CN109356749B - Variable thrust signal feedback system of solid rocket engine - Google Patents

Variable thrust signal feedback system of solid rocket engine Download PDF

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Publication number
CN109356749B
CN109356749B CN201811384181.7A CN201811384181A CN109356749B CN 109356749 B CN109356749 B CN 109356749B CN 201811384181 A CN201811384181 A CN 201811384181A CN 109356749 B CN109356749 B CN 109356749B
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China
Prior art keywords
rocket engine
solid rocket
feedback system
signal feedback
variable thrust
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CN201811384181.7A
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CN109356749A (en
Inventor
魏坤龙
张焱
韩晓静
史宏斌
张志峰
陈天宇
陈莎
魏小青
强磊
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Xian Aerospace Propulsion Institute
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Xian Aerospace Propulsion Institute
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    • 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)
  • Laminated Bodies (AREA)
  • Testing Of Engines (AREA)

Abstract

The invention discloses a variable thrust signal feedback system of a solid rocket engine, which controls the position change of a baffle plate structure of the solid rocket engine according to the position of an escape system, adopts a movable contact piece structure and a fixed contact structure, obtains the loop resistance value between two fixed contacts by closing and opening the movable contact piece and the fixed contact when the position of the baffle plate changes, and judges whether the variable thrust baffle plate mechanism of the solid rocket engine works normally or not according to the resistance value; the feedback system improves the working reliability of the escape system attitude control solid engine, and has the advantages of simple structure, high reliability and easy realization.

Description

Variable thrust signal feedback system of solid rocket engine
Technical Field
The invention belongs to the technical field of solid rocket engines, and particularly relates to a variable thrust signal feedback system of a solid rocket engine.
Background
The escape system of manned space carrier rocket is a safety lifesaving device for astronauts, and when the carrier rocket breaks down, the return capsule with astronauts can be taken away from the dangerous area to complete the separation from the carrier rocket. The escape system adopts a solid rocket engine as an attitude control power device, the solid rocket engine needs to realize two thrust working modes according to different environments of a carrier rocket, at present, a method of installing a baffle plate mechanism at the outlet of a solid rocket engine spray pipe is adopted to realize the two thrust working modes of the solid rocket engine, as shown in figure 1, when the solid rocket engine 1 works, the thrust of the solid rocket engine is reduced by changing the flow field distribution of the solid rocket engine spray pipe 2 through the baffle plate 3, which is the first thrust working mode, and when the solid rocket engine needs to realize full thrust, the baffle plate 3 is removed from the outlet of the solid rocket engine spray pipe 2 through a release mechanism, so that the engine realizes full thrust, which is the second thrust working mode, as shown in figure 2.
In order to determine whether the flow baffle normally works according to the rocket control instruction, the working state of the flow baffle needs to be monitored, and a signal of which working mode the flow baffle is in is fed back to the rocket control system for flight control.
Disclosure of Invention
In view of this, the present invention provides a variable thrust signal feedback system for a solid rocket engine, which can reliably monitor the operating state of a variable thrust baffle of the solid rocket engine.
A variable thrust signal feedback system of a solid rocket engine comprises a movable contact piece assembly 4 arranged on the lower surface of an overturning part of a flow baffle 3 and a fixed contact assembly 5 arranged on the upper surface of a support 6 of the flow baffle 3;
the movable contact spring assembly 4 comprises a movable contact spring 13, an insulating plate 12 and a first rubber sheet 11; the first rubber sheet 11 is fixedly arranged on the lower surface of the overturning part of the flow baffle 3, and the insulating plate 12 is adhered to the first rubber sheet 11; the movable contact piece 13 is a beryllium bronze sheet with an included angle theta of 10-30 degrees; one end of the movable contact piece 13 is fixed on the surface of the insulating plate 12, and the other end is tilted downwards;
the static contact assembly 5 comprises a second rubber sheet 21, a circuit board 22, a contact 23 and a lead 24; the second rubber sheet 21 is stuck on the upper surface of the support 6 of the flow baffle 3; the circuit board 22 is fixed on the second rubber sheet 21; two parallel strip-shaped copper foils 25 are covered on the upper surface of the circuit board 22, and the surface of the circuit board 22 is subjected to gold immersion treatment; the upper surfaces of the two copper foils 25 are respectively riveted with a contact 23; one end of each of the two copper foils 25 is welded with one lead 24, and the two leads 24 are connected with a resistance meter.
Preferably, the hardness HV of the material of the moving contact piece 13 is 320 to 370 in the heat treatment.
Preferably, the insulating plate 12 is made of an epoxy glass cloth laminate.
Preferably, the first rubber sheet 11 is made of a fluororubber material.
Preferably, the circuit board 22 is an epoxy glass cloth laminate sheet.
Preferably, the contact 23 is a rivet in the shape of a mushroom head, and is made of a metallic silver material.
Preferably, the lead 24 is a high temperature resistant lead.
Preferably, the surface of the movable contact piece 13 is plated with gold.
The invention has the following beneficial effects:
according to the variable thrust signal feedback system of the solid rocket engine, the position change of a flow baffle plate structure of the solid rocket engine is controlled according to the escape system, a movable contact piece structure and a fixed contact structure are adopted, the resistance value of a loop between two fixed contacts is obtained by closing and opening the movable contact piece and the fixed contact when the position of the flow baffle plate changes, and whether the variable thrust flow baffle plate mechanism of the solid rocket engine works normally is judged according to the resistance value; the feedback system improves the working reliability of the escape system attitude control solid rocket engine, and has the advantages of simple structure, high reliability and easy realization.
Drawings
FIG. 1 is a schematic diagram of a thrust-varying mechanism of a solid rocket engine in a 1 st working mode;
FIG. 2 is a schematic diagram of the 2 nd mode of operation of a variable thrust structure of a solid rocket engine;
FIG. 3 is a view of the movable contact assembly of the present invention;
fig. 4(a) is a cross-sectional view of the stationary contact assembly of the present invention;
fig. 4(b) is a top view of the stationary contact assembly of the present invention.
The rocket engine comprises a solid rocket engine 1, a nozzle 2, a baffle 3, a movable contact assembly 4, a fixed contact assembly 5, a support 6, a first rubber sheet 11, an insulating plate 12, a movable contact sheet 13, a second rubber sheet 21, a circuit board 22, a contact 23, a lead 24 and a copper foil 25.
Detailed Description
The invention is described in detail below by way of example with reference to the accompanying drawings.
The variable thrust signal feedback system of the solid rocket engine comprises a movable contact piece assembly 4 arranged on the lower surface of an overturning part of a flow baffle 3 and a fixed contact assembly 5 arranged on the upper surface of a support 6 of the flow baffle 3, as shown in figure 2.
As shown in fig. 3, the movable contact piece assembly 4 includes a movable contact piece 13, an insulating plate 12, a first rubber piece 11, and the like; the first rubber sheet 11 is fixedly arranged on the lower surface of the turnover part of the flow baffle 3, and the insulation plate 12 is integrally bonded with the first rubber sheet 11 through silicon rubber; the movable contact piece 13 is a beryllium bronze sheet with an included angle theta, the theta can be 10-30 degrees, the hardness HV is 320-370 when the material is subjected to heat treatment, and the surface of the movable contact piece 13 is plated with gold; one end of the movable contact piece 13 is riveted on the surface of the insulating plate 12, and the other end is tilted. The insulating plate 12 is an approximately rectangular sheet and is an epoxy glass cloth laminated board; the rubber sheet 11 has the same shape and size as the insulating plate, and is made of a fluororubber material.
As shown in fig. 4(a) and 4(b), the stationary contact assembly 5 includes a second rubber sheet 21, a circuit board 22, a contact 23, a wire 24, and the like; the second rubber sheet 21 is made of fluororubber and is adhered to the upper surface of the support 6 of the flow baffle 3; the circuit board 22 is a thin sheet of an approximately rectangular epoxy glass cloth laminated board, two long-strip-shaped copper foils 25 are covered on the surface of one side along the length direction, and the surface of the circuit board 22 is subjected to gold immersion treatment; the circuit board 22 is fixed on the second rubber sheet 21; the upper surfaces of the two long-strip-shaped copper foils 25 are respectively riveted with a contact 23; the contact 23 is a rivet in the shape of a mushroom head and is made of a metal silver material; one end of each of the two long-strip-shaped copper foils 25 is welded with one lead 24, and the two leads 24 are connected with an ohmmeter. The lead 24 is a high temperature resistant lead.
The thickness of the slice of the movable contact spring 13 is 0.1mm, the gilding, the thickness of the coating is 0.002 mm-0.006 mm; the insulating plate 12 is made of an epoxy glass cloth laminated board, and the thickness is 0.5 mm; the two rubber plates are made of fluororubber.
The specific working process of the variable thrust signal feedback system comprises the following steps:
(1) when the solid rocket engine is in the first working mode (i.e. thrust reducing state), as shown in fig. 1, the movable contact piece assembly 4 mounted on the baffle plate 3 and the fixed contact assembly 5 mounted on the support 6 are contacted with each other, the two contacts 23 are conducted through the movable contact piece 13 to form a closed circuit loop, and the conducting resistance value is obtained through a resistance meter connected through a lead 24.
(2) When the solid rocket engine is in the second operation mode (i.e. the full thrust state), as shown in fig. 2, the release mechanism moves the flow baffle 3 away from the outlet of the nozzle 2, the movable contact assembly 4 mounted on the flow baffle 3 is separated from the stationary contact assembly 5 mounted on the support 6, an open circuit is formed between the two contacts 23, and the disconnection resistance value is obtained by an ohmmeter connected by the wires 24.
(3) The resistance signal is transmitted to a rocket control system, and the variable thrust baffle plate can be judged to be in the first or second working mode through the change of the resistance value.
In summary, the above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims (8)

1. A variable thrust signal feedback system of a solid rocket engine is characterized by comprising a movable contact component (4) arranged on the lower surface of an overturning part of a flow baffle (3) and a fixed contact component (5) arranged on the upper surface of a support (6) of the flow baffle (3);
the movable contact piece assembly (4) comprises a movable contact piece (13), an insulating plate (12) and a first rubber piece (11); the first rubber sheet (11) is fixedly arranged on the lower surface of the overturning part of the flow baffle plate (3), and the insulating plate (12) is adhered to the first rubber sheet (11); the movable contact piece (13) is a beryllium bronze sheet with an included angle theta of 10-30 degrees; one end of the movable contact spring (13) is fixed on the surface of the insulating plate (12), and the other end is tilted downwards;
the static contact assembly (5) comprises a second rubber sheet (21), a circuit board (22), a contact head (23) and a lead (24); the second rubber sheet (21) is stuck on the upper surface of the support (6) of the flow baffle (3); the circuit board (22) is fixed on the second rubber sheet (21); two parallel strip-shaped copper foils (25) are covered on the upper surface of the circuit board (22), and the surface of the circuit board (22) is subjected to gold leaching treatment; the upper surfaces of the two copper foils (25) are respectively riveted with a contact (23); one end of each of the two copper foils (25) is welded with one lead (24), and the two leads (24) are connected with each other by a resistance meter.
2. A variable thrust signal feedback system for a solid rocket engine as claimed in claim 1, wherein the hardness HV of the material of the moving contact piece (13) is between 320-370 during heat treatment.
3. The variable thrust signal feedback system of a solid rocket engine as recited in claim 1, wherein said insulating plate (12) is made of epoxy glass cloth laminate.
4. A variable thrust signal feedback system for a solid rocket engine as recited in claim 1, wherein said first rubber sheet (11) is made of a fluororubber material.
5. A solid-rocket engine variable thrust signal feedback system as claimed in claim 1, wherein said circuit board (22) is an epoxy glass cloth laminated sheet skin.
6. A variable thrust signal feedback system for a solid rocket engine as recited in claim 1, wherein said contact (23) is a mushroom-head shaped rivet made of metallic silver material.
7. A variable thrust signal feedback system for a solid rocket engine as recited in claim 1, wherein said wire (24) is a high temperature resistant wire.
8. A variable thrust signal feedback system for a solid rocket engine as recited in claim 1, wherein said movable contact piece (13) is surface plated with gold.
CN201811384181.7A 2018-11-20 2018-11-20 Variable thrust signal feedback system of solid rocket engine Active CN109356749B (en)

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CN109356749B true CN109356749B (en) 2020-08-25

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Citations (6)

* Cited by examiner, † Cited by third party
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

Patent Citations (6)

* Cited by examiner, † Cited by third party
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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