and explanatory only and are not intended to limit the scope of the invention as claimed.

Description of drawings

The accompanying drawings, which are part of the specification of the invention, illustrate exemplary embodiments of the invention and, together with the description of the specification, serve to explain the principles of the invention.

1 is a schematic diagram of a launch vehicle launch support equivalent device according to an embodiment of the present invention;

2 is a schematic diagram of a launch vehicle launch support equivalent device according to still another embodiment of the present invention;

FIG. 3 is a flowchart of an equivalent test method for launch support of a launch vehicle according to an embodiment of the present invention.

Description of reference numbers:

101-analog launch platform, 102-movable outriggers, 103-first inclination sensor, 104-analog vertical arm, 105-second inclination sensor, 106-proximity switch simulation board, 201-take-off simulation button, 202-displacement sensor.

Detailed ways

The features and exemplary embodiments of various aspects of the present invention will be described in detail below. In order to make the objectives, technical solutions and advantages of the present invention more clear, the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments. It should be understood that the specific embodiments described herein are only configured to explain the present invention, are used to exemplify the principles of the present invention, and are not configured to limit the present invention. Additionally, the machine components in the figures are not necessarily drawn to scale. For example, the dimensions of some of the structural elements or regions in the figures may be exaggerated for other structural elements or regions to facilitate an understanding of embodiments of the present invention.

Orientation words appearing in the following description are all directions shown in the drawings, and do not limit the specific structure of the embodiments of the present invention. In the description of the present invention, it should be noted that, unless otherwise specified, the terms "installed", "connected" and "connected" should be understood in a broad sense, for example, it may be a fixed connection, a detachable connection, or an integrated ground connection; either directly or indirectly through an intermediary. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific conditions.

Furthermore, the terms "comprising," "comprising," "having," or any other variation thereof are intended to encompass a non-exclusive inclusion, whereby a structure or component that includes a list of elements includes not only those elements, but also includes not explicitly listed or inherent belong to structural parts, other mechanical parts on components. Without further limitation, an element defined by the phrase "comprising" does not preclude the presence of additional identical elements in the article or device comprising the element.

Spatial relational terms such as "below," "below," "below," "lower," "above," "above," "higher," etc. are used to facilitate description to explain an element relative to a The orientation of the two elements means that these terms are intended to encompass different orientations of the device in addition to orientations other than those shown in the figures. In addition, for example, "one element is on/under the other" can mean that two elements are in direct contact with each other, or that there are other elements between the two elements. Furthermore, terms such as "first", "second", and the like, are also used to describe various elements, regions, sections, etc. and should not be regarded as limiting. Similar terms refer to similar elements throughout the description.

It will be apparent to those skilled in the art that the present invention may be practiced without some of these specific details. The following description of the embodiments is only intended to provide a better understanding of the present invention by illustrating examples of the invention.

1 is a schematic diagram of a launch vehicle launch support equivalent device according to an embodiment of the present invention, FIG. 2 is a schematic diagram of a launch vehicle launch support equivalent device according to another embodiment of the present invention, and FIG. 3 is a launch vehicle according to an embodiment of the present invention. A flow chart of the launch support equivalent test method.

As shown in FIG. 1 , the present invention provides an equivalent device for launch support of a launch vehicle, comprising: a simulated launch platform 101 arranged on at least three movable legs 102 , and a first inclination sensor 103 installed on the simulated launch platform 101 ; The simulated erector arm 104 is arranged at one end of the simulated launch platform 101 and connected by a rotatable hinge point, and the second inclination sensor 105 is installed on the simulated erector arm 104; The proximity switch analog board 106 is used to install the simulated erector arm 102. Proximity switch of upper clamp and windproof device.

Specifically, the launch vehicle launch support equivalent device in this embodiment is used to solve the problem of no real launch support system or to control system debugging and field acceptance before a simulated launch mission. The equivalent device for launch support of the launch vehicle adopts the equivalent device with the same equipment interface of the actual launch support system. The simulated launch platform 101 simulates a real simulated launch pad, which can be made of lightweight aluminum, and is also used as an installation platform for other simulated equipment. The simulated launch platform 101 is arranged on at least three movable legs 102 , and the level of the simulated launch platform 101 is adjusted through the movable legs 102 .

In this embodiment, the movable outrigger 102 selects the same type of small-model product in the actual system, and its control logic and method are consistent with the actual system. A first inclination sensor 103 is installed on the simulated launch platform 101 for real-time feedback of the levelness of the simulated launch platform 101, that is, the verticality information of the launch vehicle. Consistency of sensor elements during launch. In one aspect of the present invention, the movable outrigger 102 is a servo electric outrigger or a hydraulic power outrigger, for example, an electric lead screw can be selected for the servo electric outrigger, and the analog launch platform 101 can be leveled by controlling the extension and contraction of the lead screw.

Among them, the simulated erecting arm 104 can simulate the actual erection process of the launch vehicle, and the simulated erecting arm 104 can be made of aluminum material, and the simulation of the erecting process can be realized manually. The simulated erecting arm 104 is arranged at one end of the simulated launching platform 101 and is connected by a rotatable hinge point with a locking device. In one aspect of the present invention, the simulated erecting arm 104 can realize any angle limit from -2 degrees to 92 degrees, and has a locking function. A second inclination sensor 105 is installed on the simulated erecting arm 104 for real-time feedback of the erecting angle of the simulated erecting arm 104. The second inclination sensor 105 can be the same product as the actual launch support system.

Additionally, a proximity switch analog board 106 in the launch vehicle launch support equivalent is used to install proximity switches for other equipment. As one of the embodiments, other devices include: a simulated erecting arm 102, an upper clamp and a windproof device, wherein the upper clamp and the windproof device have no actual simulation products, only the proximity switches of the two are used to simulate the upper clamp and windshield transmission signal. The position of the proximity switch simulation board 106 is not limited. In this embodiment, for the convenience of operation, the proximity switch simulation board 106 is arranged on the simulation launch platform 101 .

As shown in FIG. 2 , in one aspect of the present invention, the launch vehicle launch support equivalent device further includes a take-off simulation button 201 , which is arranged at the other end of the simulated launch platform 101 and used to simulate the launch signal of the launch vehicle. Specifically, by pressing the take-off simulation button 201, the launch vehicle can be simulated to launch a take-off signal supporting the equivalent device, and the equivalent device can perform an operation of simulating a fast reverse of the erector arm 104 after receiving the take-off signal.

As shown in FIG. 2 , in one aspect of the present invention, the launch vehicle launch support equivalent device further includes: a displacement sensor 202 , one end of the displacement sensor 202 is installed on the bottom surface of the simulated launch platform 101 , and the other end is installed on the movable outrigger 102 , used to feedback the length of the movable outrigger 102 . The displacement sensor 202 is responsible for realizing the detection of the movement and displacement of the movable leg 102, and it adopts the same product as the actual launch support system. In this embodiment, one end of the displacement sensor 202 is installed on the bottom surface of the analog launch platform 101, and the other end is installed at the position of the support leg seat of each movable support leg 102. In practical applications, the displacement sensor 202 can be placed on the Different positions are sufficient as long as the movement and displacement detection of the movable legs 102 can be realized.

In one aspect of the present invention, the proximity switch simulation board 106 is provided with a plurality of mounting holes for fixing the proximity switch. In one aspect of the present invention, the proximity switch simulation board 106 further includes an output indicator light, and the output indicator light is connected in parallel with the corresponding proximity switch control output signal.

Among them, the proximity switch simulation board 106 is used as the installation bracket of the proximity switch, and can also be used to control the installation bracket of the output indicator light. At the same time, the corresponding auxiliary equipment is used to simulate the closed and open states of the proximity switch, including the simulation of the vertical arm 102, the upper Proximity switch signals for clamps and draft shields. All proximity switches can use the same products as the actual launch support system. The control output indicator light is connected in parallel with the corresponding proximity switch control output signal, and the status of each proximity switch is reflected by the output indicator light.

In order to ensure the authenticity of the launch vehicle launch support equivalent device in the present invention and improve the reliability of the test results, for example, all sensors in the equivalent device use actual products consistent with the actual launch vehicle launch support system. Equivalent devices During the experiment, in the case that some sensors and equipment cannot be in place as planned, buttons, signal simulation boards or PLC modules can also be used to achieve similar functions. The devices not mentioned in this embodiment include: sensor data acquisition, analog input and output control and digital input and output control. The above devices are well known in the industry and can be improved on the basis of the present invention according to actual needs.

In another aspect, the present invention provides an equivalent control system for launch support of a launch vehicle, including the above-mentioned equivalent device for launch support of a launch vehicle, and a control device, which is electrically connected to the simulated launch platform 101, the simulated erector arm 104 and the proximity switch The simulation board 106 is used to control the actions of the simulation launch platform 101 , the simulation vertical arm 104 and the proximity switch simulation board 106 . The control device belongs to the brain of the equivalent control system supporting the launch of the launch vehicle. Through the built-in logic program, it can effectively control the leveling action of the simulated launch platform 101, control the erecting action or fast-reversing action of the simulated erecting arm 104, and control the proximity switch simulation. The proximity switch of board 106 opens or closes action.

After the rocket is transported by the rocket transporter to the launch station, the main work is as follows:

1) erect the vehicle to erect the rocket, and lower the rocket to the launch pad;

2) Open the upper clamp of the erector arm;

3) Compress the rocket windproof device;

4) Start to adjust the verticality of the rocket;

5) Release the rocket windproof device;

6) The erection arm is pre-declined to a certain angle;

7) After receiving the rocket take-off signal, start to raise the vertical arm and quickly fall back.

This launch vehicle launch support equivalent control system mainly completes the following equivalent functions:

1) Simulate the process of erecting and lowering the erecting arm 104;

2) Simulate the process of opening and holding the upper clamp of the erector arm 104;

3) Simulate the locking and unlocking process of the windproof device;

4) Simulate the leveling of the launch platform 101, that is, the process of adjusting the verticality of the rocket;

5) Simulate the process of pre-inverting and pre-inverting the erector arm 104;

6) Simulate the process of rewinding and rewinding the erector arm 104 quickly into place.

Therefore, the present invention provides an equivalent test method for launch support of a launch vehicle. The method is used for an equivalent control system for launch support of a launch vehicle. The control system includes a simulated launch platform 101, a simulated erector arm 104, a proximity switch simulation board 106 and a control system. device, the control device is electrically connected to the analog launch platform 101, the analog erector arm 104 and the proximity switch analog board 106, and the test method includes:

S100: erecting the simulated erecting arm 104 from a horizontal state to a vertical state, and the first inclination sensor 103 disposed on the simulated erecting arm 104 transmits the inclination signal of the simulated erecting arm 104 to the control device;

S200: Adjust the level of the analog launch platform 101, and the second inclination sensor 105 disposed on the analog launch platform 101 transmits the level signal to the control device;

S300: Monitor the signal output of the proximity switch on the proximity switch analog board 106, and the control device receives different proximity switch signals and sends out corresponding commands.

Specifically, the equivalent test method for launch support of the launch vehicle mainly includes simulating the erection process of the erector arm 104, the leveling process of the simulated launch platform 101, the upper clamp opening and clamping process, and the wind protection device locking and unlocking process.

Wherein, during the erecting process of the simulated erecting arm 104, the erecting simulated erecting arm 104 is from a horizontal state to a vertical state, and the first inclination sensor 103 disposed on the simulated erecting arm 104 will simulate the inclination signal of the erecting arm 104 to the control unit. During the leveling process of the simulated launch platform 101, the level of the simulated launch platform 101 is adjusted, and the second inclination sensor 105 disposed on the simulated launch platform 101 transmits the level signal to the control device. The upper clamp opening and clamping process and the wind protection device locking and unlocking process are all performed on the proximity switch simulation board 106. The test is performed by detecting the proximity switch signal output of the upper clamp and the wind protection device, and the control device receives different proximity switch signals. and issue the corresponding command.

According to one aspect of the present invention, the equivalent test method for launch support of a launch vehicle further includes: when the erection of the simulated erector arm 104 is greater than 91.5 degrees relative to the simulated launch platform 101, the control device sends out an alarm signal and closes the simulated erection arm 104. instruction.

According to one aspect of the present invention, adjusting the level of the simulated launch platform 101 includes: controlling the lengths of at least three movable legs 102 supporting the simulated launch platform 101 so that the absolute value of the level of the second tilt sensor 105 is 0 degrees - between 0.5 degrees.

According to one aspect of the present invention, monitoring the signal output of the proximity switch on the proximity switch analog board 106 includes: monitoring four proximity switches on the proximity switch analog board 106 simulating the erection arm 104 , which are the erection position proximity switch, the return Flat position proximity switch, pre-retract position proximity switch and quick retract position proximity switch.

According to one aspect of the present invention, the simulated erecting arm 104 is set to be in a horizontal state, the simulated erecting arm 104 is raised and when the erecting angle is greater than 1 degree, the signal output of the proximity switch is monitored to be leveled back in position, when the simulated erecting arm 104 is raised When the erection angle is greater than 89.5 degrees, monitor the signal output of the proximity switch in the erected position. When the simulated erecting arm 104 is set to a horizontal state, the proximity switch in the leveling position is closed, and when the erecting angle of the simulated erecting arm 104 is raised, when the erection angle is greater than 1 degree, the proximity switch in the leveling position is on, and when the simulated erecting arm 104 is raised, the proximity switch is turned on. When the erection angle of 104 is greater than 89.5 degrees, the proximity switch in the erected position is closed.

According to one aspect of the present invention, the control system includes a take-off simulation button for simulating the take-off signal of the launch vehicle, and the test method further includes: pressing the take-off simulation button and sending the take-off signal of the launch vehicle, and the control device starts the simulation after receiving the take-off signal. The vertical arm 104 fast rewinds the command, and monitors the signal output of the proximity switch in the fast rewind position. The simulated erecting arm 104 starts from 90 degrees, pre-reverses to 87 degrees, and closes the proximity switch in the pre-reversing position. After receiving the take-off signal, the simulated erecting arm 104 continues to start from 87 degrees, and quickly reverses to 75 degrees, and then quickly reverses. In-position proximity switch closed

According to one aspect of the present invention, monitoring the signal output of the proximity switch on the proximity switch analog board 106 includes: monitoring the proximity switches of two types of upper clamps on the proximity switch analog board 106 , which are the proximity switch when the upper clamp is opened and the proximity switch on the upper clamp. The clamps hold the proximity switch in place.

According to one aspect of the present invention, the control device activates the upper clamp unlocking instruction, and monitors the signal output of the proximity switch when the upper clamp is unlocked; . In some cases, based on the structural features of the upper clamp, there are two or more proximity switches set when the upper clamp is opened, and two or more proximity switches are set when the upper clamp is held in place.

According to an aspect of the present invention, monitoring the signal output of the proximity switch on the proximity switch analog board 106 includes: monitoring the proximity switches of two kinds of windproof devices on the proximity switch simulation board 106 , which are the proximity switch of the unlocked position of the windproof device and the lock of the windproof device, respectively. Tighten the proximity switch in place.

According to one aspect of the present invention, the control device activates the windproof device unlocking command, and monitors the signal output of the proximity switch when the windproof device is unlocked in place; In some cases, based on the structural features of the windproof device, there are two or more proximity switches provided with the windproof device unlocked in place, and two or more proximity switches provided with the windproof device locked in place.

In the present invention, the equivalent test method for launch support of a launch vehicle includes five simulated test procedures, and the specific operation procedures are as follows:

1. The erecting process of the simulated erecting arm 104 is as follows:

S101: simulate the horizontal state of the erecting arm 104, and adjust the horizontality to be between 0 degrees and plus or minus 0.5 degrees according to the inclination signal of the first inclination sensor;

S102: Adjust the proximity switch of the simulated erecting arm 104 to be in a closed state;

S103: The control device issues a erection command, slowly lifts the simulated erection arm 104, and monitors the real-time and accuracy of the follow-up of the inclination signal of the first inclination sensor collected by the control device;

S104: When the erection angle is greater than 1 degree, if the leveling in-position proximity switch still displays the closed state, check whether the control device gives a fault prompt of the simulated erecting arm leveling-in-position proximity switch;

S105: Monitor whether the signal output of the leveling-in-position proximity switch is normal, and when the analog erection arm 104 is closed to the erection-in-position signal, monitor whether the erection control command output disappears;

S106: Continue to erect the simulated erecting arm 104 until it is greater than 91.5 degrees, monitor whether the control device gives an alarm message and close the erecting control command.

2. The leveling process of the simulated launch platform 101 is as follows:

S201: Manually control at least three movable legs 102 to adjust the simulated launch platform 101, so that the display angle of the second inclination sensor is between 0 degrees and plus or minus 0.5 degrees;

S202: The control device sends out the leveling command of the simulated launch platform 101, that is, the rocket verticality adjustment command, and monitors the leveling of the simulated launch platform 101;

S203: monitor whether the action of the movable outrigger 102 of the simulated launch platform 101 is consistent with the control output command of the movable outrigger 102;

S204: Whether an error message is given if the vertical adjustment of the rocket is not completed within the specified time;

S205: After the verticality adjustment is normally completed, simulate whether the horizontality of the launch platform 101, that is, whether the result of the verticality of the rocket meets the accuracy requirements.

3. The process of opening and holding the upper clamp is as follows:

S301: The upper clamp is opened in place and the proximity switch is set to the closed state;

S302: The control device issues a command to hold the upper clamp;

S303: Monitor whether the output of the clamp tightening command on the control system is normal;

S304: When the proximity switch closes when the upper clamp is in place, monitor whether the upper clamp clamping command output in the control device disappears;

S305: The upper clamp is in place and the proximity switch is closed;

S306: The control device issues an instruction to open the upper clamp;

S307: Monitor whether the output of the clamp opening command on the control device is normal;

S308: When the upper clamp is opened to the limit and the proximity switch is closed, monitor whether the upper clamp opening command output in the control device disappears.

4. The locking and unlocking process of the windproof device is as follows:

S401: The windproof device is unlocked in place and the proximity switch is closed;

S402: The control device issues a windproof device locking instruction;

S403: Monitor whether the output of the locking command of the windproof device of the control device is normal;

S404: When the windproof device is locked in place and the proximity switch is closed, monitor whether the windproof device locking command output in the control device disappears;

S405: The windproof device is locked in place and the proximity switch is in the closed state;

S406: The control device issues an unlocking instruction for the windproof device;

S407: Monitor whether the output of the unlocking command of the windproof device in the control device is normal;

S408: When the proximity switch of the windproof device is unlocked in place, monitor whether the output of the unlocking command of the windproof device in the control device disappears.

5. Receiving the take-off signal to simulate the fast reversing process of the erection arm 104:

S501: Press the take-off simulation button 201;

S502: The control device issues a fast reverse command to simulate the erecting arm 104;

S503: Monitor whether the command of the control device for erecting the erection arm fast reversal is output;

S504: when the take-off simulation button 201 is pressed, monitor whether the control device fast reverse command is output;

S505: assess the response time of the control device for receiving the take-off signal;

S506: fast rewind start control reaction time and fast rewind process reaction time;

S507: When the fast rewind position proximity switch is closed, monitor whether the fast rewind command in the control device disappears.

The equivalent test method for launch support of the launch vehicle in the present invention adopts the equivalent device which is completely consistent with the equipment interface of the actual launch support system of the launch vehicle. The development of the control system of the launch support system is carried out simultaneously with the development of the overall equipment. Using the launch vehicle launch support equivalent test method can greatly shorten the development cycle, save the actual launch vehicle launch support system debugging time, and greatly save development costs. The launch vehicle launch support equivalent test method can conveniently complete the commissioning, comprehensive test, factory acceptance and system fault separation of the control subsystem of the actual launch vehicle launch support system, and is synchronously developed and advanced for the control system of the actual launch vehicle launch support system. Factory guarantee.

The above are only preferred embodiments of the present invention and are not intended to limit the present invention. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention. within.

Claims (10)

1. a launch vehicle launch support equivalent test method, it is characterized in that, this method is used for launch vehicle launch support equivalent control system, and described control system comprises simulated launch platform, simulated erector arm, proximity switch simulation board and control device, the control device is electrically connected to the analog launch platform, the analog erector arm and the proximity switch analog board, and the test method includes: erecting the simulated erecting arm from a horizontal state to a vertical state, and the first inclination sensor arranged on the simulated erecting arm transmits the inclination angle signal of the simulated erecting arm to the control device; Adjusting the level of the simulated launch platform, the second inclination sensor arranged on the simulated launch platform transmits the level signal to the control device; The signal output of the proximity switch on the proximity switch analog board is monitored, and the control device receives different proximity switch signals and sends out corresponding commands. 2. The launch vehicle launch support equivalent test method according to claim 1, wherein the adjusting the levelness of the simulated launch platform comprises: The lengths of at least three movable legs supporting the simulated launch platform are controlled so that the absolute value of the horizontality of the second inclination sensor is between 0 degrees and 0.5 degrees. 3. The carrier rocket launch support equivalent test method according to claim 1, is characterized in that, also comprises: When erecting the simulated erecting arm is greater than 91.5 degrees relative to the simulated launching platform, the control device sends an alarm signal and an instruction to close the simulated erecting arm. 4. The launch vehicle launch support equivalent test method according to claim 1, wherein the monitoring of the signal output of the proximity switch on the proximity switch analog board comprises: Monitor the four proximity switches on the proximity switch analog board simulating the erecting arm, which are the erecting position proximity switch, the leveling position proximity switch, the pre-retracting position proximity switch and the fast retracting position proximity switch. 5. The launch vehicle launch support equivalent test method according to claim 4, wherein the simulated erector arm is set to be in a horizontal state, and the simulated erector arm is lifted when the erection angle is greater than 1 degree, Monitor the signal output of the leveling position proximity switch, and monitor the signal output of the erecting position proximity switch when the erection angle of the simulated erecting arm is greater than 89.5 degrees. 6. The equivalent test method for launch support of a launch vehicle according to claim 4, wherein the control system comprises a take-off simulation button for simulating the take-off signal of the launch vehicle, and the test method further comprises: Press the take-off simulation button and send the take-off signal of the launch vehicle. After receiving the take-off signal, the control device turns on the fast reverse command of the simulated erector arm, and monitors the signal output of the fast reverse position proximity switch. 7. The launch vehicle launch support equivalent test method according to claim 1, wherein the monitoring of the signal output of the proximity switch on the proximity switch analog board comprises: Monitor the proximity switches of the two upper clamps on the proximity switch analog board, namely, the upper clamp opening proximity switch and the upper clamp tightening position proximity switch. 8 . The launch vehicle launch support equivalent test method according to claim 7 , wherein the control device starts the upper clamp unlocking instruction, and monitors the signal output of the proximity switch when the upper clamp is unlocked in place; the control The device starts the upper clamp tightening instruction, and monitors the signal output of the upper clamp close proximity switch. 9 . The launch vehicle launch support equivalent test method according to claim 1 , wherein the monitoring of the signal output of the proximity switch on the proximity switch analog board comprises: 10 . Monitor the proximity switches of two kinds of windproof devices on the proximity switch analog board, namely, the proximity switch of the windproof device unlocked in place and the proximity switch of the locked position of the windproof device. 10 . The equivalent test method for launch support of a launch vehicle according to claim 9 , wherein the control device starts an unlocking instruction of the windproof device, and monitors the signal output of the proximity switch when the windproof device is unlocked in place; the control device is turned on. 11 . The windproof device locking command monitors the signal output of the proximity switch when the windproof device is locked in place.

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