CN104747320A - Rotary control solid attitude and orbit control engine - Google Patents
Rotary control solid attitude and orbit control engine Download PDFInfo
- Publication number
- CN104747320A CN104747320A CN201510046713.6A CN201510046713A CN104747320A CN 104747320 A CN104747320 A CN 104747320A CN 201510046713 A CN201510046713 A CN 201510046713A CN 104747320 A CN104747320 A CN 104747320A
- Authority
- CN
- China
- Prior art keywords
- control
- precise tracking
- engine
- control engine
- orbit control
- 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
Abstract
The invention discloses a rotary control solid attitude and orbit control engine which comprises an outer aircraft shell, an orbit control power system and an altitude control power system. Each orbit control engine comprises an orbit control engine shell, an orbit control engine insulating layer, an orbit control engine grain, an orbit control fuel gas 90-degree pipeline and an orbit control engine jet pipe, wherein the orbit control engine shell adheres to the orbit control engine insulating layer, the orbit control engine insulating layer adheres to the orbit control engine grain, one end of the orbit control fuel gas 90-degree pipeline is connected with an eccentric fuel gas channel of the orbit control engine shell, the other end of the orbit control fuel gas 90-degree pipeline is connected with the orbit control engine jet pipe, and the orbit control engine jet pipe is located on the mass center plane of the engine. The orbit control power system comprises two or more orbit control engines. The altitude control power system comprises three or more altitude control engines. Upper output shafts of the altitude control engines are connected with inner rings of upper altitude control rolling bearings, the outer rings of the upper altitude control rolling bearings are fixedly connected with upper altitude control engine supports, and orbit control engine supports are fixedly connected with the outer aircraft shell. The rotary control solid attitude and orbit control engine is low in technical difficulty, high in feasibility, simple in structure, high in reliability and flexible in form.
Description
Technical field
The present invention relates to a kind of rotation and control solid rocket divert and attitude control motor, belong to rocket rail control technical field of engines.
Background technique
Solid gas rail control power system is mainly used on the various guided missile of air defense, anti-ballistic and Spatial Countermeasure, self kinetic energy collision mode is relied on to kill and wound and destroy threat target, total quality is light, volume is little, and end has high speed and motor-driven regulating power.
In recent decades, main each big country of the world is carrying out the research of novel solid rail control power system being applied to air defense, anti-ballistic, anti-satellite and Spatial Countermeasure field always.Current solid propellant Attitude and orbit control system can be divided into following two types: one is pulse array formula Attitude and orbit control system, guided missile passes through spinning stability, control the flight direction of guided missile by the one group of small rocket motor be arranged on around body, it is anti-ballistic to be mainly used in endoatmosphere area defense; Another kind of employing gas generator multi nozzle Attitude and orbit control system, is made up of two groups of small rocket motor: one group of attitude control engine is installed in the afterbody of blocker, for controlling the attitude of blocker; Four precise tracking are arranged in the centroidal planes of blocker, and for blocker provides higher transverse acceleration, blocker is three-axis stabilization.
Each small rocket motor in above-mentioned pulse array formula Attitude and orbit control system can only once be lighted a fire, and can not realize continuous vector and regulate, thus weaker in control accuracy; Gas generator multi nozzle Attitude and orbit control system regulates though can realize continuous vector, but because needing to realize the adjustment that Flow-rate adjustment have employed gas valve, thus the series of problems such as thermal protection, ablation, valve rod shock can be caused, require high to material technology and basic industry, technological break-through difficulty is large, becomes the technical bottleneck of solid dynamic technical development.
Summary of the invention
The object of the invention is to solve the problem, propose a kind of rotation and control solid rocket divert and attitude control motor, adopt the method for multiple jet pipe point thrust synthesis, by the multiple combination spinning movement of jet pipe along motor axle center carrying firing chamber, regulate point thrust direction of each jet pipe, to realize making a concerted effort, the change of resultant moment of force size and Orientation, produce the thrust vectoring of the motor-driven required multiple directions of body, for aircraft provides required transverse acceleration and pitching, driftage, rolling moment.
A kind of rotation controls solid rocket divert and attitude control motor, comprises aircraft skin body, rail control power system and appearance control power system;
Rail control power system comprises two precise tracking;
Precise tracking comprises precise tracking housing, precise tracking heat insulation layer, precise tracking powder column, rail control combustion gas 90 degree of pipelines, precise tracking jet pipe; Bond between two between precise tracking housing and precise tracking heat insulation layer, between precise tracking heat insulation layer and precise tracking powder column; Rail control combustion gas 90 degree of pipeline one end are connected with the eccentric blast tube of precise tracking housing, the other end connecting rail control engine jet pipe, and precise tracking jet pipe is positioned at the centroidal planes of motor;
Two rail control servo drivers are separately fixed on two precise tracking, and rail control servo driver is fixedly connected with aircraft skin body by rail control servo fixing frame;
The output shaft of each precise tracking coordinates a rail control rolling bearing inner ring respectively, and the outer shroud of rail control rolling bearing is fixedly connected with precise tracking support, and precise tracking support is fixedly connected with aircraft skin body;
Two precise tracking are staggered relatively, be provided with between two precise tracking rail control connect rolling bearing, the inner ring of rolling bearing and outer shroud respectively with two engine shaft transition fit;
Appearance control power system comprises four attitude control engines, and attitude control engine arranged off-centre, in motor head end or end, circumferentially distributes, and running shaft is with engine shaft line parallel but do not overlap;
Attitude control engine is connected by coupling with appearance control servo driver, and appearance control servo driver is fixedly connected with aircraft skin body by appearance control servo fixing frame;
The upper output shaft of attitude control engine coordinates rolling bearing inner ring in appearance control, and in appearance control, the outer shroud of rolling bearing is fixedly connected with attitude control engine upper bracket, and precise tracking support is fixedly connected with aircraft skin body;
Rolling bearing inner ring under the lower output shaft cooperation appearance control of attitude control engine, under appearance control, the outer shroud of rolling bearing is fixedly connected with attitude control engine lower support frame, and attitude control engine lower support frame is fixedly connected with aircraft skin body.
The invention has the advantages that:
(1) technical difficulty is low, and feasibility is high
Traditional gas generator Attitude and orbit control system adopts gas valve to regulate thrust direction and size, and then provides required control moment for missile armament.The high-temperature fuel gas rail control motor that the present invention proposes, by the multiple combination spinning movement of jet pipe along motor axle center carrying firing chamber, produces the thrust vectoring of the motor-driven required multiple directions of body.This conceptual design had both met the requirement of attitude orbits controlling, effectively reduced engine technology difficulty simultaneously;
(2) structure is simple, and reliability is high
Compare conventional Attitude and orbit control system, the present invention's design eliminates complicated pipeline configuration and high-temperature fuel gas valve, and adopt short and sweet structural type, at structural level, separate between rail Ore-controlling Role, posture control system, each jet pipe, be beneficial to control, reliability is high;
(3) flexible form
According to different demands, the scheme of different structure form can be derived, to meet the mode of operation under different condition.
Accompanying drawing explanation
Fig. 1 is rail control overall engine structural drawing of the present invention;
Fig. 2 is rail control power system architecture figure of the present invention;
Fig. 3 is rail control thruster structural drawing of the present invention;
Fig. 4 is appearance control power system architecture figure of the present invention;
Fig. 5 is view under appearance control power system layout of the present invention;
Fig. 6 is the rail control engine structure comprising three precise tracking of the present invention.
In figure:
1-aircraft skin body 2-rail control power system 3-appearance control power system
4-precise tracking 5-attitude control engine 6-rail control servo fixing frame
7-rail control servo driver 8-precise tracking support 9-rail control servo gear group
The control of 10-rail control rolling bearing 11-rail connects rolling bearing 12-precise tracking housing
13-precise tracking heat insulation layer 14-precise tracking powder column 15-rail control combustion gas 90 degree of pipelines
16-precise tracking jet pipe 17-appearance control servo driver 18-appearance control servo fixing frame
Rolling bearing under the control of rolling bearing 20-attitude control engine upper bracket 21-appearance in the control of 19-appearance
22-attitude control engine lower support frame
Embodiment
Below in conjunction with drawings and Examples, the present invention is described in further detail.
The present invention is that a kind of rotation controls solid rocket divert and attitude control motor, as shown in Figure 1, comprises aircraft skin body 1, rail control power system 2 and appearance control power system 3.
As shown in Figure 2, rail control power system 2 comprises two precise tracking 4;
Precise tracking 4 as shown in Figure 3, comprises precise tracking housing 12, precise tracking heat insulation layer 13, precise tracking powder column 14, rail control combustion gas 90 degree of pipelines 15, precise tracking jet pipe 16;
Identical with Conventional solid rocket motor, bond between two between precise tracking housing 12 and precise tracking heat insulation layer 13, between precise tracking heat insulation layer 13 and precise tracking powder column 14; Rail control combustion gas 90 degree of pipelines 15 are connected with the eccentric blast tube of precise tracking housing 12 by screw thread; The ablation caused for avoiding high-temperature fuel gas, rail control combustion gas 90 degree of pipelines 15 and precise tracking jet pipe 16 adopt high temperature resistant composite (such as C/SiC, C/C etc.), adopt thread connecting mode between the two.
The large and small gear of driving gear set 9 is fixedly connected with the axle of precise tracking 4, the running shaft of rail control driver 7 respectively.
Rail control rolling bearing 10 is placed in the side of driving gear set 9 near precise tracking 4, be convenient to precise tracking 4 rotate, the axle interference fit of its inner ring and precise tracking 4, outer shroud and precise tracking support 8 are connected, and precise tracking support 8 is fixed on (link such as bolt does not illustrate in the drawings) on aircraft skin body 1 by links such as bolts.
Rail control driver 7 is positioned at rail control rolling bearing 10 side, and rail control driver 7 shell is fixedly connected with rail control servo fixing frame 6; Rail control servo fixing frame 6 is fixed on (link such as bolt does not illustrate in the drawings) on aircraft skin body 1 by links such as bolts.
Two precise tracking 4 are staggered relatively, can independently rotate, and therefore only to two motors axially retraining, need provide axially locating and support reaction at two ends by the shaft shoulder of respective rail control rolling bearing 10 and precise tracking 4.Place rail control between two motors and connect rolling bearing 11, make both rotation non-interference, the inner ring of bearing and outer shroud respectively with two engine shaft transition fit.
The effect of rail control power system 2 is that therefore the jet pipe 16 of precise tracking 4 should be in the centroidal planes of aircraft, and two motors are staggered relatively up and down, axis and aircraft dead in line for aircraft provides the power of crossrange maneuvering.Precise tracking structure is similar to Conventional solid motor, and rail control powder column 14 is cigarette burning, and the high-temperature fuel gas of generation, through the crooked pipeline 15 of 90 degree, is discharged by rail control jet pipe 16.During work, each precise tracking 4 integral-rotation, because its rotary inertia is comparatively large, rail control servo driver 7, by driving gear set 9 transmission, drives precise tracking 4 to rotate.
Appearance control power system 3 as shown in Figure 4 and Figure 5, comprises four attitude control engines 5.
The effect of appearance control power system is for aircraft provides the moment of pitching, driftage and rolling, and therefore attitude control engine 5 arranged off-centre is in the head end of aircraft or end, and running shaft is with aircraft axis being parallel but do not overlap.4 attitude control engines 5 circumferentially distribute.
Attitude control engine structure is identical with precise tracking structure, only has the difference of size, does not do repeat specification at this;
Appearance control driver 17 shell is fixedly connected with appearance control servo fixing frame 18, and appearance control servo fixing frame 18 is fixed on aircraft skin body 1 by links such as bolts.The axle of attitude control engine 5 is fixedly connected with by coupling with the running shaft of appearance control driver 17.To use in appearance control rolling bearing 21 under rolling bearing 19 and appearance control, so that attitude control engine 5 rotates.Two bearings is placed in the upper and lower end of attitude control engine 5 respectively, the axle interference fit of inner ring and attitude control engine 5, and outer shroud is connected with attitude control engine upper bracket 20, attitude control engine lower support frame 22 respectively.Attitude control engine upper bracket 20, attitude control engine lower support frame 22 are fixed on aircraft skin body 1 by links such as bolts.
During work, each attitude control engine 5 integral-rotation, its rotary inertia is less, and appearance control servo driver 17 can directly drive attitude control engine 5 to rotate.
On this basis, according to actual needs, the number of motor can be adjusted, as shown in Figure 6, comprise three precise tracking.For meet simultaneously precise tracking axis to overlap with aircraft axle and jet pipe in conplane requirement, precise tracking 23 is annular, is positioned over one heart outside precise tracking 24.Precise tracking 24 is identical with aforementioned precise tracking 4 structure with precise tracking 25, does not do more descriptions.Control for the independence realizing precise tracking 23 and precise tracking 24 rotates, the rotating shaft designs at precise tracking 23 two ends is hollow-core construction, and the running shaft of precise tracking 24 extends there through, and two engine revolution axles rotate with one heart and do not contact.Now, the housing diameter of precise tracking 23 is comparatively large, and the external diameter of corresponding aircraft casing is comparatively large, and precise tracking 25 exists larger space, therefore, four attitude control engines 26 can be arranged in precise tracking 25 around, to make compact structure.
Rail control power system of the present invention comprises multiple (two and more than) precise tracking, places up and down.The structure of each precise tracking is substantially identical, forms primarily of rail control thruster, rail control servo-system, rolling bearing and fixed connecting piece.The structural type of rail control thruster is identical with general solid engines, powder column axis and aircraft dead in line, and the high-temperature fuel gas that powder column burning produces, through the pipeline of bending 90 degree, is sprayed by jet pipe, produces horizontal thrust.A rolling bearing is respectively placed with, so that engine revolution before and after precise tracking.Bearing outer ring is fixed on aircraft skin body by support.Rail control driver is fixed on aircraft skin body by support, drives rail control thruster integral-rotation by driving gear set.
Appearance control power system of the present invention: comprise four attitude control engines, eccentric placement, circle distribution.The structure of attitude control engine is substantially identical with precise tracking.Difference is, the axle of appearance control driver is directly connected on attitude control engine, drives appearance control thruster integral-rotation.
Claims (1)
1. rotate and control a solid rocket divert and attitude control motor, comprise aircraft skin body, rail control power system and appearance control power system;
Rail control power system comprises two and above precise tracking;
Precise tracking comprises precise tracking housing, precise tracking heat insulation layer, precise tracking powder column, rail control combustion gas 90 degree of pipelines, precise tracking jet pipe; Bond between two between precise tracking housing and precise tracking heat insulation layer, between precise tracking heat insulation layer and precise tracking powder column; Rail control combustion gas 90 degree of pipeline one end are connected with the eccentric blast tube of precise tracking housing, the other end connecting rail control engine jet pipe, and precise tracking jet pipe is positioned at the centroidal planes of motor;
Each precise tracking is fixedly connected with a rail control servo driver, and rail control servo driver is fixedly connected with aircraft skin body by rail control servo fixing frame;
First coordinates a rail control rolling bearing inner ring respectively with the output shaft of last precise tracking, and the outer shroud of rail control rolling bearing is fixedly connected with precise tracking support, and precise tracking support is fixedly connected with aircraft skin body;
Precise tracking is staggered relatively, be provided with between two precise tracking rail control connect rolling bearing, the inner ring of rolling bearing and outer shroud respectively with two engine shaft transition fit;
Appearance control power system comprises three and above attitude control engine, and attitude control engine arranged off-centre, in motor head end or end, circumferentially distributes, and running shaft is with engine shaft line parallel but do not overlap;
Attitude control engine is connected by coupling with appearance control servo driver, and appearance control servo driver is fixedly connected with aircraft skin body by appearance control servo fixing frame;
The upper output shaft of attitude control engine coordinates rolling bearing inner ring in appearance control, and in appearance control, the outer shroud of rolling bearing is fixedly connected with attitude control engine upper bracket, and precise tracking support is fixedly connected with aircraft skin body;
Rolling bearing inner ring under the lower output shaft cooperation appearance control of attitude control engine, under appearance control, the outer shroud of rolling bearing is fixedly connected with attitude control engine lower support frame, and attitude control engine lower support frame is fixedly connected with aircraft skin body.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510046713.6A CN104747320B (en) | 2015-01-29 | 2015-01-29 | Rotate and control solid rocket divert and attitude control motor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510046713.6A CN104747320B (en) | 2015-01-29 | 2015-01-29 | Rotate and control solid rocket divert and attitude control motor |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104747320A true CN104747320A (en) | 2015-07-01 |
| CN104747320B CN104747320B (en) | 2016-03-02 |
Family
ID=53587480
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510046713.6A Expired - Fee Related CN104747320B (en) | 2015-01-29 | 2015-01-29 | Rotate and control solid rocket divert and attitude control motor |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104747320B (en) |
Cited By (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107940106A (en) * | 2017-11-10 | 2018-04-20 | 贵州航天林泉电机有限公司 | A kind of attitude control engine pipeline support component |
| CN108688829A (en) * | 2018-05-28 | 2018-10-23 | 北京航空航天大学 | Solid-liquid power sub-orbital booster |
| CN109606740A (en) * | 2018-12-28 | 2019-04-12 | 湖北航天技术研究院总体设计所 | A kind of thrust adjustment system and its method of adjustment based on PWM adjustment |
| CN109707536A (en) * | 2018-12-28 | 2019-05-03 | 湖北航天技术研究院总体设计所 | A kind of solid attitude control dynamical system based on energy control |
| CN110220001A (en) * | 2019-06-04 | 2019-09-10 | 上海新力动力设备研究所 | A kind of driving device for solid rail control engine gas regulating valve |
| CN110360023A (en) * | 2019-07-23 | 2019-10-22 | 西安航天动力研究所 | A kind of split type adjusting center force transmission rack |
| CN110761915A (en) * | 2019-10-31 | 2020-02-07 | 湖北航天技术研究院总体设计所 | Solid attitude control engine |
| CN111946489A (en) * | 2020-08-11 | 2020-11-17 | 北京机械设备研究所 | Gravity directional array type solid engine and thrust output directional control method |
| CN112112745A (en) * | 2020-11-23 | 2020-12-22 | 蓝箭航天空间科技股份有限公司 | Self-adaptive zero-returning control method and device for engine after shutdown of spacecraft |
| CN112282970A (en) * | 2020-10-26 | 2021-01-29 | 北京机械设备研究所 | Rotary rail-controlled solid engine |
| CN112431687A (en) * | 2020-11-12 | 2021-03-02 | 太原科技大学 | Foldable rail accuse engine high temperature heat-proof mechanism |
| CN112594091A (en) * | 2020-12-15 | 2021-04-02 | 北京理工大学 | Solid attitude and orbit control engine gas valve and control method thereof |
| CN113404618A (en) * | 2021-06-24 | 2021-09-17 | 北京机械设备研究所 | Solid pulse power device |
| CN113586285A (en) * | 2021-08-30 | 2021-11-02 | 湖北三江航天红林探控有限公司 | Quick response gas power device |
| CN113899256A (en) * | 2021-09-24 | 2022-01-07 | 湖北航天技术研究院总体设计所 | Compact environment solid attitude control installation structure and method and rocket |
| CN113958427A (en) * | 2021-10-17 | 2022-01-21 | 西安长峰机电研究所 | All-around rotary posture control spray pipe for solid posture and orbit control engine |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4967982A (en) * | 1988-11-07 | 1990-11-06 | General Dynamics Corp., Pomona Division | Lateral thruster for missiles |
| JP2000028300A (en) * | 1998-07-13 | 2000-01-28 | Mitsubishi Heavy Ind Ltd | Thruster apparatus |
| US6502384B1 (en) * | 1999-09-30 | 2003-01-07 | Ihi Aerospace Co., Ltd. | Side thruster of flying object |
| US20120211596A1 (en) * | 2011-02-18 | 2012-08-23 | Raytheon Company | Propulsion and maneuvering system with axial thrusters and method for axial divert attitude and control |
| WO2012156642A1 (en) * | 2011-05-19 | 2012-11-22 | Herakles | In-flight attitude control and direct thrust flight control system of a vehicle and craft comprising such a system |
| CN203335276U (en) * | 2013-05-29 | 2013-12-11 | 湖北航天技术研究院总体设计所 | Direction-adjustable spray pipe used for solid attitude and orbit control power system |
-
2015
- 2015-01-29 CN CN201510046713.6A patent/CN104747320B/en not_active Expired - Fee Related
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4967982A (en) * | 1988-11-07 | 1990-11-06 | General Dynamics Corp., Pomona Division | Lateral thruster for missiles |
| JP2000028300A (en) * | 1998-07-13 | 2000-01-28 | Mitsubishi Heavy Ind Ltd | Thruster apparatus |
| US6502384B1 (en) * | 1999-09-30 | 2003-01-07 | Ihi Aerospace Co., Ltd. | Side thruster of flying object |
| US20120211596A1 (en) * | 2011-02-18 | 2012-08-23 | Raytheon Company | Propulsion and maneuvering system with axial thrusters and method for axial divert attitude and control |
| WO2012156642A1 (en) * | 2011-05-19 | 2012-11-22 | Herakles | In-flight attitude control and direct thrust flight control system of a vehicle and craft comprising such a system |
| CN203335276U (en) * | 2013-05-29 | 2013-12-11 | 湖北航天技术研究院总体设计所 | Direction-adjustable spray pipe used for solid attitude and orbit control power system |
Non-Patent Citations (3)
| Title |
|---|
| 张德雄等: ""动能拦截器的固体推进剂轨控和姿控系统"", 《飞航导弹》 * |
| 李瑛等: ""固体推进剂姿轨控系统高温高压燃气阀 "", 《中国宇航学会2005年固体火箭推进第22届年会 》 * |
| 谷良贤等: ""动能拦截器姿控与轨控方案设计及仿真 "", 《西北工业大学学报 》 * |
Cited By (21)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107940106A (en) * | 2017-11-10 | 2018-04-20 | 贵州航天林泉电机有限公司 | A kind of attitude control engine pipeline support component |
| CN107940106B (en) * | 2017-11-10 | 2019-09-13 | 贵州航天林泉电机有限公司 | A kind of attitude control engine pipeline support component |
| CN108688829A (en) * | 2018-05-28 | 2018-10-23 | 北京航空航天大学 | Solid-liquid power sub-orbital booster |
| CN109606740A (en) * | 2018-12-28 | 2019-04-12 | 湖北航天技术研究院总体设计所 | A kind of thrust adjustment system and its method of adjustment based on PWM adjustment |
| CN109707536A (en) * | 2018-12-28 | 2019-05-03 | 湖北航天技术研究院总体设计所 | A kind of solid attitude control dynamical system based on energy control |
| CN110220001A (en) * | 2019-06-04 | 2019-09-10 | 上海新力动力设备研究所 | A kind of driving device for solid rail control engine gas regulating valve |
| CN110360023A (en) * | 2019-07-23 | 2019-10-22 | 西安航天动力研究所 | A kind of split type adjusting center force transmission rack |
| CN110761915A (en) * | 2019-10-31 | 2020-02-07 | 湖北航天技术研究院总体设计所 | Solid attitude control engine |
| CN111946489A (en) * | 2020-08-11 | 2020-11-17 | 北京机械设备研究所 | Gravity directional array type solid engine and thrust output directional control method |
| CN112282970A (en) * | 2020-10-26 | 2021-01-29 | 北京机械设备研究所 | Rotary rail-controlled solid engine |
| CN112282970B (en) * | 2020-10-26 | 2021-08-24 | 北京机械设备研究所 | Rotary rail-controlled solid engine |
| CN112431687A (en) * | 2020-11-12 | 2021-03-02 | 太原科技大学 | Foldable rail accuse engine high temperature heat-proof mechanism |
| CN112431687B (en) * | 2020-11-12 | 2022-07-08 | 太原科技大学 | Foldable rail accuse engine high temperature heat-proof mechanism |
| CN112112745A (en) * | 2020-11-23 | 2020-12-22 | 蓝箭航天空间科技股份有限公司 | Self-adaptive zero-returning control method and device for engine after shutdown of spacecraft |
| CN112112745B (en) * | 2020-11-23 | 2021-06-01 | 蓝箭航天空间科技股份有限公司 | Self-adaptive zero-returning control method and device for engine after shutdown of spacecraft |
| CN112594091A (en) * | 2020-12-15 | 2021-04-02 | 北京理工大学 | Solid attitude and orbit control engine gas valve and control method thereof |
| CN112594091B (en) * | 2020-12-15 | 2021-12-07 | 北京理工大学 | Solid attitude and orbit control engine gas valve and control method thereof |
| CN113404618A (en) * | 2021-06-24 | 2021-09-17 | 北京机械设备研究所 | Solid pulse power device |
| CN113586285A (en) * | 2021-08-30 | 2021-11-02 | 湖北三江航天红林探控有限公司 | Quick response gas power device |
| CN113899256A (en) * | 2021-09-24 | 2022-01-07 | 湖北航天技术研究院总体设计所 | Compact environment solid attitude control installation structure and method and rocket |
| CN113958427A (en) * | 2021-10-17 | 2022-01-21 | 西安长峰机电研究所 | All-around rotary posture control spray pipe for solid posture and orbit control engine |
Also Published As
| Publication number | Publication date |
|---|---|
| CN104747320B (en) | 2016-03-02 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN104747320B (en) | Rotate and control solid rocket divert and attitude control motor | |
| US3094072A (en) | Aircraft, missiles, missile weapons systems, and space ships | |
| US9701395B2 (en) | Contra-rotating open rotor distributed propulsion system | |
| US9849970B2 (en) | Turbo engine with propeller(s) for an aircraft with a system for changing the pitch of the propeller | |
| CN108895921A (en) | Hydrogen peroxide attitude control system for solid-liquid hybrid power carrier rocket | |
| US8530809B2 (en) | Ring gear control actuation system for air-breathing rocket motors | |
| CN105736178B (en) | Combined cycle engine | |
| US4967982A (en) | Lateral thruster for missiles | |
| CN109184948B (en) | Steering spray pipe for short-distance or vertical take-off and landing aircraft | |
| AU2008324560B2 (en) | Autonomic rotor system for an aircraft | |
| US11506066B2 (en) | Fan module with variable pitch blades | |
| CN103195612A (en) | Multifunctional turbofan jet engine | |
| WO2020073683A1 (en) | Separable combined range-extending system and method for aircraft | |
| US9500456B2 (en) | Combined steering and drag-reduction device | |
| CN113958427A (en) | All-around rotary posture control spray pipe for solid posture and orbit control engine | |
| EP2920071A1 (en) | Helicopter | |
| CN102826220B (en) | Thrust device capable of balancing reactive torque | |
| US2356746A (en) | Jet propulsion device | |
| CA2308131C (en) | Exit area control mechanism for convergent divergent nozzles | |
| CN106438107A (en) | Blade propeller side jet type aeroengine | |
| CN1523318A (en) | Air-actuated cross rotor and ring form tail wing for ball ammunition and aircraft | |
| RU2470834C1 (en) | Aircraft | |
| RU2338150C1 (en) | Birotating jet shell | |
| RU2767645C1 (en) | Anti-aircraft guided missile 9m96 | |
| RU2475417C1 (en) | Flaying saucer-type aircraft |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20160302 Termination date: 20170129 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |