Unlock instant, AI-driven research and patent intelligence for your innovation.

Split-type rotary throwing separation method of rocket fairing

A separation method and fairing technology, which is applied in the direction of offensive equipment, projectiles, self-propelled bombs, etc., can solve the problems of rocket carrying capacity loss, etc., and achieve the effects of improving carrying capacity, ensuring separation, and increasing spin throwing speed

Active Publication Date: 2021-04-27
BEIJING XINGJI RONGYAO SPACE TECH CO LTD +1
View PDF5 Cites 0 Cited by
  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0006] Therefore, the technical problem to be solved in the present invention is to overcome the rocket fairing in the prior art due to the axial overload N must be selected x Separation within a certain period of time greater than zero leads to the loss of the rocket's carrying capacity, thus providing a split-lobed spin-throwing separation method for the rocket fairing

Method used

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
View more

Image

Smart Image Click on the blue labels to locate them in the text.
Viewing Examples
Smart Image
  • Split-type rotary throwing separation method of rocket fairing
  • Split-type rotary throwing separation method of rocket fairing
  • Split-type rotary throwing separation method of rocket fairing

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0063] Such as image 3 As shown, it is a separation timing design of a split-flap spin throwing separation method for a rocket fairing provided in this embodiment, wherein the abscissa is the time axis, S0 represents the time point of axial apparent acceleration control plus time backup, and S1 Indicates the time point when the lateral separation surface of the fairing 2 is unlocked, S2 represents the time point when the longitudinal separation surface of the fairing 2 is unlocked, S3 represents the time point when the centroid of the fairing 2 is over the top, and S4 represents the time point between the fairing 2 and the rocket body 1. The time point of decoupling; in addition, the binding value is between S0 and S1. According to the above sequence design, the split-flap spin throwing separation method of the present embodiment comprises the following steps:

[0064] First, after the rocket completes the second-stage flight or the third-stage flight, during the time period...

Embodiment 2

[0069] Such as Figure 4 As shown, this embodiment provides a separation timing design for a split-flap spin throwing separation method of a rocket fairing, wherein the abscissa is the time axis, D0 represents the time point of axial apparent acceleration control plus time backup, and D1 Indicates the time point when the lateral separation surface of the fairing 2 is unlocked, D2 represents the time point when the longitudinal separation surface of the fairing 2 is unlocked, D3 represents the time point when the center of mass of the fairing 2 is over the top, and D4 represents the ignition time of the next stage engine D5 represents the time point when the fairing 2 is decoupled from the rocket body 1; in addition, it is the binding value between D0 and D1. According to the above sequence design, the split-flap spin throwing separation method of the present embodiment comprises the following steps:

[0070] First of all, after the rocket completes the second-stage flight, du...

Embodiment 3

[0081] The present embodiment provides a kind of split type rotary throwing separation method of rocket fairing, and this method is substantially the same as the method in embodiment 2, and difference is: present embodiment is in such as figure 2 Start the separation of the fairing 2 during the time period C shown, and then start the third-stage flight of the rocket after the center of mass of the fairing 2 passes the top, so that the separation of the fairing 2 and the rocket body 1 is completed within the time period G.

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
Login to View More

PUM

No PUM Login to View More

Abstract

The separation method of the rocket fairing by split spin throwing provided by the present invention belongs to the technical field of launch vehicle design, and comprises the following steps: after the rocket completes the second-stage flight or the third-stage flight, within the time period when the axial overload of the rocket is equal to zero, Turn on the spinning and throwing separation of the fairing; in the process of spinning and separating the fairing, the axial force borne by the hinge connected between the fairing and the rocket body is zero for the first time as the judgment that the centroid of the fairing is over the top According to the data, and the secondary axial force suffered by the hinge is zero as the criterion for decoupling of the fairing and the rocket body; the split-type rotary throwing separation method of the rocket fairing of the present invention provides a feasible centroid of the fairing over the top and The criterion for decoupling is to realize the closure of the separation design of the fairing. The separation of the fairing is carried out during the time period when the axial overload of the rocket is equal to zero. The separation energy required is the smallest, and the take-off mass of the upper stage is reduced, thereby improving the carrying capacity of the rocket. ability.

Description

technical field [0001] The invention relates to the technical field of launch vehicle design, in particular to a split-type rotary throwing separation method for a rocket fairing. Background technique [0002] The rocket fairing is located at the front end of the rocket, which plays the role of maintaining the shape of the rocket and protecting satellites. When the launch vehicle flies out of the atmosphere, the fairing needs to be separated from the rocket body to allow the release channel for the payload. [0003] The separation of the rocket fairing can be separated by split spin throwing. The fairing using this separation method is divided into two lobes (or even multiple lobes) along the axial direction. Both the bottom end and the arrow body are fixedly connected by an unlocking device, and the bottom end of the fairing and the arrow body are hingedly connected by a detachable hinge. The separation surface between the two axial lobes of the fairing is called the long...

Claims

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
Login to View More

Application Information

Patent Timeline
no application Login to View More
Patent Type & Authority Patents(China)
IPC IPC(8): F42B15/38
CPCF42B15/38
Inventor 彭小波卢凤翎郑立伟
Owner BEIJING XINGJI RONGYAO SPACE TECH CO LTD