CN112987767A - Integrated boosting and core-level carrier rocket attitude control method - Google Patents
Integrated boosting and core-level carrier rocket attitude control method Download PDFInfo
- Publication number
- CN112987767A CN112987767A CN202110068161.4A CN202110068161A CN112987767A CN 112987767 A CN112987767 A CN 112987767A CN 202110068161 A CN202110068161 A CN 202110068161A CN 112987767 A CN112987767 A CN 112987767A
- Authority
- CN
- China
- Prior art keywords
- booster
- engine
- core
- control
- stage
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 238000000034 method Methods 0.000 title claims abstract description 27
- 238000005096 rolling process Methods 0.000 claims abstract description 24
- 239000007921 spray Substances 0.000 claims abstract description 13
- 230000002093 peripheral effect Effects 0.000 claims abstract description 6
- 230000008569 process Effects 0.000 claims abstract description 5
- 230000007246 mechanism Effects 0.000 description 4
- 238000009434 installation Methods 0.000 description 2
- 238000000926 separation method Methods 0.000 description 2
- 235000015842 Hesperis Nutrition 0.000 description 1
- 235000012633 Iberis amara Nutrition 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000011217 control strategy Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
Images
Classifications
-
- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
- G05D1/00—Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots
- G05D1/08—Control of attitude, i.e. control of roll, pitch, or yaw
- G05D1/0808—Control of attitude, i.e. control of roll, pitch, or yaw specially adapted for aircraft
- G05D1/0816—Control of attitude, i.e. control of roll, pitch, or yaw specially adapted for aircraft to ensure stability
- G05D1/0833—Control of attitude, i.e. control of roll, pitch, or yaw specially adapted for aircraft to ensure stability using limited authority control
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
Landscapes
- Engineering & Computer Science (AREA)
- Computer Security & Cryptography (AREA)
- Aviation & Aerospace Engineering (AREA)
- Radar, Positioning & Navigation (AREA)
- Remote Sensing (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Automation & Control Theory (AREA)
- Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
Abstract
The invention discloses an attitude control method of an integrated boosting and core-stage carrier rocket, wherein the carrier rocket comprises a core stage and an even number of boosters; the core stage comprises a core stage I, and the engine of the core stage I adopts a fixed spray pipe; the boosters are uniformly and rigidly connected to the outer peripheral side of the first core stage in a circumferential direction, and are rigidly connected with the first core stage in the whole process of assembly, test, filling and launching of the carrier rocket; the attitude control method realizes the pitching control and the yawing control of the carrier rocket through the equidirectional swinging of the engines of the pair of boosters in the symmetrical direction, and realizes the rolling control of the carrier rocket through the opposite tangential swinging of the engines of the pair of boosters in the symmetrical direction. The control method can improve the economy of the carrier rocket and increase the rolling moment.
Description
Technical Field
The invention belongs to the technical field of space launch transportation systems, and particularly relates to an integrated boosting and core-level carrier rocket attitude control method.
Background
In the fields of aerospace, deep space exploration and the like, higher and higher requirements are provided for the carrying capacity of a carrier rocket, in addition, stricter requirements are provided for a launching orbit and a carrying capacity gradient, and therefore, the current major medium and large carrier rockets at home and abroad often adopt a structure of binding boosters on a core level.
The main task of the attitude control of the carrier rocket is to stabilize and control the rocket to move around the mass center, so that the deviation of the attitude angle of the rocket relative to the preset attitude angle is controlled within an allowable range, and simultaneously, according to an instruction sent by a guidance system, the attitude angle of the rocket body is controlled, the thrust direction is changed, the required motion state is realized, and the mass center of the rocket is controlled to fly along the preset trajectory. The existing carrier rocket realizes attitude control through the swinging spray pipe and the servo mechanism which are arranged on the core first-stage engine, but the swinging spray pipe and the servo mechanism are arranged on the core first-stage engine, so that the problem of reducing the economical efficiency of the carrier rocket due to consumption of movable parts and components is solved.
Disclosure of Invention
In view of the above, the invention provides an integrated boosting and core-level attitude control method for a launch vehicle, which can improve the economy of the launch vehicle and increase the rolling moment.
The invention is realized by the following technical scheme:
a carrier rocket attitude control method of integrated boosting and core stage, the carrier rocket comprises a core stage and an even number of boosters; the core stage comprises a core stage I, and the engine of the core stage I adopts a fixed spray pipe; the boosters are uniformly and rigidly connected to the outer peripheral side of the core primary stage in a circumferential direction, and are rigidly connected with the core primary stage in the whole process of assembly, test, filling and launching of the carrier rocket; the attitude control method realizes the pitching control and the yawing control of the carrier rocket through the equidirectional swinging of the engines of the pair of boosters in the symmetrical direction, and realizes the rolling control of the carrier rocket through the opposite tangential swinging of the engines of the pair of boosters in the symmetrical direction.
Further, the carrier rocket comprises two thrusters, wherein the two thrusters are a first thruster and a second thruster;
the pitching control is realized by the tangential swinging of a first engine of the first booster and a second engine of the second booster in the same direction;
yaw control is achieved by the first engine of the first booster and the second engine of the second booster swinging radially in the same direction;
the rolling control is realized by the tangential swinging in opposite directions of the first engine of the first booster and the second engine of the second booster.
Further, the launch vehicle includes four of the thrusters, the four thrusters being a first thruster, a second thruster, a third thruster, and a fourth thruster, wherein: the first booster and the third booster are symmetrically arranged, and the second booster and the fourth booster are symmetrically arranged;
the pitching control is realized by the tangential swinging of the first engine of the first booster and the third engine of the third booster in the same direction;
yaw control is realized by tangential swinging of a second engine of the second booster and a fourth engine of the fourth booster in the same direction;
the rolling control is achieved by the tangential swinging in opposite directions of the first engine of the first booster and the third engine of the third booster.
Further, the launch vehicle includes four of the thrusters, the four thrusters being a first thruster, a second thruster, a third thruster, and a fourth thruster, wherein: the first booster and the third booster are symmetrically arranged, and the second booster and the fourth booster are symmetrically arranged;
the pitching control is realized by the tangential swinging control of the first engine of the first booster and the third engine of the third booster in the same direction;
the yaw control is realized by the tangential swinging control in the same direction of a second engine of the second booster and a fourth engine of the fourth booster;
the rolling control is realized by the opposite direction tangential swing control of the second engine of the second booster and the fourth engine of the fourth booster.
Still further, the core stage further comprises a core stage in series with the core stage.
Still further, the core stage further includes a core tertiary stage in series with the core secondary stage.
Further, the swing angle of the engine of the booster is 10 ° or less.
Has the advantages that:
in the integrated boosting and core-stage carrier rocket attitude control method, a booster of a carrier rocket and a core stage are always fixedly connected to form an integrated structure, a whole rocket adopts a swinging spray pipe attitude control mode, the core stage adopts a fixed spray pipe to replace a swinging spray pipe, and pitching, yawing and rolling control of the carrier rocket is realized through the homodromous or reverse swinging of different booster combinations, and the carrier rocket attitude control method has the following beneficial effects:
1. the economical efficiency of the rocket is improved, the fixed spray pipe is adopted at the core first stage, the swing spray pipe of the engine at the core first stage is eliminated, and meanwhile, the booster and the core first stage are always in rigid connection, so that moving parts required by the separation of the booster and the core first stage are reduced, and a servo mechanism for the swing of the engine at the core first stage is also reduced;
2. the rolling moment is increased, the rolling control of the carrier rocket is controlled by the opposite tangential swinging of a pair of booster engines in a symmetrical direction, and the distance between the two boosters in the symmetrical direction is greater than the installation distance of the core first-stage engine, so that the length of the rolling control force arm is increased, the rolling moment can be increased, and the swinging angle of the engine in attitude control can be reduced.
Drawings
FIG. 1 is a schematic structural view of an integrated booster and core stage launch vehicle;
FIG. 2 is a schematic view of attitude control of an integrated booster and core stage launch vehicle.
Wherein, 1-core primary, 2-core secondary, 3-core tertiary, 4-first booster, 5-second booster, 6-third booster, 7-fourth booster, 8-first engine, 9-second engine, 10-third engine, 11-fourth engine
Detailed Description
The invention is described in detail below by way of example with reference to the accompanying drawings.
The embodiment of the invention provides an integrated boosting and core-stage carrier rocket attitude control method, wherein a carrier rocket comprises a core stage and an even number of boosters; the core level comprises a core level 1, and the engine of the core level 1 adopts a fixed spray pipe; the boosters are uniformly and rigidly connected to the outer peripheral side of the core primary 1 in a circumferential direction, and are rigidly connected with the core primary 1 in the whole process of assembly, test, filling and launching of the carrier rocket; the rigid connection of the booster and the core primary 1 means that the booster and the core primary 1 are kept in rigid connection in the whole process of rocket assembly, test, filling and launching, and are separated from the core secondary 2 as a rigid whole under the condition that the core comprises two or more sections of carrier rocket configuration; as shown in the configuration of fig. 1, the core stage of the launch vehicle may include three sections in series and four thrusters rigidly connected to the core stage, i.e., the core stage includes a core primary 1, a core secondary 2, and a core tertiary 3 in series; four boosters are uniformly distributed on the outer peripheral side of the core primary 1 along the circumferential direction of the core primary 1, the four boosters are respectively a first booster 4, a second booster 5, a third booster 6 and a fourth booster 7, and the four boosters are uniformly distributed around the core primary 1 along the circumferential direction at an angle of 90 degrees;
the attitude control method realizes the pitching control and the yawing control of the carrier rocket through the equidirectional swinging of the engines of a pair of boosters in symmetrical directions, and realizes the rolling control of the carrier rocket through the opposite tangential swinging of the engines of the pair of boosters in symmetrical directions; the swing angle of the engine of the booster is less than or equal to 10 degrees, such as: 3 °, 5 °, 6 °, 7 °, 8 °, 9 °, 10 °.
In the attitude control method of the carrier rocket, the core first stage 1 adopts a fixed spray pipe, the booster adopts a swinging spray pipe, and the pitching, yawing and rolling control of the carrier rocket is realized through the equidirectional swinging or opposite direction swinging of the symmetrical azimuth booster; the booster and the core primary 1 are always rigidly connected, so that moving parts required by the separation of the booster and the core primary 1 are reduced, and a servo mechanism for swinging the core primary 1 engine is reduced, thereby improving the economy of the carrier rocket; meanwhile, the rolling control of the carrier rocket is realized by the opposite tangential swinging of a pair of booster engines in symmetrical directions, and the distance between the two boosters is greater than the installation distance of the first-stage core 1 engine, so that the length of the rolling control force arm is increased, the rolling moment is increased, and the swinging angle of the engine in attitude control can be reduced.
In one specific embodiment, the launch vehicle may include two thrusters, a first thruster 4 and a second thruster 5; the pitching control is realized by the tangential swinging of a first engine 8 of the first booster 4 and a second engine 9 of the second booster 5 in the same direction; yaw control is realized by radial swinging of a first engine 8 of the first booster 4 and a second engine 9 of the second booster 5 in the same direction; the roll control is achieved by the tangential swinging in opposite directions of the first motor 8 of the first booster 4 and the second motor 9 of the second booster 5.
As shown in the structure of fig. 1 and 2, the launch vehicle includes four thrusters, namely a first thruster 4, a second thruster 5, a third thruster 6 and a fourth thruster 7, wherein: the first booster 4 and the third booster 6 are symmetrically arranged, and the second booster 5 and the fourth booster 7 are symmetrically arranged;
the pitching control is realized by the tangential swinging of the first engine 8 of the first booster 4 and the third engine 10 of the third booster 6 in the same direction; yaw control is realized by tangential swinging in the same direction of the second engine 9 of the second booster 5 and the fourth engine 11 of the fourth booster 7; the rolling control is realized by the tangential swinging in opposite directions of the first engine 8 of the first booster 4 and the third engine 10 of the third booster 6;
alternatively, the pitch control is achieved by the unidirectional tangential roll control of the first engine 8 of the first booster 4 and the third engine 10 of the third booster 6; the yaw control is realized by the tangential swing control in the same direction of the second engine 9 of the second booster 5 and the fourth engine 11 of the fourth booster 7; the rolling control is realized by the tangential swinging control in the opposite direction of the second engine 9 of the second booster 5 and the fourth engine 11 of the fourth booster 7;
alternatively, the pitch control is realized by the tangential swing control in the same direction of the second engine 9 of the second booster 5 and the fourth engine 11 of the fourth booster 7; yaw control is realized by the tangential swinging control of the first engine 8 of the first booster 4 and the third engine 10 of the third booster 6 in the same direction; the rolling control is realized by the tangential swinging control in the opposite direction of the second engine 9 of the second booster 5 and the fourth engine 11 of the fourth booster 7;
alternatively, the pitch control is realized by the tangential swing control in the same direction of the second engine 9 of the second booster 5 and the fourth engine 11 of the fourth booster 7; yaw control is realized by the tangential swinging control of the first engine 8 of the first booster 4 and the third engine 10 of the third booster 6 in the same direction; the roll control is effected by the tangential swinging control in opposite directions of the first engine 8 of the first booster 4 and the third engine 10 of the third booster 6.
Additionally, when the launch vehicle includes six, eight, or more thrusters, attitude control of the launch vehicle may refer to a control strategy having two thrusters or four thrusters.
As shown in the structure of fig. 1, the core stage further includes a core secondary 2 in series with the core primary 1 and a core tertiary 3 in series with the core secondary 2. For a carrier rocket formed by connecting a core stage and a booster in parallel, the carrier rocket is generally called a first-stage semi-configuration carrier rocket; the carrier rocket is formed by connecting a core primary 1 and a core secondary 2 in series, wherein the core primary 1 is connected with a booster in parallel, and is generally called a secondary semi-configuration carrier rocket; the carrier rocket is formed by connecting a core first stage 1, a core second stage 2 and a core third stage 3 in series, wherein the core first stage 1 is connected with a booster in parallel, and is generally called a three-stage semi-configuration carrier rocket; the core stage is generally made up of three or less sections, but is not limited to three or more lower sections.
In the above embodiments, the same direction means that the engines of the two boosters swing in the same direction; the reverse direction means that the engines of the two boosters swing in opposite directions; the tangential direction refers to the tangential direction of the outer peripheral surface of the core stage; radial refers to the radial direction of the core stage.
In summary, the above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (7)
1. A carrier rocket attitude control method of integrated boosting and core stage is characterized in that the carrier rocket comprises a core stage and an even number of boosters; the core stage comprises a core stage I, and the engine of the core stage I adopts a fixed spray pipe; the boosters are uniformly and rigidly connected to the outer peripheral side of the core primary stage in a circumferential direction, and are rigidly connected with the core primary stage in the whole process of assembly, test, filling and launching of the carrier rocket; the attitude control method realizes the pitching control and the yawing control of the carrier rocket through the equidirectional swinging of the engines of the pair of boosters in the symmetrical direction, and realizes the rolling control of the carrier rocket through the opposite tangential swinging of the engines of the pair of boosters in the symmetrical direction.
2. A launch vehicle attitude control method according to claim 1, characterised in that said launch vehicle includes two said thrusters, a first thruster and a second thruster;
the pitching control is realized by the tangential swinging of a first engine of the first booster and a second engine of the second booster in the same direction;
yaw control is achieved by the first engine of the first booster and the second engine of the second booster swinging radially in the same direction;
the rolling control is realized by the tangential swinging in opposite directions of the first engine of the first booster and the second engine of the second booster.
3. A launch vehicle attitude control method according to claim 1, wherein said launch vehicle includes four said thrusters, said four thrusters being a first thruster, a second thruster, a third thruster, and a fourth thruster, wherein: the first booster and the third booster are symmetrically arranged, and the second booster and the fourth booster are symmetrically arranged;
the pitching control is realized by the tangential swinging of the first engine of the first booster and the third engine of the third booster in the same direction;
yaw control is realized by tangential swinging of a second engine of the second booster and a fourth engine of the fourth booster in the same direction;
the rolling control is achieved by the tangential swinging in opposite directions of the first engine of the first booster and the third engine of the third booster.
4. A launch vehicle attitude control method according to claim 1, wherein said launch vehicle includes four said thrusters, said four thrusters being a first thruster, a second thruster, a third thruster, and a fourth thruster, wherein: the first booster and the third booster are symmetrically arranged, and the second booster and the fourth booster are symmetrically arranged;
the pitching control is realized by the tangential swinging control of the first engine of the first booster and the third engine of the third booster in the same direction;
the yaw control is realized by the tangential swinging control in the same direction of a second engine of the second booster and a fourth engine of the fourth booster;
the rolling control is realized by the opposite direction tangential swing control of the second engine of the second booster and the fourth engine of the fourth booster.
5. A launch vehicle attitude control method according to any one of claims 1 to 4 characterised in that said core stage further comprises a core secondary stage in series with said core primary stage.
6. A launch vehicle attitude control method according to claim 5, characterised in that said core stage further comprises a core tertiary stage in series with said core secondary stage.
7. A method for attitude control of a launch vehicle according to any one of claims 1 to 4 wherein the roll angles of the engines of the thrusters are each 10 ° or less.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110068161.4A CN112987767B (en) | 2021-01-19 | 2021-01-19 | Carrier rocket attitude control method with integrated boosting and core level |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110068161.4A CN112987767B (en) | 2021-01-19 | 2021-01-19 | Carrier rocket attitude control method with integrated boosting and core level |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN112987767A true CN112987767A (en) | 2021-06-18 |
| CN112987767B CN112987767B (en) | 2023-07-25 |
Family
ID=76344406
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110068161.4A Active CN112987767B (en) | 2021-01-19 | 2021-01-19 | Carrier rocket attitude control method with integrated boosting and core level |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112987767B (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114384799A (en) * | 2022-01-14 | 2022-04-22 | 北京中科宇航技术有限公司 | Boosting and core-level engine combined thrust vector control method |
| CN116185058A (en) * | 2023-04-21 | 2023-05-30 | 东方空间技术(山东)有限公司 | Carrier rocket attitude control method and device and flight control computer |
| CN116552819A (en) * | 2023-04-19 | 2023-08-08 | 彭昆雅 | Swing control method of rocket and rocket |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2002228398A (en) * | 2001-01-29 | 2002-08-14 | Tech Res & Dev Inst Of Japan Def Agency | Airframe attitude controller |
| CN104898680A (en) * | 2015-05-04 | 2015-09-09 | 湖北航天技术研究院总体设计所 | Solid carrier rocket attitude control method based on solid variable-jet-direction jet engine |
| CN109606738A (en) * | 2019-01-14 | 2019-04-12 | 北京星际荣耀空间科技有限公司 | A kind of reusable carrier rocket core first-stage rocket body recycling dynamical system |
| CN110794863A (en) * | 2019-11-20 | 2020-02-14 | 中山大学 | Heavy carrier rocket attitude control method capable of customizing control performance indexes |
| CN110920923A (en) * | 2019-12-23 | 2020-03-27 | 中国人民解放军总参谋部第六十研究所 | Unmanned aerial vehicle launching device with double rocket boosters |
| CN110953940A (en) * | 2018-12-20 | 2020-04-03 | 中国人民解放军63921部队 | Method for assembling, erecting and withdrawing binding type carrier rocket |
| CN110968103A (en) * | 2019-12-12 | 2020-04-07 | 北京中科宇航探索技术有限公司 | Boosting variable-thrust attitude adjusting method and device |
| CN111516909A (en) * | 2020-04-30 | 2020-08-11 | 北京星际荣耀空间科技有限公司 | Rocket attitude control system |
-
2021
- 2021-01-19 CN CN202110068161.4A patent/CN112987767B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2002228398A (en) * | 2001-01-29 | 2002-08-14 | Tech Res & Dev Inst Of Japan Def Agency | Airframe attitude controller |
| CN104898680A (en) * | 2015-05-04 | 2015-09-09 | 湖北航天技术研究院总体设计所 | Solid carrier rocket attitude control method based on solid variable-jet-direction jet engine |
| CN110953940A (en) * | 2018-12-20 | 2020-04-03 | 中国人民解放军63921部队 | Method for assembling, erecting and withdrawing binding type carrier rocket |
| CN109606738A (en) * | 2019-01-14 | 2019-04-12 | 北京星际荣耀空间科技有限公司 | A kind of reusable carrier rocket core first-stage rocket body recycling dynamical system |
| CN110794863A (en) * | 2019-11-20 | 2020-02-14 | 中山大学 | Heavy carrier rocket attitude control method capable of customizing control performance indexes |
| CN110968103A (en) * | 2019-12-12 | 2020-04-07 | 北京中科宇航探索技术有限公司 | Boosting variable-thrust attitude adjusting method and device |
| CN110920923A (en) * | 2019-12-23 | 2020-03-27 | 中国人民解放军总参谋部第六十研究所 | Unmanned aerial vehicle launching device with double rocket boosters |
| CN111516909A (en) * | 2020-04-30 | 2020-08-11 | 北京星际荣耀空间科技有限公司 | Rocket attitude control system |
Non-Patent Citations (2)
| Title |
|---|
| 刘兴武: "超级"新科状元"──大力神-4B 运载火箭" * |
| 杨希祥 等: "基于运载能力评估的固体运载火箭推力向量控制方案比较" * |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114384799A (en) * | 2022-01-14 | 2022-04-22 | 北京中科宇航技术有限公司 | Boosting and core-level engine combined thrust vector control method |
| CN114384799B (en) * | 2022-01-14 | 2023-11-28 | 北京中科宇航技术有限公司 | Combined thrust vector control method for boosting and core-level engine |
| CN116552819A (en) * | 2023-04-19 | 2023-08-08 | 彭昆雅 | Swing control method of rocket and rocket |
| CN116552819B (en) * | 2023-04-19 | 2024-01-26 | 彭昆雅 | Swing control method of rocket and rocket |
| CN116185058A (en) * | 2023-04-21 | 2023-05-30 | 东方空间技术(山东)有限公司 | Carrier rocket attitude control method and device and flight control computer |
Also Published As
| Publication number | Publication date |
|---|---|
| CN112987767B (en) | 2023-07-25 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN112987767B (en) | Carrier rocket attitude control method with integrated boosting and core level | |
| US11319063B2 (en) | Vehicle configuration with motors that rotate between a lifting position and a thrusting position | |
| Schmidt | Modern flight dynamics | |
| US9429105B2 (en) | Rocket vehicle with integrated attitude control and thrust vectoring | |
| US20020121572A1 (en) | Integrated system for provinding 3-axis attitude-control, energy-storage, and electrical power | |
| CN115614182B (en) | Carrier rocket power system | |
| US8800913B2 (en) | Methods and apparatus for a tandem divert and attitude control system | |
| CN218329572U (en) | Solid-liquid mixed carrier rocket for continuously boosting in atmosphere | |
| CN114117758A (en) | Rocket boosting section trajectory optimization method based on particle swarm optimization | |
| CN111336868A (en) | Rocket attitude control system | |
| CN111891404A (en) | Layout method and system for electrified dual-mode thruster of high-orbit maneuvering satellite platform | |
| CN114384799A (en) | Boosting and core-level engine combined thrust vector control method | |
| CN109080851A (en) | Cube star moment of mass disymmetry is laid out attitude-control device | |
| US10926893B2 (en) | Space based magnetic vortex accelerator and methods of use thereof | |
| CN215261463U (en) | Carrier based on modularization solid power system | |
| CN109190155B (en) | Hybrid continuous low-thrust track design method adopting electric propulsion/solar sail propulsion | |
| CN115158709B (en) | Carrier rocket with pneumatic separation and power recovery system | |
| CN109573104A (en) | Manned lunar surface's Electromagnetic Launching lunar surface acceleration orbit | |
| CN114756041A (en) | Maneuvering path design method for magnetic suspension universal maneuvering satellite platform | |
| CN114719688A (en) | Pneumatic separation recoverable carrier rocket for launching suborbital load | |
| CN114750977A (en) | Pneumatic separation pull type recovery second-stage small carrier rocket with big-end melon petal sleeve cover | |
| CN108984934B (en) | Track design method based on circumferential or tangential mixed continuous low thrust | |
| US20150102129A1 (en) | Mounting assembly | |
| JPH09166399A (en) | Missile with non-cylindrical type propulsive section | |
| CN217396842U (en) | Attitude control cabin of spacecraft and spacecraft |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |