CN104696108A - Servo mechanism driven by rocket engine high-pressure kerosene - Google Patents
Servo mechanism driven by rocket engine high-pressure kerosene Download PDFInfo
- Publication number
- CN104696108A CN104696108A CN201310666218.6A CN201310666218A CN104696108A CN 104696108 A CN104696108 A CN 104696108A CN 201310666218 A CN201310666218 A CN 201310666218A CN 104696108 A CN104696108 A CN 104696108A
- Authority
- CN
- China
- Prior art keywords
- valve
- oil
- servomechanism
- pressure
- low pressure
- 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.)
- Pending
Links
Landscapes
- Fluid-Pressure Circuits (AREA)
Abstract
The invention discloses a servo mechanism driven by rocket engine high-pressure kerosene. The servo mechanism driven by rocket engine high-pressure kerosene comprises a motor, a variable pump, a flow-limiting valve, an overflow valve, a hydraulic control one-way valve, a one-way valve, a refined oil filter, a coarse oil filter, an electro-hydraulic servo valve, a zero position lock, an actuator, a feedback potentiometer, a high and low pressure filling interface, a piston rod, a servo amplifier and a high and low pressure plastic soft tube; the interior oil path of the mechanism is isolated from the outside world through the one-way valve and the hydraulic control one-way valve; the flow-limiting valve and the overflow valve are independently connected with the internal oil path of the mechanism. The servo mechanism driven by rocket engine high-pressure kerosene has the advantages that the hydraulic type zero position lock is adopted, the second level servo mechanism does not need to be started in advance to stabilize the zero position before the engine is started, the intermediate frequency motor is used for offering the power, the battery is not needed for the arrow, and then the weight is reduced, the development difficulty of the battery for the arrow is reduced, and the minitype spacecraft can be quickly launched.
Description
Technical field
The present invention relates to carrier space vehicle control system servomechanism, particularly a kind of servomechanism utilizing rocket motor high pressure kerosene to drive.
Background technique
CZ-6 Launch Vehicle Series secondary adopts the oxygen kerosene motor (YF-115G I) of a sway in both directions, the power source of high pressure kerosene as two stage servomechanism is drawn after petrolift, affect motor to provide pitching, driftage control moment, thus realize the Attitude Control and Stabilization of rocket pitching, driftage, rolling.Secondary servo-system belongs to a subtense angle of control system, is made up of a servocontroller and two two stage servomechanisms.
The servomechanism (abbreviation servomechanism) utilizing rocket motor high pressure kerosene to drive is the actuator in servo control loop, and drived control object---engine jet pipe waves, and the flight attitude completing rocket controls.Because CZ-6 rocket requires whole arrow horizontal transport, " small-sized, rapid fire " feature, require that the necessary weight of servomechanism is little, response is fast, and thrust is large, must develop the servomechanism that novel direct employing rocket motor high pressure kerosene drives.
Summary of the invention
It is little that the present invention aims to provide a kind of weight, and response is fast, the servomechanism that thrust is large, thus completes small-sized Spacecraft Launch task fast, shortens and survey the cycle of sending out, and reduces launch cost.
For reaching above-mentioned purpose, the invention provides a kind of servomechanism utilizing rocket motor high pressure kerosene to drive, primarily of supplementary energy part and servo actuator part composition.Comprise motor, variable displacement pump, flow-limiting valve, relief valve, Pilot operated check valve, one-way valve, oil filter, high-pressure safety valve, low-pressure safety valve, electrohydraulic control, zero-bit lock, actuator, feedback potentiometer, high low pressure filling interface, bypass valve, pressure transducer and high low pressure plastic flexible pipe etc.Servomechanism hydraulic schematic diagram is shown in Fig. 1.
Described servomechanism utilizes high cracking pressure one-way valve and Pilot operated check valve isolation;
Described servomechanism high low pressure drainage module is communicated with individually by body: flow-limiting valve, relief valve are drainage state voltage stabilizing current-limiting apparatus, and other valve part is safety protection, filtration, filling effect.
Described servomechanism arranges the slightly low supplementary energy of pressure: motor-pump is mainly used in motor reset to zero, system-level ground test (zero load), engine cold pendulum and servo mechanism unit test.When functional check is carried out on ground, worked by electric-motor pump, oil hydraulic pump is from fuel tank oil suction, accumulator plays voltage stabilizing accumulation of energy effect, is filtered by essential oil filter, after then zero-bit lock unlocks, enter electrohydraulic control, by the position of feedback potentiometer monitoring piston, the direct oil sump tank of low pressure oil, servomechanism internal oil passages is separated by one-way valve and Pilot operated check valve and the external world.
Described servomechanism arranges hydraulic null lock.
The invention has the advantages that, owing to have employed hydraulic type zero-bit lock, before engine ignition, two stage servomechanism does not need pre-cooling to stablize zero-bit, therefore mid-frequency motor is adopted to power, do not need battery on arrow, significantly reduce weight, decrease the development difficulty of battery on arrow.And directly utilize kerosene as medium, without the need to providing the high drive energy for servomechanism.
Accompanying drawing explanation
By reading the detailed description done non-limiting example done with reference to the following drawings, other features, objects and advantages of the present invention will become more obvious:
Fig. 1 is the servomechanism schematic diagram utilizing rocket motor high pressure kerosene to drive of the present invention;
Fig. 2 is servomechanism hydraulic schematic diagram of the present invention;
Fig. 3 is drainage module diagram of the present invention;
Fig. 4 is hydraulic null lock construction schematic diagram of the present invention;
In accompanying drawing, same or analogous reference character represents same or analogous parts.
Embodiment
The present invention is set forth further below in conjunction with accompanying drawing.The preferred embodiment of the present invention is just not used in for helping to set forth the present invention and limits the scope of the invention.The preferred embodiment of the present invention does not have all details of detailed descriptionthe, does not limit the embodiment that this invention is only described yet.Obviously, according to the content of this specification, can make many modifications and variations.This specification is chosen and is specifically described these embodiments, is to explain principle of the present invention and practical application better, thus makes art technician can utilize the present invention well.The present invention is only subject to the restriction of claims and four corner and equivalent.After the content of having read the present invention's record, those skilled in the art can make various changes or modifications the present invention, and these equivalence changes and modification fall into the scope of the claims in the present invention equally.
Now describe in detail according to a kind of servomechanism utilizing rocket motor high pressure kerosene to drive of the present invention.
Be servomechanism hydraulic schematic diagram of the present invention as shown in Figure 2, wherein motor-pump is supplementary energy, is mainly used in motor reset to zero, system-level ground test (zero load), engine cold pendulum and servo mechanism unit test.Flow-limiting valve, relief valve are drainage state voltage stabilizing current-limiting apparatus, and other valve part is safety protection, filtration, filling effect.Owing to have employed hydraulic type zero-bit lock, before engine ignition, two stage servomechanism does not need pre-cooling to stablize zero-bit, therefore adopts mid-frequency motor to power, does not need battery on arrow, significantly reduce weight, decrease the development difficulty of battery on arrow.During drainage, high pressure oil flows into servomechanism through high pressure teflon hose, first filters filter by thick oil, carry out voltage stabilizing current limliting through flow-limiting valve and relief valve again, afterwards again by essential oil filter filter, after open zero-bit lock after, enter electrohydraulic control, and then promote actuator work.By being arranged on feedback potentiometer in piston rod signal back to servoamplifier, the position of the action of monitoring servomechanism.High/low pressure safety valve is installed in system and carries out safety protection.Low pressure oil is through Pilot operated check valve, and thick oil filter, postbacks motivation by low pressure teflon hose.
When functional check is carried out on ground, worked by electric-motor pump, oil hydraulic pump is from fuel tank oil suction, accumulator plays voltage stabilizing accumulation of energy effect, is filtered by essential oil filter, after then zero-bit lock unlocks, enter electrohydraulic control, by the position of feedback potentiometer monitoring piston, the direct oil sump tank of low pressure oil, servomechanism internal oil passages is separated by one-way valve and Pilot operated check valve and the external world.
Hydraulic null lock working procedure is as Fig. 4:
In a non-operative state, valve, under the elastic force of spring promotes, is in closed condition, A import and A exports, B import and B export obstructed.In working order, when the pressure of control chamber P is greater than setting value, push rod overcomes the elastic force of spring under the effect of P mouth oil liquid pressure, and promote valve and open, A import and A export, B import and B export conducting.The oil liquid pressure now born due to A, B chamber push rod is equal, so A, B chamber valve is opened simultaneously.When the Pressure Drop of control chamber P is to setting value, spring force overcomes hydraulic coupling, and promote valve and close, A import and A export obstructed, and B import and B export obstructed.
For guaranteeing that hydraulic null is locked two chambeies and can be opened simultaneously, hydraulic null lock is designed to symmetric type, and quote servovalve inlet high pressure oil as controlling oil, simultaneously, after pinning pressurized strut two cavity oil liquid, for preventing two cavity oil liquid from causing the rising of inner fluid due to the rising of temperature, locking between inner sealing in pressurized strut two chamber and zero-bit and high-pressure safety valve has been installed.
The invention has the advantages that owing to have employed hydraulic type zero-bit lock, before engine ignition, two stage servomechanism does not need pre-cooling to stablize zero-bit, therefore adopts mid-frequency motor to power, does not need battery on arrow, significantly reduce weight, decrease the development difficulty of battery on arrow.And directly utilize kerosene as medium, without the need to providing the high drive energy for servomechanism.
Claims (6)
1. the servomechanism utilizing rocket motor high pressure kerosene to drive, comprise motor, variable displacement pump, flow-limiting valve, relief valve, Pilot operated check valve, one-way valve, essential oil filter, the filter of thick oil, electrohydraulic control, zero-bit lock, actuator, feedback potentiometer, high low pressure filling interface, piston rod, servoamplifier and high low pressure plastic flexible pipe, it is characterized in that described in-house oil circuit is isolated from the outside by described one-way valve and Pilot operated check valve; Described flow-limiting valve is communicated with described in-house oil circuit with relief valve is independent; During drainage, high pressure oil flows into described servomechanism through high-pressure plastic flexible pipe, first filters filter by thick oil, carry out voltage stabilizing current limliting through flow-limiting valve and relief valve again, after being filtered by essential oil filter more afterwards, open described zero-bit lock, enter electrohydraulic control, promote actuator work; Described feedback potentiometer is arranged in described piston rod, gives described servoamplifier signal back, the position of the action of monitoring servomechanism; Low pressure oil is through described Pilot operated check valve, and thick oil filter, postbacks motivation by low pressure plastic flexible pipe.
2. servomechanism according to claim 1, it is characterized in that described mechanism also comprises high-pressure safety valve, described actuator comprises pressurized strut, and described high-pressure safety valve is arranged on described pressurized strut two chamber and described zero-bit is locked between inner sealing place.
3. servomechanism according to claim 1, is characterized in that described zero-bit lock is designed to symmetric type, and quotes servovalve inlet high pressure oil as controlling oil.
4. servomechanism according to claim 1, is characterized in that described zero-bit lock is hydraulic type.
5. servomechanism according to claim 1, it is characterized in that described mechanism also comprises accumulator, when functional check is carried out on ground, described motor and variable displacement pump work, oil hydraulic pump is from fuel tank oil suction, filtered by essential oil filter, after described accumulator voltage stabilizing accumulation of energy, zero-bit lock unlocks, and enters electrohydraulic control, by the position of described feedback potentiometer monitoring piston, low pressure oil is by the direct oil sump tank of flexible pipe.
6. servomechanism according to claim 1, is characterized in that described mechanism also comprises low-pressure safety valve, and described safety valve is contained between described low pressure filler and Pilot operated check valve.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310666218.6A CN104696108A (en) | 2013-12-10 | 2013-12-10 | Servo mechanism driven by rocket engine high-pressure kerosene |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310666218.6A CN104696108A (en) | 2013-12-10 | 2013-12-10 | Servo mechanism driven by rocket engine high-pressure kerosene |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104696108A true CN104696108A (en) | 2015-06-10 |
Family
ID=53343573
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310666218.6A Pending CN104696108A (en) | 2013-12-10 | 2013-12-10 | Servo mechanism driven by rocket engine high-pressure kerosene |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104696108A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105022861A (en) * | 2015-06-11 | 2015-11-04 | 北京精密机电控制设备研究所 | Method for determining oil storage quantity of extrusion type servo system for carrier rocket |
| CN105332821A (en) * | 2015-10-16 | 2016-02-17 | 北京精密机电控制设备研究所 | Servo mechanism integrated with hydrogen turbine pump and servo control method |
| CN113252353A (en) * | 2021-04-06 | 2021-08-13 | 浙江蓝箭航天空间科技有限公司 | Horizontal test method for electromechanical servo mechanism of carrier rocket and computer storage medium |
| CN113638891A (en) * | 2021-04-29 | 2021-11-12 | 北京精密机电控制设备研究所 | Turbine pump test system |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4085909A (en) * | 1976-10-04 | 1978-04-25 | Ford Motor Company | Combined warm gas fin and reaction control servo |
| US5726877A (en) * | 1993-12-09 | 1998-03-10 | Mannesmann Rexroth Gmbh | Method for the adaptive adjustment of the control parameters of an electro-hydraulic axis of motion |
| CN201034807Y (en) * | 2007-04-25 | 2008-03-12 | 上海敏泰液压件有限公司 | Test bench of vaporizing oil servo gear unit test system |
| CN102767446A (en) * | 2012-06-05 | 2012-11-07 | 北京航空航天大学 | Rocket-mounted control circuit for solid/liquid power sounding rocket |
| CN103075393A (en) * | 2011-10-26 | 2013-05-01 | 北京精密机电控制设备研究所 | Novel multi-redundancy electromechanical hydrostatic servo mechanism |
| CN103075394A (en) * | 2011-10-26 | 2013-05-01 | 北京精密机电控制设备研究所 | Four-redundancy valve-controlled electro-hydraulic servo system |
-
2013
- 2013-12-10 CN CN201310666218.6A patent/CN104696108A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4085909A (en) * | 1976-10-04 | 1978-04-25 | Ford Motor Company | Combined warm gas fin and reaction control servo |
| US5726877A (en) * | 1993-12-09 | 1998-03-10 | Mannesmann Rexroth Gmbh | Method for the adaptive adjustment of the control parameters of an electro-hydraulic axis of motion |
| CN201034807Y (en) * | 2007-04-25 | 2008-03-12 | 上海敏泰液压件有限公司 | Test bench of vaporizing oil servo gear unit test system |
| CN103075393A (en) * | 2011-10-26 | 2013-05-01 | 北京精密机电控制设备研究所 | Novel multi-redundancy electromechanical hydrostatic servo mechanism |
| CN103075394A (en) * | 2011-10-26 | 2013-05-01 | 北京精密机电控制设备研究所 | Four-redundancy valve-controlled electro-hydraulic servo system |
| CN102767446A (en) * | 2012-06-05 | 2012-11-07 | 北京航空航天大学 | Rocket-mounted control circuit for solid/liquid power sounding rocket |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105022861A (en) * | 2015-06-11 | 2015-11-04 | 北京精密机电控制设备研究所 | Method for determining oil storage quantity of extrusion type servo system for carrier rocket |
| CN105022861B (en) * | 2015-06-11 | 2018-05-22 | 北京精密机电控制设备研究所 | A kind of carrier rocket definite method of squash type servo-drive system oil storage |
| CN105332821A (en) * | 2015-10-16 | 2016-02-17 | 北京精密机电控制设备研究所 | Servo mechanism integrated with hydrogen turbine pump and servo control method |
| CN113252353A (en) * | 2021-04-06 | 2021-08-13 | 浙江蓝箭航天空间科技有限公司 | Horizontal test method for electromechanical servo mechanism of carrier rocket and computer storage medium |
| CN113252353B (en) * | 2021-04-06 | 2023-09-22 | 浙江蓝箭航天空间科技有限公司 | Carrier rocket electromechanical servo mechanism horizontal test method and computer storage medium |
| CN113638891A (en) * | 2021-04-29 | 2021-11-12 | 北京精密机电控制设备研究所 | Turbine pump test system |
| CN113638891B (en) * | 2021-04-29 | 2024-03-15 | 北京精密机电控制设备研究所 | Turbine pump test system |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN104696108A (en) | Servo mechanism driven by rocket engine high-pressure kerosene | |
| ES2697150T3 (en) | Hydraulic strut assembly for semi-lever landing gear | |
| CN105443451B (en) | A kind of multikilowatt waves output triple redundance electrohydraulic digital servo-drive system | |
| US9440829B2 (en) | Adjusting damping properties of an in-line passive heave compensator | |
| US20230356557A1 (en) | Hydraulic Fluid Supply System, In Particular For A Suspension System | |
| CN103075393A (en) | Novel multi-redundancy electromechanical hydrostatic servo mechanism | |
| CN109630317A (en) | Rail attitude control integration space propulsion system based on electrodynamic pump | |
| CN104421225A (en) | Marine steering gear hydraulic loading test apparatus | |
| CN112594233B (en) | Pressure boost oil feeding system | |
| KR20160130231A (en) | Travel and work functions integrated into a hydraulic hybrid system | |
| CN204646828U (en) | Servo-hydraulic final controlling element | |
| US10969035B2 (en) | Redundant vehicle control systems | |
| CN103670801A (en) | Multi-redundancy pump control servo mechanism for thrust vector control of liquid oxygen kerosene engine | |
| CN104196784B (en) | A kind of cabin section integration electrohydraudic servomechanism | |
| EP3102450B1 (en) | Powerboost hub | |
| CN105523197A (en) | Triple-redundancy digital servo system for quickly responding to 10kW-grade linear output | |
| CN103321975B (en) | A kind of low-high pressure soft start hydraulic oil source system | |
| CN103075394B (en) | Four-redundancy valve-controlled electro-hydraulic servo system | |
| CN103620232A (en) | Electro-hydraulic hybrid drive device | |
| CN105383675A (en) | EHA-VPVM drive steering engine system | |
| CN112594093A (en) | Control system of reciprocating displacement pump for solid-liquid rocket engine | |
| CN107091253A (en) | A kind of hydraulic pressure performs equipment | |
| CN203463382U (en) | Low-high pressure soft start hydraulic oil source system | |
| CN203644243U (en) | Aircraft thrust simulation system | |
| CN108286544B (en) | Aviation pump high speed drive servo system with throttle volume composite control |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20150610 |