Nitrogen propelling system with multiple thrust groups

Abstract

The utility model provides a nitrogen propelling system with multiple thrust groups. The nitrogen propelling system comprises a high-pressure gas cylinder, a plurality of spray pipe groups and a ring pipe. The high-pressure gas cylinders are connected with the multiple spray pipe sets through gas cylinder branches, and the multiple spray pipe sets are evenly arranged on the circumference of the rocket body in the circumferential direction. The gas cylinder branch is communicated with an annular pipe, and the annular pipe is connected with an external nitrogen source and provides nitrogen for the high-pressure gas cylinder. An inflation valve used for controlling inflation and deflation of the high-pressure gas cylinder is arranged on the annular pipe. According to the nitrogen propelling system, the multiple spraying pipe sets are used in cooperation, the thrust requirement for rocket attitude adjustment when the high-pressure gas cylinder is located in the high-pressure and low-pressure interval is met, and meanwhile the nitrogen utilization rate is increased. Besides, the pipeline adopts a distribution mode of the annular pipe and the branch pipes, so that the pressure difference among the high-pressure gas cylinders can be balanced, the thrust released by the plurality of spray pipe groups can be balanced, interference force is avoided, and the rocket attitude adjustment is more stable and efficient.

Description

TECHNICAL FIELD

[0001] The utility model relates to rocket attitude regulation and control technical field, concretely is a nitrogen gas propelling system of multi-thrust group. BACKGROUND

[0002] The nitrogen gas propelling system is utilized high pressure nitrogen gas to accelerate and spray out through the spray pipe and produces the thrust, has the fast response speed, the high reliability, the non-toxicity non-pollution, the reusable advantage, is widely used in the attitude control of carrier and satellite orbit control. Compared with the chemical propellant combustion mode, the specific impulse of nitrogen gas propelling is low, therefore the nitrogen gas propelling system is relatively less on the rocket as the auxiliary power system uses. Along with the all rocket non-toxicity, the reusable demand, the nitrogen gas propelling system gradually shows the advantage, and it can also carry out the rocket body attitude adjustment, the recovery area control etc.

[0003] The nitrogen gas propelling system is because the second flow is big, adopts the drop pressure type working mode. When the gas cylinder pressure is low to certain degree, the spray pipe thrust reduces obviously, leads to the weak rocket body attitude control force, the control precision reduces. Meanwhile nitrogen gas is discharged and is expanded and does work, and the medium temperature continuously reduces, makes nitrogen gas pressure superimposed reduction, leads to the low utilization rate of nitrogen gas propelling system, the nitrogen gas propelling system is heavy. UTILITY MODEL CONTENT

[0004] The utility model aims at overcoming the prior art's insufficient, provides a nitrogen gas propelling system of multi-thrust group to solve the problem that the nitrogen gas utilization rate is low in prior art and the thrust of nitrogen gas system propelling in different stages cannot reach the demand.

[0005] The utility model provides a nitrogen gas propelling system of multi-thrust group, the nitrogen gas propelling system includes: high pressure gas cylinder, multiple spray pipe groups and ring pipe, the high pressure gas cylinder is connected multiple spray pipe groups through gas cylinder branch, and multiple spray pipe groups are evenly arranged on the circumference of rocket body along the circumferential direction, the gas cylinder branch communicates ring pipe, and ring pipe is connected external nitrogen gas source and provides nitrogen gas for high pressure gas cylinder, and the inflation valve door for controlling the inflation and deflation of high pressure gas cylinder is arranged on ring pipe.

[0006] Further, a group of the spray pipe group is correspondingly communicated with one high pressure gas cylinder.

[0007] Further, the spray pipe group includes A spray pipe and B spray pipe, wherein the throat diameter of the A spray pipe and the B spray pipe is different, and the A spray pipe and the B spray pipe are communicated with the gas cylinder branch through the spray pipe branch respectively.

[0008] Further, the nozzle direction of the A spray pipe and the B spray pipe is perpendicular to the axis of the rocket body and tangent to the surface of the rocket body.

[0009] Further, two of the A nozzles are oppositely arranged with nozzle directions pointing in opposite directions; two of the B nozzles are oppositely arranged with nozzle directions pointing in opposite directions; and the two A nozzles and the two B nozzles are arranged in a lower direction along an axis direction of the rocket body.

[0010] Further, a nozzle valve for controlling nitrogen delivery is arranged at an inlet of each of the A nozzle and the B nozzle.

[0011] In the embodiment of the utility model, the part of the ring pipe located upstream of the inflation valve is provided with a filter.

[0012] According to the above embodiment, the nitrogen propelling system with multiple thrust groups provided by the utility model has at least the following benefits: the nitrogen propelling system is used in cooperation with multiple groups of nozzles, meets the demand of the rocket attitude adjustment thrust in the high and low pressure intervals of the drop pressure type working high pressure cylinder, and improves the utilization rate of nitrogen.

[0013] In addition, the pipeline adopts a ring pipe + branch pipe mode, and each cylinder corresponds to the position of the corresponding thrust device, reduces the flow resistance between the cylinder and the thrust device, balances the pressure difference between multiple cylinders by using the ring pipe, avoids the problems of thrust deviation and attitude interference on the rocket body between different quadrants, and improves the stability of the rocket attitude adjustment.

[0014] It should be understood that the above general description and the following detailed description are only exemplary and explanatory, and cannot limit the scope of the utility model. BRIEF DESCRIPTION OF DRAWINGS

[0015] The following drawings are part of the specification of the utility model, which illustrates the example embodiments of the utility model, and the attached drawings and the description of the specification are used to illustrate the principle of the utility model.

[0016] Figure 1 The utility model provides a kind of nitrogen propelling system of multiple thrust group for the top view structural drawing of the utility model.

[0017] Figure 2 The utility model provides a kind of connection structural drawing of nitrogen propelling system of multiple thrust group for the utility model.

[0018] Explanation of reference signs:

[0019] 1-high pressure cylinder, 2-cylinder branch, 3-nozzle group, 4-rocket body, 5-nozzle branch, 6-ring pipe, 7-inflation valve, 8-filter;

[0020] 31-A nozzle, 32-B nozzle, 33-nozzle valve. DETAILED DESCRIPTION

[0021] Various exemplary embodiments of the present invention are now described in detail. This detailed description should not be considered as a limitation of the present invention, but should be understood as a more detailed description of certain aspects, features and implementations of the present invention.

[0022] Various improvements and variations can be made to the specific embodiments described in this utility model without departing from the scope or spirit of this utility model, which will be obvious to those skilled in the art. Other embodiments derived from this utility model description will also be obvious to those skilled in the art. This application specification and embodiments are merely exemplary.

[0023] This invention provides a nitrogen propulsion system with multiple thrust groups, such as... Figure 1 and 2 The diagram shows the structure of the nitrogen propulsion system. In a specific embodiment, the nitrogen propulsion system includes: a high-pressure gas cylinder 1, multiple nozzle assemblies 3, and a ring pipe 6. The high-pressure gas cylinder 1 is connected to the multiple nozzle assemblies 3 via a cylinder branch line 2. The multiple nozzle assemblies 3 are evenly arranged circumferentially around the circumference of the rocket body 4. Figure 1 As shown, the four nozzle groups 3 are evenly distributed around the circumference of the rocket body 4. Figure 2 As shown, in this embodiment, there are 4 high-pressure gas cylinders 1 and 4 sets of nozzle groups 3, where each set of nozzle groups 3 is connected to one high-pressure gas cylinder 1.

[0024] In addition, gas cylinder branch 2 is connected to ring pipe 6, which is connected to an external nitrogen source to provide nitrogen to high-pressure gas cylinder 1. In this embodiment, ring pipe 6 is set up to balance the pressure between each high-pressure gas cylinder 1, ensure that the thrust of nozzle group 3 in different quadrants is the same, and avoid interference forces when nozzles in different quadrants are working.

[0025] A filling valve 7 for controlling the filling and releasing of the high-pressure gas cylinder 1 is provided on the ring pipe 6. In this embodiment, the filling valve 7 is a solenoid valve.

[0026] In a specific embodiment of this utility model, the nozzle assembly 3 includes nozzle A 31 and nozzle B 32. Nozzle A 31 and nozzle B 32 have different throat diameters. Different throat diameters result in different thrust magnitudes under the same nozzle inlet pressure. In this embodiment, the inlet diameter of nozzle A 31 is smaller than the throat diameter of nozzle B 32.

[0027] Nozzle A 31 and Nozzle B 32 are respectively connected to cylinder branch 2 through nozzle branch 5.

[0028] The throat diameter of the A nozzle 31 is small, and is used when the internal pressure of the high-pressure cylinder 1 is in the high-pressure interval, so as to avoid excessive thrust in the early stage. The throat diameter of the B nozzle 32 is large, and is used when the internal pressure of the high-pressure cylinder 1 is in the low-pressure interval, so as to ensure that the thrust meets the demand of the rocket attitude adjustment when the pressure of the high-pressure cylinder 1 is low. Meanwhile, the use of the large-throat-diameter nozzle can make the high-pressure cylinder 1 work in a lower pressure interval, thereby improving the utilization rate of the nitrogen propelling system.

[0029] Further, the nozzle direction of the A nozzle 31 and the B nozzle 32 is perpendicular to the axis of the rocket body 4 and tangent to the surface of the rocket body 4.

[0030] Further, the two A nozzles 31 are oppositely arranged, and the nozzle direction is directed to the opposite direction. The two B nozzles 32 are oppositely arranged, and the nozzle direction is directed to the opposite direction. The two nozzles of the same type are oppositely arranged, so as to start or close different nozzles according to the different attitude of the rocket when the attitude adjustment is controlled, and to realize accurate attitude adjustment.

[0031] As shown in Figure 1 Fig. 2, the two A nozzles 31 and the two B nozzles 32 are arranged in the up-down direction along the axis of the rocket body 4. That is, in the axial direction of the rocket body, the two A nozzles 31 are arranged above the two B nozzles 32, or the two A nozzles 31 are arranged below the two B nozzles 32. Since the start of the A nozzle 31 and the B nozzle 32 needs to be determined according to the pressure of the high-pressure cylinder, the up-down arrangement along the axis is to ensure that the thrust directions of the A nozzle 31 and the B nozzle 32 are the same.

[0032] Further, the inlet of the A nozzle 31 and the B nozzle 32 is provided with a nozzle valve 33 for controlling the nitrogen delivery. Preferably, the nozzle valve 33 is an electromagnetic valve.

[0033] In the embodiment, the outlet of the nozzle valve 33 is connected to the inlet of the nozzle, and the two are connected through a sleeve nut, so as to reduce the cavity of the two, and improve the pulse working response.

[0034] The corresponding electromagnetic valve action instruction is issued by the rocket according to the attitude adjustment demand, the corresponding electromagnetic valve is powered on and the valve is opened, the corresponding nozzle will have nitrogen gas flow, and then the thrust is generated. When the attitude adjustment is not needed, the corresponding electromagnetic valve is powered off and the valve is closed, the nitrogen gas flow of the corresponding nozzle is cut off, and the thrust is not generated.

[0035] In order to reduce the pipeline flow resistance in the working of the nitrogen propelling system, the high-pressure cylinder 1 in each quadrant and the electromagnetic valve on the corresponding nozzle group 3 are arranged approximately coaxially, so that the length of the pipeline through which the gas flows from the high-pressure cylinder to the electromagnetic valve is the shortest, and the pipeline flow resistance is reduced.

[0036] In the specific embodiment of the utility model, the filter 8 is arranged on the part of the annular pipe 6 upstream of the inflation valve 7 to avoid sundries from entering during the process of inflating the high-pressure gas cylinder and to protect the electromagnetic valve downstream.

[0037] The above is only the specific embodiment of the utility model, and any equivalent changes and modifications made by any person skilled in the art without departing from the concept and principle of the utility model shall belong to the protection scope of the utility model.

Claims

1. A multi-thrust class nitrogen propellant system characterized by, The nitrogen propelling system comprises: a high-pressure gas cylinder (1), multiple groups of nozzle groups (3) and a ring pipe (6); the high-pressure gas cylinder (1) is connected with multiple groups of the nozzle groups (3) through a gas cylinder branch (2), and the multiple groups of the nozzle groups (3) are evenly arranged on the circumference of a rocket body (4) in a circumferential direction; The gas cylinder branch (2) is communicated with the ring pipe (6), and the ring pipe (6) is connected with an external nitrogen gas source to provide nitrogen for the high-pressure gas cylinder (1); An inflation valve (7) for controlling the inflation and deflation of the high-pressure gas cylinder (1) is arranged on the ring pipe (6).

2. The multiple-thrust-class nitrogen propulsive system of claim 1, wherein, One group of the nozzle groups (3) corresponds to one high-pressure gas cylinder (1).

3. The multiple-thrust-class nitrogen propulsive system of claim 1 or 2, wherein, The nozzle group (3) comprises an A nozzle (31) and a B nozzle (32), wherein, The throat diameter of the A nozzle (31) is different from that of the B nozzle (32); The A nozzle (31) and the B nozzle (32) are respectively communicated with the gas cylinder branch (2) through a nozzle branch (5).

4. The multiple-thrust-class nitrogen propulsive system of claim 3, wherein, The nozzle direction of the A nozzle (31) and the B nozzle (32) is perpendicular to the axis of the rocket body (4) and tangent to the surface of the rocket body (4).

5. The multiple-thrust-class nitrogen propulsive system of claim 3, wherein, Two A nozzles (31) are oppositely arranged, and the nozzle direction is towards opposite directions; Two B nozzles (32) are oppositely arranged, and the nozzle direction is towards opposite directions; Two A nozzles (31) and two B nozzles (32) are arranged in an up-down manner in the axial direction of the rocket body (4).

6. The multiple-thrust-class nitrogen propulsive system of claim 3, wherein, A nozzle valve (33) for controlling nitrogen delivery is arranged at the inlet of the A nozzle (31) and the B nozzle (32).

7. The multiple-thrust-class nitrogen propulsive system of claim 2, wherein, A filter (8) is arranged on the part of the ring pipe (6) upstream of the inflation valve (7).

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