Inertial navigation-based fast response rocket delivery system and delivery method

An inertial navigation and fast response technology, applied in surveying and navigation, general control systems, control/regulation systems, etc., can solve the problems of crashes, non-professionals are not allowed, and the cost of a single machine is high, so as to improve the carrying capacity, Improved reconnaissance ability and shorter response time

Active Publication Date: 2018-02-09
HARBIN INST OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0007] But drone reconnaissance also has certain limitations:
[0009] 2) Short battery life: Because the UAV consumes a lot of power, especially when it is loaded, the power consumption is faster, and the UAV generally cannot carry too large a battery, so the battery life is short
[0010] 3) The cost of a stand-alone machine is relatively high: if it loses control midway, a mechanical failure occurs, or the power is exhausted, a crash may occur, causing large economic losses, and may also cause damage to people or equipment on the ground
[0011] 4) Operators are required to have a high level of operation

Method used

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  • Inertial navigation-based fast response rocket delivery system and delivery method
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  • Inertial navigation-based fast response rocket delivery system and delivery method

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specific Embodiment approach 1

[0061] Specific implementation manner one: such as figure 1 As shown, a fast response rocket launch system based on inertial navigation includes: nose cone 1, cargo compartment 2, propulsion compartment 3 and all-terrain crawler 24;

[0062] Such as figure 2 As shown, the load compartment 2 is arranged between the nose cone 1 and the propulsion compartment 3. In the load compartment 2 are arranged in sequence the ejection plate 4, the middle end plate 10 and the lower end plate 20 of the load compartment and the upper end plate 21 of the propulsion compartment. The carrier plate 34 is provided with separating holes 32 at the center positions of the lower end plate 20 of the load compartment and the upper end plate 21 of the propulsion compartment respectively, and the connecting rod 17 passes through the two separating holes 32;

[0063] One end of the connecting rod 17 located in the loading compartment 2 is connected to the cross steering wheel 16, and one end of the connecting ...

specific Embodiment approach 2

[0142] Specific embodiment two: this embodiment is different from specific embodiment one in that: the laminate slide rail 9 is in a concave shape, and the fixing strip 25 is embedded in the groove groove of the laminate slide rail 9 along the laminate slide rail 9 slide.

[0143] The laminate slide rail 9 is in a concave shape, and a second basswood laminate and a third basswood laminate are arranged on the first basswood laminate. The second basswood laminate and the third basswood laminate are parallel to each other and Perpendicular to the first linden wood laminate;

[0144] The track width of the layer slide rail 9 is greater than the width of the fixing bar 25.

[0145] Other steps and parameters are the same as in the first embodiment.

specific Embodiment approach 3

[0146] Specific embodiment three: this embodiment is different from specific embodiment one or two in that the carbon rod slide rail 8 is composed of two parallel carbon rods, the distance between the two carbon rods is 4.5mm, and the baffle 27 -1 After the anti-rollover spring 26 is compressed, the extension shaft 27 slides along the carbon rod slide rail 8.

[0147] Other steps and parameters are the same as those in the first or second embodiment.

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Abstract

The invention relates to an inertial navigation-based fast response rocket delivery system and delivery method. With the inertial navigation-based fast response rocket delivery system and delivery method of the invention adopted, the problems of low loading capacity, short flight time, high cost per unit, requirements for high operation level of operators and insufficient reconnaissance on the ground of an existing unmanned aerial vehicle delivery system and the problems of low control precision and poor cross-country capacity of ground reconnaissance cars of an existing rocket delivery systemcan be solved. The system of the invention includes a nose cone, a loading module, a propulsion module and an all-terrain crawler. The flight process of the delivery system of the present invention can be completed in less than one minute; and a process from the assembly of the system to the completion of a mission can be completed within five minutes; the propulsion module designed in the systemof the invention can be configured with 19 C-class engines at most; the maximum load of the loading module can reach 2KG; and the cost of the system of the present invention is 600 yuan which is muchlower than the cost of several thousands of yuan of mainstream unmanned aerial vehicles on the market at present. The delivery system and delivery method of the invention can be used for the materialdelivery and remote reconnaissance field.

Description

Technical field [0001] The invention relates to a small quick-response rocket launching system and a launching method based on inertial navigation. Background technique [0002] 1. Existing technology using drone reconnaissance [0003] At present, UAV technology at home and abroad is relatively mature, but it mainly focuses on the use of airborne equipment for reconnaissance. Its main advantages are: [0004] 1) Quick response: When there is a mission requirement, the drone can be used to fly near the reconnaissance area. [0005] 2) Flexible and controllable: It can reach the sky above any place within the flightable range, and can repeat reconnaissance on a certain place. [0006] 3) Many data can be returned: image data and other remote sensing data can be returned by equipped with cameras and scientific equipment. [0007] But UAV reconnaissance also has certain limitations: [0008] 1) Small load: Limited by the speed of the motor, the maximum lift that the UAV power unit can provi...

Claims

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Application Information

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IPC IPC(8): G05B19/042G01C5/06G01C21/18
Inventor 奚瑞辰马恩煜何湘远胡佳辉李梦思尹悦
Owner HARBIN INST OF TECH
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