Method for predicting interstage thermal separation motion of carrier rocket
A launch vehicle, separation motion technology, applied in special data processing applications, instruments, electrical digital data processing, etc., can solve the problems of huge impact on separation safety and large prediction errors, and achieves low computational cost, easy implementation, and reduced research and development. cost effect
Pending Publication Date: 2020-12-22
北京星途探索科技有限公司
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Problems solved by technology
That is, the inter-stage environmental parameters are predicted under no separation motion, and the separation motion parameters are predicted under a given environmental parameter, and the correlation between the two is excluded, resulting in a large prediction error
Especially for the interaction force between the upper and lower stages during the separation process, as the decisive factor for the normal operation of the thermal separation between the stages, its error has a huge impact on the safety of separation and brings great potential risks to the rocket flight
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[0016] Based on the thermal separation of the first stage in the atmosphere of a multi-stage launch vehicle, the mass balance, energy balance, and dynamic balance equations of the interstage pressure holding section and the separation movement section in the separation process are established, and the interstage between the upper stage and the lower stage is further modeled The force is used to complete the mathematical expression of the physical process of thermal separation, and to realize the prediction of environmental parameters and motion parameters in the process of thermal separation between stages. The main process is as follows;
[0017] 1) Indicates the environmental parameters of the pressure holding section between stages: the pressure in the cabin p i , gas temperature T i
[0018] Application claim 2, 3 described equation groups:
[0019]
[0020]
[0021] in is the injection flow rate of the upper stage engine; V 0 is the initial volume between stag...
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The invention discloses a prediction method for interstage thermal separation motion of a carrier rocket. The prediction method is an equivalent modeling prediction method considering the coupling effect of environment and motion parameters. According to the method, aiming at primary thermal separation in the atmosphere of the multistage carrier rocket, the simultaneous prediction of environmentalparameters and motion parameters in the thermal separation process is realized by establishing mass balance, energy balance and dynamic balance equations of an interstage pressure building section and a separation motion section in the separation process and modeling the acting force of upper-stage gas on the lower stage, and a good effect is achieved.
Description
technical field [0001] The invention is an equivalent modeling method aimed at predicting the thermal separation motion of a launch vehicle, which is used for the design of thermal separation between rocket stages under multiple disturbances and strong nonlinearity, and belongs to the field of separation system design of launch vehicles and missiles. Background technique [0002] The separation system of the launch vehicle is an important subsystem of the rocket. Its function is to separate and throw away the useless parts that have completed their scheduled work during the flight of the rocket and throw them away, so as to improve the mass characteristics of the rocket and increase the carrying capacity. . There are generally two types of interstage separation in rocket flight: one is cold separation, which is characterized in that the upper stage engine is ignited to work after the two stages are separated to a certain distance. The other is thermal separation, which is c...
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IPC IPC(8): G06F30/15G06F119/08G06F119/14
CPCG06F30/15G06F2119/08G06F2119/14
Inventor 刘强孙永丰谢雪明石亦琨徐然
Owner 北京星途探索科技有限公司