CN109356749A - A kind of solid propellant rocket change propulsive signal feedback system - Google Patents
A kind of solid propellant rocket change propulsive signal feedback system Download PDFInfo
- Publication number
- CN109356749A CN109356749A CN201811384181.7A CN201811384181A CN109356749A CN 109356749 A CN109356749 A CN 109356749A CN 201811384181 A CN201811384181 A CN 201811384181A CN 109356749 A CN109356749 A CN 109356749A
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- CN
- China
- Prior art keywords
- feedback system
- solid propellant
- signal feedback
- propellant rocket
- movable contact
- 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.)
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/96—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by specially adapted arrangements for testing or measuring
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
- F02K9/32—Constructional parts; Details not otherwise provided for
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/80—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Testing Of Engines (AREA)
- Laminated Bodies (AREA)
Abstract
The invention discloses a kind of solid propellant rocket change propulsive signal feedback systems, according to the change in location of escape system attitude control solid engines flow-stopping plate structure, using movable contact spring structure and stationary contact point structure, pass through the closure and disconnection between movable contact spring and stationary contact when flow-stopping plate change in location, loop resistance value between two stationary contacts is obtained, judges whether solid engines change propulsive flow-stopping plate mechanism works normally according to resistance value；The feedback system improves escape system attitude control solid engines functional reliability, and has the advantages that simple, highly reliable, the easy realization of structure.
Description
Technical field
The invention belongs to Solid Rocket Motor Technology fields, and in particular to a kind of solid propellant rocket change propulsive signal
Feedback system.
Background technique
Manned space flight carrier rocket escape system is the safety device for life-saving of astronaut, when carrier rocket breaks down,
Return capsule with astronaut can be taken away danger area, complete the separation with carrier rocket.Escape system uses solid-rocket
For engine as attitude control power device, solid propellant rocket needs to realize two kinds of thrust work according to carrier rocket varying environment
Mode realizes two kinds of solid propellant rocket using the method in SRM Nozzle exit installation flow-stopping plate mechanism at present
Thrust working method, as shown in Figure 1, being sprayed by flow-stopping plate 3 to solid propellant rocket when solid propellant rocket 1 works
The change of 2 Flow Field Distribution of pipe, reduces Thrust of Solid Rocket Motor, this is the first thrust working method, and when solid is sent out
When motivation needs to realize full thrust, flow-stopping plate 3 is removed by solid rocket motor nozzle 2 by relieving mechanism and is exported, to make
Engine realizes full thrust, this is second of thrust working method, as shown in Figure 2.
In order to judge that flow-stopping plate whether according to rocket control instruction normal work, needs to carry out the working condition of flow-stopping plate
Monitoring, feeds back to rocket control system for its signal for being in any working method and carries out flight control.
Summary of the invention
It, can be in view of this, the object of the present invention is to provide a kind of solid propellant rocket change propulsive signal feedback system
The working condition of reliable monitoring solid engines change propulsive flow-stopping plate.
A kind of solid propellant rocket change propulsive signal feedback system, including being mounted under the flip portion of flow-stopping plate (3)
The movable contact spring component (4) on surface and be mounted on flow-stopping plate (3) support (6) upper surface stationary contact component (5)；
The movable contact spring component (4) includes movable contact spring (13), insulation board (12) and the first sheet rubber (11)；First sheet rubber
(11) it is fixedly mounted on the flip portion lower surface of flow-stopping plate (3), insulation board (12) is bonded on the first sheet rubber (11)；Dynamic touching
Piece (13) is the beryllium-bronze thin slice with θ angle, and θ takes 10 °~30 °；Movable contact spring (13) one end is fixed on insulation board (12) surface,
The other end tilts downwards；
The stationary contact component (5) includes the second sheet rubber (21), circuit board (22), contact (23) and conducting wire (24)；The
Two sheet rubbers (21) are pasted onto support (6) upper surface of flow-stopping plate (3)；Circuit board (22) is fixed on the second sheet rubber (21)；
Circuit board (22) upper surface is covered with the parallel strip copper foil (25) of twice, circuit board (22) surface leaching gold processing；Twice copper foil
(25) upper surface respectively rivets a contact (23)；Respectively weld a conducting wire (24), two conducting wires in one end of twice copper foil (25)
(24) ohmmeter is connected between.
Preferably, hardness HV is between 320~370 when the material heat treatment of movable contact spring (13).
Preferably, insulation board (12) is made of epoxy glass cloth laminated board.
Preferably, the first sheet rubber (11) uses fluorubber material.
Preferably, circuit board (22) is epoxy glass cloth laminated board thin skin.
Preferably, the contact (23) is the rivet of mushroom-head shape, made of metallic Silver material.
Preferably, the conducting wire (24) uses high temperature resistant wire.
Preferably, movable contact spring (13) surface gold-plating.
The invention has the following beneficial effects:
A kind of solid propellant rocket change propulsive signal feedback system of the invention, starts according to escape system attitude control solid
The change in location of machine flow-stopping plate structure passes through movable contact spring when flow-stopping plate change in location using movable contact spring structure and stationary contact point structure
Closure and disconnection between stationary contact, obtain loop resistance value between two stationary contacts, judge that solid starts according to resistance value
Whether machine change propulsive flow-stopping plate mechanism works normally；The feedback system improves escape system attitude control solid engines reliable operation
Property, and have the advantages that simple, highly reliable, the easy realization of structure.
Detailed description of the invention
Fig. 1 is the 1st kind of working method schematic diagram of solid engines change propulsive mechanism；
Fig. 2 is the 2nd kind of working method schematic diagram of solid engines change propulsive structure；
Fig. 3 is movable contact spring assembly assumption diagram of the invention；
Fig. 4 (a) is the sectional view of stationary contact component of the invention；
Fig. 4 (b) is the top view of stationary contact component of the invention.
Wherein, 1- solid propellant rocket, 2- jet pipe, 3- flow-stopping plate, 4- movable contact spring component, 5- stationary contact component, 6- branch
Seat, the first sheet rubber of 11-, 12- insulation board, 13- movable contact spring, the second sheet rubber of 21-, 22- circuit board, 23- contact, 24- conducting wire,
25- copper foil.
Specific embodiment
The present invention will now be described in detail with reference to the accompanying drawings and examples.
A kind of solid propellant rocket change propulsive signal feedback system of the invention, as shown in Fig. 2, including being mounted on baffle
The stationary contact component 5 of the movable contact spring component 4 of the flip portion lower surface of plate 3 and 6 upper surface of support for being mounted on flow-stopping plate 3.
As shown in figure 3, movable contact spring component 4 includes movable contact spring 13, insulation board 12 and first sheet rubber 11 etc.；First sheet rubber
11 are fixed on the flip portion lower surface for being mounted on flow-stopping plate 3, and insulation board 12 is whole viscous by silicon rubber and the first sheet rubber 11
It connects；Movable contact spring 13 is the beryllium-bronze thin slice with θ angle, and θ is 10 °~30 ° desirable, it is desirable that hardness HV is 320 when material heat treatment
Between~370,13 surface of movable contact spring carries out gold-plated；13 one end of movable contact spring is riveted on 12 surface of insulation board, and the other end tilts.Insulation
Plate 12 is the rectangular thin slice of approximation, using epoxy glass cloth laminated board；The shapes and sizes and insulation board of sheet rubber 11
It is identical, using fluorubber material.
As shown in Fig. 4 (a) and 4 (b), stationary contact component 5 includes the second sheet rubber 21, circuit board 22, contact 23 and conducting wire
24 etc.；Second sheet rubber 21 uses fluorubber material, is pasted onto 6 upper surface of support of flow-stopping plate 3；Circuit board 22 is an approximation
Rectangular epoxy glass cloth laminated board thin skin is covered with twice strip copper foil 25, circuit board on one side surface along its length
22 surfaces leaching gold processing；Circuit board 22 is fixed on the second sheet rubber 21；25 upper surface of twice strip copper foil respectively rivets one
Contact 23；Contact 23 is the rivet of mushroom-head shape, is made of metallic Silver material；It respectively welds one end of twice strip copper foil 25
A conducting wire 24 is connect, connects ohmmeter between two conducting wires 24.Conducting wire 24 uses high temperature resistant wire.
The sheet thickness of movable contact spring 13 is 0.1mm, gold-plated, thickness of coating 0.002mm~0.006mm；Insulation board 12 uses
Epoxy glass cloth laminated board production, with a thickness of 0.5mm；Two rubber slabs are made of fluorubber.
The specific work process of change propulsive signal feedback system of the invention are as follows:
(1) when solid engines are in the first working method (thrust reduction state), as shown in Figure 1, being mounted on
Movable contact spring component 4 above flow-stopping plate 3 contacts with each other with the stationary contact component 5 being mounted on above support 6, will by movable contact spring 13
Two contacts 23 are connected, and form circuit closed loop, obtain conduction resistance value by the ohmmeter that conducting wire 24 connects.
(2) when solid engines are in second of working method (main stage), as shown in Fig. 2, relieving mechanism
The outlet that flow-stopping plate 3 is removed to jet pipe 2, the movable contact spring component 4 being mounted on flow-stopping plate 3 and the stationary contact being mounted on support 6
Component 5 separates, and forms open circuit between two contacts 23, obtains off resistance value by the ohmmeter that conducting wire 24 connects.
(3) resistance signal is transmitted to rocket control system, change propulsive flow-stopping plate can determine whether by the variation of resistance value
In first or second of working method.
In conclusion the above is merely preferred embodiments of the present invention, being not intended to limit the scope of the present invention.
All within the spirits and principles of the present invention, any modification, equivalent replacement, improvement and so on should be included in of the invention
Within protection scope.
Claims (8)
1. a kind of solid propellant rocket change propulsive signal feedback system, which is characterized in that including being mounted on turning over for flow-stopping plate (3)
Turn the movable contact spring component (4) of portion lower surface and is mounted on the stationary contact component (5) of support (6) upper surface of flow-stopping plate (3)；
The movable contact spring component (4) includes movable contact spring (13), insulation board (12) and the first sheet rubber (11)；First sheet rubber (11)
It is fixedly mounted on the flip portion lower surface of flow-stopping plate (3), insulation board (12) is bonded on the first sheet rubber (11)；Movable contact spring
It (13) is the beryllium-bronze thin slice with θ angle, θ takes 10 °~30 °；Movable contact spring (13) one end is fixed on insulation board (12) surface, separately
One end tilts downwards；
The stationary contact component (5) includes the second sheet rubber (21), circuit board (22), contact (23) and conducting wire (24)；Second rubber
Film (21) is pasted onto support (6) upper surface of flow-stopping plate (3)；Circuit board (22) is fixed on the second sheet rubber (21)；Circuit
Plate (22) upper surface is covered with the parallel strip copper foil (25) of twice, circuit board (22) surface leaching gold processing；Twice copper foil (25)
Upper surface respectively rivets a contact (23)；A conducting wire (24) is respectively welded in one end of twice copper foil (25), two conducting wires (24) it
Between connect ohmmeter.
2. a kind of solid propellant rocket change propulsive signal feedback system as described in claim 1, which is characterized in that movable contact spring
(13) hardness HV is between 320~370 when material heat treatment.
3. a kind of solid propellant rocket change propulsive signal feedback system as described in claim 1, which is characterized in that insulation board
(12) it is made of epoxy glass cloth laminated board.
4. a kind of solid propellant rocket change propulsive signal feedback system as described in claim 1, which is characterized in that the first rubber
Film (11) uses fluorubber material.
5. a kind of solid propellant rocket change propulsive signal feedback system as described in claim 1, which is characterized in that circuit board
It (22) is epoxy glass cloth laminated board thin skin.
6. a kind of solid propellant rocket change propulsive signal feedback system as described in claim 1, which is characterized in that the touching
Head (23) is the rivet of mushroom-head shape, is made of metallic Silver material.
7. a kind of solid propellant rocket change propulsive signal feedback system as described in claim 1, which is characterized in that described to lead
Line (24) uses high temperature resistant wire.
8. a kind of solid propellant rocket change propulsive signal feedback system as described in claim 1, which is characterized in that described dynamic
Contact (13) surface gold-plating.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811384181.7A CN109356749B (en) | 2018-11-20 | 2018-11-20 | Variable thrust signal feedback system of solid rocket engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811384181.7A CN109356749B (en) | 2018-11-20 | 2018-11-20 | Variable thrust signal feedback system of solid rocket engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109356749A true CN109356749A (en) | 2019-02-19 |
| CN109356749B CN109356749B (en) | 2020-08-25 |
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ID=65332443
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811384181.7A Active CN109356749B (en) | 2018-11-20 | 2018-11-20 | Variable thrust signal feedback system of solid rocket engine |
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| Country | Link |
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| CN (1) | CN109356749B (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB800770A (en) * | 1955-03-10 | 1958-09-03 | Havilland Engine Co Ltd | Nozzle assemblies for jet propulsion apparatus |
| US4957249A (en) * | 1988-04-07 | 1990-09-18 | Messerschmitt-Boelkow-Blohm Gmbh | Thrust vector control flap with a merging convex, concave inner contour, for jet aircraft and method for operating the same |
| JPH09236049A (en) * | 1996-02-28 | 1997-09-09 | Tech Res & Dev Inst Of Japan Def Agency | Deflecting body of flying body |
| CN1548708A (en) * | 2003-05-06 | 2004-11-24 | 峰 汪 | Electronic air throttling flap body |
| CN103541833A (en) * | 2012-07-10 | 2014-01-29 | 北京航天发射技术研究所 | Single-spray-pipe rocket combustion-gas stream drainage device |
| RU2579294C1 (en) * | 2015-06-16 | 2016-04-10 | Акционерное общество "Конструкторское бюро химавтоматики" | Liquid rocket engine with baffle at nozzle section |
-
2018
- 2018-11-20 CN CN201811384181.7A patent/CN109356749B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB800770A (en) * | 1955-03-10 | 1958-09-03 | Havilland Engine Co Ltd | Nozzle assemblies for jet propulsion apparatus |
| US4957249A (en) * | 1988-04-07 | 1990-09-18 | Messerschmitt-Boelkow-Blohm Gmbh | Thrust vector control flap with a merging convex, concave inner contour, for jet aircraft and method for operating the same |
| JPH09236049A (en) * | 1996-02-28 | 1997-09-09 | Tech Res & Dev Inst Of Japan Def Agency | Deflecting body of flying body |
| CN1548708A (en) * | 2003-05-06 | 2004-11-24 | 峰 汪 | Electronic air throttling flap body |
| CN103541833A (en) * | 2012-07-10 | 2014-01-29 | 北京航天发射技术研究所 | Single-spray-pipe rocket combustion-gas stream drainage device |
| RU2579294C1 (en) * | 2015-06-16 | 2016-04-10 | Акционерное общество "Конструкторское бюро химавтоматики" | Liquid rocket engine with baffle at nozzle section |
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| Publication number | Publication date |
|---|---|
| CN109356749B (en) | 2020-08-25 |
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