A rocket take-off bottom resistance detection device
A technology of detection device and test device, applied in the direction of measurement device, measurement of rapid changes, instruments, etc., can solve the problem of no rocket bottom resistance test research special literature and other problems, and achieve the effect of improving measurement accuracy
Active Publication Date: 2021-07-13
BEIJING INST OF SPACE LAUNCH TECH +1
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Problems solved by technology
During the rocket launch simulation test, occasionally an arrow bottom pressure sensor or temperature and heat flow sensor is attached to simply test the arrow bottom negative pressure or heat flow, but there is no special literature on rocket bottom resistance test research, especially the special detection device for rocket takeoff bottom resistance
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[0028] In addition to the embodiments described below, the invention can be embodied in other embodiments or carried out in different ways. It is, therefore, to be understood that the invention is not limited to the details of construction of the components described in the following description or shown in the drawings.
[0029] Such as figure 1 , 2 As shown, a rocket take-off bottom resistance characteristic detection device includes a simulated rocket body 1, an engine 2, an aerodynamic resistance test device 3, and a hoisting device 4; the simulated rocket body 1 includes a hood 11 connected sequentially from top to bottom, Rocket body shell 12, rocket bottom skirt 13, simulated rocket body 1 covering engine 2; said aerodynamic resistance test device 3 includes a first force measuring device 31 and a second force measuring device 32, and the first force measuring device is fixed on the top of the engine The second force-measuring device is fixed at the joint between the ...
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A rocket take-off bottom resistance detection device of the present invention comprises a simulated rocket body (1), an engine (2), an aerodynamic resistance testing device (3), and a hoisting device (4); the simulated rocket body (1) includes The hood (11), the rocket body casing (12), and the rocket bottom skirt (13) that are connected in sequence, the bottom of the hood (11) is connected with the top of the rocket body casing (12), and the simulated rocket body casing (12) bottom is connected to the rocket body casing (12). The upper part of the bottom skirt (13) is connected, and the simulated rocket body (1) is coated with a simulated engine (2); the aerodynamic resistance testing device (3) includes a first force measuring device (31), a second force measuring device (32), The first force-measuring device is fixed on the top of the simulated engine; the second force-measuring device is fixed at the connection between the simulated hood and the simulated rocket shell; the lower end of the hoisting device (4) is fixed to the simulated engine (2), and the upper end passes through the hood In the center, the entire simulated rocket body is hoisted on the top wall (31), and the simulated rocket body (1) can freely slide for a certain distance along the hoisting device (4).
Description
technical field [0001] The invention belongs to the technical field of rocket launching, and in particular relates to the detection technology of rocket take-off bottom resistance. Background technique [0002] During rocket take-off, the special plume ejected by the gas jet near the bottom of the arrow will form a low-pressure area at the bottom of the rocket body, which will generate aerodynamic resistance at the bottom and cause the loss of rocket take-off thrust; in special cases, this plume will also A lateral thrust is created near the bottom of the rocket body, causing a special aerodynamic moment. The aerodynamic drag at the bottom and the lateral thrust caused by the plume are collectively referred to as the rocket take-off bottom drag. [0003] The rocket take-off bottom resistance is directly related to the additional aerodynamic characteristic coefficients considered in the design of the rocket's take-off trajectory and take-off attitude control scheme, and dete...
Claims
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IPC IPC(8): G01L23/00
CPCG01L23/00
Inventor 陈劲松吕永志邓海潮吴新跃王明华王玉波刘国英王帅
Owner BEIJING INST OF SPACE LAUNCH TECH