CN111665817A - Carrier rocket launching support equivalent test method - Google Patents
Carrier rocket launching support equivalent test method Download PDFInfo
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- CN111665817A CN111665817A CN202010400458.1A CN202010400458A CN111665817A CN 111665817 A CN111665817 A CN 111665817A CN 202010400458 A CN202010400458 A CN 202010400458A CN 111665817 A CN111665817 A CN 111665817A
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- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B23/00—Testing or monitoring of control systems or parts thereof
- G05B23/02—Electric testing or monitoring
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
Technical Field
The invention relates to the field of launch of carrier rockets, in particular to an equivalent test method for launch support of a carrier rocket.
Background
With the rapid development of aerospace industry in China, a 'three-dimensional' launching test mode gradually appears in a launching test mode of a carrier rocket. In the process of developing the equipment in the 'three-translation' launch test mode, the actual process and the period of developing the launch support system equipment of the carrier rocket are very long, the control system equipment of the launch support system equipment of the carrier rocket does not have actual equipment of the launch support system of the carrier rocket in the process of developing and can be used for system debugging and factory acceptance, and if the test is carried out on the actual launch support system of the carrier rocket, the time is wasted and the development expenditure is increased.
In view of this, it is necessary to design an equivalent test method for launch support of a launch vehicle, which avoids the long development cycle and can save the joint debugging time of the launch support system of the launch vehicle.
Disclosure of Invention
The invention aims to overcome the defects of the prior art and provide an equivalent test method for launch support of a carrier rocket.
The invention provides a carrier rocket launching support equivalent test method, which is used for a carrier rocket launching support equivalent control system, wherein the control system comprises a simulated launching platform, a simulated vertical arm, a proximity switch simulation board and a control device, the control device is electrically connected with the simulated launching platform, the simulated vertical arm and the proximity switch simulation board, and the test method comprises the following steps: erecting the simulated vertical arm from a horizontal state to a vertical state, and transmitting an inclination angle signal of the simulated vertical arm to the control device by a first inclination angle sensor arranged on the simulated vertical arm; 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; and monitoring the signal output of the proximity switch on the proximity switch simulation board, and the control device receives different proximity switch signals and sends corresponding instructions.
According to one aspect of the invention, the adjusting the levelness of the analog launch platform comprises: controlling the length of at least three movable legs supporting the analog launching platform so that the absolute value of the levelness of the second tilt sensor is between 0 and 0.5 degrees.
According to one aspect of the invention, the launch vehicle launch support equivalent test method further comprises: and when the simulated vertical arm is erected for more than 91.5 degrees relative to the simulated launching platform, the control device sends out an alarm signal and an instruction for closing the simulated vertical arm.
According to one aspect of the invention, the monitoring of the signal output of the proximity switch on the proximity switch analog board comprises: and monitoring four proximity switches simulating the vertical arms on the proximity switch simulation board, namely a vertical-to-position proximity switch, a leveling-back-to-position proximity switch, a pre-reverse-to-position proximity switch and a fast reverse-to-position proximity switch.
According to one aspect of the invention, the simulation vertical arm is set to be in a horizontal state, when the vertical angle of the simulation vertical arm is raised to be greater than 1 degree, the signal output of the leveling-in-place proximity switch is monitored, and when the vertical angle of the simulation vertical arm is greater than 89.5 degrees, the signal output of the leveling-in-place proximity switch is monitored.
According to one aspect of the invention, the control system comprises a takeoff simulation button for simulating a takeoff signal of the launch vehicle, and the test method further comprises: and pressing a takeoff simulation button and sending a takeoff signal of the carrier rocket, starting the simulated vertical arm fast-falling instruction after the control device receives the takeoff signal, and monitoring the signal output of the fast-falling-to-position approach switch.
According to one aspect of the invention, the monitoring of the signal output of the proximity switch on the proximity switch analog board comprises: and monitoring the proximity switches of the two upper clamps on the proximity switch simulation board, namely the proximity switch with the upper clamp opened in place and the proximity switch with the upper clamp clasped in place.
According to one aspect of the invention, the control device starts an upper clamp unlocking instruction and monitors the signal output of the proximity switch when the upper clamp is unlocked in place; and the control device starts an upper clamp clasping instruction and monitors the signal output of the proximity switch in which the upper clamp clasps in place.
According to one aspect of the invention, the monitoring of the signal output of the proximity switch on the proximity switch analog board comprises: and monitoring the proximity switches of the two windproof devices on the proximity switch simulation board, namely the windproof device unlocking in-place proximity switch and the windproof device locking in-place proximity switch.
According to one aspect of the invention, the control device starts a windproof device unlocking instruction, and monitors signal output of a proximity switch when the windproof device is unlocked in place; and the control device starts a windproof device locking instruction and monitors the signal output of the windproof device locking in place proximity switch.
The carrier rocket launching support equivalent test method provided by the invention comprises the test of a simulated vertical arm, the test of a simulated launching platform and the test of a proximity switch simulation board, can conveniently finish the debugging and the comprehensive test of a control subsystem of an actual carrier rocket launching support system, the delivery acceptance and the system fault separation, and provides guarantee for the synchronous development and the delivery ahead of schedule of the control subsystem of the actual carrier rocket launching support system.
It is to be understood that both the foregoing general description and the following detailed description are exemplary and explanatory only and are not restrictive of the invention, as claimed.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate exemplary embodiments of the invention and together with the description, serve to explain the principles of the invention.
FIG. 1 is a schematic illustration of a launch vehicle launch support equivalent of one embodiment of the present invention;
FIG. 2 is a schematic illustration of a launch vehicle launch support equivalent of yet another embodiment of the present invention;
FIG. 3 is a flow chart of a launch vehicle launch support equivalence test method of one embodiment of the invention.
Description of reference numerals:
101-simulation launching platform, 102-movable supporting leg, 103-first tilt angle sensor, 104-simulation vertical arm, 105-second tilt angle sensor, 106-proximity switch simulation board, 201-takeoff simulation button and 202-displacement sensor.
Detailed Description
Features and exemplary embodiments of various aspects of the present invention will be described in detail below, and in order to make objects, technical solutions and advantages of the present invention more apparent, the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments. It is to be understood that the specific embodiments described herein are merely illustrative of the invention and are not to be construed as limiting the invention, for the purposes of illustrating the principles of the invention. Additionally, the components in the drawings are not necessarily to scale. For example, the dimensions of some of the elements or regions in the figures may be exaggerated relative to other elements or regions to help improve understanding of embodiments of the present invention.
The directional terms used in the following description are used in the illustrated directions, and do not limit the specific configurations of the embodiments of the present invention. In the description of the present invention, it should be noted that, unless otherwise specified, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning fixedly connected, detachably connected, or integrally connected; may be directly connected or indirectly connected through an intermediate. The specific meaning of the above terms in the present invention can be understood as appropriate to those of ordinary skill in the art.
Furthermore, the terms "comprises," "comprising," "includes," "including," "has," "having" or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a structure or component comprising a list of elements does not include only those elements but may include other mechanical components not expressly listed or inherent to such structure or component. Without further limitation, an element defined by the phrase "comprising … …" does not exclude the presence of additional like elements in the article or device comprising the element.
Spatially relative terms such as "below," "… below," "lower," "above," "… above," "upper," and the like are used for convenience in describing the positioning of one element relative to a second element and are intended to encompass different orientations of the device in addition to different orientations than those illustrated in the figures. Further, for example, the phrase "one element is over/under another element" may mean that the two elements are in direct contact, or that there is another element 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 taken as limiting. Like terms refer to like elements throughout the description.
It will be apparent to one skilled in the art that the present invention may be practiced without some of these specific details. The following description of the embodiments is merely intended to provide a better understanding of the present invention by illustrating examples of the present invention.
Fig. 1 is a schematic view of a launch vehicle launch support equivalent apparatus according to an embodiment of the present invention, fig. 2 is a schematic view of a launch vehicle launch support equivalent apparatus according to still another embodiment of the present invention, and fig. 3 is a flowchart of a launch vehicle launch support equivalent test method according to an embodiment of the present invention.
As shown in fig. 1, the present invention provides a launch support equivalent apparatus for a launch vehicle, comprising: the simulated launching platform 101 is arranged on at least three movable supporting legs 102, and a first inclination angle sensor 103 is arranged on the simulated launching platform 101; the simulation vertical arm 104 is arranged at one end of the simulation launching platform 101 and connected through a rotatable hinge point, and a second inclination angle sensor 105 is arranged on the simulation vertical arm 104; a proximity switch simulation board 106 for mounting a proximity switch simulating the riser arm 102, upper clamp and windshield.
Specifically, the launch vehicle launch support equivalent device in this embodiment is used to solve the problem that there is no real launch support system or that it is used to control system debugging and acceptance on the spot before simulating the launch task. The carrier rocket launching support equivalent device adopts an equivalent device with completely consistent actual launching support system equipment interfaces, and the simulated launching platform 101 simulates a real simulated launching platform, can adopt light aluminum materials and is also used as a mounting platform of other simulation equipment. The analog launching platform 101 is arranged on at least three movable legs 102, and the levelness of the analog launching platform 101 is adjusted through the movable legs 102.
In the present embodiment, the movable leg 102 selects the same type of small-size product in the actual system, and the control logic and method thereof are consistent with the actual system. The first inclination angle sensor 103 is installed on the simulated launching platform 101 and used for feeding back the levelness of the simulated launching platform 101, namely the perpendicularity information of the rocket in transport in real time, and the first inclination angle sensor 103 can be used by an actual launching support system, so that the consistency of sensor elements in the simulated launching process is ensured. In one aspect of the present invention, the movable support leg 102 is a servo electric support leg or a hydraulic power support leg, for example, the servo electric support leg may select an electric screw, and the leveling of the simulation launching platform 101 is realized by controlling the extension and retraction of the screw.
The simulated erecting arm 104 can simulate the real erecting process of the carrier rocket, and the simulated erecting arm 104 can be made of aluminum materials and can simulate the erecting process manually. The analog vertical arm 104 is arranged at one end of the analog launching platform 101 and is connected through a rotatable hinge point with a locking device. In one aspect of the invention, the simulated erector arm 104 is capable of any angle of-2 to 92 degrees of spacing and has a locking function. A second tilt sensor 105 is installed on the simulated vertical arm 104 for real-time feedback of the vertical angle of the simulated vertical arm 104, and the second tilt sensor 105 can be a product like an actual launching support system.
In addition, the proximity switch simulation board 106 in the launch support equivalent of the launch vehicle is used to install proximity switches for other equipment. As one of the embodiments, the other apparatus includes: the erecting arm 102, the upper tong and the wind guard are simulated, wherein the upper tong and the wind guard have no actual simulation product and only proximity switches of the upper tong and the wind guard are adopted to simulate transmission signals of the upper tong and the wind guard. The position of the proximity switch simulation board 106 is not limited, and in this embodiment, the proximity switch simulation board 106 is disposed on the analog transmission platform 101 for convenience of operation.
As shown in fig. 2, in one aspect of the invention, the launch vehicle launch support equivalent further comprises: and a takeoff simulation button 201 which is arranged at the other end of the simulated launching platform 101 and is used for simulating a takeoff signal of the carrier rocket. Specifically, the launch simulation button 201 can be pressed to simulate the launch of the carrier rocket to launch a launch signal supporting the equivalent device, and the equivalent device executes the operation of simulating the quick falling of the vertical arm 104 after receiving the launch signal.
As shown in fig. 2, in one aspect of the invention, launch of a launch vehicle supports equivalent means, further comprising: and one end of the displacement sensor 202 is installed on the bottom surface of the analog launching platform 101, and the other end of the displacement sensor 202 is installed on the movable leg 102, and is used for feeding back the length of the movable leg 102. The displacement sensor 202 is responsible for detecting the displacement of the movable leg 102, which is a product of the actual launching support system. In this embodiment, one end of the displacement sensor 202 is installed on the bottom surface of the analog launching platform 101, and the other end is installed at the leg seat position of each movable leg 102, and in practical application, the displacement sensor 202 can be placed at different positions according to different principles, as long as the movable displacement detection of the movable leg 102 can be realized.
In one aspect of the present invention, the proximity switch analog board 106 is provided with a plurality of mounting holes for securing the proximity switch. In one aspect of the present invention, the proximity switch analog board 106 further includes an output indicator light connected in parallel with the corresponding proximity switch control output signal.
The proximity switch simulation board 106 is used as a mounting bracket of the proximity switch, and can also be used for controlling a mounting bracket of the output indicator light, and meanwhile, corresponding auxiliary equipment is matched for simulating the closing and opening states of the proximity switch, including simulation of proximity switch signals of the vertical arm 102, the upper clamp and the windproof device. All proximity switches can use the same product as the actual emission support system, the control output indicator lamp is connected with the corresponding proximity switch control output signal in parallel, and the state of each proximity switch is reflected through the output indicator lamp.
In order to ensure the authenticity of the equivalent device supported by launch of the carrier rocket and improve the reliability of the test result, for example, all sensors in the equivalent device adopt actual products consistent with an actual carrier rocket launch support system. In the experimental process of the equivalent device, under the condition that some sensors and equipment cannot be in place according to a plan, a button, a signal simulation board card or a PLC module can be used for realizing similar functions. Devices not mentioned in this example are: the device comprises a sensor for data acquisition, analog quantity input and output control and digital quantity input and output control, is well known in the industry, and can be improved and designed on the basis of the invention according to actual use requirements.
In another aspect, the present invention provides an equivalent control system for launch support of a launch vehicle, comprising the equivalent device for launch support of a launch vehicle, and a control device electrically connected to the simulated launch platform 101, the simulated lift arm 104, and the proximity switch simulation board 106, for controlling the actions of the simulated launch platform 101, the simulated lift arm 104, and the proximity switch simulation board 106. The control device belongs to the brain of a carrier rocket launching support equivalent control system, can effectively control the leveling action of the simulated launching platform 101, the erecting action or the fast-falling action of the simulated erecting arm 104 and the opening or closing action of the proximity switch simulation board 106 through a built-in logic program.
After the rocket is transported to a launching station by a rocket transporting and erecting vehicle, the following work is mainly carried out:
1) the vertical vehicle is used for erecting the rocket and putting the rocket down to the launching platform;
2) opening the clamp on the vertical arm;
3) compressing the rocket windproof device;
4) starting to adjust the perpendicularity of the rocket;
5) the rocket windproof device is released;
6) the vertical arm is pre-inclined for a certain angle;
7) and receiving a rocket takeoff signal, and starting to lift the vertical arm to fall quickly.
The carrier rocket launching support equivalent control system mainly achieves the following equivalent functions:
1) simulating the processes of erecting and lowering the erecting arm 104;
2) simulating the upper clamp opening and clasping process of the vertical arm 104;
3) simulating the locking and unlocking process of the windproof device;
4) simulating the leveling of the launching platform 101, namely the rocket perpendicularity adjusting process;
5) simulating the process of pre-falling and pre-falling in place of the vertical arm 104;
6) the process of snapping and snapping the riser arm 104 into place is simulated.
Therefore, the invention provides a launch support equivalent test method of a launch vehicle, which is used for a launch support equivalent control system of the launch vehicle, wherein the control system comprises a simulated launch platform 101, a simulated vertical arm 104, a proximity switch simulation board 106 and a control device, the control device is electrically connected with the simulated launch platform 101, the simulated vertical arm 104 and the proximity switch simulation board 106, and the test method comprises the following steps:
s100: the erecting simulation erecting arm 104 is in a horizontal state to a vertical state, and a first inclination angle sensor 103 arranged on the simulation erecting arm 104 transmits an inclination angle signal of the simulation erecting arm 104 to the control device;
s200: adjusting the levelness of the analog launching platform 101, and transmitting a levelness signal to the control device by a second inclination angle sensor 105 arranged on the analog launching platform 101;
s300: the signal output of the proximity switch on the proximity switch analog board 106 is monitored, and the control device receives different proximity switch signals and sends corresponding instructions.
Specifically, the carrier rocket launching support equivalent test method mainly comprises the steps of simulating the erecting process of the erecting arm 104, simulating the leveling process of the launching platform 101, the opening and holding process of the upper clamp, and the locking and unlocking process of the windproof device.
In the process of erecting the simulated erecting arm 104, the simulated erecting arm 104 is erected from a horizontal state to a vertical state, and the first inclination angle sensor 103 arranged on the simulated erecting arm 104 transmits an inclination angle signal of the simulated erecting arm 104 to the control device. In the leveling process of the analog transmitting platform 101, the levelness of the analog transmitting platform 101 is adjusted, and a second inclination angle sensor 105 arranged on the analog transmitting platform 101 transmits a levelness signal to the control device. The upper clamp opening and clasping process and the windproof device locking and unlocking process are carried out on the proximity switch analog board 106, testing is carried out by detecting the proximity switch signal output of the upper clamp and the windproof device, and the control device receives different proximity switch signals and sends corresponding instructions.
According to one aspect of the invention, the launch vehicle launch support equivalent test method further comprises: when the erecting simulation erecting arm 104 is larger than 91.5 degrees relative to the simulation launching platform 101, the control device sends out an alarm signal and an instruction for closing the simulation erecting arm 104.
According to one aspect of the present invention, adjusting the levelness of the analog launch platform 101 comprises: the length of at least three movable legs 102 supporting the analog launch platform 101 is controlled such that the absolute value of the levelness of the second tilt sensor 105 is between 0 degrees and 0.5 degrees.
In accordance with one aspect of the present invention, monitoring the signal output of the proximity switches on the proximity switch analog board 106 includes: four proximity switches simulating the raising arm 104 on the proximity switch simulation board 106 are monitored, namely a raising to position proximity switch, a leveling back to position proximity switch, a pre-falling to position proximity switch and a fast falling to position proximity switch.
According to one aspect of the present invention, the simulated riser arm 104 is set to a horizontal state, the simulated riser arm 104 is raised and the signal output of the leveling to position proximity switch is monitored when the riser angle is greater than 1 degree, and the signal output of the leveling to position proximity switch is monitored when the riser angle of the simulated riser arm 104 is greater than 89.5 degrees. When the simulated vertical arm 104 is set to be in a horizontal state, the leveling-in-place proximity switch is in a closed state, when the vertical angle of the simulated vertical arm 104 is raised to be greater than 1 degree, the leveling-in-place proximity switch is in an open state, and when the vertical angle of the simulated vertical arm 104 is greater than 89.5 degrees, the vertical-in-place proximity switch is in a closed state.
According to one aspect of the invention, the control system comprises a takeoff simulation button for simulating a takeoff signal of the launch vehicle, and the test method further comprises: the takeoff simulation button is pressed down and a takeoff signal of the carrier rocket is sent out, the control device starts the simulated erecting arm 104 fast-falling instruction after receiving the takeoff signal, and the signal output of the fast-falling approaching switch is monitored. The simulated vertical arm 104 starts from 90 degrees, falls to 87 degrees in advance, the fall to approach switch is closed, after the takeoff signal is received, the simulated vertical arm 104 continues to start from 87 degrees, falls to 75 degrees quickly, and falls to the close switch is closed
In accordance with one aspect of the present invention, monitoring the signal output of the proximity switches on the proximity switch analog board 106 includes: the proximity switches of the two upper clamps on the proximity switch simulation board 106 are monitored, namely the proximity switch with the upper clamp in place opened and the proximity switch with the upper clamp in place clasped.
According to one aspect of the invention, the control device starts an upper clamp unlocking instruction and monitors the signal output of the proximity switch when the upper clamp is unlocked in place; the control device starts an upper clamp clasping instruction and monitors the signal output of the proximity switch for the upper clamp clasping in place. In some cases, the upper clamp is set to two or more open-in-place proximity switches and the upper clamp is set to two or more hug-in-place proximity switches based on structural characteristics of the upper clamp.
In accordance with one aspect of the present invention, monitoring the signal output of the proximity switches on the proximity switch analog board 106 includes: the proximity switches of the two windshields on the proximity switch simulation board 106 are monitored, namely the windshield unlock-in-place proximity switch and the windshield lock-in-place proximity switch.
According to one aspect of the invention, the control device starts a windproof device unlocking instruction and monitors signal output of the proximity switch when the windproof device is unlocked in place; and the control device starts a locking instruction of the windproof device and monitors the signal output of the proximity switch when the windproof device is locked in place. In some cases, two or more of the windproof means unlocking in-place proximity switches are provided and two or more of the windproof means locking in-place proximity switches are provided based on the structural characteristics of the windproof means.
In the invention, the carrier rocket launching support equivalent test method comprises five simulation test processes, and the specific operation process is as follows:
firstly, the process of simulating the erecting of the erecting arm 104 specifically comprises:
s101: simulating the horizontal state of the vertical arm 104, and adjusting the levelness to between 0 degree and plus or minus 0.5 degree according to the inclination angle signal of the first inclination angle sensor;
s102: adjusting the simulated vertical arm 104 to level back to the position to close the proximity switch;
s103: the control device sends a vertical instruction, slowly lifts the simulated vertical arm 104, and monitors the real-time performance and accuracy of the inclination angle signal follow-up of the first inclination angle sensor acquired by the control device;
s104: when the rising vertical angle is larger than 1 degree, if the leveling-in-place proximity switch still displays a closed state, detecting whether the control device gives a fault prompt for simulating the leveling-in-place proximity switch of the rising vertical arm;
s105: monitoring whether the signal output of the leveling in-place proximity switch is normal or not, and monitoring whether the output of the erecting control instruction disappears or not when the erecting in-place signal of the simulated erecting arm 104 is closed;
s106: and (5) continuing to erect the simulation erecting arm 104 until the angle is more than 91.5 degrees, monitoring whether the control device gives alarm information and closing the erecting control instruction.
Secondly, the leveling process of the simulation launching platform 101 specifically comprises the following steps:
s201: manually controlling at least three movable supporting legs 102 to adjust the simulation launching platform 101, so that the display angle of the second tilt angle sensor is between 0 degree and plus or minus 0.5 degree;
s202: the control device sends out a leveling instruction of the simulation launching platform 101, namely a rocket perpendicularity adjusting instruction, and monitors the leveling condition of the simulation launching platform 101;
s203: monitoring whether the action condition of the movable supporting leg 102 of the simulation launching platform 101 is consistent with a control output instruction of the movable supporting leg 102 or not;
s204: whether error prompt is given or not is given after rocket perpendicularity adjustment is not completed within a specified time;
s205: after the perpendicularity adjustment is normally finished, whether the levelness of the simulation launching platform 101, namely the rocket perpendicularity result meets the precision requirement or not is judged.
Thirdly, the opening and holding processes of the upper clamp are as follows:
s301: the upper clamp is opened to the proper position and is close to the closed state of the switch;
s302: the control device sends an upper clamp clasping instruction;
s303: monitoring whether the clamp holding instruction output on the control system is normal or not;
s304: when the upper clamp is tightly held in place and is close to the switch, monitoring whether the output of an upper clamp holding instruction in the control device disappears;
s305: the upper clamp is tightly held in place and is close to the switch position;
s306: the control device sends an upper clamp opening instruction;
s307: monitoring whether the output of a clamp opening instruction on the control device is normal or not;
s308: when the upper clamp is opened in place and is close to the opening and closing of the switch, whether the output of an upper clamp opening instruction in the control device disappears or not is monitored.
Fourthly, the locking and unlocking process of the wind-proof device is specifically as follows:
s401: the wind-proof device is unlocked to the proper position and is close to the closed state of the switch;
s402: the control device sends out a locking instruction of the windproof device;
s403: monitoring whether the locking instruction output of the windproof device of the control device is normal or not;
s404: when the windproof device is locked in place and is close to the switch, monitoring whether the windproof device locking instruction output in the control device disappears;
s405: the wind-proof device is locked in place and approaches to the closed state of the switch;
s406: the control device sends out an unlocking instruction of the windproof device;
s407: monitoring whether the unlocking instruction output of the windproof device in the monitoring device is normal;
s408: when the windproof device is unlocked in place and is close to the opening and closing state, whether the unlocking instruction output of the windproof device in the control device disappears or not is monitored.
Fifthly, receiving a takeoff signal to simulate the fast falling process of the vertical arm 104:
s501: pressing the takeoff simulation button 201;
s502: the control device sends out a command for simulating the quick falling of the vertical arm 104;
s503: monitoring whether a control device outputs a vertical arm rising and falling command or not;
s504: when the takeoff simulation button 201 is pressed, whether a fast-falling instruction of the control device is output or not is monitored;
s505: the response time of the takeoff signal received by the assessment control device is shortened;
s506: fast-reverse start-up control reaction time and fast-reverse process reaction time;
s507: when the fast-fall-to-bit approach switch is closed, whether a fast-fall command disappears in the control device is monitored.
The equivalent device applied in the equivalent test method for the launch support of the carrier rocket adopts the method which is completely consistent with the interface of the actual launch support system equipment of the carrier rocket, ensures that the development of the control system of the actual launch support system of the carrier rocket and the development of the overall equipment are synchronously carried out after the scheme of the actual launch support system of the carrier rocket is preliminarily determined, and can greatly shorten the development period, save the debugging time of the actual launch support system of the carrier rocket and greatly save the development expenditure. The carrier rocket launching support equivalent test method can conveniently finish debugging and comprehensive test of a control subsystem of an actual carrier rocket launching support system, delivery acceptance and system fault separation, and provides guarantee for synchronous development and delivery ahead of schedule of the control system of the actual carrier rocket launching support system.
The present invention is not limited to the above preferred embodiments, and any modifications, equivalent substitutions, improvements, etc. within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. A launch vehicle support equivalence test method is used for a launch vehicle support equivalence control system, the control system comprises a simulated launch platform, a simulated vertical arm, a proximity switch simulation board and a control device, the control device is electrically connected with the simulated launch platform, the simulated vertical arm and the proximity switch simulation board, and the test method comprises the following steps:
erecting the simulated erecting arm from a horizontal state to a vertical state, and transmitting an inclination angle signal of the simulated erecting arm to the control device by a first inclination angle sensor arranged on the simulated erecting arm;
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;
and monitoring the signal output of the proximity switch on the proximity switch simulation board, and the control device receives different proximity switch signals and sends corresponding instructions.
2. The launch vehicle launch support equivalence test method of claim 1, wherein said adjusting a levelness of said simulated launch platform comprises:
controlling the length of at least three movable legs supporting the analog launching platform so that the absolute value of the levelness of the second tilt sensor is between 0 and 0.5 degrees.
3. The launch vehicle launch support equivalence test method of claim 1, further comprising:
and when the simulated vertical arm is erected for more than 91.5 degrees relative to the simulated launching platform, the control device sends out an alarm signal and an instruction for closing the simulated vertical arm.
4. The launch vehicle launch support equivalent test method of claim 1, wherein said monitoring signal output of a proximity switch on said proximity switch analog board comprises:
and monitoring four proximity switches simulating the vertical arms on the proximity switch simulation board, namely a vertical-to-position proximity switch, a leveling-back-to-position proximity switch, a pre-reverse-to-position proximity switch and a fast reverse-to-position proximity switch.
5. The launch vehicle support equivalence test method of claim 4, wherein the simulated lift arm is set to a horizontal position, wherein raising the simulated lift arm monitors the signal output of the leveling-in-place proximity switch when the lift angle is greater than 1 degree, and monitors the signal output of the leveling-in-place proximity switch when the lift angle of the simulated lift arm is greater than 89.5 degrees.
6. The launch vehicle launch support equivalent test method of claim 4, wherein the control system includes a takeoff simulation button for simulating a takeoff signal of the launch vehicle, the test method further comprising:
and pressing a takeoff simulation button and sending a takeoff signal of the carrier rocket, starting the simulated vertical arm fast-falling instruction after the control device receives the takeoff signal, and monitoring the signal output of the fast-falling-to-position approach switch.
7. The launch vehicle launch support equivalent test method of claim 1, wherein said monitoring signal output of a proximity switch on said proximity switch analog board comprises:
and monitoring the proximity switches of the two upper clamps on the proximity switch simulation board, namely the proximity switch with the upper clamp opened in place and the proximity switch with the upper clamp clasped in place.
8. The launch vehicle support equivalence test method of claim 7, wherein the control device initiates an upper clamp unlock command, monitoring a signal output of a proximity switch to which the upper clamp is unlocked; and the control device starts an upper clamp clasping instruction and monitors the signal output of the proximity switch in which the upper clamp clasps in place.
9. The launch vehicle launch support equivalent test method of claim 1, wherein said monitoring signal output of a proximity switch on said proximity switch analog board comprises:
and monitoring the proximity switches of the two windproof devices on the proximity switch simulation board, namely the windproof device unlocking in-place proximity switch and the windproof device locking in-place proximity switch.
10. The launch vehicle support equivalence test method of claim 9, wherein the control device initiates a windshield unlock command, monitors signal output of a proximity switch in which the windshield is unlocked in place; and the control device starts a windproof device locking instruction and monitors the signal output of the windproof device locking in place proximity switch.
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| WO2021228155A1 (en) * | 2020-05-13 | 2021-11-18 | 蓝箭航天空间科技股份有限公司 | Carrier rocket launching support equivalent device and control system |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7082379B1 (en) * | 2002-03-08 | 2006-07-25 | Intellectual Assets Llc | Surveillance system and method having an adaptive sequential probability fault detection test |
| CN108562188A (en) * | 2018-03-20 | 2018-09-21 | 西安航天动力技术研究所 | Sounding rocket emitter high-precision control system |
| CN109896049A (en) * | 2018-11-22 | 2019-06-18 | 北京航天发射技术研究所 | A kind of rectangular co-ordinate flexible non-contact formula connector automatic butt jointing device and method |
| CN110595279A (en) * | 2019-08-08 | 2019-12-20 | 蓝箭航天技术有限公司 | Perpendicularity adjusting method for liquid rocket |
| CN111023899A (en) * | 2019-11-05 | 2020-04-17 | 蓝箭航天空间科技股份有限公司 | Rocket transferring and erecting system |
| CN111103902A (en) * | 2020-01-02 | 2020-05-05 | 蓝箭航天空间科技股份有限公司 | Leveling control system and method for rocket launching platform |
-
2020
- 2020-05-13 CN CN202010400458.1A patent/CN111665817B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7082379B1 (en) * | 2002-03-08 | 2006-07-25 | Intellectual Assets Llc | Surveillance system and method having an adaptive sequential probability fault detection test |
| CN108562188A (en) * | 2018-03-20 | 2018-09-21 | 西安航天动力技术研究所 | Sounding rocket emitter high-precision control system |
| CN109896049A (en) * | 2018-11-22 | 2019-06-18 | 北京航天发射技术研究所 | A kind of rectangular co-ordinate flexible non-contact formula connector automatic butt jointing device and method |
| CN110595279A (en) * | 2019-08-08 | 2019-12-20 | 蓝箭航天技术有限公司 | Perpendicularity adjusting method for liquid rocket |
| CN111023899A (en) * | 2019-11-05 | 2020-04-17 | 蓝箭航天空间科技股份有限公司 | Rocket transferring and erecting system |
| CN111103902A (en) * | 2020-01-02 | 2020-05-05 | 蓝箭航天空间科技股份有限公司 | Leveling control system and method for rocket launching platform |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2021228155A1 (en) * | 2020-05-13 | 2021-11-18 | 蓝箭航天空间科技股份有限公司 | Carrier rocket launching support equivalent device and control system |
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