CN209814334U - Rocket body recovery attitude control power system and carrier rocket - Google Patents
Rocket body recovery attitude control power system and carrier rocket Download PDFInfo
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- CN209814334U CN209814334U CN201920179579.0U CN201920179579U CN209814334U CN 209814334 U CN209814334 U CN 209814334U CN 201920179579 U CN201920179579 U CN 201920179579U CN 209814334 U CN209814334 U CN 209814334U
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Abstract
The application provides appearance accuse driving system and carrier rocket are retrieved to rocket body, and the system includes: at least one gas cylinder, a gas source output switch and a plurality of Laval nozzles; the gas cylinder is connected with the Laval nozzle through an inflation pipeline, and the gas source output switch is arranged on the inflation pipeline so as to control the on-off of the inflation pipeline; the gas cylinder is used for filling compressed gas with preset pressure, and when the gas source output switch is turned on, the compressed gas stored in the gas cylinder is sprayed outwards through the Laval nozzle after passing through the gas charging pipeline to generate thrust, so that attitude control force is provided for the rocket body in the stage before the rocket body is recovered to enter a dense atmosphere. This application adopts compressed gas to spray as the energy, and after a sub-arrow body and the separation of the last level arrow body, a sub-arrow body has not got into before the dense atmosphere, provides attitude control's power supply for the arrow body. The performance of each component has direct detection performance, and is favorable for the recovery and the reuse of the arrow body.
Description
Technical Field
The application belongs to the technical field of carriers, and particularly relates to an arrow body recovery attitude control power system and a carrier rocket.
Background
With the continuous progress of science and technology, the launch vehicle as a vehicle is advancing from a single use stage to a plurality of repeated use stages. In order to realize the repeated use of the carrier rocket, a sub-stage rocket body of the carrier rocket needs to be recycled. After the first-stage rocket body of the carrier rocket is separated from the upper-stage rocket body, the first-stage rocket body needs to return to the atmosphere again according to the set track and land at a preset place, and the process needs to carry out accurate orbit control and attitude control on the rocket body.
At present, the recoverable rocket body is generally provided with a grid rudder. Attitude control after the one-level arrow body enters the dense atmosphere can be realized through the grid rudder. However, when the arrow body of one sub-stage is just separated from the arrow body of the upper stage, the air in the environment where the arrow body of one sub-stage is located is relatively thin, and the posture adjustment of a larger angle is required at this time, so that the posture adjustment of the arrow body of one sub-stage at the previous stage of entering the dense atmosphere needs to be performed by using an auxiliary power system.
Disclosure of Invention
In order to overcome the problems in the related art at least to a certain extent, the application provides an arrow body recovery attitude control power system and a carrier rocket.
According to a first aspect of embodiments of the present application, there is provided an arrow body recovery attitude control power system, comprising:
at least one gas cylinder is arranged in the gas cylinder,
an air source output switch is arranged on the air-conditioning system,
the plurality of Laval nozzles are arranged on the arrow body, at least two Laval nozzles are positioned on two sides of the axial section of the arrow body when the Laval nozzles are arranged on the arrow body, the nozzle directions are opposite, and the nozzle directions are respectively vertical to the central axis of the arrow body;
the gas cylinder is connected with the Laval nozzle through an inflation pipeline, and the gas source output switch is arranged on the inflation pipeline to control the on-off of the inflation pipeline;
the gas cylinder is used for filling into the compressed gas who has preset pressure, and when the air supply output switch was opened, the compressed gas of storage was in the gas cylinder the pipeline is in after outwards spouting through the Laval spray tube, produces thrust to the stage before retrieving the arrow body and getting into dense atmosphere provides gesture control power for the arrow body.
In the rocket body recovery attitude control power system, the number of the air source output switches and the number of the Laval nozzles are eight, and the inflation pipeline comprises an inflation main path and an inflation branch path; each gas cylinder is connected with the main inflation path, and eight main inflation paths are connected to one main inflation path;
each inflation branch is provided with one air source output switch; one end of the air source output switch is connected with the inflation branch, the other end of the air source output switch is connected with one end of a pipeline at the front end of the spray pipe, and the other end of the pipeline at the front end of the spray pipe is connected with the Laval spray pipe.
Compressed gas stored in the gas cylinder is jetted outwards through each Laval nozzle after passing through the main inflation path and the branch inflation path, and thrust is generated.
Furthermore, one end of the main inflation path connected with the gas cylinder is provided with a charging and discharging port, and the main inflation path connected with the gas cylinder through the charging and discharging port is provided with a mechanical inflation switch.
Furthermore, a connector is arranged on the inflation main path where the mechanical inflation switch is connected with the gas cylinder, and the gas cylinder is connected with the rocket body pressurization conveying system through the connector.
Above-mentioned appearance accuse driving system is retrieved to arrow body, still be provided with the gas cylinder pressure detection table on aerifing the main road, the gas cylinder pressure detection table is used for detecting the compressed gas's of gas cylinder output pressure.
Above-mentioned appearance accuse driving system is retrieved to arrow body, arrow body is retrieved appearance and is controlled driving system and install at a sub-arrow body end, the gas cylinder is installed the end before the preceding case of a sub-arrow body, Laval spray tube is installed on the stage section.
Further, the arrow body recovery attitude control power system is not overlapped with an engine in an upper arrow body in the arrow body axis direction.
Furthermore, the eight gas cylinders are grouped into four groups in pairs; each group of the gas cylinders is used for being uniformly arranged at intervals of 90 degrees around the axis of the arrow body in the length direction.
Furthermore, the eight Laval nozzles are grouped into four groups in pairs; each group of the Laval nozzles are uniformly arranged at intervals of 90 degrees around the axis of the arrow body in the length direction, and each group of the Laval nozzles are positioned between two adjacent groups of the gas cylinders.
Preferably, the two said laval nozzles in each group are arranged symmetrically with respect to a horizontal central axis or a vertical central axis in a cross section perpendicular to the direction of flight of the launch vehicle as symmetry axes.
According to a second aspect of embodiments of the present application, there is provided a launch vehicle comprising any of the rocket body recovery attitude control power systems described above.
According to the above embodiments of the present application, at least the following advantages are obtained:
this appearance accuse driving system is retrieved to arrow body fills compressed gas in the gas cylinder through setting up gas cylinder, air supply output switch and Laval spray tube, opens corresponding air supply output switch on aerifing the branch road, and the gas cylinder outwards sprays compressed gas through corresponding Laval spray tube, produces thrust, provides the attitude control power for recoverable arrow body.
Through setting up gas cylinder pressure measurement table and air supply output switch among this application rocket body retrieves appearance accuse driving system, can be in assembly test process or the supplementary quantitative analysis rocket body of the actual flight in-process of operation rocket retrieves appearance accuse driving system whether normal work, thereby can avoid the inherent congenital defect that can't directly carry out the performance detection of initiating explosive device completely, and then can avoid increasing the product production quantity and carrying out the consumption nature side evidence test of spot check ignition on a large scale to the same batch product that goes on for the reliability of side evidence flight product, can show reduce cost.
The arrow body recovery posture control power system is reliable in principle, simple in structure, beneficial to recovery and reuse of arrow bodies and beneficial to cost reduction.
It is to be understood that both the foregoing general description and the following detailed description are exemplary and explanatory only and are not restrictive of the scope of the invention, as claimed.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of the specification of the application, illustrate embodiments of the application and together with the description, serve to explain the principles of the application.
Fig. 1 is a schematic structural diagram of an arrow body recovery attitude control power system according to an embodiment of the present application.
Fig. 2 is a schematic diagram of an arrangement mode of a gas cylinder and a laval nozzle in an arrow body recovery attitude control power system according to an embodiment of the present application.
Fig. 3 is a partial enlarged view of the arrangement mode of a gas cylinder and a laval nozzle in an arrow body recovery attitude control power system according to an embodiment of the present application.
Fig. 4 is a cross-sectional view of an rocket body recovery attitude control power system provided in an embodiment of the present application, wherein a flight direction of a launch vehicle is perpendicular to a paper surface.
Description of reference numerals:
1. a gas cylinder; 2. an air source output switch; 3. a Laval nozzle; 4. an inflation pipeline; 41. an inflation main road; 42. an inflation branch; 5. a pipeline at the front end of the spray pipe; 6. an air discharge port; 7. a mechanical inflation switch; 8. an interface; 9. and a gas cylinder pressure detection meter.
Detailed Description
For the purpose of promoting a clear understanding of the objects, aspects and advantages of the embodiments of the present application, reference will now be made to the accompanying drawings and detailed description, wherein like reference numerals refer to like elements throughout.
The illustrative embodiments and descriptions of the present application are provided to explain the present application and not to limit the present application. Additionally, the same or similar numbered elements/components used in the drawings and the embodiments are used to represent the same or similar parts.
As used herein, "first," "second," …, etc., are not specifically intended to mean in a sequential or chronological order, nor are they intended to limit the application, but merely to distinguish between elements or operations described in the same technical language.
With respect to directional terminology used herein, for example: up, down, left, right, front or rear, etc., are simply directions with reference to the drawings. Accordingly, the directional terminology used is intended to be illustrative and is not intended to be limiting of the present teachings.
As used herein, the terms "comprising," "including," "having," "containing," and the like are open-ended terms that mean including, but not limited to.
As used herein, "and/or" includes any and all combinations of the described items.
References to "plurality" herein include "two" and "more than two"; reference to "multiple sets" herein includes "two sets" and "more than two sets".
As used herein, the terms "substantially", "about" and the like are used to modify any slight variation in quantity or error that does not alter the nature of the variation. In general, the range of slight variations or errors that such terms modify may be 20% in some embodiments, 10% in some embodiments, 5% in some embodiments, or other values. It should be understood by those skilled in the art that the aforementioned values can be adjusted according to actual needs, and are not limited thereto.
Certain words used to describe the present application are discussed below or elsewhere in this specification to provide additional guidance to those skilled in the art in describing the present application.
The inventor of the application finds out in the process of research and development that: the compressed air stores certain energy, and according to the type of gas medium, pressure, temperature and other parameters of the gas source and the pressure difference between the gas source and the outside gas, the compressed air can generate reverse thrust through the injection of the pipeline system. If the piping system is properly arranged and a laval nozzle is used at the outlet, the resulting injection force is sufficient to provide attitude control of the recovered rocket body prior to entry into the dense atmosphere. The compressed air can be used as a power source of the attitude control power system in the arrow body recovery process in the stage.
The rocket body recovery attitude control power system comprises at least one gas cylinder, a gas source output switch and a Laval nozzle;
the at least two Laval nozzles are arranged on two sides of the axial section of the arrow body when the Laval nozzles are arranged on the arrow body, the nozzle directions are opposite, and the nozzle directions are respectively vertical to the central axis of the arrow body; that is, the directions of the nozzles can be in the same plane or in different planes perpendicular to the central axis of the arrow body.
The gas cylinder is connected with the Laval nozzle through an inflation pipeline, and the gas source output switch is arranged on the inflation pipeline so as to control the on-off of the inflation pipeline;
the gas cylinder is used for filling compressed gas with preset pressure, and when the gas source output switch is turned on, the compressed gas stored in the gas cylinder is ejected outwards through the Laval nozzle after passing through the gas charging pipeline to generate thrust, so that effective attitude control force is provided for the rocket body in the stage before the rocket body is recovered to enter a dense atmosphere, and the attitude of the rocket body is adjusted.
This application appearance accuse driving system is retrieved to arrow body adopts compressed gas to spray as the energy, and after a sub-arrow body and the separation of last level arrow body, a sub-arrow body does not get into before the dense atmosphere yet, provides attitude control's power supply to a sub-arrow body. The principle of this application arrow body recovery gesture accuse driving system is reliable, and the performance of each subassembly all possesses the detectability, and product cost is low, is favorable to the recovery and the used repeatedly of arrow body, is favorable to reduce cost.
The arrow recovery attitude control power system of the present application will be described in detail with reference to specific embodiments.
Example one
As shown in fig. 1 and fig. 2, the rocket body recovery attitude control power system provided by the embodiment includes at least one gas cylinder 1, eight gas source output switches 2 and eight laval nozzles 3. The gas bottle 1 is connected with the laval nozzle 3 through the charging pipeline 4, wherein the charging pipeline 4 comprises a main charging path 41 and a branch charging path 42. Each gas bottle 1 is connected with a main inflation path 41, and the main inflation path 41 is connected with eight inflation branch paths 42. Each inflation branch 42 is provided with an air source output switch 2 to control the on-off of the inflation branch 42. One end of the gas source output switch 2 is connected with the inflation branch 42, the other end of the gas source output switch is connected with one end of the spray pipe front end pipeline 5, and the other end of the spray pipe front end pipeline 5 is connected with the Laval spray pipe 3.
Compressed gas stored in the gas cylinder 11 is injected outwards through each Laval nozzle 3 after passing through the inflation main path 41 and the inflation branch path 42, and thrust is generated to provide a power source for attitude control of the rocket body. The arrow attitude control mainly comprises pitching, yawing and rolling.
In order to realize the posture control of the rocket body, at least two Laval nozzles 3 are arranged on two sides of the axial section of the rocket body when the rocket body is arranged, the nozzle directions are opposite, and the nozzle directions are respectively vertical to the central axis of the rocket body, namely the planes of the at least two Laval nozzles 3 are respectively vertical to the rocket axis.
In the present embodiment, the charging and discharging port 6 is provided at one end of the main charging path 41 connected to the gas cylinder 1. The main inflation path 41 connecting the inflation/deflation port 6 and the gas cylinder 1 is provided with a mechanical inflation switch 7. In the preparation stage of the carrier rocket taking off, the air charging and discharging port 6 is connected with a ground air source, the mechanical air charging switch 7 is opened, and a proper amount of compressed air can be charged into the air bottle 1.
In addition, an interface 8 can be arranged on an inflation main path 41 connected with the mechanical inflation switch 7 and the gas bottle 1, and the gas bottle 1 is connected with the rocket body pressurizing and conveying system through the interface 8, so that the sharing of the gas source of the rocket body recovery attitude control power system and the rocket pressurizing and conveying system can be realized. When the gas bottle 1 is connected with the rocket body pressurizing and conveying system, in order to ensure the normal work of the rocket body pressurizing and conveying system, the type of compressed gas required to be filled in the gas bottle 1 can be determined according to the type of gas required by the rocket body pressurizing and conveying system.
In the present embodiment, a cylinder pressure detection meter 9 is further disposed on the main inflation path 41, and the cylinder pressure detection meter 9 is used for detecting the pressure of the compressed gas output by the gas cylinder 1.
By arranging the gas cylinder pressure detection meter 9, whether the rocket body recovery attitude control power system works normally or not can be analyzed quantitatively in the final assembly test process or the actual flight process of running the rocket in an auxiliary manner; by arranging the air source output switch 2, the air source output switch 2 can be opened after the system is inflated, and whether the rocket body recovery attitude control power system works normally or not is qualitatively judged by detecting whether the Laval nozzle 3 generates air flow or not; thereby can avoid initiating explosive device inherent unable direct performance testing's congenital defect completely, and then can avoid increasing the product production quantity and carrying out the consumptive property side certificate experiment of spot check ignition on a large scale to the same batch product that carries out for the reliability of side certificate flight product, can show reduce cost.
It will be appreciated that the cylinder pressure sensing gauge 9 may be connected to the cylinder 1 pressure monitoring device by a cable. The air source output switch 2 is an electric control switch and is connected with external control equipment through a control signal line. In the process of carrier rocket flight, when attitude control force needs to be provided for the rocket body, the external control equipment sends a control signal to the air source output switch 2 to control the opening of the air source output switch 2 on the corresponding inflation branch 42 so as to supply air for the Laval nozzle 3.
The initial value of the thrust generated by the compressed gas ejected from the laval nozzle 3 can be determined from the relevant parameters such as the pressure, temperature, volume of the gas cylinder 1 and the expansion ratio of the laval nozzle 3.
In addition, when the rocket body recovery attitude control power system is used, the throat diameter, the expansion ratio, the quantity and the gas consumption of the Laval nozzle 3 can be determined according to the theoretical calculation of the initial state; after the gas consumption is calculated, the number and the bearing pressure of the gas cylinders 1 can be determined, and the initial charging pressure of the gas cylinders 1 can be properly adjusted to meet the use requirements of different working conditions.
The arrow body recovery posture control power system is installed at a sublevel arrow body end. Specifically, the gas cylinder 1 is arranged at the front bottom of a front box of a sub-step arrow body, and the Laval nozzle 3 is arranged on a step section. In order to avoid the influence on the stage separation, the whole system does not overlap with the engine in the upper stage arrow body in the arrow body axis direction.
The eight gas cylinders 1 are arranged into eight, and the eight gas cylinders 1 are divided into four groups in pairs. Each set of cylinders 1 is intended to be evenly spaced at 90 deg. intervals around the axis of the arrow body in its length direction.
The eight laval nozzles 3 are grouped in pairs into four groups. Each group of laval nozzles 3 is arranged evenly at 90 ° intervals around the axis of the arrow body in the length direction, and each group of laval nozzles 3 is located between two adjacent groups of gas cylinders 1. The two laval nozzles 3 in each group are symmetrically arranged with a horizontal central axis or a vertical central axis in a cross section perpendicular to the flight direction of the launch vehicle as an axis of symmetry. Referring to fig. 4, the H-line is the horizontal central axis and the V-line is the vertical central axis. The nozzle directions of each group of the laval nozzles 3 are opposite, and the straight line where the nozzle direction of each group of the laval nozzles 3 is located is perpendicular to the straight line where the nozzle direction of the adjacent group of the laval nozzles 3 is located.
Specifically, the first laval nozzle is disposed on the right side of a vertical central axis in a cross section perpendicular to the flight direction of the launch vehicle, and the second laval nozzle is symmetrically disposed on the left side of the vertical central axis with the vertical central axis as a symmetry axis.
The third Laval nozzle is arranged above a horizontal central axis in a cross section perpendicular to the flight direction of the carrier rocket, and the fourth Laval nozzle is symmetrically arranged below the horizontal central axis by taking the horizontal central axis as a symmetry axis.
The fifth Laval nozzle is arranged on the left side of a vertical central shaft in a cross section perpendicular to the flight direction of the carrier rocket, the vertical central shaft is taken as a symmetry axis, and the sixth Laval nozzle is symmetrically arranged on the right side of the vertical central shaft.
The seventh laval nozzle is disposed below a horizontal central axis in a cross section perpendicular to a flight direction of the launch vehicle, and the eighth laval nozzle is disposed above the horizontal central axis symmetrically with the horizontal central axis as a symmetry axis.
In the preparation stage of the carrier rocket taking off, the mechanical inflation switch 7 is opened, and compressed gas with preset pressure is filled into the gas bottle 1 through the inflation and deflation port 6. The compressed gas may be compressed air, nitrogen, helium, etc.
After the arrow body of one sub-stage is separated from the arrow body of the upper stage, the arrow body of one sub-stage enters the return stage. And according to an instruction sent by the one-level arrow body control system, sequentially opening the corresponding gas source output switches 2 according to a preset control strategy, so that the corresponding Laval nozzles 3 spray compressed gas outwards to generate thrust, and controlling the pitching, yawing and rolling control postures of the one-level arrow body.
Specifically, when the third laval nozzle and the eighth laval nozzle are opened simultaneously and the remaining laval nozzles 3 are closed, the situation that the pitch angle of the sub-stage rocket body deviates from the theoretical value in the positive direction can be eliminated.
When the fourth Laval nozzle and the seventh Laval nozzle are opened at the same time and the other Laval nozzles 3 are closed, the situation that the negative direction of the pitch angle of a sub-step arrow body deviates from the principle value can be eliminated.
When the first Laval nozzle and the sixth Laval nozzle are opened at the same time, and the other Laval nozzles 3 are closed, the condition that the yaw angle of the rocket body at one sub-stage deviates from the theoretical value can be eliminated.
When the second Laval nozzle and the fifth Laval nozzle are opened at the same time, and the other Laval nozzles 3 are closed, the condition that a sub-step arrow body deviates from the theoretical value in the negative direction in terms of pitching and yawing can be eliminated.
When the second, fourth, sixth and eighth Laval nozzles are simultaneously opened and the other Laval nozzles 3 are closed, the condition that the roll-on angle of the one-step arrow body deviates from the theoretical value in the positive direction can be eliminated.
When the first Laval nozzle, the third Laval nozzle, the fifth Laval nozzle and the seventh Laval nozzle are opened simultaneously and the other Laval nozzles 3 are closed, the situation that the rolling angle of a sub-step arrow body deviates from the theoretical value in the negative direction can be eliminated.
In this embodiment, the gas cylinder 1 and the main inflation path 41 are connected by a screw thread, and a sealing member is provided at the connection point to provide sealing property. The Laval nozzle 3 and the nozzle front end pipeline 5 are in threaded connection or welded, and a sealing part is arranged at the joint when the threaded connection is adopted, so that the sealing performance is achieved. The laval nozzle 3 may be machined from a metallic material.
The foregoing is merely an illustrative embodiment of the present application, and any equivalent changes and modifications made by those skilled in the art without departing from the spirit and principles of the present application shall fall within the protection scope of the present application.
Claims (11)
1. An arrow body recovery attitude control power system is characterized by comprising:
at least one gas cylinder is arranged in the gas cylinder,
an air source output switch is arranged on the air-conditioning system,
the plurality of Laval nozzles are arranged on the arrow body, at least two Laval nozzles are positioned on two sides of the axial section of the arrow body when the Laval nozzles are arranged on the arrow body, the nozzle directions are opposite, and the nozzle directions are respectively vertical to the central axis of the arrow body;
the gas cylinder is connected with the Laval nozzle through an inflation pipeline, and the gas source output switch is arranged on the inflation pipeline to control the on-off of the inflation pipeline;
the gas cylinder is used for filling into the compressed gas who has preset pressure, and when the air supply output switch was opened, the compressed gas of storage was in the gas cylinder the pipeline is in after outwards spouting through the Laval spray tube, produces thrust to the stage before retrieving the arrow body and getting into dense atmosphere provides gesture control power for the arrow body.
2. The rocket body recovery attitude control power system according to claim 1, wherein the number of the air source output switches and the laval nozzle are eight, and the inflation pipeline comprises an inflation main path and an inflation branch path; each gas cylinder is connected with the main inflation path, and eight main inflation paths are connected to one main inflation path;
each inflation branch is provided with one air source output switch; one end of the gas source output switch is connected with the inflation branch, the other end of the gas source output switch is connected with one end of a pipeline at the front end of the spray pipe, and the other end of the pipeline at the front end of the spray pipe is connected with the Laval spray pipe;
compressed gas stored in the gas cylinder is jetted outwards through each Laval nozzle after passing through the main inflation path and the branch inflation path, and thrust is generated.
3. The arrow body recovery attitude control power system according to claim 2, wherein an air charging and discharging port is provided at one end of the main air charging path connected to the air cylinder, and a mechanical air charging switch is provided on the main air charging path connected to the air cylinder.
4. The arrow body recovery attitude control power system according to claim 3, wherein a port is provided on the main inflation path where the mechanical inflation switch is connected to a gas cylinder, and the gas cylinder is connected to an arrow body pressurization conveying system through the port.
5. The arrow body recovery attitude control power system according to claim 2, 3 or 4, wherein a gas cylinder pressure detection meter is further arranged on the inflation main path, and the gas cylinder pressure detection meter is used for detecting the pressure of compressed gas output by the gas cylinder.
6. The arrow body recovery attitude control power system according to claim 1, wherein the arrow body recovery attitude control power system is mounted on a sublevel arrow body end, the gas cylinder is mounted on a front bottom of a front box of the sublevel arrow body, and the laval nozzle is mounted on a stage section.
7. The arrow recovery attitude control power system according to claim 6, wherein the arrow recovery attitude control power system is non-overlapping with an engine in an upper stage arrow body in an arrow body axis direction.
8. The arrow recovery attitude control power system according to claim 2, 3 or 4, wherein eight gas cylinders are grouped in pairs into four groups; each group of the gas cylinders is used for being uniformly arranged at intervals of 90 degrees around the axis of the arrow body in the length direction.
9. The rocket body recovery attitude control power system according to claim 8, wherein eight of said Laval nozzles are grouped in pairs into four groups; each group of the Laval nozzles are uniformly arranged at intervals of 90 degrees around the axis of the arrow body in the length direction, and each group of the Laval nozzles are positioned between two adjacent groups of the gas cylinders.
10. The rocket body recovery attitude control power system according to claim 9, wherein two of said laval nozzles in each group are disposed symmetrically with respect to a horizontal central axis or a vertical central axis in a cross section perpendicular to a flight direction of the launch vehicle as a symmetry axis.
11. A launch vehicle comprising the rocket body recovery attitude control power system according to any one of claims 1 to 10.
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| CN201920179579.0U CN209814334U (en) | 2019-02-01 | 2019-02-01 | Rocket body recovery attitude control power system and carrier rocket |
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| CN201920179579.0U CN209814334U (en) | 2019-02-01 | 2019-02-01 | Rocket body recovery attitude control power system and carrier rocket |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109774975A (en) * | 2019-02-01 | 2019-05-21 | 北京蓝箭空间科技有限公司 | Rocket body recycles attitude control dynamical system and carrier rocket |
| CN115158709A (en) * | 2022-06-07 | 2022-10-11 | 精易兴航(北京)科技创新有限公司 | Carrier rocket with pneumatic separation and power recovery system |
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2019
- 2019-02-01 CN CN201920179579.0U patent/CN209814334U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109774975A (en) * | 2019-02-01 | 2019-05-21 | 北京蓝箭空间科技有限公司 | Rocket body recycles attitude control dynamical system and carrier rocket |
| CN115158709A (en) * | 2022-06-07 | 2022-10-11 | 精易兴航(北京)科技创新有限公司 | Carrier rocket with pneumatic separation and power recovery system |
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