CN118009803A - Ground testing, launching and controlling system of rocket - Google Patents

Abstract

The application discloses a ground test launch control system of a rocket, which relates to the field of test control systems, and comprises: the detection, launch and control front end component is connected with the target arrow body, and is used for supplying power to the target arrow body and directly carrying out interactive operation of instructions and data with the target arrow body; the system comprises an overall network component, a control module and a control module, wherein the overall network component comprises an overall network front end and an overall network back end, the overall network front end and the overall network back end form a ring network, and the control module is connected with the overall network component; the monitoring, launching and controlling back-end component is connected with the overall network back-end and is used for receiving data of a target rocket body and issuing a remote instruction.

Description

Ground testing, launching and controlling system of rocket

Technical Field

The present disclosure relates to the field of test control systems, and more particularly, to a ground launch control system for a rocket.

Background

The ground test launch control system is one of important systems of the rocket, and can realize functions of power supply and distribution, state control, parameter monitoring and the like in the ground test and launching processes of the rocket. With the rapid development of commercial aerospace, users increasingly demand miniaturized, low-cost and highly reliable ground detection and control systems. However, the current ground test initiation control system can not meet the requirements of miniaturization, low cost and high reliability.

Disclosure of Invention

In the summary, a series of concepts in a simplified form are introduced, which will be further described in detail in the detailed description. The summary of the application is not intended to define the key features and essential features of the claimed subject matter, nor is it intended to be used as an aid in determining the scope of the claimed subject matter.

In a first aspect, the present application provides a ground testing launch control system for a rocket, including:

The detection, launch and control front end component is connected with the target arrow body, and is used for supplying power to the target arrow body and directly carrying out interactive operation of instructions and data with the target arrow body;

A global network component, wherein the global network component comprises a global network front end and a global network back end, the global network front end and the global network back end form a ring network, and the test initiation control front end component is connected with the global network component;

and the testing, launching and controlling back-end component is connected with the overall network back-end, and is used for receiving the data of the target arrow body and issuing a remote instruction.

In a possible embodiment, the overall network front end includes a plurality of front end switches, the overall network back end includes a plurality of back end switches, all of the front end switches are connected into a first stack unit by a stack module and a stack cable, and all of the back end switches are connected into a second stack unit by a stack module and a stack cable.

In one possible embodiment, the front-end switch and the back-end switch transmit data over dual redundant optical fibers.

In a possible implementation manner, the detecting, initiating and controlling front-end component includes a programmable power supply combination portion, the programmable power supply combination portion includes a servo power supply and three control power supplies, the first control power supply provides electric energy for a core control system of the target rocket body, the second control power supply provides electric energy for a power adjusting component of the target rocket body, the third control power supply provides electric energy for a backup power supply, and the servo power supply provides electric energy for an engine of the target rocket body.

In a possible implementation manner, the measurement and control front end component comprises a measurement and control combination part, the measurement and control combination part comprises a bus communication device, a measurement and control computer and a relay, the relay is connected with the measurement and control computer, the bus communication device is connected with the measurement and control computer, and the bus communication device is used for receiving and sending CAN messages to realize communication interaction with a target arrow body.

In a possible embodiment, the bus communication device, the measurement and control computer and the relay are of redundant design.

In a possible implementation manner, the rocket ground test launch control system further comprises a power test control front end component, wherein the power test control front end component is connected with the test launch control front end component, and the power test control front end component is used for generating and issuing test and control instructions of the power system.

In a possible implementation manner, the rocket ground measurement and launch control system further comprises a power measurement and control rear end assembly, wherein the power measurement and control front end assembly and the power measurement and control rear end assembly are connected with the overall network rear end, and the power measurement and control rear end assembly is used for remotely controlling the power system.

In one possible implementation manner, the rocket ground measurement and launch control system further comprises a power measurement and control rear end assembly and a measurement front end assembly, wherein the measurement front end assembly is connected with the front end of the overall network, the measurement rear end assembly is connected with the rear end of the overall network, the measurement front end assembly is used for remote measurement and remote control in the process of testing and launching, and the measurement rear end assembly is used for remote control.

In one possible implementation, the test initiation control backend component includes a plurality of host computers.

In summary, the ground testing launch control system of the rocket according to the embodiment of the application comprises: the detection, launch and control front end component is connected with the target arrow body, and is used for supplying power to the target arrow body and directly carrying out interactive operation of instructions and data with the target arrow body; a global network component, wherein the global network component comprises a global network front end and a global network back end, the global network front end and the global network back end form a ring network, and the test initiation control front end component is connected with the global network component; and the testing, launching and controlling back-end component is connected with the overall network back-end, and is used for receiving the data of the target arrow body and issuing a remote instruction. According to the ground testing launch control system of the rocket, provided by the embodiment of the application, through the design of the annular network, even if part of the network has problems, the system can still operate, so that the risk of failure in launching is reduced. The front end component for testing, launching and controlling is directly connected with the rocket body, and the data and control instructions can be transmitted quickly and safely through the design of the overall network. This configuration of the system allows the operator to monitor the arrow body status in real time and to control it in real time, which is critical to address any emergency situations that may occur during the firing process. The design of the rocket ground test launch control system improves the success rate of launching tasks and ensures the safety and efficiency in the task execution process through the structural components and the network design. And by selecting mature goods shelf products and combining design measures such as key equipment redundancy, bus network redundancy, cable network important signal redundancy and the like, the remote communication of the overall network based on a front-end mechanism and a back-end mechanism is adopted, so that the rocket detecting and launching control system with low cost, high reliability, long distance and universality is provided.

Additional advantages, objects, and features of the application will be set forth in part in the description which follows and in part will become apparent to those having ordinary skill in the art upon examination of the following or may be learned from practice of the application.

Drawings

Various other advantages and benefits will become apparent to those of ordinary skill in the art upon reading the following detailed description of the preferred embodiments. The drawings are only for purposes of illustrating the preferred embodiments and are not to be construed as limiting the specification. Also, like reference numerals are used to designate like parts throughout the figures. In the drawings:

FIG. 1 is a schematic structural diagram of a ground test launch control system for a rocket according to an embodiment of the present application;

FIG. 2 is a schematic structural diagram of another rocket ground survey launch control system according to an embodiment of the present application;

FIG. 3 is a schematic diagram of a network component according to an embodiment of the present application;

The correspondence between the reference numerals and the component names in fig. 1to 3 is:

a ground test launch control system of the 100 rocket; 101, testing an initiating and controlling front-end component; 102 overall network components; 1021 overall network front end; 1022 overall network backend; 103 testing the launch control backend component.

Detailed Description

The terms "first," "second," "third," "fourth" and the like in the description and in the claims and in the above drawings, if any, are used for distinguishing between similar objects and not necessarily for describing a particular sequential or chronological order. It is to be understood that the data so used may be interchanged where appropriate such that the embodiments described herein may be implemented in other sequences than those illustrated or otherwise described herein. Furthermore, the terms "comprises," "comprising," and "having," and any variations thereof, are intended to cover a non-exclusive inclusion, such that a process, method, system, article, or apparatus that comprises a list of steps or elements is not necessarily limited to those steps or elements expressly listed but may include other steps or elements not expressly listed or inherent to such process, method, article, or apparatus. The following description of the embodiments of the present application will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present application, but not all embodiments.

Referring to fig. 1, a schematic structural diagram of a ground testing launch control system 100 of a rocket according to an embodiment of the present application may specifically include:

The detection and control front end component 101, the detection and control front end component 101 is connected with a target arrow body, the detection and control front end component 101 is used for supplying power to the target arrow body and directly carrying out interaction operation of instructions and data with the target arrow body;

A global network component 102, wherein the global network component 102 comprises a global network front end 1021 and a global network back end 1022, the global network front end 1021 and the global network back end 1022 form a ring network, and the measurement and control front end component 101 is connected to the global network component 102;

And the testing, launching and controlling back-end component 103, wherein the testing, launching and controlling back-end component 103 is connected with the overall network back-end 1022, and the testing, launching and controlling back-end component 103 is used for receiving the data of the target arrow body and issuing a remote instruction.

The ground detection and initiation control (measurement, emission and control) system provided by the embodiment of the application is composed of three main parts: a test initiation front end component 101, an overall network component 102, and a test initiation back end component 103.

The front end module 101 is the front end of the system and is directly connected to the target arrow. The power supply is mainly used for supplying power to the arrow body and directly carrying out instruction and data interaction with the arrow body. And allows real-time monitoring and control of the arrow body state, providing accurate support for the firing of the arrow body. The power supply function ensures the normal working state of the arrow body in the ground waiting period, and the direct interaction of the instruction and the data ensures that all preparation works before the transmission can be completed accurately.

The overall network component 102 includes front-end and back-end of the overall network, which together form a ring network. The ring network enhances the stability and reliability of the system, and if a part of the network fails, data transmission can be performed through the other side of the ring network, so that the continuous working capacity of the system is ensured. In addition, the test initiation front end component 101 is connected to other parts of the system through this overall network, making the transmission of data and control instructions more efficient and secure.

The test initiation back-end component 103 is located at the back-end of the system, connecting to the back-end of the overall network. The main function of this component is to receive data from the target arrow and issue remote instructions as required. The test initiation control back-end component 103 is responsible for processing all data sent back from the arrow body, such as various parameters and status information during the firing process, and sending control instructions to the arrow body when necessary, so as to ensure the success of the firing and the safety of the arrow body

The system can be used for selecting general goods shelf products, adopting a front-end and rear-end distributed system architecture, constructing an overall network by using an Ethernet technology, and performing real-time interaction with a measurement system and a power measurement and control system through the overall network. The front-end equipment is directly connected with the rocket, and the rear-end equipment is used as a control command center for conducting command control on the front-end equipment. During launching, the rocket can be remotely launched and controlled in real time outside the safe distance.

In summary, the ground testing launch control system of the rocket provided by the embodiment of the application is designed through the annular network, and even if part of the network has problems, the system can still operate, so that the risk of failure in launching is reduced. The front end component for testing, launching and controlling is directly connected with the rocket body, and the data and control instructions can be transmitted quickly and safely through the design of the overall network. This configuration of the system allows the operator to monitor the arrow body status in real time and to control it in real time, which is critical to address any emergency situations that may occur during the firing process. The design of the rocket ground test launch control system improves the success rate of launching tasks and ensures the safety and efficiency in the task execution process through the structural components and the network design. And by selecting mature goods shelf products and combining design measures such as key equipment redundancy, bus network redundancy, cable network important signal redundancy and the like, the remote communication of the overall network based on a front-end mechanism and a back-end mechanism is adopted, so that the rocket detecting and launching control system with low cost, high reliability, long distance and universality is provided.

In some examples, the overall network front end includes a plurality of front end switches, the overall network back end includes a plurality of back end switches, all of the front end switches are connected into a first stacked unit by a stacked module and a stacked cable, and all of the back end switches are connected into a second stacked unit by a stacked module and a stacked cable.

Illustratively, a plurality of head-end switches are connected by a particular stack module and stack cable to form a logically first stack unit. This means that these physically independent switches can be managed and configured as a single switch through the same stacking technique, with the backend switches also connected as a second stacking unit, achieving a logical singulation like the front-end stack.

Stacking multiple switches into a single logical unit greatly simplifies the complexity of network management. The network administrator can configure and monitor the entire stack unit through a single interface without having to operate each switch separately. Stacking techniques may also increase the reliability of the network. In a stacked configuration, failure of a single device does not result in failure of the entire system. Through proper configuration, the fault transfer and the load balancing can be realized, and the stability and the usability of the whole network are improved.

With the illustration of fig. 3, the front end and the back end of the overall network both adopt two switches, and the two front end (back end) switches adopt a special stacking module and stacking cables to form a stacking unit, so that the port density is increased, and meanwhile, the bandwidth of the overall network is also greatly improved. After stacking, one exchanger can perform unified configuration and management on the other exchanger. In the mode of using a high-speed port, the same port transmits and receives data to and from the uplink and downlink respectively, and finally an annular structure is formed, so that redundancy is realized to a certain extent.

In some examples, the front-end switch and the back-end switch transmit data over dual redundant optical fibers.

The front-end switch and the back-end switch are transmitted by dual redundancy optical fibers, each single-machine node on the front-end network and each single-machine node on the back-end network are interconnected through dual redundancy channels, after any switch fails, the overall network can isolate the failed switch, the reconstructed overall network can still ensure normal communication among each single-machine node, and the communication reliability of the test initiation control system is improved. Meanwhile, the instrument and the equipment with the standard Ethernet interface can be connected to the overall network, so that information interconnection is realized.

In summary, the ground test launch control system of the rocket provided by the embodiment of the application provides a network with simplified management experience, high reliability, excellent performance and expansibility and good interconnection and compatibility through a stacking technology and double redundant optical fiber transmission. The characteristics enable the network to adapt to the requirements of rapid change, meanwhile, the high-efficiency and stable operation is kept, and the stability of the ground test launch control system of the rocket is improved.

In some examples, the test initiation control front end component includes a programmable power supply assembly, where the programmable power supply assembly includes a servo power supply and three control power supplies, the first control power supply provides power for a core control system of the target arrow body, the second control power supply provides power for a power adjustment component of the target arrow body, the third control power supply provides power for a backup power supply, and the servo power supply provides power for an engine of the target arrow body.

Illustratively, the servo power supply is dedicated to providing power to the engine of the target arrow. The servo power supply can provide high-precision and controllable power output to ensure that the engine control system can accurately regulate the operation of the engine. The core control system of the first control power supply target arrow body provides electric energy. The core control system may include critical functions such as flight control, navigation, communication, and data processing, and the stable power supply of these systems is the basis for ensuring that the arrow body flies along a predetermined path. The second control power supply provides electric energy for the power adjusting component of the target rocket body. The power conditioning assembly includes a propellant supply, engine thrust adjustment, etc., which require precise control to achieve speed and direction adjustment during flight. The third control power supply serves as a backup power supply. In critical task execution, a failure at any single point may result in the failure of the entire task. Thus, the backup power supply is provided to ensure that critical parts of the system continue to operate in the event of a problem with the primary power supply.

As shown in fig. 2, the dc power supplies 1-3 are 28V power supplies, and can provide control power for each single machine of the on-arrow control system, wherein the dc power supply 1, i.e. the first control power supply load, comprises a central computer, an optical fiber inertial measurement unit, a comprehensive controller, an engine servo system, a lithium battery and the like, the dc power supply 2, i.e. the second control power supply on-arrow load, comprises a regulating valve servo system, a power system electromagnetic valve and the like, and the dc power supply 3, i.e. the third control power supply, is used as a backup power supply. The detection and initiation control system can monitor the working state of the direct current power supply, and if the working state is abnormal, the direct current power supply is switched to the standby power supply, so that the continuous and reliable power supply of 28V on an arrow is ensured. The 160V power supply provides electric energy for the servo power supply to the engine of the target rocket body.

In summary, the ground test launch control system of the rocket provided by the embodiment of the application can be optimally designed according to respective electric energy requirements and characteristics by configuring special power supplies for different systems and components, so that the safety and reliability of the whole system are improved. In particular, the servo power supply provides stable and controllable power to the engine, which is critical to maintaining stable operation of the aircraft engine. The third control power supply is used as a backup power supply, so that the continuous working capacity of the system in the face of unpredictable conditions is improved, and the success rate of task execution is increased. By careful division and special configuration of the power supply, the energy can be managed more effectively, ensuring that each system or component can obtain the required electrical energy at the appropriate time, thereby optimizing the overall energy use efficiency.

In some examples, the measurement and control front-end component includes a measurement and control combination portion, where the measurement and control combination portion includes a bus communication device, a measurement and control computer, and a relay, where the relay is connected to the measurement and control computer, where the bus communication device is connected to the measurement and control computer, and where the bus communication device is configured to send and receive CAN messages to implement communication interaction with a target rocket body.

Illustratively, the bus communication device is the core of the communication and is responsible for transceiving CAN (Controller Area Network) messages. The CAN bus is a high-reliability network protocol, and the bus communication equipment performs communication interaction with the target arrow body through CAN messages, transmits instructions and receives state information of the arrow body. The measurement and control computer is the brain of the combination part and is responsible for processing all measurement and control tasks. The method receives data from the target arrow body, analyzes the data by running a preset software program, and sends a control command back to the target arrow body according to the requirement. The measurement and control computer is also responsible for coordinating the operation of the bus communication device and the relay. The relay serves as an interface here to connect the supervisory computer to other systems or circuits that may need to be controlled. The circuit can be opened or closed according to the instruction of the measurement and control computer so as to control other devices. The relay is mainly matched with a measurement and control computer to realize the functions of analog quantity/digital quantity acquisition and switching value output, complete power failure on an rocket, control instruction transmission, various data acquisition and the like, receive the control instruction of a rear-end main control computer through an overall network and jointly complete the testing and control tasks of the rocket. By configuring two relays and adopting a hot backup mechanism, the correct and reliable transmission of control instructions and collected data between the arrow and the ground is ensured.

According to the scheme provided by the embodiment of the application, the CAN bus communication equipment is used, so that efficient and reliable communication with the target arrow body CAN be realized. The use of the CAN bus ensures stability and immunity to data transmission. The measurement and control computer is used as a central node and can intensively process all data and control logic. This centralized control architecture simplifies the complexity of the system and improves the efficiency of processing data and making decisions. Through the relay, the measurement and control computer can flexibly control other devices or systems. The control mode can be used for executing simple on/off tasks and can also be used for more complex control logic, so that the flexibility and the expandability of the system are improved.

In some examples, the bus communication device, the measurement and control computer, and the relay are of redundant design.

By way of example, by employing a redundant design, the bus communication device, the test control computer, and the relay all have backup systems or components to ensure seamless switching in the event of failure of the primary system or component, thereby maintaining continuous operation of the system and successful completion of tasks.

Specifically, the main control computer and the measurement and control computer are used as the most important control equipment of the measurement, control and control system, the measurement, control and control main control software and the measurement, control and control software are respectively operated, 2 computers are respectively configured, and when the main computer fails, the main computer is immediately switched to the backup computer, so that the controllability of the whole test and emission process is ensured.

Overall network communication redundancy: 4 switches are selected, and the two switches comprise 2 front-end switches and 2 back-end switches, and meanwhile, double-redundancy optical fiber channels are adopted for communication between the front-end switches and the back-end switches, so that the reliability of overall network communication is greatly improved.

Cable network important signal redundancy: important signals such as power supply, power distribution and interruption control, time sequence control signals and the like all take the form of double-point double-line so as to ensure the accuracy and reliability of important signal transmission.

Bus topology redundancy: and a bus architecture with two buses which are mutually backup is adopted, namely a control CAN bus and a test CAN bus. The two buses are identical in physical lines and circuit interfaces, with only a small amount of information flow differing. The control bus mainly transmits control information, the data volume is smaller, the test bus is used as a backup of the control bus, and besides the control information, all measurement information and telemetry information are transmitted, and the data volume is larger.

Under the condition that the bus communication equipment, the measurement and control computer and the relay all adopt redundant designs, the faults of any single equipment can be processed by automatically switching to the backup equipment, and the normal operation of the system is hardly affected. The redundant design allows the system to continue to operate without downtime when a component of the system requires maintenance or replacement, which greatly improves the maintainability and usability of the system.

In some examples, the rocket ground test launch control system further comprises a power test control front end assembly, wherein the power test control front end assembly is connected with the test launch control front end assembly, and the power test control front end assembly is used for power system test and control instruction generation and launch operation.

Illustratively, the power measurement and control front end assembly is dedicated to testing and control of the power system. The test system is connected with a test launch control front end component, is mainly used for testing a power system, and is used for executing test operation on a rocket power system such as an engine, so that the power system can reach a preset performance standard before being launched. And the system is also responsible for generating and issuing control instructions, generating corresponding control instructions according to test results and emission requirements, and issuing the control instructions to a power system so as to adjust or optimize the performance of the power system. The assembly ensures that the power system of the rocket is subjected to strict test before being launched, and can receive real-time control instructions to adjust the state, thereby ensuring the success of the launching task.

In some examples, the rocket ground test launch control system further comprises a power test control rear end assembly, wherein the power test control front end assembly and the power test control rear end assembly are connected with the overall network rear end, and the power test control rear end assembly is used for remotely controlling the power system.

The power measurement and control rear end component is also an annular ring of the rocket ground measurement and control system, and is connected with the power measurement and control front end component and the overall network rear end. The main function of the rocket power system is remote control, and the remote control capability of the rocket power system is provided. This means that an operator can send a control command from the ground control center to the power system through the power measurement and control back-end assembly to perform operations such as starting, adjustment or closing. The introduction of the power measurement and control rear end component enhances the control capability of the rocket power system in the preparation stage and the launching process, and improves the flexibility and the safety of launching tasks.

In some examples, the rocket ground survey launch control system further comprises a power measurement and control rear end assembly and a measurement rear end assembly, wherein the measurement front end assembly is connected with the overall network front end, the measurement rear end assembly is connected with the overall network rear end, the measurement front end assembly is used for remote measurement and remote control operation in the process of testing and launching, and the measurement rear end assembly is used for remote control.

Illustratively, the measurement front-end assembly is responsible for collecting telemetry data of the rocket, such as position, velocity, temperature, etc., and performing remote operations during testing and launching. These data are critical to monitoring rocket state and performance. The measurement back-end assembly is used for remote control. The remote control system receives instructions from a control center and forwards the instructions to the rocket through a general network, so that remote control operation of the rocket is realized.

The two components work together, so that the real-time data collection and remote control capability in the rocket launching process are ensured, and the method has important significance for ensuring the safety and the success of rocket launching. By the mode, the rocket can be comprehensively monitored and controlled, so that the success rate and the safety of a launching task are improved.

In some examples, the test initiation back-end component includes a plurality of host computers.

Illustratively, the back-end component includes a plurality of host computers designed to increase the processing power, reliability and redundancy of the overall system. This design allows the system to perform tasks in a distributed manner while providing a failed backup. The introduction of multiple host computers in a critical system can provide immediate failback. If one computer fails, the other computer can immediately take over its tasks, ensuring continuous operation of the system.

The above embodiments are only for illustrating the technical solution of the present application, and are not limiting; although the application has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical scheme described in the foregoing embodiments can be modified or some technical features thereof can be replaced by equivalents; such modifications and substitutions do not depart from the spirit and scope of the technical solutions of the embodiments of the present application.

Claims (10)

1. A ground testing launch control system of a rocket, comprising:

The detection, launch and control front end component is connected with the target arrow body, and is used for supplying power to the target arrow body and directly carrying out interactive operation of instructions and data with the target arrow body;

The system comprises an overall network component, a control module and a control module, wherein the overall network component comprises an overall network front end and an overall network back end, the overall network front end and the overall network back end form a ring network, and the control module is connected with the overall network component;

The monitoring, launching and controlling back-end component is connected with the overall network back-end and is used for receiving data of a target rocket body and issuing a remote instruction.

2. A rocket ground survey launch control system according to claim 1 wherein said overall network front end comprises a plurality of front end switches and said overall network back end comprises a plurality of back end switches, all of said front end switches being connected by stacking modules and stacking cables into a first stacking unit and all of said back end switches being connected by stacking modules and stacking cables into a second stacking unit.

3. A rocket ground survey launch control system according to claim 1 wherein said front-end switches and said back-end switches transmit data via dual redundant optical fibers.

4. The rocket ground test launch control system according to claim 1, wherein said test launch control front end assembly comprises a programmable power supply assembly comprising a servo power supply and three control power supplies, a first control power supply providing power to a core control system of said target rocket body, a second control power supply providing power to a power regulating assembly of said target rocket body, a third control power supply providing power to a backup power supply, said servo power supply providing power to an engine of said target rocket body.

5. The rocket ground test initiation control system according to claim 1, wherein the test initiation control front end assembly comprises a test initiation control combination part, the test initiation control combination part comprises a bus communication device, a test initiation control computer and a relay, the relay is connected with the test initiation control computer, the bus communication device is connected with the test initiation control computer, and the bus communication device is used for receiving and transmitting CAN messages to realize communication interaction with a target rocket body.

6. A rocket ground survey and launch control system according to claim 1 wherein said bus communication equipment, said survey and control computer and said relays are of redundant design.

7. A rocket ground survey and control system according to claim 1, further comprising a power measurement and control front end assembly, wherein the power measurement and control front end assembly is connected with the survey and control front end assembly, and the power measurement and control front end assembly is used for power system testing and control instruction generation and issuing operations.

8. A rocket ground survey launch control system according to claim 1 and further comprising a power measurement and control rear end assembly, said power measurement and control front and rear end assembly being connected to said overall network rear end, said power measurement and control rear end assembly being for remote control of a power system.

9. A rocket ground survey launch control system according to claim 1 and further comprising a survey front end assembly and a survey back end assembly, said survey front end assembly being connected to said general network front end and said survey back end assembly being connected to said general network back end, said survey front end assembly being for telemetry and remote control during testing, launching, said survey back end assembly being for remote control.

10. A rocket ground survey and launch control system according to claim 1 wherein said survey and launch control backend assembly comprises a plurality of master computers.