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An air-to-surface missile control full-process simulation system and method

A simulation system and whole process technology, applied in the field of air-to-surface missile control whole process simulation system, can solve the problems of many test items, low fidelity, split control system electrical and algorithm integrity, etc. High degree of performance, the effect of solving the problem of delivery security

Active Publication Date: 2019-02-19
THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The independent development of the above-mentioned tests split the integrity of the electrical and algorithmic control system, and the integrity of the two stages of air-to-surface guided missile flight and autonomous flight, resulting in many problems such as many test items, poor flexibility, and low degree of realism.

Method used

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  • An air-to-surface missile control full-process simulation system and method
  • An air-to-surface missile control full-process simulation system and method
  • An air-to-surface missile control full-process simulation system and method

Examples

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Embodiment 1

[0040] see figure 1 As shown, the embodiment of the present invention provides a full-process simulation system for air-to-surface missile control, including a carrier simulator 1, a high-speed real-time simulation computer 2, an integrated controller 3, a missile-borne computer 4, a steering gear 5, and a power supply 6.

[0041] Said aircraft simulator 1 simulates the stage of flying with air-to-surface missiles, generates aircraft navigation information and instructions, and connects to the 1553B bus as a BC node of the 1553B bus;

[0042] The high-speed real-time simulation computer 2 simulates the navigation information of the two stages of air-to-surface missile guided flight and autonomous flight, and receives the steering gear 5 angle feedback and sends the number of pulses through the CAN bus;

[0043] The integrated controller 3 receives all 1553B bus messages and CAN bus messages, completes the conversion of the two protocol messages, and controls the flow of messag...

Embodiment 2

[0052] On the basis of embodiment 1, see figure 2 As shown, the present invention provides an air-to-surface missile control full-flow simulation method, comprising the following steps:

[0053] Step 1, start the carrier simulator 1, start the high-speed real-time simulation computer 2, power on the power supply 6, the carrier simulator 1 sends a power-on command for the launch system, the air-to-surface missile launch system powers on and self-checks, and feedbacks the description of the hanging object Information, self-test results;

[0054] Step 2: Aircraft Simulator 1 generates and binds task data, selects the generation method of navigation information for the flight stage of the airborne missile and air-to-surface missile: the trajectory generator generates or plays back the historical flight data, and the missile-borne computer 4 feeds back the task binding results, Reference attached image 3 ;

[0055] In step 3, the aircraft simulator 1 sends the aircraft navigat...

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Abstract

The invention discloses an air-to-surface missile control full-flow simulation system, which relates to the technical field of ballistic missile simulation. The air-to-surface missile control full-flow simulation system of the invention comprises a carrier simulator, a high-speed real-time simulation computer, a missile-borne computer, an integrated controller, a steering gear and a power supply.The communication network is established between various parts through CAN bus and 1553B bus. The carrier simulator simulates the real carrier, controls the launching process, sends the carrier navigation information and monitors the flight data. The high-speed real-time simulation computer simulates air-to-surface missile inertial unit, and gives air-to-surface missile navigation information; themissile-borne computer uses aircraft navigation information and air-to-surface missile navigation information to complete the closed-loop solution of navigation and guidance law. The invention realizes the complete verification of the whole work flow, the whole logic chain, the whole data stream and the whole algorithm domain of the air-to-surface missile. The invention also discloses an air-to-surface missile control whole process simulation method, wherein the trajectory generation is closer to the flight process, and the simulation test is more reliable.

Description

technical field [0001] The invention relates to the technical field of ballistic missile simulation, in particular to an air-to-surface missile control full-flow simulation system and method. Background technique [0002] Different from ballistic missiles launched from a static state on the ground, air-to-surface missiles use the aircraft inertial group information and missile inertial group information to perform dynamic base alignment and transition navigation calculations during the flight phase of the carrier aircraft. According to the alignment and navigation calculations As a result, timing and logic judgments are made on whether the alignment is good, whether the off-beam conditions are met, and whether ignition is allowed; after receiving the carrier aircraft off-beam 0s, the shift procedure is implemented, and the launch coordinate system is established according to the current launch point position and target point position information. Complete the online trajecto...

Claims

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Application Information

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IPC IPC(8): G06F17/50
CPCG06F30/20
Inventor 黄鑫鑫张力杨登峰蒋金龙罗伟叶昌朱正辉贾昆杨利兰王永圣
Owner THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD
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