CN104733860A - Automatic gate control device for landing spacecraft channel and validation method - Google Patents
Automatic gate control device for landing spacecraft channel and validation method Download PDFInfo
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- CN104733860A CN104733860A CN201510101570.4A CN201510101570A CN104733860A CN 104733860 A CN104733860 A CN 104733860A CN 201510101570 A CN201510101570 A CN 201510101570A CN 104733860 A CN104733860 A CN 104733860A
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- recoverable capsule
- sensitive axes
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Abstract
An automatic gate control device for a landing spacecraft channel comprises an accelerometer, two signal amplification circuits, switch-on direction control circuits, filter capacitors, drive circuits and a single-pole double-throw magnetic self-locking microwave switch. The output end of the accelerometer is connected with the input ends of the two signal amplification circuits, the output ends of the two signal amplification circuits are led to the input ends of the corresponding switch-on direction control circuits, and the other input ends of the switch-on direction control circuits are connected with the output end of the single-pole double-throw magnetic self-locking microwave switch. The filter capacitors are connected between the switch-on direction control circuits and the single-pole double-throw magnetic self-locking microwave switch. The output ends of the switch-on direction control circuits are led to the input ends of the corresponding drive circuits, and the output ends of the drive circuits are led to the control end of the single-pole double-throw magnetic self-locking microwave switch.
Description
Technical field
The present invention relates to the automatic gating control field of landing spacecraft channel, specifically the automatic gate control device of a kind of landing spacecraft channel and verification method.
Background technology
In order to ensure the communication after recoverable spacecraft landing, the two secondary alien frequencies antenna arrays that current spacecraft adopts 180 ° to install form the nearly total space and cover, and every width element antenna half space covers.Because recoverable spacecraft Post Landing Attitude is unknown, current microwave switch, without Intelligent detection circuit, cannot select the antenna transmission radiofrequency signal that gain direction is good automatically.Can the switch of gating automatically so need to adopt, realize effective transmitting of radiofrequency signal.Can use to realize controlling existing design from gating, in gravity switch as shown in Figure 5, conducting medium mercury is vacuum sealed to glass shell by this switch, and one end of two fixed electrodes is through packaging shell in housing, and the other end is exposed welding lead.When switch is just put, mercury is pasted in bottom due to gravity, and positive and negative electrode disconnects i.e. not on-state.This kind of switch is when being inverted angle > 45 °, and switch is just connected.Though but to have certain automatic detection function handoff angle too large for this kind of switch, current spacecraft is for realizing real-time telemetry remote control, two secondary half space antennas need to switch as far as possible soon, this kind of switch is glass shell simultaneously, can not bear vibration and ballistics environment, and conducting medium is mercury, if power met by switch, encapsulation is broken, mercury is revealed, and will cause severe contamination to electronic equipment.And mercury just becomes to solidify state at-39.7 °, the reliability of switch connection reduces.Therefore this kind of switch performance index error, poor reliability, is difficult to be applicable to all kinds of spacecraft, especially experiences the landing-type spacecraft of various mechanics in space and landing mission.
Summary of the invention
This provides the automatic gate control device of a kind of landing spacecraft channel, and solved handoff angle in prior art large, switch speed is slow, fragile, can cause severe contamination after damage to other electronic equipments.The present invention additionally provides a kind of verification method based on the automatic gate control device of landing spacecraft channel simultaneously.
The technical scheme of technical solution problem of the present invention is: the automatic gate control device of a kind of landing spacecraft channel comprises accelerometer, signal amplification circuit, connection directional control circuit, filter capacitor, drive circuit, single-pole double throw magnetic self-locking microwave switch.
The output of accelerometer is connected with 2 road signal amplification circuit inputs respectively, 2 road signal amplification circuit outputs lead to the input of each self-corresponding connection directional control circuit respectively, another input connecting directional control circuit is also connected with single-pole double throw magnetic self-locking microwave switch on-state remote measurement end, connect between directional control circuit and single-pole double throw magnetic self-locking microwave switch on-state remote measurement end and be provided with filter capacitor, the output connecting directional control circuit leads to the input of corresponding drive circuit, drive circuit output leads to the control end of single-pole double throw magnetic self-locking microwave switch, accelerometer is for becoming capacitive accelerometer, accelerometer can detect gravity at the responsive axial component of equipment, and output difference divided voltage signal, the differential voltage signal that accelerometer exports is input to two paths of signals amplifying circuit respectively according to opposite polarity and amplifies.
Connecting directional control circuit is a logical AND gate, adopts the output of signal amplification circuit and the on-state telemetered signal of single-pole double throw magnetic self-locking microwave switch, jointly carries out connection direction controlling and judges.
The beneficial effect of device of the present invention is that 1 this device can detect automatically and the more excellent width of two slave antenna relative points of the asymmetric installation of gating communicates, and has that to switch critical angle little, the advantage that radiofrequency signal insertion loss is little.2 these devices also have the advantage of nontoxic pollution-free concurrently simultaneously, even if the damage of this device also can not other equipment of collateral damage and components and parts.This device also can be used for the landing of native to this world environment, and due to the difference of acceleration of gravity, switching critical angle can change, and other functional performances can not because of the factor such as air pressure, temperature product error.
the technical scheme of another technical problem that the present invention solves is: a kind of verification method based on the automatic gate control device of landing spacecraft channel, the method comprises the following steps:
(1) determine the space layout that landing-type space-vehicle antenna is right, be applied as example with recoverable capsule, determine antenna and horizontal plane angle and azimuth, azimuth is antenna at horizontal plane projection and the angle in recoverable capsule 0 ° of direction, can determine the direction in space of antenna.
(2) calculate and detect the direction of sensitive axes, obtain this axle and horizontal plane angle α and azimuthal angle beta.
(3) according to α and β calculated, carry out structural design, make equipment sensitive axes consistent with the detection sensitive axes direction calculated.Be applied as example with recoverable capsule, when detecting sensitive axes positive direction relative level and facing up, the width antenna channel that equipment automatic gating positive direction is corresponding, vice versa.
(4) equipment of the present invention is arranged on landing-type spacecraft, for recoverable capsule, is arranged in recoverable capsule.
(5) calculate the angle in two antennas/sensitive axes relative level face under recoverable capsule rolling and heeling condition, computation model as shown in Figure 4, can obtain computing formula:
。
α is the angle of antenna/sensitive axes and horizontal plane.
β is the projection of antenna/sensitive axes forward on large bottom surface and the angle in recoverable capsule 0 ° of direction.
° reverse caster angle, θ=90; θ ∈ [-90 °, 90 °].
Inclination angle is the angle of recoverable capsule bottom surface and horizontal plane, inclination angle ∈ [0 °, 180 °].
γ=180 ° positive roll angle, γ ∈ [0 °, 360 °].
Roll angle is the angle between the minimum point direction of recoverable capsule incline direction and recoverable capsule 0 ° of direction, is roll angle.Roll angle ∈ [0 °, 360 °].
δ is and axis and horizontal plane angle after rolling.
(6) according to result of calculation, select typical condition, in relative 0 ° of direction, recoverable capsule lifts by special angle γ place, and the angle of inclination of lifting is inclination angle, detects the transmitting power of each width antenna, verifies by the gating validity of equipment of the present invention.
The beneficial effect of method of testing of the present invention is: designer can be allowed according to the concrete structure of different spacecrafts by checking, the position of reasonable arrangement antenna, or reach optimum signal reflex effect according to the structure of the position reasonable arrangement spacecraft internal components of antenna.
Accompanying drawing explanation
Fig. 1 is electrical block diagram of the present invention.
Fig. 2 is that signal of the present invention moves towards block diagram.
Fig. 3 is the computation model of sensitive axes of the present invention.
Fig. 4 be inventive antenna/sensitive axes spacecraft tilt and under tumbling state with the computation model of horizontal plane angle.
Fig. 5 is gravity switch schematic diagram in prior art.
Description of reference numerals: 1 accelerometer, 2 signal amplification circuits, 3 filter capacitors, 4 connect directional control circuit, 5 drive circuits, 6 single-pole double throw magnetic self-locking microwave switches.
Embodiment
Below in conjunction with accompanying drawing 1 to 2, the present invention will be further described.
The automatic gate control device of a kind of landing spacecraft channel comprises: accelerometer 1,2 road signal amplification circuit 2, connection directional control circuit 3, filter capacitor 4, drive circuit 5, single-pole double throw magnetic self-locking microwave switch 6.
The output of accelerometer 1 is connected with 2 road signal amplification circuit 2 inputs respectively, 2 road signal amplification circuit 2 outputs lead to the input of each self-corresponding connection directional control circuit 4 respectively, another input connecting directional control circuit 4 is also connected with order dpdt double-pole double-throw (DPDT) magnetic self-locking microwave switch 6 on-state remote measurement end, connect between directional control circuit 4 and order dpdt double-pole double-throw (DPDT) magnetic self-locking microwave switch 6 on-state remote measurement end and be provided with filter capacitor 3, the output connecting directional control circuit 4 leads to the input of corresponding drive circuit 5, drive circuit 5 output leads to the control end of single-pole double throw magnetic self-locking microwave switch 6.
Accelerometer 1 is for becoming capacitive accelerometer, accelerometer can detect gravity at the responsive axial component of equipment, and output difference divided voltage signal, this differential voltage signal according to opposite polarity respectively entering signal amplifying circuit 2 amplify, signal amplification circuit 2 is made up of differential amplifier.The signal that differential amplifier exports leads to respective connection directional control circuit 4 respectively, and connect directional control circuit 4 and carry out logic decision to the two paths of signals after amplification, connecting directional control circuit 4 is a logical AND gate.A road signal higher than threshold voltage will trigger drive circuit 5, a road signal lower than threshold circuit does not then trigger, single-pole double throw magnetic self-locking microwave switch 6 on-state telemetered signal, as a road Logic judgment signal, can prevent from triggering driving to on-state is lasting.
be described further below in conjunction with accompanying drawing 3 to 4 pairs of the inventive method.
A kind of verification method based on the automatic gate control device of landing spacecraft channel comprises the following steps:
1 determines the space layout that landing-type space-vehicle antenna is right, is applied as example with recoverable capsule, and determine antenna and horizontal plane angle and azimuth, azimuth is antenna at horizontal plane projection and the angle in recoverable capsule 0 ° of direction, can determine the direction in space of antenna.
2 calculate and detect the direction of sensitive axes, obtain this axle and horizontal plane angle α and azimuthal angle beta.
The direction detecting sensitive axes should be identical with the vertical line direction of two antenna angle bisector plane, and computation model as shown in Figure 2
(3) according to α and β calculated, carry out structural design, make equipment sensitive axes consistent with the detection sensitive axes direction calculated.Be applied as example with recoverable capsule, when detecting sensitive axes positive direction relative level and facing up, the width antenna channel that equipment automatic gating positive direction is corresponding, vice versa.
(4) equipment of the present invention is arranged on landing-type spacecraft, for recoverable capsule, is arranged in recoverable capsule.
(5) calculate the angle in two antennas/sensitive axes relative level face under recoverable capsule rolling and heeling condition, computation model as shown in Figure 4, can obtain computing formula:
。
α is the angle of antenna/sensitive axes and horizontal plane.
β is the projection of antenna/sensitive axes forward on large bottom surface and the angle in recoverable capsule 0 ° of direction.
° reverse caster angle, θ=90; θ ∈ [-90 °, 90 °].
Inclination angle is the angle of recoverable capsule bottom surface and horizontal plane, inclination angle ∈ [0 °, 180 °].
γ=180 ° positive roll angle, γ ∈ [0 °, 360 °].
Roll angle is the angle between the minimum point direction of recoverable capsule incline direction and recoverable capsule 0 ° of direction, is roll angle.Roll angle ∈ [0 °, 360 °].
δ is and axis and horizontal plane angle after rolling.
(6) according to result of calculation, select typical condition, at special angle place, relative 0 ° of direction, recoverable capsule is tilted, detects the transmitting power of each width antenna.
Claims (3)
1. the automatic gate control device of landing spacecraft channel comprises: accelerometer (1), signal amplification circuit (2), filter capacitor (3), connect directional control circuit (4), drive circuit (5), single-pole double throw magnetic self-locking microwave switch (6), it is characterized in that: the output of described accelerometer (1) is connected with 2 road signal amplification circuit (2) inputs respectively, described 2 road signal amplification circuit (2) outputs lead to the input of each self-corresponding connection directional control circuit (4) respectively, another input of described connection directional control circuit (4) is also connected with single-pole double throw magnetic self-locking microwave switch (6) on-state remote measurement end, filter capacitor (3) is provided with between described connection directional control circuit (4) and single-pole double throw magnetic self-locking microwave switch (6) on-state remote measurement end, the output of described connection directional control circuit (4) leads to the input of corresponding drive circuit (5), described drive circuit (5) output leads to the control end of single-pole double throw magnetic self-locking microwave switch (6), described accelerometer (1) is for becoming capacitive accelerometer, described accelerometer (1) can detect gravity at the responsive axial component of equipment, and output difference divided voltage signal, the differential voltage signal that accelerometer (1) exports is input to two paths of signals amplifying circuit (2) respectively according to opposite polarity and amplifies.
2. the automatic gate control device of a kind of landing spacecraft channel according to claim 1, it is characterized in that: described connection directional control circuit (4) is a logical AND gate, adopt the output of signal amplification circuit (2) and the on-state telemetered signal of single-pole double throw magnetic self-locking microwave switch (6), jointly carry out connection direction controlling and judge.
3., based on a verification method for the automatic gate control device of landing spacecraft channel described in claim 1 or 2, the method comprises the following steps:
A determines the space layout that landing-type space-vehicle antenna is right, is applied as example with recoverable capsule, and determine antenna and horizontal plane angle and azimuth, azimuth is antenna at horizontal plane projection and the angle in recoverable capsule 0 ° of direction, can determine the direction in space of antenna;
B calculates and detects the direction of sensitive axes, obtains this axle and horizontal plane angle α and azimuthal angle beta; Detecting the direction of sensitive axes should be identical with the vertical line direction of two antenna angle bisector plane, computation model as shown in Figure 2:
C, according to α and β calculated, carries out structural design, makes equipment sensitive axes consistent with the detection sensitive axes direction calculated;
Example is applied as with recoverable capsule, when detecting sensitive axes positive direction relative level and facing up, the width antenna channel that equipment automatic gating positive direction is corresponding, vice versa;
Equipment of the present invention is arranged on landing-type spacecraft by d, for recoverable capsule, is arranged in recoverable capsule;
E calculates the angle in two antennas/sensitive axes relative level face under recoverable capsule rolling and heeling condition, and computation model as shown in Figure 4, can obtain computing formula:
Wherein:
α is the angle of antenna/sensitive axes and horizontal plane;
β is the projection of antenna/sensitive axes forward on large bottom surface and the angle in recoverable capsule 0 ° of direction;
° reverse caster angle, θ=90; θ ∈ [-90 °, 90 °];
Inclination angle is the angle of recoverable capsule bottom surface and horizontal plane, inclination angle ∈ [0 °, 180 °];
γ=180 ° positive roll angle, γ ∈ [0 °, 360 °];
Roll angle is the angle between the minimum point direction of recoverable capsule incline direction and recoverable capsule 0 ° of direction, is roll angle; Roll angle ∈ [0 °, 360 °];
δ is and axis and horizontal plane angle after rolling;
F, according to result of calculation, selects typical condition, at special angle place, relative 0 ° of direction, is tilted by recoverable capsule, detects the transmitting power of each width antenna.
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| CN201510101570.4A CN104733860B (en) | 2015-03-06 | 2015-03-06 | A kind of automatic gate control device of landing spacecraft channel and verification method |
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| CN201510101570.4A CN104733860B (en) | 2015-03-06 | 2015-03-06 | A kind of automatic gate control device of landing spacecraft channel and verification method |
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| CN104733860A true CN104733860A (en) | 2015-06-24 |
| CN104733860B CN104733860B (en) | 2019-03-12 |
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Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2020417C1 (en) * | 1991-04-04 | 1994-09-30 | Мелешко Владислав Валентинович | Inertial navigation system |
| CN1876501A (en) * | 2006-05-31 | 2006-12-13 | 哈尔滨工业大学 | Three axis directional controlling method for stabilizing posture in deep space based on behavior mode |
| CN102636168A (en) * | 2011-02-10 | 2012-08-15 | 泰为信息科技公司 | Navigation system comprising an accelerometer and corresponding method of operation |
-
2015
- 2015-03-06 CN CN201510101570.4A patent/CN104733860B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2020417C1 (en) * | 1991-04-04 | 1994-09-30 | Мелешко Владислав Валентинович | Inertial navigation system |
| CN1876501A (en) * | 2006-05-31 | 2006-12-13 | 哈尔滨工业大学 | Three axis directional controlling method for stabilizing posture in deep space based on behavior mode |
| CN102636168A (en) * | 2011-02-10 | 2012-08-15 | 泰为信息科技公司 | Navigation system comprising an accelerometer and corresponding method of operation |
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