CN102975869A - Detector propelling module and working method thereof - Google Patents
Detector propelling module and working method thereof Download PDFInfo
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- CN102975869A CN102975869A CN2012105384136A CN201210538413A CN102975869A CN 102975869 A CN102975869 A CN 102975869A CN 2012105384136 A CN2012105384136 A CN 2012105384136A CN 201210538413 A CN201210538413 A CN 201210538413A CN 102975869 A CN102975869 A CN 102975869A
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- propulsion module
- detector
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- propulsion
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Abstract
The invention relates to a detector propelling module, which comprises a front cover arranged on the front end of the propelling module. The detector propelling module further comprises an electronic unit arranged inside the front cover, a propelling module body with an accommodation structure inside, a fuel unit arranged inside the accommodation structure, and a fixing structure for fixing the fuel unit, wherein the electronic unit is used for distributing power, supplying power and controlling the propelling module, the propelling module is abutted with a carrier rocket and ground support equipment through an interface structure, and a power unit arranged outside the propelling module is used for accelerating, braking and adjusting the posture of the propelling module; and the working method of the propelling module comprises the motions of fire galloping, approaching fire braking, surrounding fire flying and the like. The detector propelling can be used for orbit transportation tasks in Mars and other deep-sky interplanetary detections, the structure is simple, the design risks are smaller, and the detector propelling module is particularly suitable for the long-distance deep-sky detection task of an unmanned detector.
Description
Technical field
The present invention relates to the space flight field of detecting, particularly relate to the propulsion module of the detector of a kind of Mars or other planets.
Background technology
At present, the plan of China's mars exploration is directly sent into the earth to fiery escape orbit by the CZ-3C carrier rocket with Mars probes (around detector, propulsion module, hard landing device).Entering Mars probes behind the escape orbit need to also finish and just can enter predetermined ring fire track after the processes such as the fire flight of running quickly, nearly fire preparing are moving, attitude adjustment and carry out ring fire flight
Propulsion module is responsible for the rail control to fiery process, and nearly fire preparing is moving, and after propulsion module ran out of gas, propulsion module was abandoned.
Summary of the invention
For solving the problems of the technologies described above, the invention provides a kind of detector propulsion module, comprise a protecgulum, it is characterized in that, comprising:
Be located at the electronic unit of described protecgulum inside, described electronic unit comprises a power module and an electric control module, and described power module is used for distribution and the power supply of this propulsion module, and described electric control module is finished the control to this propulsion module;
The one propulsion module body that is connected with described protecgulum, described propulsion module body interior is provided with an accommodating structure;
One is located at the fuel unit in the described accommodating structure, and described fuel unit provides fuel for this propulsion module;
One fixed sturcture that is connected with described propulsion module body is used for fixing described fuel unit;
One interface structure that is connected with described propulsion module body is used for and the docking of carrier rocket and ground-support equipment;
And be installed in this propulsion module outside power unit, described power unit is used to this propulsion module acceleration, braking and attitude adjustment.
Preferably, described power module is used for distribution and the power supply of this propulsion module, and multipath electrovalve and the electric heating sheets of described electric control module by controlling this propulsion module finished control to the propulsion module power unit, monitors simultaneously and control the temperature in the propulsion module.
Preferably, described propulsion module body is cylindrical, and its inner accommodating structure is honeycomb type tubular sandwich structure, and this honeycomb type tubular sandwich structure comprises the cylinder of a plurality of hollows; The material of described this external surface of propulsion module adopts carbon fiber skin, and the material of described honeycomb type tubular sandwich structure adopts metallic aluminium.
Preferably, described fuel unit comprises that a plurality of elliposoidal tanks and that are full of fuel are full of the composite gas cylinder of unreactable gas, and described gas cylinder is used for controlling described elliposoidal tank makes it enter position to be consumed.
Preferably, the quantity of described cylinder and described elliposoidal tank and bodily form coupling, described each elliposoidal tank is installed in respectively in each cylinder.
Preferably, described fixed sturcture comprises the first tank support that is fixed on described propulsion module body front end and is fixed on the second tank support of described propulsion module body rear end, described the first tank support is provided with a plurality of the first circular holes and one second circular hole, and described the second support is provided with first circular hole identical with described the first tank support the first circular hole quantity; Described the first circular hole and described elliposoidal tank coupling also fix the position of described elliposoidal tank, and described the second circular hole and described gas cylinder coupling also fix the position of described gas cylinder.
Preferably, described power unit comprises a main thrust device and an attitude thruster, and described main thrust device is installed in described fixed sturcture, and described attitude thruster is installed in described this external surface of propulsion module.
Preferably, described main thrust device comprises the sustainer, main engine of a 450N, and described attitude thruster comprises that 2 in pitching driving engine, the 10N driftage driving engine of 10N selects the rolling driving engine of 2 and 10N to select 8.
Preferably, described interface structure cooperates riveted joint to be connected with described propulsion module body with being connected by glueing joint.
The present invention also provides a kind of method of work of detector propulsion module simultaneously, and following steps are carried out in its fire flight that is used for running quickly successively:
Ground send action, this course of action propulsion module are in dormant state and bear emission process and cause mechanics overload, vibration, noise circumstance;
The fire of running quickly moves, and the fiery track correction of running quickly is finished in this action, track is kept and run quickly fire section appearance control propelling;
Nearly fire preparing is moving, and this action reduces the flying speed of detector, and detector is caught by Mars gravitation, enters a highly elliptic orbit;
The ring fire flare maneuver, this action is adjusted the ring fire track profile of detector, makes detector enter planned orbit, and propulsion module separated with detector after detector entered planned orbit.
Preferably, carry out in the send action process of ground at propulsion module, propulsion module bottom is connected with the interface adapter of carrier rocket, the top be connected around device, two hard landing device sides are hung on propulsion module; In the fiery course of action of running quickly, propulsion module is positioned at the afterbody of detector, and Mars is positioned at the detector top around device; In the moving process of nearly fire preparing, propulsion module is positioned at the front portion of detector flight.
The invention provides a kind of detector propulsion module and method of work thereof, can finish to planetary probe keep at track correction, track in the planet transfer process, attitude adjustment and the tasks such as nearly fire preparing is moving, ring fire flight; The present invention can be used for mars exploration and the interspace detection track transportation burden of other deep spaces, and it is simple in structure, and the design risk is less, is particularly useful for the remote survey of deep space task of unmanned probing device.
Description of drawings
Fig. 1 is a kind of detector propulsion module structural representation provided by the invention;
Fig. 2 is a kind of detector propulsion module working process scheme drawing provided by the invention.
The specific embodiment
Referring to the accompanying drawing that the embodiment of the invention is shown, hereinafter the present invention will be described in more detail.Yet the present invention can be with many multi-form realizations, and should not be construed as the restriction of the embodiment that is subjected in this proposition.On the contrary, it is abundant and complete open in order to reach proposing these embodiment, and makes those skilled in the art understand scope of the present invention fully.In these accompanying drawings, for clarity sake, may zoom in or out size and the relative size in layer and zone.
Embodiment
As shown in Figure 1, a kind of detector propulsion module provided by the invention, comprise the protecgulum 1 of being located at this propulsion module front end, also comprise the electronic unit of being located at protecgulum 1 inside, electronic unit comprises a power module and an electric control module, described power module is used for distribution and the power supply of this propulsion module, and described electric control module is finished the control to this propulsion module;
The one propulsion module body 2 that is connected with described protecgulum, propulsion module body 2 inside are provided with an accommodating structure;
One is located at the fuel unit in the described accommodating structure, and described fuel unit provides fuel for this propulsion module;
One fixed sturcture that is connected with described propulsion module body is used for fixing described fuel unit;
One interface structure that is connected with described propulsion module body is used for and the docking of carrier rocket and ground-support equipment;
And be installed in this propulsion module outside power unit, described power unit is used to this propulsion module acceleration, braking and attitude adjustment.
In the present embodiment, power module is used for distribution and the power supply of this propulsion module, and multipath electrovalve and the electric heating sheets of described electric control module by controlling this propulsion module finished control to the propulsion module power unit, monitors simultaneously and control the temperature in the propulsion module.Concrete, power module mainly is to finish propulsion module run quickly distribution and power supply after the ring fire track separates in the fiery flight course; Electric control module comprises control mechanism, execution unit propulsive mechanism and is located at the two middle switching mechanism, wherein the function of switching mechanism is the control command that receives control mechanism, and control exactly various electromagnetic valves (about 41 tunnel) and the electric heating sheets (about 20 tunnel) of propulsive mechanism according to these instructions on time, gather simultaneously all temperature simulation amounts in the propulsion module, and the temperature simulation amount converted to concrete data data, will finish solid inspection and temperature control to this propulsion module according to the temperature control rule of setting behind the temperature data uploading control mechanism simultaneously.
Described fuel unit comprises that a plurality of elliposoidal tanks 3 and that are full of fuel are full of the composite gas cylinder of the gas of inertia, and gas cylinder is used for control elliposoidal tank 3 makes it enter position to be consumed.In this example, be provided with altogether that six bottles of volumes are long-pending to be the elliposoidal tank 3 of 100L, it is fuel that its inside is full of double base N2O4/MMH; Gas cylinder volume is 30L, and inside is full of helium or nitrogen, and its air pressure inside is 35MPa.Each cylinder in the propulsion module body 2 and the quantity of elliposoidal tank 3 and bodily form coupling, each elliposoidal tank 3 is installed in respectively in each cylinder.
Described fixed sturcture comprises the first tank support that is fixed on propulsion module body 2 front ends and the second tank support that is fixed on propulsion module body 2 rear ends, the first tank support is provided with a plurality of the first circular holes and one second circular hole, and the second tank support is provided with first circular hole identical with the first tank support the first circular hole quantity; Described the first circular hole and elliposoidal tank 3 couplings also fix the position of elliposoidal tank 3, and described the second circular hole and gas cylinder coupling also fix the position of described gas cylinder.
Described power unit comprises a main thrust device and attitude thruster, and the main thrust device comprises the sustainer, main engine of a 450N; The attitude thruster comprises that 2 in pitching driving engine, the 10N driftage driving engine of 10N selects the rolling driving engine of 2 and 10N to select 8.Interface structure cooperates riveted joint to be connected with propulsion module body 2 with being connected by glueing joint.
As shown in Figure 2, the method for work of a kind of detector propulsion module provided by the invention, the method comprise the following action that this propulsion module is done:
Ground send action, this course of action propulsion module are in dormant state and bear emission process and cause mechanics overload, vibration, noise circumstance;
The fire of running quickly moves, and the fiery track correction of running quickly is finished in this action, track is kept and run quickly fire section appearance control propelling;
Nearly fire preparing is moving, and this action reduces the flying speed of detector, and detector is caught by Mars gravitation, enters a highly elliptic orbit;
The ring fire flare maneuver, this action is adjusted the ring fire track profile of detector, makes detector enter planned orbit, and propulsion module separated with detector after detector entered planned orbit.
Each action is carried out successively, propulsion module is made the ground send action in A flies to the process of B, do the fire action of running away from C flies to the process of F, and it is moving to make nearly fire preparing from G flies to the process of H, make the ring fire flare maneuver in the I stage, and finally separate with detector.
Send action propulsion module position on detector during each action also is constantly to change, wherein:
Carry out in the send action process of ground at propulsion module, propulsion module bottom is connected with the interface adapter of carrier rocket, the top be connected around device, two hard landing device sides are hung on propulsion module; In the fiery course of action of running quickly, propulsion module is positioned at the afterbody of detector, and Mars is positioned at the detector top around device; In the moving process of nearly fire preparing, propulsion module is positioned at the front portion of detector flight.
More than the disclosed preferred embodiment of the present invention just be used for helping to set forth the present invention.Preferred embodiment does not have all details of detailed descriptionthe, does not limit this invention yet and only is the described specific embodiment.Obviously, according to the content of this specification sheets, can make many modifications and variations.These embodiment are chosen and specifically described to this specification sheets, is in order to explain better principle of the present invention and practical application, thereby the present invention can be understood and utilize to the technical field technical personnel well under making.The present invention only is subjected to the restriction of claims and four corner and equivalent.
The invention provides a kind of detector propulsion module and method of work thereof, can finish to planetary probe keep at track correction, track in the planet transfer process, attitude adjustment and the tasks such as nearly fire preparing is moving, ring fire flight; The present invention can be used for mars exploration and the interspace detection track transportation burden of other deep spaces, and it is simple in structure, and the design risk is less, is particularly useful for the remote survey of deep space task of unmanned probing device.
Claims (11)
1. a detector propulsion module comprises the protecgulum of being located at this propulsion module front end, it is characterized in that, comprising:
Be located at the electronic unit of described protecgulum inside, described electronic unit comprises a power module and an electric control module, and described power module is used for distribution and the power supply of this propulsion module, and described electric control module is finished the control to this propulsion module;
The one propulsion module body that is connected with described protecgulum, described propulsion module body interior is provided with an accommodating structure;
One is located at the fuel unit in the described accommodating structure, and described fuel unit provides fuel for this propulsion module;
One fixed sturcture that is connected with described propulsion module body is used for fixing described fuel unit;
One interface structure that is connected with described propulsion module body is used for and the docking of carrier rocket and ground-support equipment;
And be installed in this propulsion module outside power unit, described power unit is used to this propulsion module acceleration, braking and attitude adjustment.
2. detector propulsion module as claimed in claim 1, it is characterized in that, described power module is used for distribution and the power supply of this propulsion module, multipath electrovalve and the electric heating sheets of described electric control module by controlling this propulsion module finished control to the propulsion module power unit, monitors simultaneously and control the temperature in the propulsion module.
3. detector propulsion module as claimed in claim 1 is characterized in that, described propulsion module body is cylindrical, and its inner accommodating structure is honeycomb type tubular sandwich structure, and this honeycomb type tubular sandwich structure comprises the cylinder of a plurality of hollows; The material of described this external surface of propulsion module adopts carbon fiber skin, and the material of described honeycomb type tubular sandwich structure adopts metallic aluminium.
4. detector propulsion module as claimed in claim 3, it is characterized in that, described fuel unit comprises that a plurality of elliposoidal tanks and that are full of fuel are full of the composite gas cylinder of the gas of inertia, and described gas cylinder is used for controlling described elliposoidal tank makes it enter position to be consumed.
5. detector propulsion module as claimed in claim 4 is characterized in that, the quantity of described cylinder and described elliposoidal tank and bodily form coupling, and described each elliposoidal tank is installed in respectively in each cylinder.
6. detector propulsion module as claimed in claim 4 is characterized in that, described fixed sturcture comprises
Be fixed on the first tank support and the second tank support that is fixed on described propulsion module body rear end of described propulsion module body front end, described the first tank support is provided with a plurality of the first circular holes and one second circular hole, and described the second tank support is provided with first circular hole identical with described the first tank support the first circular hole quantity;
Described the first circular hole and described elliposoidal tank coupling also fix the position of described elliposoidal tank, and described the second circular hole and described gas cylinder coupling also fix the position of described gas cylinder.
7. detector propulsion module as claimed in claim 1 is characterized in that, described power unit comprises a main thrust device and an attitude thruster.
8. detector propulsion module as claimed in claim 7, it is characterized in that, described main thrust device comprises the sustainer, main engine of a 450N, and described attitude thruster comprises that 2 in pitching driving engine, the 10N driftage driving engine of 10N selects the rolling driving engine of 2 and 10N to select 8.
9. detector propulsion module as claimed in claim 1 is characterized in that, described interface structure cooperates riveted joint to be connected with described propulsion module body with being connected by glueing joint.
10. the method for work of a detector propulsion module, its fire flight that is used for running quickly is characterized in that, carries out successively following steps:
Ground send action, this course of action propulsion module are in dormant state and bear emission process and cause mechanics overload, vibration, noise circumstance;
The fire of running quickly moves, and the fiery track correction of running quickly is finished in this action, track is kept and run quickly fire section appearance control propelling;
Nearly fire preparing is moving, and this action reduces the flying speed of detector, and detector is caught by Mars gravitation, enters a highly elliptic orbit;
The ring fire flare maneuver, this action is adjusted the ring fire track profile of detector, makes detector enter planned orbit, and propulsion module separated with detector after detector entered planned orbit.
11. method as claimed in claim 9 is characterized in that, carries out in the send action process of ground at propulsion module, propulsion module bottom is connected with the interface adapter of carrier rocket, the top be connected around device, two hard landing device sides are hung on propulsion module; In the fiery course of action of running quickly, propulsion module is positioned at the afterbody of detector, and Mars is positioned at the detector top around device; In the moving process of nearly fire preparing, propulsion module is positioned at the front portion of detector flight.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012105384136A CN102975869A (en) | 2012-12-13 | 2012-12-13 | Detector propelling module and working method thereof |
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| Application Number | Priority Date | Filing Date | Title |
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| CN2012105384136A CN102975869A (en) | 2012-12-13 | 2012-12-13 | Detector propelling module and working method thereof |
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| CN102975869A true CN102975869A (en) | 2013-03-20 |
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| CN2012105384136A Pending CN102975869A (en) | 2012-12-13 | 2012-12-13 | Detector propelling module and working method thereof |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103402274A (en) * | 2013-07-02 | 2013-11-20 | 上海卫星工程研究所 | WiFi relay communication system applied to Mars detection |
| CN107985629A (en) * | 2017-10-17 | 2018-05-04 | 上海宇航系统工程研究所 | Mars exploration method and Mars probes |
| CN113879567A (en) * | 2021-09-06 | 2022-01-04 | 北京空间飞行器总体设计部 | High-reliability composite power supply system applied to Mars landing patrol task |
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| US20070051854A1 (en) * | 2005-09-07 | 2007-03-08 | The Boeing Company | Space depot for spacecraft resupply |
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| US5271226A (en) * | 1992-04-24 | 1993-12-21 | The United States Of America, As Represented By The Secretary Of Commerce | High speed, amplitude variable thrust control |
| US5533331A (en) * | 1994-05-25 | 1996-07-09 | Kaiser Marquardt, Inc. | Safe propulsion system for missile divert thrusters and attitude control thrusters and method for use of same |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN103402274A (en) * | 2013-07-02 | 2013-11-20 | 上海卫星工程研究所 | WiFi relay communication system applied to Mars detection |
| CN103402274B (en) * | 2013-07-02 | 2016-03-16 | 上海卫星工程研究所 | A kind of WiFi relay communication system being applicable to mars exploration |
| CN107985629A (en) * | 2017-10-17 | 2018-05-04 | 上海宇航系统工程研究所 | Mars exploration method and Mars probes |
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| CN113879567B (en) * | 2021-09-06 | 2024-04-02 | 北京空间飞行器总体设计部 | High-reliability composite power supply system applied to Mars landing inspection task |
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Application publication date: 20130320 |